https://wiki.developspace.net/w/api.php?action=feedcontributions&feedformat=atom&user=Arthurguest 2026-04-15T11:07:59Z User contributions MediaWiki 1.37.0 https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2477 2010-07-08T17:52:50Z

<p>Arthurguest: </p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> Related files for this project can be viewed by [[ITV:Files|clicking here]].<br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> <br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.<br /> <br /> <br /> &#039;&#039;&#039;FIGURE 1. MISSION CHARACTERISTICS<br /> <br /> [[File:Figure_1_Mission_Characteristics.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 2. HLLV OPTIONS<br /> <br /> [[File:Figure_2_HLLV_Options.jpg]]<br /> <br /> <br /> &#039;&#039;&#039;FIGURE 3. MISSION PAYLOADS<br /> <br /> [[File:Figure_3_Mission_payloads.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 4. DELTA IV INTEGRATED ANALYSIS<br /> <br /> [[File:Figure_4_Delta_IV_integrated_analysis.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 5. CENTAUR V1 INTEGRATED ANALYSIS<br /> <br /> [[File:Figure_5_Centaur_V1_integrated_analysis.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 6. PREFERRED ITV DESIGNS<br /> <br /> [[File:Figure_6_Preferred_ITV_Designs.jpg]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=ITV:Files&diff=2476 2010-07-08T17:51:38Z

<p>Arthurguest: Created page with &#039;Here is a collection of working files to be used as part of the ITV project. AIAA Space 2010 Extended Abstract as submitted: File:ITV_Extended_Abstract_(as_submitted).pdf W…&#039;</p> <hr /> <div>Here is a collection of working files to be used as part of the ITV project.<br /> <br /> AIAA Space 2010 Extended Abstract as submitted:<br /> [[File:ITV_Extended_Abstract_(as_submitted).pdf]]<br /> <br /> WORD draft of extended abstract:<br /> [[File:ITV_Extended_Abstract_v5.doc]]<br /> <br /> ITV spreadsheet:<br /> [[File:Interplanetary_Transfer_Vehicle_v3.xls]]<br /> <br /> ITV D4H design spreadsheet:<br /> [[File:ITV_design_D4H_v3.xls]]<br /> <br /> ITV results powerpoint:<br /> [[FIle: ITV_results_v4.ppt]]<br /> <br /> Launch vehicle powerpoint:<br /> [[File:ITV_Launch_Vehicles.ppt]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:ITV_Launch_Vehicles.ppt&diff=2475 2010-07-08T17:40:34Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:ITV_results_v4.ppt&diff=2474 2010-07-08T17:38:09Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:ITV_design_D4H_v3.xls&diff=2473 2010-07-08T17:37:16Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Interplanetary_Transfer_Vehicle_v3.xls&diff=2472 2010-07-08T17:36:54Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:ITV_Extended_Abstract_v5.doc&diff=2471 2010-07-08T17:34:11Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:ITV_Extended_Abstract_(as_submitted).pdf&diff=2470 2010-07-08T17:33:52Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2469 2010-07-08T16:50:58Z

<p>Arthurguest: </p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> <br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.<br /> <br /> <br /> &#039;&#039;&#039;FIGURE 1. MISSION CHARACTERISTICS<br /> <br /> [[File:Figure_1_Mission_Characteristics.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 2. HLLV OPTIONS<br /> <br /> [[File:Figure_2_HLLV_Options.jpg]]<br /> <br /> <br /> &#039;&#039;&#039;FIGURE 3. MISSION PAYLOADS<br /> <br /> [[File:Figure_3_Mission_payloads.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 4. DELTA IV INTEGRATED ANALYSIS<br /> <br /> [[File:Figure_4_Delta_IV_integrated_analysis.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 5. CENTAUR V1 INTEGRATED ANALYSIS<br /> <br /> [[File:Figure_5_Centaur_V1_integrated_analysis.jpg]]<br /> <br /> &#039;&#039;&#039;FIGURE 6. PREFERRED ITV DESIGNS<br /> <br /> [[File:Figure_6_Preferred_ITV_Designs.jpg]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Projects&diff=2468 2010-07-08T16:49:26Z

<p>Arthurguest: </p> <hr /> <div>This page lists projects and groups hosted by DevelopSpace. DevelopSpace intends to host projects and groups that are relevant to DevelopSpace&#039;s mission of building up the technical foundations for human space activities. Projects/groups do not need to be created or operated by DevelopSpace in order to be hosted here -- if you would like additional information on hosting your project with DevelopSpace, please contact [[user:pwooster|Paul Wooster]].<br /> <br /> =Project Listing=<br /> <br /> ==Active Projects==<br /> <br /> *[[Minimalist Human Mars Mission]]. Project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars (possibly with an initial emergency return capability). This initial Mars outpost could also be the nucleus of an initial Mars colony. Includes reference data, system analysis, and investigation of design options.<br /> <br /> *[[Interplanetary Transfer Vehicle]]. This project presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> ==Project Proposals==<br /> *[[Mars Solar Power]]. Project to investigate the feasibility of solar power on the surface of Mars for either as the sole primary power source or in conjunction with other power source (e.g., nuclear reactors). Includes reference data, system analysis, and investigation of design options.<br /> <br /> ==Hosted Groups and Teams==<br /> *[[MIT_SSAG|MIT Space Systems Architecture Group]]. A research group in the MIT Department of Aeronautics and Astronautics, focusing on human space exploration architecture.<br /> <br /> *[[MIT Rocket Team]]. A student group at MIT devoted to getting students involved with projects related to rocketry (chiefly focused on liquid fuel propulsion).<br /> <br /> Note: To create a project, add a link to the project page and a brief description of the project.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2467 2010-07-08T16:48:21Z

<p>Arthurguest: </p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> <br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.<br /> <br /> <br /> &#039;&#039;&#039;FIGURE 1. MISSION CHARACTERISTICS<br /> [[File:Figure_1_Mission_Characteristics.jpg]]<br /> <br /> &quot;&quot;FIGURE 2. HLLV OPTIONS<br /> [[File:Figure_2_HLLV_Options.jpg]]<br /> <br /> &quot;&quot;FIGURE 3. MISSION PAYLOADS<br /> [[File:Figure_3_Mission_payloads.jpg]]<br /> <br /> &quot;&quot;FIGURE 4. DELTA IV INTEGRATED ANALYSIS<br /> [[File:Figure_4_Delta_IV_integrated_analysis.jpg]]<br /> <br /> &quot;&quot;FIGURE 5. CENTAUR V1 INTEGRATED ANALYSIS<br /> [[File:Figure_5_Centaur_V1_integrated_analysis.jpg]]<br /> <br /> &quot;&quot;FIGURE 6. PREFERRED ITV DESIGNS<br /> [[File:Figure_6_Preferred_ITV_Designs.jpg]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2466 2010-07-08T00:37:30Z

<p>Arthurguest: </p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> <br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.<br /> <br /> [[File:Figure_1_Mission_Characteristics.jpg]]<br /> [[File:Figure_2_HLLV_Options.jpg]]<br /> [[File:Figure_3_Mission_payloads.jpg]]<br /> [[File:Figure_4_Delta_IV_integrated_analysis.jpg]]<br /> [[File:Figure_5_Centaur_V1_integrated_analysis.jpg]]<br /> [[File:Figure_6_Preferred_ITV_Designs.jpg]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_6_Preferred_ITV_Designs.jpg&diff=2465 2010-07-08T00:35:29Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_5_Centaur_V1_integrated_analysis.jpg&diff=2464 2010-07-08T00:35:13Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_4_Delta_IV_integrated_analysis.jpg&diff=2463 2010-07-08T00:34:58Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_3_Mission_payloads.jpg&diff=2462 2010-07-08T00:34:41Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_2_HLLV_Options.jpg&diff=2461 2010-07-08T00:34:22Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=File:Figure_1_Mission_Characteristics.jpg&diff=2460 2010-07-08T00:33:58Z

<p>Arthurguest: </p> <hr /> <div></div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2459 2010-07-08T00:32:17Z

<p>Arthurguest: /* Integrated Performance Analysis */</p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> <br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Interplanetary_Transfer_Vehicle&diff=2458 2010-07-08T00:31:39Z

<p>Arthurguest: Created page with &#039;= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO = == Introduction and Motivation == This paper presents design concepts for interp…&#039;</p> <hr /> <div>= Interplanetary Transfer Vehicle Concepts for Near Term Human Exploration Missions beyond LEO =<br /> <br /> == Introduction and Motivation ==<br /> This paper presents design concepts for interplanetary transfer vehicles that could be used to carry out deep space missions envisioned by the “Flexible Path” scenario described in the final report of the Augustine Commission [1]. These include missions to lunar orbit, libration points, Geostationary Orbit (GEO), Near Earth Objects (NEOs), as well as a lunar flyby. The focus of the analysis presented here is on interplanetary transfer vehicle concepts which can be realized in the near-term, i.e. by the end of the 2010s or the beginning of the 2020s. The selection of preferred interplanetary transfer vehicle designs is based on a comprehensive integrated performance analysis of mission types and propulsive capabilities.<br /> <br /> == Ground Rules and Assumptions ==<br /> The following mission types for interplanetary transfer vehicles are considered: a lunar flyby, a low lunar orbit mission, a mission to GEO, a mission to a Sun-Earth libration point (such as SE-L2), and a mission to a NEO (see FIgure 1). All of these mission types can be carried out with mission durations that lie within the US experience of microgravity exposure, yet offer significant benefits with regard to advancing experience with deep-space human spaceflight operations as well as provide relevant science opportunities [2] [1].<br /> <br /> 3 options for shuttle-derived heavy-lift launch vehicles were considered (see Figure 2): a side-mount vehicle with two 4-segment solid rocket boosters and 3 Space Shuttle Main Engines (SSMEs), an inline vehicle with two 4-segment solid rocket boosters and 3 SSMEs, as well as an inline vehicle with two 5-segment solid rocket boosters and 4 SSMEs; all based on conceptual designs by NASA [3][4]. Vehicles with upper stages based on the RL-10 engine or J-2X engine were not considered because their availability by the end of the 2010s or beginning of the 2020s would be less likely [1].<br /> <br /> For in-space propulsion, the upper stage of the Delta IV Heavy EELV and the Centaur V1 upper stage of the Atlas V EELV were considered [5] [6]; furthermore, it was assumed that the Crew Exploration Vehicle (CEV) with its crew module and service module (propulsive module) [7] would be available. For additional pressurized / habitable volume, it was assumed that a crew compartment similar to the lunar lander ascent stage compartment [4] would be available. <br /> <br /> == Mission Payloads ==<br /> Figure 3 provides an overview of the payloads associated with the different mission types outlined above. For the short-duration lunar flyby and lunar orbit missions, the CEV itself provides sufficient pressurized volume for 4 people; for the longer-duration GEO, SE-L2, and NEO missions it is assumed that the additional crew compartment would be utilized. Additional payloads are tailored to the specific mission types.<br /> <br /> == Integrated Performance Analysis ==<br /> In order to assess the compatibility of launch vehicle, in-space propulsion, and mission payload choices, an integrated performance analysis of in-space propulsion options (differentiated by the number of Delta IH Heavy or Centaur V1 upper stages) was carried out over a range of possible payloads. The results are shown in Figure 4 and Figure 5; payload masses for different mission types as well as LEO-launch mass limits for different launch vehicle choices are highlighted.<br /> <br /> == Preferred Interplanetary Transfer Vehicle Designs ==<br /> For each launch vehicle option, preferred interplanetary transfer vehicle designs were selected (see Figure 6):<br /> <br /> * For the 4-segment SRB, 3 SSME side-mount and in-line vehicles, using a two-launch architecture with two sequentially mounted Centaur V1 upper stages and the additional crew compartment and science payload on the first launch, and two sequentially mounted Centaur V1 upper stages and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch (two sequentially mounted Centaur V1 upper stages and the CEV) can be utilized alone to carry out lunar flyby and orbit missions.<br /> * For the 5-segment SRB, 4 SSME in-line vehicle, using a two-launch architecture with two sequentially mounted Delta IV Heavy upper stages on the first launch, and one Delta IV Heavy upper stage, the additional crew compartment and science payload and the CEV on the second launch is the preferred configuration. The vehicle and spacecraft for the second launch without the extra crew compartment can be utilized alone to carry out lunar flyby and orbit missions.<br /> <br /> == Conclusions and Further Work ==<br /> From the above analyses, a number of findings can be derived:<br /> <br /> * Significant exploration beyond LEO is possible based on a shuttle-derived heavy-lift launch vehicle with a LEO net payload capability of more than 70 mt, the CEV, adapted EELC upper stages, and an additional pressurized crew compartment (for longer-duration missions).<br /> * The missions enabled by the above elements can provide significant operational experience beyond LEO, provide insight into the effects of the interplanetary radiation environment on humans, and result in sample return from Near Earth Objects.<br /> * These missions require no more than 1-2 launches of the heavy-lift launch vehicle; assuming that the heavy-lift launch vehicle can be launched 4-6 times per year (supported by the record of shuttle launches), 2-3 such 2-launch missions could be carried out each year.<br /> * The integrated performance analysis suggests that more ambitious deep space mission such as Mars flyby missions may be possible given a two-launch architecture using one of the above launch vehicles. <br /> <br /> A number of recommendations for future work could also be derived:<br /> <br /> * While the above missions are of particular relevance to the Flexible Path scenario, these missions are relevant as initial exploration missions to whatever scenario is chosen for NASA’s future human spaceflight strategy.<br /> * The preferred interplanetary transfer vehicle concepts should be subjected to more detailed design analysis.<br /> * The application of 2-launch architectures to more ambitious deep space missions such as Mars flyby missions should be investigated.<br /> * The analysis should be extended to include other currently available in-space propulsion and habitation assets. <br /> <br /> == References ==<br /> [1] Review of Human Spaceflight Plans Committee, Seeking a Human Spaceflight Program Worthy of a Great Nation – Final Report, Washington, DC, October 2009.<br /> <br /> [2] International Academy of Astronautics, The Next Steps in Exploring Deep Space – Final Report, July 9, 2004.<br /> <br /> [3] Shannon, J., Shuttle-Derived Heavy Lift Launch Vehicle, Presented to the Review of U.S. Human Spaceflight Plans Committee, June 17, 2009.<br /> <br /> [4] Exploration Systems Architecture Study Team, Exploration Systems Architecture Study - Final Report, NASA, November 2005.<br /> <br /> [5] Wade, M., Centaur website - http://www.astronautix.com/stages/centaur.htm, accessed January 28, 2010.<br /> <br /> [6] Wade, M., Delta IV website - http://www.astronautix.com/lvs/deltaiv.htm, accessed January 28, 2010.<br /> <br /> [7] Korsmeyer, D., Constellation Enabled Mission: Human Exploration of Near Earth Objects - Technical Assessment Study, NASA Advisory Council Briefing, July 18, 2007.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2391 2010-04-25T02:40:24Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [[Open_Source_Engineering_Tools|Open Source Engineering Tools]]<br /> <br /> Aims to catalog, review, aid in the use of, and encourage the creation and enhancement of open source tools for engineering (with a particular emphasis towards space).<br /> <br /> [[InterestingLinks|Interesting Links]]<br /> <br /> Links to external sites of interest for the DevelopSpace concept<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [[DevelopSpace_Information_Systems| DevelopSpace Information Systems]]<br /> <br /> Effort intended to foster the establishment and support of DevelopSpace&#039;s information systems, including project hosting infrastructure.<br /> <br /> [[SiteRequests| A List of Site Requests]]<br /> <br /> This is where to discuss features you would like to see included as part of the DevelopSpace platform.<br /> &lt;/div&gt;<br /> <br /> __NOTOC__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Follow-on_Projects&diff=2390 2010-04-18T23:17:47Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> For the following three technologies / systems, further in-depth analysis and prototype development / test could deliver significant benefit:<br /> <br /> = Surface power =<br /> <br /> *Further parametric analysis and modeling<br /> <br /> *More detailed design of selected architectures<br /> <br /> *Development of a solar array deployment prototype and test<br /> <br /> = Mars aerocapture and EDL =<br /> <br /> *Comprehensive search for available aerodynamic data<br /> <br /> *More detailed trajectory and aerodynamic modeling, including entry GN&amp;C<br /> <br /> *Analysis of aeroshell structural design and internal layout<br /> <br /> = Logistics, re-supply and ISPP =<br /> <br /> *Further analysis of packaging of re-supply, possibly development of a prototype and field testing<br /> <br /> *More detailed parametric modeling of life-support and crew systems<br /> <br /> *More detailed exploration of the ISPP architecture space<br /> <br /> *More detailed modeling of spare part needs and in-situ manufacturing</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Mars_Wish_List&diff=2389 2010-04-18T23:17:37Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> The following is a list of items (technologies, designs, datasets, etc.) that would be useful to an endeavor aiming to send humans to Mars -- in particular as part of a minimal initial &quot;toe-hold&quot; outpost, such as that being designed by the [[Minimalist Human Mars Mission]] project. The emphasis is on items which could reasonably be developed in the next 5 to 10 years with relatively modest resources and in something approaching a university or other research group setting, with the possibility also for individual contributions.<br /> <br /> In general, to be most useful, an item would have seen significant hardware development and on Earth ground testing (where possible). The solution would also be an open implementation, where anyone could pick the design up and use it as is or modify it as appropriate for their needs. In other words, something developed with an approach along the lines of what DevelopSpace espouses -- namely, that technical information be shared in an open source manner to accelerate its spread and make it more valuable to users.<br /> <br /> Please comment on and enhance this list, including by linking to activities and resources of relevance to the items here. Hopefully this list will also as an inspiration for individuals and groups aiming to hasten the day when humans walk on Mars.<br /> <br /> <br /> =Interplanetary Transportation=<br /> <br /> ==Mars Landing Navigation Systems==<br /> <br /> Automated navigation systems for Mars surface landing, including hazard identification and avoidance. Could include use of pre-emplaced navigation aids for targeted landing relative to existing surface assets.<br /> <br /> ==In-situ produced propellant rocket performance characterization==<br /> <br /> Characterization of rocket engine performance using propellants produced locally on Mars. Primarily of interest for a round-trip Mars mission, as opposed to a one-way settlement focus. Propellants of interest include ethylene-oxygen (C2H4/LOX) and methane-oxygen (CH4/LOX).<br /> <br /> ==Large-scale Mars aero-entry technology==<br /> <br /> Development of technologies to enable entry, descent, and landing (EDL) of masses greater than those supported by current robotic Mars EDL technology. Ability to support masses of greater than 10 mt in a single aeroshell.<br /> <br /> ==Deep-space navigation systems==<br /> <br /> Hardware, software, and complete solutions for deep-space navigation (out to approximately 2 AU). Emphasis on low mass, cost, and power. Would ideally not require investment in significant infrastructure at Earth or Mars.<br /> <br /> =Power=<br /> <br /> ==Mars surface solar power==<br /> <br /> Automated, large scale (football field+) solar array transport, surface deployment, and maintenance systems<br /> <br /> ==Surface energy storage systems==<br /> High energy density electrical power storage systems (aiming in particular towards high energy density relative to Earth imported mass)<br /> <br /> ==Internal combustion engines==<br /> Mars surface internal combustion engines (LOX, plus various fuels, e.g., C2H4, CH4, CO, etc), possibly with water exhaust reclamation.<br /> <br /> =Life Support, Logistics, and Local Resource Utilization=<br /> <br /> ==Atmospheric gas collection systems==<br /> Mars atmosphere collection systems (at minimum CO2; adding N2 and Ar is useful; H2O depends on energy/mass intensity relative to other options)<br /> <br /> ==Water-ice extraction systems==<br /> Mars permafrost mining systems (for varying wt% H2O); note, this is much easier than mining putative lunar ice<br /> <br /> ==High capacity cryocoolers==<br /> Good, high capacity Mars surface cryocoolers (options for just soft/medium cryogens (e.g., LOX, CH4, C2H4), or also for hard cryogen (LH2))<br /> <br /> ==Hydrogen transport technology==<br /> Earth-Mars hydrogen transport systems (not necessarily as LH2)<br /> <br /> ==Local resource chemical processing==<br /> Basic ISRU chemical processing systems (e.g., H2O electrolysis, Sabatier, RWGS, CO2 electrolysis, ethylene production, etc.)<br /> <br /> ==General life support systems==<br /> High closure physical-chemical life support systems (e.g., air revitalization, water recycling)<br /> <br /> ==Food storage and transport from Earth==<br /> &quot;Food system&quot; for food supplied from Earth. Consider being able to survive on food shipped 5 years ago.<br /> <br /> ==Mars surface food production systems==<br /> Means to produce food on the surface of Mars. Could include small scale systems for supplementing food transported from Earth as well as eventual full scale systems that could provide for the majority of the sustenance for the surface population.<br /> <br /> ==Simple in-situ manufacturing systems==<br /> Means of making simple spare parts and other critical elements. Initial emphasis on simple machine shop type tools along with stereo lithography techniques.<br /> <br /> ==Simple raw materials production==<br /> Production of raw materials without extensive infrastructure needs. Includes plastics such as polyethylene, epoxies, simple ceramics, etc. Would include identification of simple materials whose local production could have benefits sufficient to make-up for the investment in infrastructure.<br /> <br /> =Outpost and Surface Exploration Systems=<br /> <br /> ==Mars surface communication and navigation systems==<br /> Enable moderate to long distance overland communication and navigation without the use of an extensive satellite constellation. A variety of approaches exist to accomplish this, and options could be pursued in parallel.<br /> <br /> ==Very high data rate Mars-Earth back-haul comm system==<br /> Provides for large quantities of data collected by the systems on Mars to be transferred back to Earth. It may be worth exploring optical in addition to RF data transmission methods.<br /> <br /> ==Good Mars surface EVA suits==<br /> Suits that could support human performed exploration and maintenance activities outside of pressurized habitats or rovers. Ideally would be able to support hundreds of EVAs with limited maintenance and need for spare parts.<br /> <br /> ==Data collection, analysis for site selection==<br /> This is a precursor activity focused on identifying and assessing potential outpost locations. Includes acquiring additional data to support assessment.<br /> <br /> ==Very long distance surface mobility systems==<br /> To maximize exploration effectiveness, and possibly to make possible the use of specific resources, having a method of traversing 100&#039;s to 1000&#039;s of km across the surface of Mars would be useful. Methods of doing so in an automated fashion, in addition to doing so with personnel involved, would be beneficial.<br /> <br /> ==Solar flare / SPE warning systems==<br /> Systems for detection and warning of hazardous solar events. Could include means of forecasting events prior to occurrence, with some level of uncertainty associated with the forecast.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Follow-on_Projects&diff=2388 2010-04-18T23:17:08Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> <br /> For the following three technologies / systems, further in-depth analysis and prototype development / test could deliver significant benefit:<br /> <br /> = Surface power =<br /> <br /> *Further parametric analysis and modeling<br /> <br /> *More detailed design of selected architectures<br /> <br /> *Development of a solar array deployment prototype and test<br /> <br /> = Mars aerocapture and EDL =<br /> <br /> *Comprehensive search for available aerodynamic data<br /> <br /> *More detailed trajectory and aerodynamic modeling, including entry GN&amp;C<br /> <br /> *Analysis of aeroshell structural design and internal layout<br /> <br /> = Logistics, re-supply and ISPP =<br /> <br /> *Further analysis of packaging of re-supply, possibly development of a prototype and field testing<br /> <br /> *More detailed parametric modeling of life-support and crew systems<br /> <br /> *More detailed exploration of the ISPP architecture space<br /> <br /> *More detailed modeling of spare part needs and in-situ manufacturing</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/References&diff=2387 2010-04-18T23:17:01Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> The following is a list of key references for the MinMars project.<br /> <br /> =Key References=<br /> <br /> *One-way to Mars, George W. Herbert, AAS 96-322, The Case for Mars VI : Making Mars an Affordable Destination, Boulder, CO, 1996.<br /> <br /> * [http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980037039_1998107111.pdf The Reference Mission of the NASA Mars Exploration Study Team, NASA/SP-6107 (PDF)] [July 1997]<br /> <br /> * [http://ston.jsc.nasa.gov/collections/TRS/_techrep/SP-6107-ADD.pdf Addendum to the NASA Mars DRM, NASA/SP—6107–ADD (PDF)] [June 1998]<br /> <br /> * [http://ston.jsc.nasa.gov/collections/TRS/_techrep/TP-2001-209371.pdf NASA Mars surface reference mission, NASA/TP—2001–209371 (PDF)] [December 2001]<br /> <br /> *[http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000025321_2000013335.pdf Human Mars Mission Weights and Mass Properties, NASA CR-2000-209874 PT1 (PDF)] [Brothers, October 1999]<br /> <br /> *[http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070025041_2007023230.pdf Exploration Blueprint Data Book, NASA TM-2007-214763 (PDF)] [Bret Drake, July 2007] Great source of NASA concepts for human exploration from the late 1990s and early 2000s<br /> <br /> *[http://www.lampsacus.com/documents/MARSDIRECTSPACEEXPLORATION.pdf Mars Direct - A Simple, Robust, and Cost Effective Architecture for the Space Exploration Initiative (PDF)] [Zubrin, 1991] Overview of the Mars Direct exploration architecture<br /> <br /> *[http://www.ssdl.gatech.edu/TechPapers.htm Georgia Tech SSDL - Technical Papers] Georgia Institute of Technology Space Systems Design Lab - Technical Papers on Mars EDL<br /> <br /> *[http://trs-new.jpl.nasa.gov/dspace/bitstream/2014/41432/1/09-3135.pdf Austere Human Mission to Mars] NASA JPL (H. Price et al) Minimalist Mars Design Reference Mission [Space 2009 AIAA Conference Paper]<br /> <br /> *[http://trs-new.jpl.nasa.gov/dspace/bitstream/2014/41431/1/09-3642.pdf Austere Human Mission to Mars] NASA JPL (H. Price et al) [AIAA Presentation Slides]<br /> <br /> *[http://www.nasa.gov/pdf/373665main_NASA-SP-2009-566.pdf NASA Design Reference Architecture 5.0] NASA-SP-2009-566 [July 2009]<br /> <br /> *[http://www.nasa.gov/pdf/373667main_NASA-SP-2009-566-ADD.pdf NASA Design Reference Architecture 5.0 Addendum] NASA-SP-2009-566-ADD [July 2009]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Integration_of_Results&diff=2386 2010-04-18T23:16:53Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> =Repository of Working Models=<br /> <br /> * Manifests<br /> <br /> http://svn.developspace.net/svn/minmars/users/arthur/Manifest/</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Finance_and_Costing&diff=2385 2010-04-18T23:16:38Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> == Repository of Working Models ==<br /> <br /> http://svn.developspace.net/svn/minmars/users/arthur/cost%20analysis/</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/ISRU&diff=2384 2010-04-18T23:16:29Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> In-Situ Resource Utilization (ISRU) involves the use of resources found or manufactured at Mars in order to reduce the mission&#039;s dependency on supplies from Earth and improve living and working conditions at the outpost.<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/ISRU/<br /> <br /> = Possible ISRU Processes =<br /> <br /> The following processes have been identified as providing potential benefit for a Mars toehold outpost.<br /> <br /> <br /> == Atmospheric CO2 Compression ==<br /> *Process description: compression of Martian atmosphere (mostly CO2)<br /> *Scaling values (based on NASA Mars DRM 1.0):<br /> **Mass requirement: 3 kg equipment / kg CO2 per day (System is assumed to include thermal control equipment)<br /> **Power requirement: 15 We / kg CO2 per day<br /> **Volume requirement: ???<br /> <br /> == Buffer Gas Extraction ==<br /> *Process description: ???<br /> *Scaling values (based on NASA Mars DRM 1.0):<br /> **Mass requirement: 3 kg equipment / kg N2 per day (System is assumed to include thermal control equipment)<br /> **Power requirement: 15 We / kg N2 per day<br /> **Volume requirement: ???<br /> <br /> == Sabatier Process ==<br /> *Chemical reaction: CO2 + 4 H2 &lt;-&gt; CH4 + 2 H2O<br /> *Scaling values (based on NASA Mars DRM 1.0):<br /> **Mass requirement: 22 kg equipment / kg H2O per day (System is assumed to include thermal control equipment)<br /> **Power requirement: 50 We / kg H2O per day<br /> **Volume requirement: ???<br /> <br /> == Reverse Water Gas Shift ==<br /> *Chemical Reaction: CO2 + H2 &lt;-&gt; H2O + CO<br /> * Scaling values: ???<br /> <br /> == CO2 Electrolysis ==<br /> *Chemical Reaction: CO2 &lt;-&gt; O2 + CO<br /> *Scaling Values (based on NASA Mars DRM 1.0):<br /> **Mass requirement: 40 kg equipment / kg O2 per day (System is assumed to include thermal control equipment)<br /> **Power requirement: 1190 We / kg O2 per day<br /> **Volume Requirement: ???<br /> <br /> == H2O Electrolysis ==<br /> *Chemical reaction: 2 H2O &lt;-&gt; O2 + 2 H2<br /> *Scaling Values: ???<br /> <br /> == Ethylene Synthesis ==<br /> *Chemical reaction: 2 CO + 4 H2 &lt;-&gt; C2H4 + 2 H20<br /> **RWGS as precursor reaction<br /> *Scaling values: ???<br /> <br /> == Soil Water Extraction ==<br /> *Process description:<br /> **Transparent tent is used as greenhouse to heat surface soil to evaporate water in soil<br /> **Water is condensed at cold plate in tent and collected<br /> **Soil water content of 3% (by mass) assumed<br /> *Scaling values:<br /> **Mass Requirement: 1 kg equipment / kg H2O per day (based on Case for Mars, Ch 7) (System is assumed to include thermal control equipment)<br /> **Power Requirement: 500 We / kg H2O per day (this is an estimate)<br /> **Volume Requirement: ???<br /> <br /> = Proposed ISRU architectures =<br /> <br /> [[Image:ISRU_architecture_1.jpg| thumb|center|upright=2.5| alt=ISRU architecture #1| ISRU architecture #1]] [[Image:ISRU_architecture_2.jpg| thumb|center|upright=2.5| alt=ISRU architecture #2| ISRU architecture #2]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Logistics&diff=2383 2010-04-18T23:16:21Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Logistics/<br /> http://svn.developspace.net/svn/minmars/users/arthur/Purification/<br /> <br /> = Preliminary Logistics Assessment =<br /> <br /> == General Study Objectives ==<br /> *Carry out an assessment of re-supply needs for the outpost given different technologies<br /> **Including high-closure life support, ISRU<br /> *Identify key re-supply drivers and carry out in-depth analyses<br /> *Identify interesting technologies with high payoff in re-supply mass reduction<br /> **Carry out initial modeling and testing of these technologies<br /> *Formulate plan for further technology development<br /> <br /> == Preliminary Re-Supply Assessment (1) ==<br /> [[Image:Preliminary_Re-Supply_Assessment_1.jpg| thumb|center|upright=2.5| alt=Preliminary Re-Supply Assessment (1)|Preliminary Re-Supply Assessment (1)]] <br /> <br /> == Preliminary Re-Supply Assessment (2) ==<br /> [[Image:Preliminary_Re-Supply_Assessment_2.jpg| thumb|center|upright=2.5| alt=Preliminary Re-Supply Assessment (2)|Preliminary Re-Supply Assessment (2)]] <br /> <br /> == Preliminary Insights ==<br /> *Existing technologies allow for re-supply masses per opportunity of under 2 mt / person<br /> *Remaining high-mass re-supply items are food and spare parts<br /> **These should be focus of in-depth analyses<br /> <br /> = Updated Logistics Assessment =<br /> <br /> == General Study Objectives ==<br /> *Carry out an assessment of re-supply needs for the outpost given different technologies<br /> **Including high-closure life support, ISRU<br /> *Identify key re-supply drivers and carry out in-depth analyses<br /> *Identify interesting technologies with high payoff in re-supply mass reduction<br /> **Carry out initial modeling and testing of these technologies<br /> *Formulate plan for further technology development<br /> <br /> == Mars Surface Habitat Architectures 1-5 ==<br /> <br /> [[Image:Mars_Surface_Habitat_Architectures_1-5.jpg| thumb|center|upright=2.5| alt=IMars Surface Habitat Architectures 1-5|Mars Surface Habitat Architectures 1-5]] <br /> <br /> == Mars Surface Habitat Architectures 5-9 ==<br /> <br /> [[Image:Mars_Surface_Habitat_Architectures_5-9.jpg| thumb|center|upright=2.5| alt=Mars Surface Habitat Architectures 5-9|Mars Surface Habitat Architectures 5-9]] <br /> <br /> == Mars Surface Habitat Architectures 9-13 ==<br /> <br /> [[Image:Mars_Surface_Habitat_Architectures_9-13.jpg| thumb|center|upright=2.5| alt=Mars Surface Habitat Architectures 9-13|Mars Surface Habitat Architectures 9-13]]<br /> <br /> == Preliminary Insights ==<br /> *Existing technologies allow for re-supply masses per opportunity of ~2mt / person<br /> **This includes fairly conservative tare fractions on pressurized logistics and fluid re-supply<br /> *Remaining high-mass re-supply items are:<br /> *Food<br /> *Spare parts (fans, multi-filtration beds, etc.)<br /> *Hygiene &amp; health re-supply (soap, first-aid, etc.)<br /> *Hydrogen for ISRU<br /> <br /> = Food Logistics Reduction =<br /> *Many options for closure of the food loop have been investigated over the decades<br /> *Two major families of option:<br /> **1. Chemical regeneration of food from waste<br /> ***Synthesized chemicals suitable for long-term ingestion include: glucose, glycerin, ethanol, formose sugars<br /> **2. Biological regeneration of food from waste<br /> ***Algae (also for CO2 regeneration)<br /> ***Higher plants (wheat, corn, vegetables, etc.)<br /> ***Animals (fish, chicken)<br /> <br /> == Food Sourcing ==<br /> *Reminder: food remains one of the largest re-supply items (strong incentive for achieving higher closure)<br /> *Ways to close the food loop (in order of difficulty)<br /> **Growing fruits / vegetables with aeroponics / hydroponics<br /> **Growing algae, subsequent processing into edible form<br /> **Growing edible fungi (for some types no light required)<br /> **Traditional soil agriculture using Martian soil / regolith<br /> **Breeding animals (chicken, fish; both still quite inefficient)<br /> **Chemical regeneration of foods (formose, lipids, starch etc.)<br /> **Analysis required to determine which ways are most effective during different stages of colony<br /> *Notional roadmap as point of departure:<br /> **Phase 1:<br /> ***Food mostly imported from Earth in de-hydrated form<br /> ***Some fruits and vegetables grown hydro- / aeroponically to supplement de-hydrated food (nutrients brought from Earth)<br /> ***Possibly use of some fungi / algae as nutrition supplement<br /> **Phase 2:<br /> ***Food partially imported from Earth, partially generated locally<br /> ***In-situ nutrient production, use of Martian soil<br /> ***Possibly use of some fungi / algae as nutrition supplement<br /> **Phase 3:<br /> ***Food mostly produced on Mars using in-situ nutrients and soil<br /> ***Algae and fungi as supplement, possibly also some animals<br /> ***Predominantly vegetarian life-style<br /> <br /> = Surface Manufacturing =<br /> <br /> == Surface Manufacturing Strategy ==<br /> *Major needs during the early toehold stage:<br /> **Manufacturing of spare parts for subsystems<br /> **Manufacturing of IVA / EVA tools<br /> **Possibly manufacturing of structure for expansion of pressurized volume and for ISCP<br /> *Materials than can be produced in-situ on Mars:<br /> **Polyethylene (PE) and other polymers (from RWGS)<br /> **Iron / steel (significant infrastructure required)<br /> **Ceramics and bricks (from baking regolith)<br /> **Aluminum (significant infrastructure required)<br /> **Copper (significant infrastructure required)<br /> *Chapter 7 in Zubrin’s case for Mars provides a good overview<br /> *Quantitative assessment of infrastructure required<br /> *Acquiring water on Mars<br /> **4 possible sources:<br /> ***Underground aquifer<br /> ***Topsoil (1-3% by weight)<br /> ***Atmosphere<br /> ***Permafrost<br /> *Extraction from topsoil and atmosphere may be easiest initially (less infrastructure)<br /> **Could use tent-like structure, condenser, and sunlight (concept by Zubrin)<br /> *Water provides breathing oxygen and hydrogen for further ISCP (also PE)<br /> *It has been proposed to synthesize PE based on products from RWGS:<br /> **6H2+2CO2=&gt;2H2O+2CO+4H2<br /> **2CO+4H2=&gt;C2H4+2H2O<br /> **n x C2H4 =&gt; PE<br /> *We need to carry out a more detailed analysis of these processes<br /> <br /> = Minimal Industrial Needs for a Minimal Mars Colony - A Home O&#039;Centric Insight (By: Andrew Tubbiolo) =<br /> <br /> *What is a colony? It is a home.<br /> **Terrestrial Home<br /> ***Constant influx of goods.<br /> ***Constant influx of food.<br /> ***Constant efflux of waste.<br /> **Colonial Home<br /> ***Constant need to manufacture or remanufacture goods.<br /> ***Production of food and air<br /> ***Reprocessing of waste<br /> *Means of Manufacturing is the Linchpin<br /> **What do you need to manufacture goods?<br /> **What do you need to make the tools to grow food?<br /> **What do you need to make the tools to reprocess and reuse waste streams?<br /> **You need tools.<br /> *What Kind of Tools?<br /> *Mechanical<br /> *Electrical<br /> ==Mechanical Ensemble==<br /> *The Lathe.<br /> **Work rotates.<br /> **Tool moves about work.<br /> **Machines conical sections<br /> **Holds accuracy to 0.001”<br /> **Can make parts for engines in the tens of kilowatt class<br /> *The Mill<br /> **Tool rotates<br /> **Work is moved about the tool.<br /> **Used to machine planer sections.<br /> **Machines to 0.001”.<br /> **Up to tens of kilowatt class machines.<br /> *Surface grinder<br /> **Tool rotates<br /> **Work moved about tool<br /> **Machines planer surfaces<br /> **Accuracy to 0.0001”<br /> ==Electrical Ensemble.==<br /> *EDA Tools.<br /> **Specify system needs.<br /> **Schematic capture.<br /> **Simulation.<br /> **PCB Layout<br /> *Circuit Prototype<br /> **Test ideas and concepts in a manner that allows fast changes.<br /> *PCB Fabrication<br /> **Manufacture permanent solution on site<br /> *Test Equipment<br /> **Logic Analyzer<br /> ***Monitor many channels logic state simultaneously<br /> **Oscilloscope<br /> ***Monitor signals to high resolution<br /> **EDA PC Environment<br /> ***Project documents<br /> <br /> ==Putting it all together==<br /> *Terrestrial thermal power source project rated at 500+ W<br /> **Aluminum foundry<br /> **Thermal engine power source<br /> **Thermal refrigeration power source<br /> **Power source for a small boiler<br /> <br /> *Mechanical Mounts<br /> **Integration sphere interface<br /> ***Fast on demand fabrication<br /> ***Allows reactions to needs not foreseen<br /> <br /> *Propulsion<br /> **A tall order for sure, but on Mars even simple propulsion systems can be quite effective.<br /> <br /> *Constant Needs of Colonial Industry<br /> **Support Systems<br /> ***Power generation<br /> ***Atmosphere generation<br /> ***Raw materials<br /> ***Food production<br /> ***Transportation<br /> ***Tool needs for goods requirements<br /> **Industrial Expansion<br /> ***Use your tools to make more tools<br /> ***Raw materials mining<br /> ***Refinement<br /> ***Component manufacturing<br /> ***Tool manufacturing<br /> <br /> ==Conclusion==<br /> *Tools make the colony.<br /> *Tools provide the goods needed to support human life.<br /> *Tools provide the means to make new tools.<br /> *Tools provide means to expand.<br /> *Colonizing is an effort in tool making and operations.<br /> *Engineered systems can be built integrated and tested in the terrestrial home.<br /> *Colonize the home as a prelude to Mars.<br /> <br /> = Water Recycling / Spares Management =<br /> <br /> ==Introduction ==<br /> *A review of the major methods for water recycling.<br /> *The spares needs for the different technologies are identified<br /> *The future work will consist in completing the estimates of the spares amounts for the different technologies<br /> <br /> ==Water recycling methods==<br /> ===Distillation (phase change processes)===<br /> *Vapor compression distillation (VCD)<br /> *Thermoelectric integrated membrane evaporation (TIMES)<br /> *Vapor phase catalytic ammonia removal (VAPCAR)<br /> *Other<br /> <br /> ===Filtration===<br /> *Reverse osmosis (RO)<br /> *Multifiltration<br /> *Other<br /> <br /> ===Differences between distillation and filtration===<br /> *Higher quality water (i.e. potable) is usually recycled using distillation, because it is a process conducted at higher temperatures (phase change) thus killing bacteria. Lower quality water (i.e. flush water) is recycled by filtration.<br /> <br /> ==Distillation Systems Spares Needs==<br /> *Vapor Compression Distillation (VCD)<br /> **H2O Pre-treatment expendable chemicals<br /> **H2O Post-treatment expendable chemicals<br /> **Components of Evaporator, Condenser, Condensate collector<br /> *Thermoelectric Integrated Membrane Evaporation Subsystem (TIMES)<br /> **H2O Pre-treatment expendable chemicals<br /> **H2O Post-treatment expendable chemicals<br /> **Thermoelectric Heat Pump<br /> **Hollow fiber membranes<br /> *Vapor Phase Catalytic Ammonia Removal (VAPCAR)<br /> **No expendable chemicals<br /> **Hollow fiber membranes<br /> **Catalyst beds<br /> <br /> ===VCD Data [Ref Zdankiewicz &amp; Chu]===<br /> <br /> *Component: Distillation Unit<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 18400<br /> ***In Normal Mode: 8012<br /> **Mass [kg]: 16<br /> **Vol, [m^3]: 28.4<br /> <br /> *Component: Liquid Level Sensor<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 17200<br /> ***In Normal Mode: 6812<br /> **Mass [kg]: ???<br /> **Vol, [m^3]: ???<br /> <br /> *Component: Still Drive Motor<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 5512<br /> ***In Normal Mode: 5512<br /> **Mass [kg]: ???<br /> **Vol, [m^3]: ???<br /> <br /> *Component: Fluids Pump<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 18400<br /> ***In Normal Mode: 7012<br /> **Mass [kg]: 6.4<br /> **Vol, [m^3]: 9.3<br /> <br /> *Component: Peristaltic Tubing<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 17520<br /> ***In Normal Mode: 7012<br /> **Mass [kg]: ???<br /> **Vol, [m^3]: ???<br /> <br /> *Component: Waste Storage Tank<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 14600<br /> ***In Normal Mode: 6812<br /> **Mass [kg]: ???<br /> **Vol, [m^3]: ???<br /> <br /> *Component: Recycle/Filter Tank<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 10900<br /> ***In Normal Mode: 6812<br /> **Mass [kg]: 5.9<br /> **Vol, [m^3]: 72.3<br /> <br /> *Component: Ancillary Components (valves, sensors, plumbing)<br /> **Demonstrated Life [hr]<br /> ***Direct Exposure to Environment: 16380<br /> ***In Normal Mode: 5992<br /> **Mass [kg]: ???<br /> **Vol, [m^3]: ???<br /> <br /> *VCD is sized to process 18.1 kg/d of liquid waste to meet the needs of a three-person crew;<br /> *Recycle tank (the one in the table is the dry weight) sized for 90-day operation at 0.18 kg/p/d of solids to meet the needs of a three-person crew;<br /> *Packaging overhead is 12%.<br /> <br /> ==Filtration Systems Spares Needs==<br /> *Reverse Osmosis<br /> **Membranes. Alternatives:<br /> ***Inside skinned hollow fiber membrane<br /> ***Dual layer membrane<br /> **Multifiltration<br /> ***Filters<br /> ***Ion-exchange resin beds<br /> ***Charcoal<br /> <br /> == References ==<br /> *Budininkas, P., Rasouli, F. and Wydeven, T. Development of a Water Recovery Subsystem Based on Vapor Phase Catalytic Ammonia Removal (VPCAR) 1986<br /> *Dehner, G. F., Reysa, R. P. Thermoelectric Integration Membrane Evaporation Subsystem Water Recovery Technology Update 1985<br /> *Dehner, G. F., Winkler, E. H. and Reysa, R. P. Thermoelectric Integrated Membrane Evaporation Subsystem Operational Improvements 1984<br /> *Gorensek, M. B., Baer-Peckham, D. Space Station Water Recovery Trade Study - Phase Change Technology 1988<br /> *Herrmann, C. C. High-Recovery Low-Pressure Reverse Osmosis 1992<br /> *Hitt, A. J., III, Renfro, R. H., Schien, K. F. and Streams, E. Criteria Definition and Performance Testing of a Space Station Experiment Water Management System 1988<br /> *Ishida, H., Ohshima, M., Shimoda, T. and Shiraishi, A. Development of Low Pressure Membrane Distillation 1998<br /> *Noble, L. D. J., Schubert, F. H. and Graves, R. E. An Assessment of the Readiness of Vapor Compression Distillation for Spacecraft Wastewater Processing 1991<br /> *Ray, R. Membrane-Based Water and Energy-Recovery Systems for the Manned Space Station 1985<br /> *Ray, R. J., Babcock, W. C., Barss, R. P., Andrews, T. A. and LaChapelle, E. D. A Novel Reverse-Osmosis Wash Water Recycle System for Manned Space Stations 1984<br /> *Reysa, R. P., Price, D. F., Olcott, T. and Gaddis, J. L. Hyperfiltration Wash Water Recovery Subsystem - Design and Test Results<br /> *Schubert, F. H. Phase Change Water Recovery Techniques: Vapor Compressor Distillation and Thermoelectric/Membrane Concepts 1983<br /> *Winkler, E. H., Verostko, C. E. and Dehner, G. F. Urine Pretreatment for Waste Water Processing Systems 1983<br /> *Zdankiewicz, E. M., Chu, J. Phase Change Water Recovery for Space Station - Parametric Testing and Analysis 1986<br /> <br /> ==Vapor Compression Distillation Example==<br /> *http://www.aquatechnology.net/vaporcompressiondistillers.html<br /> **Step 1: In a vapor compression(VC) system, the distillation process begins in the boiling chamber, just as it does in virtually any other distiller. What separates this method from other distillation methods is what comes after the boiling chamber.<br /> **Step 2: In a Vapor Compression VC6000, VC3000, VC1500 and VC800 system the boiling process begins with both heating elements turned on. As the water in the boiling chamber reaches near boiling temperatures, the compressor turns on, which engages the unique non-contacted liquid ring seal.When the boiling begins, the #2 heating element turns off and the #1 heating element cycles on and off maintaining the boiling at just the right temperature for maximum efficiency. The steam from the boiling water flows through a baffling system and then into the compressor.<br /> **Step 3: In the compressor, the steam is pressurized, which raises the steam&#039;s temperature before it is routed through a special heat exchanger located inside the boiling chamber. The steam (under pressure) is at a higher temperature than the feed water inside the boiling chamber<br /> **Step 4: The pressurized steam gives off its heat to the tap water inside the boiling chamber, causing this water to boil, which creates more steam. In technical terms, the steam &quot;gives up its latent heat of vaporization&quot; to the water inside the boiling chamber.<br /> **Step 5: While the pressurized steam is giving up its latent heat, the steam will condense. One of the heating elements will cycle on and off periodically as needed to provide any &quot;make-up&quot; heat that is required to keep the system operating at optimum temperature for maximum efficiency.<br /> **Step 6: At this stage, the condensed steam is considered distilled water but is still very hot--only slightly cooler than boiling temperature. To get maximum efficiency from the VC systems, the hot distilled water preheats the incoming feed water that will be distilled.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Surface_Mobility&diff=2382 2010-04-18T23:16:13Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> = Repository of Working Models =<br /> <br /> NONE<br /> <br /> =Baseline Surface Mobility Capabilities=<br /> *Unpressurized<br /> **2 independent unpressurized rovers on traverse, each can carry the entire crew back to base in contingency<br /> **Exploration radius is limited by contingency constraints and EVA time<br /> **Due to 2 independent vehicles on traverse drive-back constraint applies<br /> **This is different from the walk-back constraint for Apollo traverses which had only a single vehicle – the LRV<br /> **20 – 25 km ideal exploration radius from base can be achieved for 6 – 8 hour excursion<br /> *Pressurized<br /> **2 independent pressurized vehicles on traverse, each can carry the entire crew back to base in contingency<br /> **Either the camper concept or a pressurized rover can be used (we think there are advantages to the camper concept)<br /> **Exploration radius is limited by consumables and energy storage mass rather than contingency constraints<br /> **For the analysis presented here we assumed 2 pressurized rovers with a total mass of 5700 kg (nominal 2 crew)<br /> <br /> [[Image:Baseline_Surface_Mobility.jpg| thumb|center|upright=2.5| alt=Baseline_Surface_Mobility.jpg|Baseline Surface Mobility Concept]] <br /> <br /> == Baseline Surface Exploration Capabilities == <br /> <br /> [[Image:Baseline_Surface_Mobility_Capabilities.jpg| thumb|center|upright=2.5| alt=Baseline_Surface_Mobility_Capabilities.jpg|Baseline Surface Mobility Capabilities]]<br /> <br /> == Extension of Pressurized Mobility Radius ==<br /> *Self-propelled trailer<br /> **5700 kg trailer, 1000 kg chassis + drive train and 4700 kg energy storage mass<br /> **Trailer is self-propelled<br /> ***Analysis shows parasitic drag results in higher mass than propelled trailer<br /> **Trailer is delivered to base as with logistics excess capability<br /> <br /> [[Image:Self_Propelled_Trailer.jpg| thumb|center|upright=2.5| alt=Self_Propelled_Trailer.jpg|Self Propelled Trailer Concept]]<br /> <br /> *“Mars gas station”<br /> **Self-propelled chassis with energy storage and solar power generation is pre-positioned<br /> **Crew visits station with pressurized rovers and swaps energy storage (“pit stop”)<br /> **Can theoretically be extended indefinitely<br /> <br /> [[Image:Mars_Gas_Station.jpg| thumb|center|upright=2.5| alt=Mars_Gas_Station.jpg|Mars Gas Station]]<br /> <br /> == Extended Surface Exploration Capabilities ==<br /> <br /> [[Image:Extended_Surface_Exploration_Capabilities_1.jpg| thumb|center|upright=2.5| alt=Extended_Surface_Exploration_Capabilities_1.jpg]]<br /> <br /> [[Image:Extended_Surface_Exploration_Capabilities_2.jpg| thumb|center|upright=2.5| alt=Extended_Surface_Exploration_Capabilities_2.jpg]]<br /> <br /> [[Image:Extended_Surface_Exploration_Capabilities_3.jpg| thumb|center|upright=2.5| alt=Extended_Surface_Exploration_Capabilities_3.jpg]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Surface_Infrastructure&diff=2381 2010-04-18T23:16:05Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Surface%20infrastructure/<br /> <br /> =Surface Infrastructure (Survival Infrastructure, Surface Operations, Operational Infrastructure)=<br /> <br /> ==Survival Infrastructure==<br /> *Habitation<br /> **Thermal, Structural, Crew Facilities, Radiation, Avionics<br /> *Logistics<br /> **Resupply options, ISRU capability<br /> *Power Supply<br /> **Power requirements, system robustness<br /> <br /> ==Surface Operations==<br /> *What does the crew do when they are on Mars (other than survive)?<br /> **Maintenance and repair (survival)<br /> **Infrastructure improvements<br /> **Public Relations<br /> **Exploration<br /> **Science<br /> *How many crew members are optimal?<br /> *What tools &amp; infrastructure are required?<br /> <br /> ==Operational Infrastructure==<br /> *Maintenance and Repair<br /> **Spares, Repair Tools, etc.<br /> **What is the sparing strategy?<br /> *Infrastructure Improvement<br /> **Technology Demonstrations (ISRU)<br /> **How can someone on Mars improve their own life?<br /> *Exploration Tools and Equipment<br /> **Robotic Assistants<br /> **What is the goal of exploration?<br /> *Science Tools and Equipment<br /> **Instruments and Payloads<br /> *Communications<br /> **Surface communications (Exploration &amp; Science), Earth-Mars communications (“Public Relations”), etc.<br /> *EVA Infrastructure<br /> **Suits, Consumables, etc.<br /> **What is the EVA frequency &amp; schedule?<br /> *Mobility Options<br /> **Habitat Mobility, Unpressurized Rovers, Pressurized Rovers, etc.<br /> **How much mobility is required?<br /> <br /> ==Future Work==<br /> *Further analysis of each segment of “operational infrastructure” to determine trade space<br /> **What exactly is needed?<br /> **What are the possible solutions?<br /> *Perform lit review to determine near-term capabilities for surface operations<br /> <br /> =Surface Infrastructure Update=<br /> <br /> ==Overview==<br /> *Ongoing process to size all surface infrastructure elements based on previous literature<br /> *Key questions being analyzed<br /> **What infrastructure is needed?<br /> **Can this be done in 5 – 10 mt landed payload?<br /> *Focused on two types of elements<br /> **Cargo<br /> ***Either pre-deployed or re-supply<br /> ***Pre-deployed must survive 2+ years on the surface<br /> ***How much autonomous construction is required?<br /> **Crewed<br /> ***30-day surface survival capability<br /> ***EVA Suits and Mobility included<br /> ***No consideration for in-space transit<br /> *Surface Infrastructure Categories<br /> **Structures<br /> ***Pressurized &amp; Unpressurized<br /> ***Habitation<br /> ***Rigid &amp; Inflatable<br /> **Power<br /> ***Minimal integrated power (for keep alive of pre-deployed elements)<br /> ***Deployed surface power<br /> **Thermal<br /> ***Minimal integrated thermal<br /> ***Deployed surface radiators<br /> **Communication &amp; Navigation<br /> ***Mars surface network<br /> ***Mars-Earth network<br /> **Life Support<br /> ***Based on Wilfried’s assessment<br /> **In-situ Resource Utilization<br /> ***Basic vs. extended capability<br /> **Crew systems<br /> ***Medical<br /> ***Hygiene<br /> **Maintenance &amp; Repair<br /> ***Facilities, Spare Parts, Raw Materials<br /> **Science &amp; Exploration<br /> ***Facilities &amp; Tools<br /> **Extra Vehicular Activities<br /> ***EVA Suits &amp; Spares<br /> **Surface Mobility<br /> ***Unpressurized Crew Mobility<br /> ***Pressurized Crew Mobility<br /> ***Asset Mobility<br /> **Consumables &amp; Logistics<br /> ***Initial cache &amp; resupply <br /> <br /> *Cargo Landers<br /> **Individual units that are able to sustain initial period without interaction with other systems<br /> ***Common structure (5m by 5m rigid cylinder) (~1mt)<br /> ***Basic power, thermal, communications, avionics (~ 1mt)<br /> ***Each element can carry ~3mt of payload<br /> **Approximately five cargo landers required<br /> ***Deployable power &amp; thermal systems<br /> ***Central life support and ISRU<br /> ***Logistics &amp; cargo lander<br /> ***Habitat lander(s)<br /> ***Mobility asset (pressurized and unpressurized rovers &amp; asset mobility)<br /> <br /> = A &quot;Small-Package Approach&quot; to Mars Surface Infrastructure (2mt case) =<br /> *Sizing the Small Packages<br /> **“Estimated landed payload mass extensibility of the MSL EDL architecture: ~2 t (max)”<br /> ***Mars Design Reference Architecture 5.0 Study – Executive Summary [B. Drake – Dec 4, 2008]<br /> **We can scale the MSL aeroshell based on a constant ballistic coefficient<br /> ***~30m^3 of volume available (~66 kg/m^3 cargo density)<br /> <br /> ==Surface Infrastructure==<br /> *Habitation elements<br /> **Habitable volume, crew accommodations, ECLSS, EVA systems, medical<br /> **Hard-shells &amp; inflatables<br /> *Mobility elements<br /> **Crew mobility &amp; infrastructure deployment (autonomously?)<br /> *Offloading infrastructure<br /> **Crane or davit could be used with mobility element<br /> *Logistics containers<br /> **Pressurized &amp; unpressurized logistics<br /> *Power system<br /> **Addressed independently of other infrastructure<br /> <br /> ===Habitation===<br /> *A combination of inflatable and hard-shell elements<br /> *3x cylindrical vertical hard-shells<br /> **2m diameter and 2.5 m height (~3.2 m^2)<br /> **1x EVA access and maintenance<br /> **1x ECLSS equipment / mission ops<br /> **1x crew accommodations (galley, WC)<br /> *3x inflatables (~35 m^2 each)<br /> **2x bedrooms (2 persons each)<br /> **1 x common space (wardroom, exercise, medical)<br /> <br /> *Inflatables<br /> **Antarctic Habitat Demonstrator<br /> ***8 ft max head room<br /> ***Floor area: 384 sq ft (24 ft x 16 ft) [35.7 m^2]<br /> ***Packed System: 1000 lbs [455 kg]<br /> ***2 packages (3 ft by 4 ft by 8 ft)<br /> ***Source: Spampinato, P. “Expandable Habitat Structures for Long Duration Lunar Missions”. 3rd Space Exploration Conference &amp; Exhibit. Feb 2008. ILC Dover.<br /> <br /> *Hard-Shell Structures<br /> **Hard-shell cylinders should be &lt; 1 mt to allow delivery of subsystems and should have multiple connection hatches to allow outpost assembly<br /> ***Based on current estimates of 2.5m high by 2m diameter cylinder has a mass of ~1mt (with adapters included)<br /> <br /> ===Mobility/Offloading Elements===<br /> *Deliver two mobility chassis with integrated offloading capability (crane)<br /> *Crew delivered in two pressurized cabs which double as pressurized rovers<br /> **CMC (Crewed Mobility Chassis)<br /> ***NASA’s current estimate for the CMC is 969 kg dry vehicle mass (3 mt payload)<br /> ***Source: Culbert, C. “Lunar Surface Systems Project Overview.” USCC Programmatic Workshop on NASA Lunar Surface Systems Concepts. NASA. Feb 2009. <br /> **LSMS (Lunar Surface Manipulator System)<br /> ***NASA’s current estimate for the LSMS is 190 kg (6 mt capability)<br /> ***Source: Culbert, C. “Lunar Surface Systems Project Overview.” USCC Programmatic Workshop on NASA Lunar Surface Systems Concepts. NASA. Feb 2009. <br /> **Mobility elements used for both crew exploration and infrastructure deployment<br /> **Crew cab for NASA’s SPR (Small Pressurized Rover) is ~3 mt<br /> <br /> ==Logistics==<br /> *Each logistics flight will require a hard-shell container for pressurized supplies with unpressurized pallet and fluids storage<br /> **2 mt for entire system (including wrappings)<br /> **Can we reuse the habitat hard-shell?<br /> ***Probably not because of unpressurized logistics mass<br /> **Transported using mobility element and attached to outpost<br /> <br /> ==Notional Deployment==<br /> *Opportunity One<br /> **Flight 1<br /> ***2x Mobility elements with cranes<br /> **Flight 2<br /> ***ECLSS Cylinder<br /> **Flight 3<br /> ***EVA Cylinder<br /> **Flight 4<br /> ***Crew Accommodations Cylinder<br /> **Flight 5<br /> ***Common Inflatable (plus fittings)<br /> **Flight 6<br /> ***Bedroom 1 Cylinder (plus fittings)<br /> **Flight 7<br /> ***Bedroom 2 Cylinder (plus fittings)<br /> **Flights 8 – 11<br /> ***Power<br /> *Opportunity Two<br /> **Flight 1-4<br /> ***Logistics<br /> **Flight 5-7<br /> ***Crew 1<br /> **Flight 8-10<br /> ***Crew 2<br /> *Opportunity Three+<br /> **Flight 1-4<br /> ***Logistics<br /> **Flight 5-10<br /> ***Infrastructure<br /> <br /> ==Notional Outpost==<br /> <br /> [[Image:Notional_2mt_Case_Outpost.jpg| thumb|center|upright=2.5| alt=Notional_2mt_Case_Outpost.jpg|Notional 2mt Case Outpost]] <br /> <br /> ==Summary/Notes/Future Work==<br /> *Summary<br /> **Based on a 2 mt payload, a initial outpost appears feasible with ~10 flights per opportunity<br /> *Notes<br /> **It may be necessary to delay crews one opportunity to emplace safety stocks (crew launches on third opportunity)<br /> **ECLSS/mission ops systems may require two cylinders<br /> **DRM 3.0 ECLSS ~4.6 mt (including consumables)<br /> *Future Work<br /> **Develop point designs to ensure feasibility of each element<br /> <br /> =Surface Infrastructure for the 10 mt case=<br /> <br /> <br /> ==Aeroshell==<br /> *Mass<br /> **Aeroshell mass set as a fraction of the payload mass (first estimate: AMF = 0.4)<br /> **Total mass set by launch vehicle capability (first estimate: Falcon 9 Heavy = 29,610)<br /> **Based on the above estimates there is 21,150 kg for payload (surface cargo + descent stage)<br /> <br /> [[Image:10mt_Aeroshell.jpg| thumb|center|upright=2.5| alt=10mt_Aeroshell.jpg|Notional Aeroshell for the 10 mt Case]] <br /> <br /> *Shape &amp; Volume<br /> **Aeroshell shape is estimated to have be a conical frustum with a base diameter of 7.0 m and a height of 6.5 m with a 20° wall angle<br /> **The aeroshell is assumed to be composed of two connected pieces<br /> ***A bottom section with a height of 2.5 m (based on descent engine height) which is jettisoned<br /> ****The useable volume of this section is a cylinder with a diameter of 5.18 m and a height of 2.5 m (52.7 m3)<br /> ***A top section with a height of 4.5 m and a base diameter of 5.18 m (usable volume = 47.5 m3)<br /> **The total usable volume for the aeroshell is 100.2 m3 <br /> <br /> ==Descent Stage==<br /> *Mass<br /> **One N2O4-MMH engine based on 26.7 kN OME<br /> ***Isp = 316 sec<br /> **Delta-V for terminal descent estimated to be 1200 m/s<br /> **Propellant required = 6,789 kg<br /> **Structural mass fraction for propulsion system = 0.2 <br /> ***Note: structural mass fraction is inert mass over propellant mass<br /> **Landing structure is estimated to be 10% of landed mass (approx 1,436 kg)<br /> **These estimates allow for 11,567 kg of surface cargo to be delivered each flight<br /> *Shape &amp; Volume<br /> **One N2O4-MMH engine based on 26.7 kN OME<br /> **Engine envelope of 2.5 m height by 1.5 m diameter<br /> **Two fuel tanks &amp; two oxidizer tanks<br /> ***Cylindrical with semi-spherical end-caps (3.0 m3)<br /> **Height: 2.5 m – Diameter: 1.4 m<br /> **Packaged to fit in 5.18 m diameter by 2.5 m height cylinder in lower section of aeroshell<br /> **Initial packaging leaves four “cargo bays” of approximately 4.0 m3 each<br /> <br /> [[Image:10mt_Descent_Stage_Packaging.jpg| thumb|center|upright=2.5| alt=10mt_Descent_Stage_Packaging.jpg|Notional Descent Stage Packaging for the 10 mt Case]] <br /> <br /> ==MinMars lander cargo capacity==<br /> *Top section of aeroshell<br /> **Conical frustum <br /> ***Available volume: 47.5 m3<br /> ***Base diameter: 5.19 m<br /> ***Height: 4.5 m<br /> ***Top diameter: 1.90 m<br /> *Bottom section of aeroshell<br /> **4 cargo bays<br /> ***Triangular prism<br /> ***Volume: 4.0 m3<br /> ***Base length : 1.79 m<br /> ***Height: 2.5 m<br /> *The maximum cargo volume is 63.5 m3.<br /> *The maximum cargo mass capacity is 11.57 mt.<br /> *Baseline architecture has two lander types<br /> **Unpressurized cargo delivery<br /> **Pressurized habitation &amp; logistics module<br /> <br /> ==Unpressurized Cargo Lander==<br /> *Common descent stage with four cargo bays<br /> *Large unpressurized cargo is placed on top of the descent stage and contained by aeroshell<br /> **Inflatable habitation modules<br /> **Surface power systems<br /> **Pressurized rovers<br /> *Large cargo will require a means of offloading<br /> **Crane &amp; surface mobility<br /> *How do we remove the top section of the aeroshell? <br /> <br /> ==Common Pressurized Module==<br /> *Concept: Use a common module for all habitation (hab, lab, workshop) and pressurized logistics delivery and add in necessary subsystem hardware to adapt each module to its needs<br /> *This concept may allow reuse of logistics modules as “hotel rooms” and eliminate the need for early inflatable modules (low TRL)<br /> *With large element surface mobility that is capable of transporting landers (over prepared ground) to allow connection between units would be beneficial<br /> <br /> ==Initial habitat concept==<br /> *Two floor habitat integral with top section of the aeroshell<br /> **Main floor is 2.5 m high with a floor area of 21 m2 (226 ft2)<br /> **Top floor is 2.0 m high with a floor area of 8.9 m2 (96 ft2)<br /> **Two floor are connected through a 1 m diameter tunnel in the middle of the floor<br /> *Habitat is connected to two “airlocks” which replace two cargo bays in the descent stage<br /> **Triangular prisms with a volume of 4m3<br /> <br /> ===Initial Subsystems===<br /> *Structures: 2400 kg<br /> **Based on surface area and area density from DRM 3.0 (21 kg/m2)<br /> *Life support systems: 316 kg<br /> **Based on two crew and HSMAD hardware for Wilfried’s architecture<br /> *Comm-info management: 320 kg<br /> **Taken from DRM 3.0<br /> *Thermal: 184 kg<br /> **Based on two crew and scaled from DRM 3.0<br /> *Total mass of generic pressurized element = 3220 kg<br /> *Cargo capacity remaining on lander = 8347 kg<br /> <br /> ==Logistics flights==<br /> *Pressurized logistics: 4000 kg (2 crew)<br /> **Estimated volume: 13-16 m3<br /> **Note: Usable volume on top floor is 9.6 m3<br /> *Unpressurized cargo: 1000 kg (spares, etc.)<br /> **Volume available is 4 m3<br /> *Furniture and interior furnishings: 2000 kg<br /> **Estimate (Cal Tech MSM estimated 1000 kg)<br /> **As logistics are used / moved (to other modules upper storage sections) habitat becomes available as living space<br /> *Flights 3 &amp; 4 (opportunity 2) can be used as logistics flights and provide two 2-person habitats<br /> <br /> ==Crew flights==<br /> *Two concepts: <br /> **Identical habitats with all required crew accommodations in each (for two crew)<br /> **One habitat (galley, wardroom, hygiene) &amp; one laboratory (medical, maintenance, etc)<br /> *First concept has each aeroshell pushed separately to Mars using two TMI stages each<br /> *Second concept has the crew join up and travel to Mars in two connected aeroshells<br /> **Crew all lands in habitat<br /> *In space power stage will be needed for transit to Mars<br /> **Either one or two depending on concept<br /> *Consumables for trip (4.5 kg/p/d for 210 days) total 3.78 mt and 12.5 – 15 m3<br /> **Can be stored in upper level storage area and used consumables can be jettisoned before entry to Mars<br /> *“Airlocks” can be modified for the trip to provide four private quarters with 4 m3 each.<br /> *Based on HSMAD, crew accommodations system hardware require ~2.9 mt for two crew<br /> *On Mars surface, top floor used for logistics storage, main floor for common area<br /> *Private quarters are set up in logistics modules<br /> *Is 21 m2 of floor space on the main floor enough for all common crew systems (galley, hygiene, operations, etc.)?<br /> *At Martian surface, crew will remain in habitat for ~7 days to acclimatize.<br /> *Then use unpressurized rovers (one per habitat in cargo bay) to transit to pre-positioned goods and work to set up base<br /> *Note: How do we supply surface power to Habitats before 25kW pre-positioned systems are connected? <br /> <br /> ==Other thoughts==<br /> *Inflatable modules may not be required on first flights<br /> **Replace with pressurized mobility?<br /> **Currently have 4 unpressurized rovers manifested<br /> ***One on each cargo flight<br /> ***One on each crewed flight<br /> *With four crew and a consumables requirement of 2 mt /opportunity/person:<br /> **Each of the following opportunities will require both flights to be logistics modules<br /> **Logistics modules could be adapted to be workshops, laboratories, etc. using the 2 mt set aside for furniture<br /> <br /> ==Notional Flight Manifest==<br /> *Opportunity 1 (identical flights)<br /> **1 pressurized rover<br /> **1 unpressurized rover<br /> **Surface power systems<br /> **Offloading hardware and large element mobility<br /> *Opportunity 2 (identical flights)<br /> **Pressurized module<br /> **Furniture to adapt to living quarters for two crew<br /> **Pressurized logistics<br /> **Unpressurized logistics<br /> *Opportunity 3 (crew)<br /> **One habitat (common area for four crew) flight<br /> **One laboratory / medical / exercise flight<br /> **2 unpressurized rovers<br /> *Opportunity 4+ (two identical flights)<br /> **Pressurized module<br /> **Pressurized logistics<br /> **Unpressurized logistics<br /> **How are these adapted?</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Surface_Power&diff=2380 2010-04-18T23:15:57Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Mars%20surface%20power/<br /> <br /> = Preliminary Surface Power System Assessment =<br /> <br /> [[Image:Preliminary_Surface_Power_System_Assessment.jpg| thumb|center|upright=2.5| alt=Preliminary_Surface_Power_System_Assessment.jpg| Preliminary Surface Power System Assessment]] <br /> <br /> = Mars Surface Power Generation and Energy Storage =<br /> <br /> == Surface Power Architecture Tree ==<br /> * There are two basic types of analyses that can be carried out:<br /> **Equal power analysis: all systems provide the same (constant) power output at any point in time<br /> **Equal energy analysis: all systems provide the same usable energy per day (for photovoltaic systems this means increased power generation during the day)<br /> <br /> [[Image:Surface_Power_Architecture_Tree.jpg| thumb|center|upright=2.5| alt=Surface_Power_Architecture_Tree.jpg| Surface Power Architecture Tree]] <br /> <br /> == Modeling ==<br /> *Created model for a Mars solar array based on following major requirements:<br /> **Array must be sized for end-of-life power generation capabilities<br /> **Array must be sized to provide the required power during the year’s minimum incident solar energy period<br /> *Model Assumptions:<br /> **On Mars, optical depth of 0.4 (equivalent to hazy skies)<br /> **Tracking arrays at both locations are multi-axis and keep incident flux perpendicular to array over the day<br /> **Nighttime power of 20 kW, with daytime power enforced when sun is 12 degrees above the horizon<br /> **Mars analysis done for an equatorial location (actually not optimal location for solar power on Mars):<br /> ***Optimal location at 31° N, with a minimum of 6.57(kW-h/m^2/sol) and 49% daylight/sol for a period of 100 sols <br /> ***Northern latitudes better than corresponding southern latitude<br /> <br /> [[Image:Daily_Solar_Incidence_Energy_Levels.jpg| thumb|center|upright=2.5| alt=Daily_Solar_Incidence_Energy_Levels.jpg| Daily Solar Incidence Energy Levels]] <br /> <br /> ===Inputs===<br /> *Minimum solar energy<br /> *Eclipse Time<br /> *Daytime/nighttime power req.<br /> *Power distribution eff.<br /> *Solar array eff.<br /> *Degradation per year<br /> *Array lifetime<br /> *Optical depth<br /> *Latitude<br /> *Array packing density<br /> *Battery type<br /> <br /> ===Outputs===<br /> *Array area<br /> *System mass<br /> *System volume<br /> <br /> == Results ==<br /> <br /> [[Image:Mass_Specific_Power.jpg| thumb|center|upright=2.5| alt=Mass_Specific_Power.jpg| Mass Specific Power]] <br /> <br /> [[Image:Volume_Specific_Power.jpg| thumb|center|upright=2.5| alt=Volume_Specific_Power.jpg| Volume Specific Power]] <br /> <br /> == Other Considerations for Large Solar Array Fields on Mars ==<br /> ===Deployment time===<br /> *Considered a 10,000 m^2 rollout array field which will provide 63kW average power for about 100kW daytime power<br /> *Assume array blankets are 2m wide for easy storage and handling by two astronauts<br /> *Assume each blanket weighs 100lbs again for easy handling<br /> *With 0.06 kg/m^2 expected array density, need only 14 blankets total<br /> *Assume astronauts can unroll array at a walking speed of 1m/s, requires only 3hrs for unrolling<br /> *Most time will be needed for unloading positioning and hookup, if assume 1hr for this for each array, total deployment time *approximately 17 work hours for 2 crew<br /> ===Power delivery during deployment===<br /> *If we are conservative and say deployment takes 1 week, we need either a 10kW RTG or fuel cell system to provide 10kW power over the week<br /> *RTG system would be approximately 1200kg and 0.6 m^3<br /> *If use RFC, need 2400kg system with volume 8.4 m^3<br /> <br /> == Future Work ==<br /> *Reassess architecture options in MinMars colony context. Previous power analysis for shorter round trip mission. <br /> *Operations considerations such as dust removal and maintenance.<br /> *Dust storm power generation.<br /> <br /> == Issues to be resolved ==<br /> *RFC performance may be significantly reduced compared to our assumptions<br /> **300 Wh/kg or less<br /> **Could possibly be enhanced by generating oxygen for RFC in-situ (~ 25% of RFC mass)<br /> *Effect of wind speed on roll-out arrays<br /> **Would they be blown away?<br /> *Degradation, dust removal<br /> *Robotic deployment<br /> <br /> = Surface Power Architecture Analysis Follow-up =<br /> <br /> == Areas of Revision ==<br /> *Regenerative fuel cell performance<br /> **Original Energy Density<br /> ***~700 Wh/kg<br /> **Revised Energy Density<br /> ***~250 Wh/kg<br /> *Wind considerations<br /> **Found that a wind speed of 7.35 m/s would in fact lift the solar array off the surface.<br /> **Altered conceptual array design to include Kevlar areas equal to 10% of the total array area to provide space for Martian rock placement for weighing down the array. <br /> **9.2 kg/m^2 of rock is needed in the 10% Kevlar regions to secure the array against the top recorded Mars wind of 25 m/s.<br /> **The major effect of this consideration is increased deployment time.<br /> *Latitude considerations<br /> **Ran model for multiple latitudes to show change in performance based on location.<br /> **Optimal location at 31° N, with a minimum of 6.57(kW-h/m^2/sol) and 49% daylight/sol for a period of 100 sols.<br /> **Northern latitudes better than corresponding southern latitude. <br /> <br /> == Updated Results==<br /> <br /> [[Image:Mass_Specific_Power_vs_Latitude.jpg| thumb|center|upright=2.5| alt=Mass_Specific_Power_vs_Latitude.jpg| Mass Specific Power versus Latitude]] <br /> <br /> [[Image:Volume_Specific_Power_vs_Latitude.jpg| thumb|center|upright=2.5| alt=Volume_Specific_Power_vs_Latitude.jpg| Volume Specific Power versus Latitude]] <br /> ==Effects on Deployment Time==<br /> *Considered the 100kW average power system located at the equator.<br /> **Requires a 25,000 m^2 rollout array field due to addition of the Kevlar areas.<br /> **Assume array blankets are 2m wide for easy storage and handling by two astronauts<br /> **Assume each blanket weighs 80lbs again for easy handling<br /> **With 0.07 kg/m^2 expected array density, need only 18 blankets total<br /> **Assume astronauts can unroll array at a walking speed of 1m/s, requires only 7hrs for unrolling<br /> **Time will be needed for unloading positioning and hookup, if assume 1hr for this for each array this adds 18hrs<br /> **In addition to this rocks must be placed in the Kevlar areas. Assume Kevlar areas are 1ft in length and the complete 2m width. Need 5.6kg of rock in each area. There are 225 of these Kevlar areas per array so a total of 4050 of these areas. Assuming 2 rocks are needed per area to secure the 2 sides of the array this requires 8100 rocks to be placed. If 30 seconds is needed to pick and place a rock this will take 33.75hrs for 2 crew.<br /> *Total deployment time is then 66hrs for 2 crew members <br /> *Power delivery during deployment:<br /> **We see that deployment gives 0.76 kW per man hour, therefore we only need 13.2 man hours to reach a capability of 10 kW which is enough for minimal stay alive power.<br /> **If you are conservative and neglect this and say full deployment and initial usefulness takes 1 week, we need either a 10kW RTG or fuel cell system to provide 10kW power over the week<br /> **RTG system would be approximately 1200kg and 0.6 m^3<br /> **If use RFC, need 2400kg system with volume 8.4 m^3<br /> *Sensitivity of total deployment time to different factors:<br /> **Sensitivity to array area=0.99<br /> **Sensitivity to walking time=0.96<br /> **Sensitivity to rock placement time=0.97<br /> **Sensitivity to off-load and hookup time=0.965<br /> **We see that the total deployment time is most sensitive to walking time so the design should be sure to make the unrolling of the array by astronauts in suits easy</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/EDL&diff=2379 2010-04-18T23:15:47Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> This section requires further editing to include all previous efforts.<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Transportation/<br /> <br /> = Major EDL Challenges for MinMars =<br /> *Significantly higher ballistic coefficient than MSL<br /> **Lower landing altitude than for MSL helps (denser atmosphere)<br /> **Landing altitude possibly as low as -2 km<br /> *Higher landing accuracy<br /> **2-5 km vs. 20 km<br /> **But pre-deployed assets available (in orbit and on the ground)<br /> *No use of main parachute(s)<br /> **Vehicle never slows down sufficiently for existing parachute technology (&lt; Mach 2); also issues with chute scaling<br /> **All-propulsive descent will likely be required<br /> **Possibly use of a supersonic drogue parachute for aeroshell forebody separation and stabilization<br /> *Off-center aerodynamic heating<br /> **Large aeroshell diameter leads to different Re-number regime, turbulent flow over forebody heat shield<br /> **Maximum heating may no longer occur at center / nose of heat shield but off-center in turbulent region<br /> <br /> Question: in a worst-case scenario, could we deliver MinMars infrastructure�and crew with existing (Viking-based) EDL technology (or extensions thereof)?<br /> <br /> = EDL System for 2 mt Useful Mass =<br /> <br /> *Transportation assessment assuming capability for 1 mt usable surface payload<br /> *Crew transportation:<br /> **2 crew per 25 mt package<br /> **In-space habitat that is discarded prior to aerocapture / entry<br /> **2 crew either enter together in single aeroshell or each crew has individual aeroshell<br /> *Transportation of supplies and spare parts<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of power and ISRU systems<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of unpressurized mobility systems<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of habitat and workshop<br /> **Difficult, may require inflatable modules with interior outfitting; subsequent assembly on the surface<br /> <br /> [[Image:MSL_Technology_Extension.jpg| thumb|center|upright=2.5| alt=MSL_Technology_Extension.jpg| MSL Technology Extension for Ballistic Coefficient 115 kg/m2]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/InSpace_Transportation&diff=2378 2010-04-18T23:15:39Z

<p>Arthurguest: </p> <hr /> <div>[[Minimalist_Human_Mars_Mission|Return to MinMars Home Page]]<br /> <br /> This section requires further editing to include all previous efforts.<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Transportation/<br /> <br /> = Minimalist Transportation Concept = <br /> <br /> == Transportation Challenges ==<br /> *How do we transport crew and cargo to the Martian surface using 25 mt launch vehicles?<br /> **25 mt is “worst-case scenario”<br /> **Larger payload capabilities would facilitate transportation and also lead to scaling benefits<br /> *Specific challenges:<br /> **Launch and LEO orbit assembly<br /> **Mars aerocapture and EDL<br /> ***Ballistic coefficient (entry body mass, diameter, shape)<br /> ***Altitude at Mach 3 / aeroshell separation<br /> **Propulsive descent (800 m/s assumed for now)<br /> **Final landing GN&amp;C, landing error reduction<br /> **Hazard avoidance<br /> *Falcon 9 Heavy assumed as reference LV<br /> **~28 mt to 300 km LEO<br /> **~4 m x ~10 m cylinder of usable volume in shroud<br /> <br /> == Mars Aerocapture and Entry Vehicle ==<br /> *Entry vehicle is based on conic blunted body<br /> **20 degree side-wall angle<br /> **Drag coefficient: ~1.6<br /> **L/D: ~0.3<br /> *Total mass is 12 mt, leading to a ballistic coefficient of around 600 kg/m2<br /> **Mach 3 altitude ~ 5 km<br /> *Final descent propulsion based on MMH / N2O4<br /> **Isp = 320 s<br /> **8 tanks (4 fuel, 4 oxidizer)<br /> *Cargo to surface: ca. 5 mt<br /> <br /> == Cargo Transportation Concept ==<br /> *Transportation concept based on dual blunt-shaped entry bodies<br /> **Reduces ballistic coefficient per entry body (~ 600 kg/m2)<br /> **Allows for simple blunt-body shape<br /> *Entry bodies are launched together with additional cruise systems<br /> **Solar arrays, batteries, radiators<br /> **Entry bodies separate prior to aerocapture and aeroentry<br /> *2 Earth departure stages are launched after the entry bodies<br /> **Stages dock to entry bodies for dual burn Earth departure<br /> *Initial analysis indicates that ~25 mt can be injected towards Mars using LOX / kerosene stages<br /> **~10 mt useful cargo mass on Mars surface (~ 5 mt per entry body)<br /> *Crew transportation with entry body (cargo) and additional transit habitat<br /> **2 sets of solar arrays, batteries, and radiators<br /> **Transit habitat is jettisoned prior to aerocapture<br /> *2 Earth departure stages are launched separately and docked<br /> **Dual burn Earth departure<br /> **LOX / kerosene propulsion<br /> *Initial analysis indicates that 2-3 crew can be delivered to Mars surface this way<br /> **Crew can be sustained for 30+ days on surface after landing<br /> **Unpressurized mobility delivered with crew<br /> <br /> == Transportation Results &amp; Future Work ==<br /> *4-6 crew can be transported to Mars with 6 Falcon 9 heavy launches<br /> **Launch cost of ca. $ 600 Mn (ca. $ 100 Mn per launch)<br /> *3 Falcon 9 heavy launches can deliver a minimum of 10 mt of useful mass to the Martian surface<br /> **Equivalent to 26-month consumables demand for 4 crew<br /> *Forward work:<br /> **More detailed design of aeroshell and descent stage<br /> **More detailed design of Earth departure propulsion<br /> ***Including propellant type trade<br /> **Investigation of different entry body shapes <br /> <br /> == Transportation Update ==<br /> *Previous transportation strategy was based on use of ~12 mt aeroshells with diameters around 5 m<br /> *This leads to a significantly increased number of aeroshells that need to be built, as well as to reduced maximum volume of items that can be transported to Mars<br /> *Analysis was carried out to determine whether it is possible to use a single ~24 mt aeroshell<br /> <br /> == Aerodynamic Properties ==<br /> *Basic shape is blunted cone with 20-degree side-wall angle<br /> *Achieves L/D of 0.3 at 18.5-degree angle of attack<br /> *Drag coefficient of ~1.5 at 18.5-degree angle of attack<br /> *Shape is similar to SpaceX Dragon capsule<br /> **May be possible to utilize aerodynamic database from Dragon<br /> **Possibly use Dragon derivative?<br /> <br /> == Preliminary Transportation Cost Assessment ==<br /> *Falcon 9 Heavy [FY 2008 $]<br /> **$ 94.5 Mn per shot for LEO mission<br /> *Lander costs [FY 2004 $]<br /> **Dry mass: 2453 kg<br /> **Development: $ 1482 Mn<br /> **Production (1st unit): $ 112 Mn<br /> *Aeroshell costs [FY 2004 $]<br /> **Dry mass: 8000 kg<br /> **Development: $ 2839 Mn<br /> **Production (1st unit): $ 245 Mn<br /> *TMI stage [FY 2004 $]<br /> **Dry mass: ~5000 kg<br /> **Development: $ 560 Mn<br /> **Production (1st unit): $ 32 Mn<br /> *Approximate marginal cost for transporting 10 mt to the surface of Mars:<br /> **(3 x 94.5 + 2 x 32 + 112 + 245)*1.2 = 845.4<br /> **$ 84540 / kg on the surface of Mars<br /> <br /> == Concept Overview for 2 mt Case ==<br /> <br /> *“2 mt case”: integrated payloads of no more than 2 mt can be landed on the surface of Mars; extension of current Mars EDL technology<br /> *Cargo transportation<br /> **All cargo packages are landed on the surface of Mars using scaled-up MSL-type vehicles<br /> **Each cargo package and the associated cruise stage and EDL system is launched and injected towards Mars using an EELV-class launch vehicle (Falcon 9 heavy, Delta IV heavy, Atlas V heavy, etc.)<br /> *Crew transportation<br /> **Similar approach as for 10 mt case, but different hab / EDL design<br /> **Mars Transfer Vehicle is assembled in LEO out of 3 payloads of ~25 mt<br /> ***1st payload: habitat + Mars entry vehicle (same entry vehicle as for cargo)<br /> ***2nd and 3rd payloads: each one ~25 mt propulsion stage for TMI<br /> **2 crew are transported using this transfer vehicle</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2377 2010-04-18T23:11:22Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [[Open_Source_Engineering_Tools|Open Source Engineering Tools]]<br /> <br /> Aims to catalog, review, aid in the use of, and encourage the creation and enhancement of open source tools for engineering (with a particular emphasis towards space).<br /> <br /> [[InterestingLinks|Interesting Links]]<br /> <br /> Links to external sites of interest for the DevelopSpace concept<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [[DevelopSpace_Information_Systems| DevelopSpace Information Systems]]<br /> <br /> Effort intended to foster the establishment and support of DevelopSpace&#039;s information systems, including project hosting infrastructure.<br /> <br /> [[SiteRequests| A List of Site Requests]]<br /> <br /> This is where to discuss features you would like to see included as part of the DevelopSpace platform.<br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Projects&diff=2376 2010-04-18T23:09:48Z

<p>Arthurguest: /* Project Listing */</p> <hr /> <div>This page lists projects and groups hosted by DevelopSpace. DevelopSpace intends to host projects and groups that are relevant to DevelopSpace&#039;s mission of building up the technical foundations for human space activities. Projects/groups do not need to be created or operated by DevelopSpace in order to be hosted here -- if you would like additional information on hosting your project with DevelopSpace, please contact [[user:pwooster|Paul Wooster]].<br /> <br /> =Project Listing=<br /> <br /> ==Active Projects==<br /> <br /> *[[Minimalist Human Mars Mission]]. Project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars (possibly with an initial emergency return capability). This initial Mars outpost could also be the nucleus of an initial Mars colony. Includes reference data, system analysis, and investigation of design options.<br /> <br /> ==Project Proposals==<br /> *[[Mars Solar Power]]. Project to investigate the feasibility of solar power on the surface of Mars for either as the sole primary power source or in conjunction with other power source (e.g., nuclear reactors). Includes reference data, system analysis, and investigation of design options.<br /> <br /> ==Hosted Groups and Teams==<br /> *[[MIT_SSAG|MIT Space Systems Architecture Group]]. A research group in the MIT Department of Aeronautics and Astronautics, focusing on human space exploration architecture.<br /> <br /> *[[MIT Rocket Team]]. A student group at MIT devoted to getting students involved with projects related to rocketry (chiefly focused on liquid fuel propulsion).<br /> <br /> Note: To create a project, add a link to the project page and a brief description of the project.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2375 2010-04-18T23:07:37Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [[Open_Source_Engineering_Tools|Open Source Engineering Tools]]<br /> <br /> Aims to catalog, review, aid in the use of, and encourage the creation and enhancement of open source tools for engineering (with a particular emphasis towards space).<br /> <br /> [[InterestingLinks|Interesting Links]]<br /> <br /> Links to external sites of interest for the DevelopSpace concept<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [[DevelopSpace_Information_Systems| DevelopSpace Information Systems]]<br /> <br /> Effort intended to foster the establishment and support of DevelopSpace&#039;s information systems, including project hosting infrastructure.<br /> <br /> [[SiteRequests| A List of Site Requests]]<br /> <br /> This is where to discuss features you would like to see included as part of the DevelopSpace platform.<br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2374 2010-04-18T23:04:30Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [[Open_Source_Engineering_Tools|Open Source Engineering Tools]]<br /> <br /> [[InterestingLinks|Interesting Links]]<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [[DevelopSpace_Information_Systems| DevelopSpace Information Systems]]<br /> <br /> [[SiteRequests| A List of Site Requests]]<br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2373 2010-04-18T23:03:50Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [[Open_Source_Engineering_Tools|Open Source Engineering Tools]]<br /> <br /> [[InterestingLinks|Interesting Links]]<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [[DevelopSpace_Information_Systems| DevelopSpace Information Systems Project]]<br /> <br /> [[SiteRequests| A List of Site Requests]]<br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2372 2010-04-18T23:03:22Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace (coming soon)]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> [Open_Source_Engineering_Tools|Open Source Engineering Tools]<br /> [InterestingLinks|Interesting Links]<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> [DevelopSpace_Information_Systems| DevelopSpace Information Systems Project]<br /> [SiteRequests| A List of Site Requests]<br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2371 2010-04-18T23:00:39Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[Minimalist_Human_Mars_Mission|A Minimalist Human Mission to Mars]]<br /> <br /> This project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Minimalist_Human_Mars_Mission&diff=2370 2010-04-18T22:59:13Z

<p>Arthurguest: </p> <hr /> <div>The Minimalist Human Mars Mission(aka MinMars) project aims to design a near-term feasible Mars missions based on the concept of sending humans on a one-way mission to the surface of Mars.<br /> <br /> =Project Overview=<br /> <br /> Project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> ==Project Motivation==<br /> <br /> For many reasons, it is our destiny as humans to expand our presence. since the existence of our species, we have expanded our habitat over almost the entire Earth. This expansion was enabled by using technology (e.g. living in central Europe or northern Minnesota and surviving the winter). The next logical step is to go beyond Earth. This requires more significant reliance on technology. In addition to expanding our presence, there may be numerous other benefits from this such as rekindling of frontier spirit, societal invigoration, generating new technologies and knowledge, backing up our species and its achievements.<br /> <br /> === Why Mars? ===<br /> <br /> Why would we want to expand to Mars, instead of other destinations such as the Moon?<br /> <br /> Of all the bodies of the inner solar system eligible for near-term colonization, Mars is the most suitable. Mars has an atmosphere, specifically a CO2 atmosphere (GCR/SPR protection, feedstock for ISRU). All the other elements necessary for sustained human existence are present in one form or another on the Martian surface (nitrogen, hydrogen, oxygen, carbon, iron, aluminum, etc). From a mass/energy perspective, the Martian surface is about as hard to reach as the lunar surface. Mars has a higher gravity level than on the Moon.<br /> <br /> Major challenges of Mars are that it takes longer to get there and aeroentry / aerocapture is required.<br /> <br /> === Why are we interested in doing this? ===<br /> <br /> The establishment of a self-sustained human colony off the Earth should be one of the driving goals of human spaceflight.<br /> <br /> Mars surface is the most suitable place for establishing a self-sustained human colony in the foreseeable future.<br /> <br /> Architecture-level analysis is effective in identifying the driving challenges for establishing the toehold and guide future analyses.<br /> <br /> === How to Colonize Mars ===<br /> <br /> Many ideas have been put forth (Zubrin, Case for Mars conference proceedings, etc). Here are some initial ideas for our project:<br /> <br /> *Humans will be sent one way, possibly with an initial emergency return capability (return capability could be based on direct return)<br /> *Re-supply will initially be provided from Earth, possibly augmented with ISRU on Mars (initially atmosphere-based ISRU / possibly also greenhouses for growing food)<br /> *The population of the colony will be assumed to grow over time (maybe 4 crew initially, minimum of 2 additional every opportunity)<br /> <br /> ==Project Goals==<br /> <br /> 1. To determine what would be involved in implementing a sustained human presence on Mars in the near future by way of one-way colonization for minimum closure and maximum closure levels for constant or growing population size.<br /> <br /> 2. To investigate the cost of providing the colony with the capability for emergency evacuation back to Earth.<br /> <br /> 3. To gain an understanding of the financial needs and the time phasing of a near-term Mars colonization program.<br /> <br /> 4. To further develop the DevelopSpace infrastructure through identification of infrastructure needs.<br /> <br /> = MinMars Toehold Architecture = <br /> <br /> Architecture Tradespace:<br /> *In-situ water production: yes, no<br /> *Mars surface landed mass: 2 mt, 8 mt, 45 mt<br /> *Significant in-situ food production: yes, no<br /> <br /> Invariant architecture choices:<br /> *Oxygen production from Mars atmosphere<br /> *Water recycling<br /> *In-situ production of a limited amount of vegetables and fruit<br /> *Power generation and energy storage using amorphous silicon arrays and Li-ion batteries<br /> <br /> ==Operational Architecture==<br /> <br /> The overall operational architecture for the initial toehold is based on one-way flights delivering cargo and crew to the Martian surface (potentially with an emergency return capability). Mars capture is assumed to be accomplished by aerocapture. Subsequent lifting entry and propulsive descent are used to deliver payloads to the single surface outpost site (outpost location is subject to a variety of factors (insolation, water, elevation). The exact size and payload capability of each lander depends on the Earth departure architecture and entry body chosen.<br /> <br /> == Major Challenges Identified ==<br /> <br /> Mars entry, descent, and landing of 10+ mt payloads<br /> *What would be the entry mass associated with 10 mt payloads?<br /> *What is the landing accuracy that can be achieved?<br /> <br /> Food production on the surface of Mars<br /> *Is it worthwhile; break-even with re-supply from Earth?<br /> *Food production architecture analysis<br /> <br /> Spare parts re-supply / in-situ production &amp; manufacturing strategy<br /> *What is the cumulative spare parts need without manufacturing?<br /> *Which spare parts can be easily manufactured on Mars?<br /> *What manufacturing infrastructure should be imported first?<br /> *What raw materials can be easily produced on the surface of Mars?<br /> <br /> Mars surface habitation infrastructure design / deployment<br /> *Especially for transportation scenarios where Mars surface payload capability is closer to 1 mt (MSL)<br /> <br /> Test of solar array deployment<br /> *Build a prototype and test deploy<br /> <br /> = Models and Results =<br /> <br /> == Areas of Focus ==<br /> <br /> The following pages include more in-depth discussion of the work done on the critical areas of designing a minimalist human Mars mission:<br /> <br /> *[[MinMars:InSpace_Transportation|In-space Transportation]]<br /> *[[MinMars:EDL|Entry, Descent, and Landing]]<br /> *[[MinMars:Surface Power|Surface Power]]<br /> *[[MinMars:Surface Infrastructure|Surface Infrastructure]]<br /> *[[MinMars:Surface Mobility|Surface Mobility]]<br /> *[[MinMars:Logistics|Logistics]]<br /> *[[MinMars:ISRU|In-Situ Resource Utilization]]<br /> *[[MinMars:Finance_and_Costing|Finance and Costing]]<br /> *[[MinMars:Integration_of_Results|Integration of Results]]<br /> <br /> == Conference Papers on MinMars ==<br /> <br /> === IAC 2008 ===<br /> The following repository contains our IAC 2008 paper and presentation.<br /> <br /> http://svn.developspace.net/svn/minmars/minMars%20reports/IAC%202008%20paper/<br /> <br /> === IAC 2010 ===<br /> The following repository contains our IAC 2010 abstract.<br /> <br /> http://svn.developspace.net/svn/minmars/minMars%20reports/IAC%202010%20paper/<br /> <br /> == Subversion Repository ==<br /> <br /> [[SVN|Subversion]] version control system used to store files associated with this project. Repository is available at http://svn.developspace.net/svn/minmars/. For more information on how to use the repository, see the [[SVN]] page.<br /> <br /> Read-only access to the repository is available to anyone. For write access, please contact [mailto:info@developspace.net info@developspace.net].<br /> <br /> = Additional Information = <br /> <br /> == Mars Wish List ==<br /> <br /> The [[Mars Wish List]] page lists a number of items which would be useful at the initiation of a minimalist human Mars mission, such as being designed by this project.<br /> <br /> == MinMars Follow-On Projects ==<br /> <br /> The MinMars project has identified a number of enabling technologies / systems required for establishing a human Mars surface toehold. For these focus areas, separate projects will be established on DevelopSpace in the near future.<br /> <br /> The [[MinMars:Follow-on Projects| Follow-on Projects]] page lists the identified focus areas.<br /> <br /> = Project Team =<br /> <br /> *[mailto:wilfried.hofstetter@gmail.com| Wilfried Hofstetter] (project lead)<br /> *[mailto:paul.wooster@gmail.com| Paul Wooster] (advisor)<br /> <br /> *[mailto:guest.arthur@gmail.com| Arthur Guest]<br /> *Thomas Coffee<br /> *Alessandro Golkar<br /> *Chase Cooper<br /> *Ryan McLinko<br /> *Alar Kolk<br /> *Aaron Schultz<br /> *Emily Grosse (listening in)<br /> <br /> Our project mailing list: [mailto:minmars@lists.developspace.net| minmars@lists.developspace.net]<br /> <br /> = References = <br /> <br /> A list of key references for this project can be found at [[MinMars:References]].</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Minimalist_Human_Mars_Mission&diff=2369 2010-04-18T22:58:49Z

<p>Arthurguest: </p> <hr /> <div>The Minimalist Human Mars Mission(aka MinMars) project aims to design a near-term feasible Mars missions based on the concept of sending humans on a one-way mission to the surface of Mars.<br /> Contents [hide]<br /> 1 Project Overview<br /> 1.1 Project Motivation<br /> 1.1.1 Why Mars?<br /> 1.1.2 Why are we interested in doing this?<br /> 1.1.3 How to Colonize Mars<br /> 1.2 Project Goals<br /> 2 MinMars Toehold Architecture<br /> 2.1 Operational Architecture<br /> 2.2 Major Challenges Identified<br /> 3 Models and Results<br /> 3.1 Areas of Focus<br /> 3.2 Conference Papers on MinMars<br /> 3.2.1 IAC 2008<br /> 3.2.2 IAC 2010<br /> 3.3 Subversion Repository<br /> 4 Additional Information<br /> 4.1 Mars Wish List<br /> 4.2 MinMars Follow-On Projects<br /> 5 Project Team<br /> 6 References<br /> [edit]Project Overview<br /> <br /> Project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> [edit]Project Motivation<br /> <br /> For many reasons, it is our destiny as humans to expand our presence. since the existence of our species, we have expanded our habitat over almost the entire Earth. This expansion was enabled by using technology (e.g. living in central Europe or northern Minnesota and surviving the winter). The next logical step is to go beyond Earth. This requires more significant reliance on technology. In addition to expanding our presence, there may be numerous other benefits from this such as rekindling of frontier spirit, societal invigoration, generating new technologies and knowledge, backing up our species and its achievements.<br /> [edit] Why Mars?<br /> Why would we want to expand to Mars, instead of other destinations such as the Moon?<br /> Of all the bodies of the inner solar system eligible for near-term colonization, Mars is the most suitable. Mars has an atmosphere, specifically a CO2 atmosphere (GCR/SPR protection, feedstock for ISRU). All the other elements necessary for sustained human existence are present in one form or another on the Martian surface (nitrogen, hydrogen, oxygen, carbon, iron, aluminum, etc). From a mass/energy perspective, the Martian surface is about as hard to reach as the lunar surface. Mars has a higher gravity level than on the Moon.<br /> Major challenges of Mars are that it takes longer to get there and aeroentry / aerocapture is required.<br /> [edit] Why are we interested in doing this?<br /> The establishment of a self-sustained human colony off the Earth should be one of the driving goals of human spaceflight.<br /> Mars surface is the most suitable place for establishing a self-sustained human colony in the foreseeable future.<br /> Architecture-level analysis is effective in identifying the driving challenges for establishing the toehold and guide future analyses.<br /> [edit] How to Colonize Mars<br /> Many ideas have been put forth (Zubrin, Case for Mars conference proceedings, etc). Here are some initial ideas for our project:<br /> Humans will be sent one way, possibly with an initial emergency return capability (return capability could be based on direct return)<br /> Re-supply will initially be provided from Earth, possibly augmented with ISRU on Mars (initially atmosphere-based ISRU / possibly also greenhouses for growing food)<br /> The population of the colony will be assumed to grow over time (maybe 4 crew initially, minimum of 2 additional every opportunity)<br /> [edit]Project Goals<br /> <br /> 1. To determine what would be involved in implementing a sustained human presence on Mars in the near future by way of one-way colonization for minimum closure and maximum closure levels for constant or growing population size.<br /> 2. To investigate the cost of providing the colony with the capability for emergency evacuation back to Earth.<br /> 3. To gain an understanding of the financial needs and the time phasing of a near-term Mars colonization program.<br /> 4. To further develop the DevelopSpace infrastructure through identification of infrastructure needs.<br /> [edit] MinMars Toehold Architecture<br /> <br /> Architecture Tradespace:<br /> In-situ water production: yes, no<br /> Mars surface landed mass: 2 mt, 8 mt, 45 mt<br /> Significant in-situ food production: yes, no<br /> Invariant architecture choices:<br /> Oxygen production from Mars atmosphere<br /> Water recycling<br /> In-situ production of a limited amount of vegetables and fruit<br /> Power generation and energy storage using amorphous silicon arrays and Li-ion batteries<br /> [edit]Operational Architecture<br /> <br /> The overall operational architecture for the initial toehold is based on one-way flights delivering cargo and crew to the Martian surface (potentially with an emergency return capability). Mars capture is assumed to be accomplished by aerocapture. Subsequent lifting entry and propulsive descent are used to deliver payloads to the single surface outpost site (outpost location is subject to a variety of factors (insolation, water, elevation). The exact size and payload capability of each lander depends on the Earth departure architecture and entry body chosen.<br /> [edit] Major Challenges Identified<br /> <br /> Mars entry, descent, and landing of 10+ mt payloads<br /> What would be the entry mass associated with 10 mt payloads?<br /> What is the landing accuracy that can be achieved?<br /> Food production on the surface of Mars<br /> Is it worthwhile; break-even with re-supply from Earth?<br /> Food production architecture analysis<br /> Spare parts re-supply / in-situ production &amp; manufacturing strategy<br /> What is the cumulative spare parts need without manufacturing?<br /> Which spare parts can be easily manufactured on Mars?<br /> What manufacturing infrastructure should be imported first?<br /> What raw materials can be easily produced on the surface of Mars?<br /> Mars surface habitation infrastructure design / deployment<br /> Especially for transportation scenarios where Mars surface payload capability is closer to 1 mt (MSL)<br /> Test of solar array deployment<br /> Build a prototype and test deploy<br /> [edit] Models and Results<br /> <br /> [edit] Areas of Focus<br /> <br /> The following pages include more in-depth discussion of the work done on the critical areas of designing a minimalist human Mars mission:<br /> In-space Transportation<br /> Entry, Descent, and Landing<br /> Surface Power<br /> Surface Infrastructure<br /> Surface Mobility<br /> Logistics<br /> In-Situ Resource Utilization<br /> Finance and Costing<br /> Integration of Results<br /> [edit] Conference Papers on MinMars<br /> <br /> [edit] IAC 2008<br /> The following repository contains our IAC 2008 paper and presentation.<br /> http://svn.developspace.net/svn/minmars/minMars%20reports/IAC%202008%20paper/<br /> [edit] IAC 2010<br /> The following repository contains our IAC 2010 abstract.<br /> http://svn.developspace.net/svn/minmars/minMars%20reports/IAC%202010%20paper/<br /> [edit] Subversion Repository<br /> <br /> Subversion version control system used to store files associated with this project. Repository is available at http://svn.developspace.net/svn/minmars/. For more information on how to use the repository, see the SVN page.<br /> Read-only access to the repository is available to anyone. For write access, please contact info@developspace.net.<br /> [edit] Additional Information<br /> <br /> [edit] Mars Wish List<br /> <br /> The Mars Wish List page lists a number of items which would be useful at the initiation of a minimalist human Mars mission, such as being designed by this project.<br /> [edit] MinMars Follow-On Projects<br /> <br /> The MinMars project has identified a number of enabling technologies / systems required for establishing a human Mars surface toehold. For these focus areas, separate projects will be established on DevelopSpace in the near future.<br /> The Follow-on Projects page lists the identified focus areas.<br /> [edit] Project Team<br /> <br /> Wilfried Hofstetter (project lead)<br /> Paul Wooster (advisor)<br /> Arthur Guest<br /> Thomas Coffee<br /> Alessandro Golkar<br /> Chase Cooper<br /> Ryan McLinko<br /> Alar Kolk<br /> Aaron Schultz<br /> Emily Grosse (listening in)<br /> Our project mailing list: minmars@lists.developspace.net<br /> [edit] References<br /> <br /> A list of key references for this project can be found at MinMars:References.</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Main_Page&diff=2368 2010-04-18T22:58:11Z

<p>Arthurguest: </p> <hr /> <div>&lt;!-- BANNER ACROSS TOP OF PAGE --&gt;<br /> {| id=&quot;mp-topbanner&quot; style=&quot;width:100%; background:#fcfcfc; margin-top:1.2em; border:1px solid #ccc;&quot;<br /> | style=&quot;width:56%; color:#000;&quot; |<br /> <br /> &lt;!-- &quot;WELCOME TO DEVELOPSPACE&quot; AND ARTICLE COUNT --&gt;<br /> {| style=&quot;width:280px; border:none; background:none;&quot;<br /> | style=&quot;width:280px; text-align:center; white-space:nowrap; color:#000;&quot; |<br /> &lt;div style=&quot;font-size:162%; border:none; margin:0; padding:.1em; color:#000;&quot;&gt;Welcome to DevelopSpace!&lt;/div&gt;<br /> &lt;div style=&quot;top:+0.2em; font-size:95%;&quot;&gt;the open-source repository for space exploration.&lt;/div&gt;<br /> |}<br /> <br /> &lt;!-- PORTAL LIST ON RIGHT-HAND SIDE --&gt;<br /> | style=&quot;width:11%; font-size:95%;&quot; |<br /> * [[Projects|Projects]]<br /> * [[Reference_Library|Reference Library]]<br /> |}<br /> <br /> &lt;!-- STRAPLINE IMMEDIATELY BELOW BANNER --&gt;<br /> {| id=&quot;mp-strapline&quot; style=&quot;width:100%; background:none; margin:-.8em 0 -.7em 0;&quot;<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:left; white-space:nowrap; color:#000;&quot; | [[DevelopSpace:About|About Us]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[People|People]]&amp;nbsp;&#039;&#039;&#039;·&#039;&#039;&#039; [[Help:Contents|Help]]<br /> | style=&quot;font-size:95%; padding:10px 0; margin:0; text-align:right; white-space:nowrap; color:#000;&quot; |<br /> [[SiteRequests|Suggested Features]]<br /> |}<br /> <br /> &lt;!-- WHAT IS DEVELOPSPACE? --&gt;<br /> {| id=&quot;mp-upper&quot; style=&quot;margin:0; background:none;&quot;<br /> <br /> | class=&quot;MainPageBG&quot; style=&quot;width:55%; border:1px solid #cef2e0; background:#f5fffa; vertical-align:top; color:#000;&quot; |<br /> {| id=&quot;mp-left&quot; style=&quot;width:100%; vertical-align:top; background:#f5fffa;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfa-h2&quot; style=&quot;margin:3px; background:#cef2e0; font-size:120%; font-weight:bold; border:1px solid #a3bfb1; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> What is DevelopSpace?<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;&quot; | &lt;div id=&quot;mp-tfa&quot; style=&quot;padding:2px 5px&quot;&gt;<br /> <br /> The goal of DevelopSpace is to build-up the technical foundations for human space activities. DevelopSpace will engage in scientific and educational endeavors with a focus on open sharing of relevant technical resources and fostering related technical activities and innovations. DevelopSpace will enable a wide variety of individuals and groups to participate in the exploration, development, and utilization of space. You can learn more about DevelopSpace at our [[DevelopSpace:About|About Us]] page. <br /> <br /> This website is dedicated to both advancing the DevelopSpace concept, a general reference for the technical space community, and as a hosting platform for space related technical projects. The content on this site is intended to grow over time. All interested individuals are invited to participate and contribute. Please add relevant items and help in expanding the information available here. You can modify a page by clicking the &quot;edit&quot; button at the top. <br /> <br /> To follow DevelopSpace&#039;s progress and to become involved, please join our <br /> [http://lists.developspace.net/listinfo.cgi/ds-news-developspace.net ds-news] announcement mailing list and [http://lists.developspace.net/listinfo.cgi/ds-discuss-developspace.net ds-discuss] higher volume discussion list by emailing <br /> [mailto:ds-news-subscribe@lists.developspace.net ds-news-subscribe@lists.developspace.net] and [mailto:ds-discuss-subscribe@lists.developspace.net ds-discuss-subscribe@lists.developspace.net] respectively.<br /> <br /> <br /> Publications featuring DevelopSpace include:<br /> * [http://www.linux.com/feature/118137 Linux.com article describing the DevelopSpace concept]<br /> * [[:Image:AIAA2007-OpeningSpaceforHumanity.pdf|AIAA Space 2007 conference paper describing motivation for DevelopSpace]]<br /> *[[:Image:IAC_2008_Minimalist_Mars.pdf|Open Innovation for Space Systems Using the Developspace Platform for Designing a Near-Term Human Mars Mission]] (Paper presented at the 2008 International Astronautical Congress in Glasgow, Scotland)<br /> <br /> <br /> &lt;/div&gt;<br /> <br /> |}<br /> | style=&quot;border:1px solid transparent;&quot; |<br /> <br /> &lt;!-- FEATURED PROJECT; REFERENCE LIBRARY --&gt;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:45%; border:1px solid #cedff2; background:#f5faff; vertical-align:top;&quot;|<br /> {| id=&quot;mp-right&quot; style=&quot;width:100%; vertical-align:top; background:#f5faff;&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-itn-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> Today&#039;s Featured DevelopSpace Project<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px&quot; | &lt;div id=&quot;mp-itn&quot;&gt;<br /> <br /> [[MinMars:Main|A Minimalist Human Mission to Mars]]<br /> <br /> Project aims to design a near-term feasible human Mars mission based on the concept of sending humans one way to Mars. This approach has a number of advantages compared to the tradition &quot;there-and-back&quot; exploration approach that all previous human space missions have followed, particularly with regard to the mass requirements of the mission. The humans on Mars would be re-supplied periodically and would have the tools and infrastructure for a mostly self-sustained existence. An emergency return capability based on the direct return approach could be provided to mitigate the effects of catastrophic equipment failure on Mars; it is one of the goals of the project to determine the cost of providing such a return capability. This initial Mars outpost (Mars &quot;toehold&quot;) could also be the nucleus of an initial Mars colony, growing over time through dispatching additional crew and infrastructure to the outpost.<br /> <br /> [[Projects|Click to view other projects]]<br /> <br /> &lt;/div&gt;<br /> |-<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-otd-h2&quot; style=&quot;margin:3px; background:#cedff2; font-size:120%; font-weight:bold; border:1px solid #a3b0bf; text-align:left; color:#000; padding:0.2em 0.4em;&quot;&gt;<br /> <br /> The Space Exploration Reference Library<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding:2px 5px 5px&quot; | &lt;div id=&quot;mp-otd&quot;&gt;<br /> <br /> Our Reference Library catalogs a variety of technical information of interest to those developing space-related systems. The library is maintained by volunteer contributors and emphasizes freely available technical references. Please make use of and expand this resource for the overall space development community.<br /> <br /> [[Reference_Library|View the articles]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- TODAY&#039;S FEATURED PICTURE --&gt;<br /> {| style=&quot;margin:4px 0 0 0; width:100%; background:none;&quot;<br /> | class=&quot;MainPageBG&quot; style=&quot;width:100%; border:1px solid #ddcef2; background:#faf5ff; vertical-align:top; color:#000;&quot;|<br /> {| style=&quot;vertical-align:top; background:#faf5ff; color:#000; width:100%&quot;<br /> ! style=&quot;padding:2px&quot; | &lt;h2 id=&quot;mp-tfp-h2&quot; style=&quot;margin:3px; background:#ddcef2; font-size:120%; font-weight:bold; border:1px solid #afa3bf; text-align:left; color:#000; padding:0.2em 0.4em&quot;&gt;<br /> <br /> Hosting your project on DevelopSpace...<br /> <br /> &lt;/h2&gt;<br /> |-<br /> | style=&quot;color:#000;padding: 2px&quot; | &lt;div id=&quot;mp-tfp&quot;&gt;<br /> <br /> DevelopSpace provides free hosting services for projects advancing the technical foundations for human space activities. A listing of currently hosted projects is available by clicking [[Projects|clicking here]]. At present, projects are offered space on this wiki, mailing list hosting, and Subversion version control repository hosting. We intend to expand our offerings over time to assist projects in their success. If you are interested in hosting your project with DevelopSpace or if there are particular services that would be of interest to you, please [mailto:info@developspace.net let us know].<br /> <br /> [[Project_Hosting|Learn how to host your project on DevelopSpace]]<br /> <br /> &lt;/div&gt;<br /> |}<br /> |}<br /> &lt;!-- SECTIONS AT BOTTOM OF PAGE --&gt;<br /> &lt;div id=&quot;mp-other&quot; style=&quot;padding-top:4px; padding-bottom:2px;&quot;&gt;<br /> == Other areas of DevelopSpace ==<br /> <br /> === Open-Source Engineering ===<br /> <br /> === Improving DevelopSpace Infrastructure ===<br /> <br /> &lt;/div&gt;<br /> <br /> __NOTOC____NOEDITSECTION__</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=User:Arthurguest&diff=2367 2010-04-18T22:57:14Z

<p>Arthurguest: </p> <hr /> <div>== Contact Info ==<br /> <br /> *Name: Arthur Guest<br /> *Email: [mailto:guest.arthur@gmail.com guest.arthur@gmail.com]<br /> *Phone: 617-680-2813<br /> *Address: Unit#3 - 126 North Washington Street, Boston, MA, USA 02114 ([http://maps.google.com/maps?q=126+N+Washington+Street+Boston+MA+02114+USA Google Maps])<br /> <br /> === [[Arthur&#039;s Task List]] ===</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Arthur%27s_Task_List&diff=2365 2010-04-18T19:30:50Z

<p>Arthurguest: </p> <hr /> <div>= Projects =<br /> * Continue to clean up MinMars project as the &#039;flagship&#039; project example<br /> *Clean up project repository<br /> ** Move DevelopSpace Information Systems Project &amp; Open Source Engineering Tools Project out of Projects group and into new section?<br /> ** What should be done with MIT SSAG and MIT Rocket Team &quot;Projects&quot;?<br /> ** What should be done with Mars Solar Project?<br /> * Create new projects: Interplanetary Transfer Vehicle Concepts for Near-Term Human Exploration Missions beyond Low Earth Orbit; Flexible Path Design<br /> <br /> = Project Hosting =<br /> * Develop new section for assisting new projects from outside of DevelopSpace to use our site (infrastructure, user manuals, templates, etc)<br /> <br /> = Exploration Reference Library =<br /> * Clean up and update reference library<br /> * Try to include 1-2 line summaries of references<br /> <br /> = Information System Section =<br /> * Integrate DevelopSpace Information System project and SiteRequests sections<br /> <br /> = Open-source Philosophy Section =<br /> * Look into developing stand-alone open-source section<br /> * Possibility of including reference library on open-source systems<br /> * Integrate Interesting Links section</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=Arthur%27s_Task_List&diff=2360 2010-04-18T19:21:25Z

<p>Arthurguest: New page: = Projects = *Clean up project repository ** Move DevelopSpace Information Systems Project &amp; Open Source Engineering Tools Project out of Projects group and into new section? ** What shoul...</p> <hr /> <div>= Projects =<br /> *Clean up project repository<br /> ** Move DevelopSpace Information Systems Project &amp; Open Source Engineering Tools Project out of Projects group and into new section?<br /> ** What should be done with MIT SSAG and MIT Rocket Team &quot;Projects&quot;?<br /> ** What should be done with Mars Solar Project?<br /> ** Create new projects: Interplanetary Transfer Vehicle Concepts for Near-Term Human Exploration Missions beyond Low Earth Orbit, Flexible Path Design<br /> * Continue to clean up MinMars Project<br /> <br /> = Project Hosting =<br /> * Develop new section for assisting new projects from outside of DevelopSpace to use our site (infrastructure, user manuals, templates, etc)<br /> <br /> = Exploration Reference Library =<br /> * Clean up and update reference library<br /> * Try to include 1-2 line summaries of references<br /> <br /> = Open-source/Information Systems Section =<br /> * Look into developing stand-alone open-source/information systems section</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/InSpace_Transportation&diff=2353 2010-04-18T19:05:03Z

<p>Arthurguest: </p> <hr /> <div>[[MinMars:Main|Return to MinMars Home Page]]<br /> <br /> This section requires further editing to include all previous efforts.<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Transportation/<br /> <br /> = Minimalist Transportation Concept = <br /> <br /> == Transportation Challenges ==<br /> *How do we transport crew and cargo to the Martian surface using 25 mt launch vehicles?<br /> **25 mt is “worst-case scenario”<br /> **Larger payload capabilities would facilitate transportation and also lead to scaling benefits<br /> *Specific challenges:<br /> **Launch and LEO orbit assembly<br /> **Mars aerocapture and EDL<br /> ***Ballistic coefficient (entry body mass, diameter, shape)<br /> ***Altitude at Mach 3 / aeroshell separation<br /> **Propulsive descent (800 m/s assumed for now)<br /> **Final landing GN&amp;C, landing error reduction<br /> **Hazard avoidance<br /> *Falcon 9 Heavy assumed as reference LV<br /> **~28 mt to 300 km LEO<br /> **~4 m x ~10 m cylinder of usable volume in shroud<br /> <br /> == Mars Aerocapture and Entry Vehicle ==<br /> *Entry vehicle is based on conic blunted body<br /> **20 degree side-wall angle<br /> **Drag coefficient: ~1.6<br /> **L/D: ~0.3<br /> *Total mass is 12 mt, leading to a ballistic coefficient of around 600 kg/m2<br /> **Mach 3 altitude ~ 5 km<br /> *Final descent propulsion based on MMH / N2O4<br /> **Isp = 320 s<br /> **8 tanks (4 fuel, 4 oxidizer)<br /> *Cargo to surface: ca. 5 mt<br /> <br /> == Cargo Transportation Concept ==<br /> *Transportation concept based on dual blunt-shaped entry bodies<br /> **Reduces ballistic coefficient per entry body (~ 600 kg/m2)<br /> **Allows for simple blunt-body shape<br /> *Entry bodies are launched together with additional cruise systems<br /> **Solar arrays, batteries, radiators<br /> **Entry bodies separate prior to aerocapture and aeroentry<br /> *2 Earth departure stages are launched after the entry bodies<br /> **Stages dock to entry bodies for dual burn Earth departure<br /> *Initial analysis indicates that ~25 mt can be injected towards Mars using LOX / kerosene stages<br /> **~10 mt useful cargo mass on Mars surface (~ 5 mt per entry body)<br /> *Crew transportation with entry body (cargo) and additional transit habitat<br /> **2 sets of solar arrays, batteries, and radiators<br /> **Transit habitat is jettisoned prior to aerocapture<br /> *2 Earth departure stages are launched separately and docked<br /> **Dual burn Earth departure<br /> **LOX / kerosene propulsion<br /> *Initial analysis indicates that 2-3 crew can be delivered to Mars surface this way<br /> **Crew can be sustained for 30+ days on surface after landing<br /> **Unpressurized mobility delivered with crew<br /> <br /> == Transportation Results &amp; Future Work ==<br /> *4-6 crew can be transported to Mars with 6 Falcon 9 heavy launches<br /> **Launch cost of ca. $ 600 Mn (ca. $ 100 Mn per launch)<br /> *3 Falcon 9 heavy launches can deliver a minimum of 10 mt of useful mass to the Martian surface<br /> **Equivalent to 26-month consumables demand for 4 crew<br /> *Forward work:<br /> **More detailed design of aeroshell and descent stage<br /> **More detailed design of Earth departure propulsion<br /> ***Including propellant type trade<br /> **Investigation of different entry body shapes <br /> <br /> == Transportation Update ==<br /> *Previous transportation strategy was based on use of ~12 mt aeroshells with diameters around 5 m<br /> *This leads to a significantly increased number of aeroshells that need to be built, as well as to reduced maximum volume of items that can be transported to Mars<br /> *Analysis was carried out to determine whether it is possible to use a single ~24 mt aeroshell<br /> <br /> == Aerodynamic Properties ==<br /> *Basic shape is blunted cone with 20-degree side-wall angle<br /> *Achieves L/D of 0.3 at 18.5-degree angle of attack<br /> *Drag coefficient of ~1.5 at 18.5-degree angle of attack<br /> *Shape is similar to SpaceX Dragon capsule<br /> **May be possible to utilize aerodynamic database from Dragon<br /> **Possibly use Dragon derivative?<br /> <br /> == Preliminary Transportation Cost Assessment ==<br /> *Falcon 9 Heavy [FY 2008 $]<br /> **$ 94.5 Mn per shot for LEO mission<br /> *Lander costs [FY 2004 $]<br /> **Dry mass: 2453 kg<br /> **Development: $ 1482 Mn<br /> **Production (1st unit): $ 112 Mn<br /> *Aeroshell costs [FY 2004 $]<br /> **Dry mass: 8000 kg<br /> **Development: $ 2839 Mn<br /> **Production (1st unit): $ 245 Mn<br /> *TMI stage [FY 2004 $]<br /> **Dry mass: ~5000 kg<br /> **Development: $ 560 Mn<br /> **Production (1st unit): $ 32 Mn<br /> *Approximate marginal cost for transporting 10 mt to the surface of Mars:<br /> **(3 x 94.5 + 2 x 32 + 112 + 245)*1.2 = 845.4<br /> **$ 84540 / kg on the surface of Mars<br /> <br /> == Concept Overview for 2 mt Case ==<br /> <br /> *“2 mt case”: integrated payloads of no more than 2 mt can be landed on the surface of Mars; extension of current Mars EDL technology<br /> *Cargo transportation<br /> **All cargo packages are landed on the surface of Mars using scaled-up MSL-type vehicles<br /> **Each cargo package and the associated cruise stage and EDL system is launched and injected towards Mars using an EELV-class launch vehicle (Falcon 9 heavy, Delta IV heavy, Atlas V heavy, etc.)<br /> *Crew transportation<br /> **Similar approach as for 10 mt case, but different hab / EDL design<br /> **Mars Transfer Vehicle is assembled in LEO out of 3 payloads of ~25 mt<br /> ***1st payload: habitat + Mars entry vehicle (same entry vehicle as for cargo)<br /> ***2nd and 3rd payloads: each one ~25 mt propulsion stage for TMI<br /> **2 crew are transported using this transfer vehicle</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/EDL&diff=2352 2010-04-18T19:04:55Z

<p>Arthurguest: </p> <hr /> <div>[[MinMars:Main|Return to MinMars Home Page]]<br /> <br /> This section requires further editing to include all previous efforts.<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Transportation/<br /> <br /> = Major EDL Challenges for MinMars =<br /> *Significantly higher ballistic coefficient than MSL<br /> **Lower landing altitude than for MSL helps (denser atmosphere)<br /> **Landing altitude possibly as low as -2 km<br /> *Higher landing accuracy<br /> **2-5 km vs. 20 km<br /> **But pre-deployed assets available (in orbit and on the ground)<br /> *No use of main parachute(s)<br /> **Vehicle never slows down sufficiently for existing parachute technology (&lt; Mach 2); also issues with chute scaling<br /> **All-propulsive descent will likely be required<br /> **Possibly use of a supersonic drogue parachute for aeroshell forebody separation and stabilization<br /> *Off-center aerodynamic heating<br /> **Large aeroshell diameter leads to different Re-number regime, turbulent flow over forebody heat shield<br /> **Maximum heating may no longer occur at center / nose of heat shield but off-center in turbulent region<br /> <br /> Question: in a worst-case scenario, could we deliver MinMars infrastructure�and crew with existing (Viking-based) EDL technology (or extensions thereof)?<br /> <br /> = EDL System for 2 mt Useful Mass =<br /> <br /> *Transportation assessment assuming capability for 1 mt usable surface payload<br /> *Crew transportation:<br /> **2 crew per 25 mt package<br /> **In-space habitat that is discarded prior to aerocapture / entry<br /> **2 crew either enter together in single aeroshell or each crew has individual aeroshell<br /> *Transportation of supplies and spare parts<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of power and ISRU systems<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of unpressurized mobility systems<br /> **Can be scaled down and delivered with individual aeroshells in 1 mt packages<br /> *Transportation of habitat and workshop<br /> **Difficult, may require inflatable modules with interior outfitting; subsequent assembly on the surface<br /> <br /> [[Image:MSL_Technology_Extension.jpg| thumb|center|upright=2.5| alt=MSL_Technology_Extension.jpg| MSL Technology Extension for Ballistic Coefficient 115 kg/m2]]</div>

Arthurguest https://wiki.developspace.net/w/index.php?title=MinMars/Surface_Power&diff=2351 2010-04-18T19:04:29Z

<p>Arthurguest: </p> <hr /> <div>[[MinMars:Main|Return to MinMars Home Page]]<br /> <br /> = Repository of Working Models =<br /> http://svn.developspace.net/svn/minmars/users/arthur/Mars%20surface%20power/<br /> <br /> = Preliminary Surface Power System Assessment =<br /> <br /> [[Image:Preliminary_Surface_Power_System_Assessment.jpg| thumb|center|upright=2.5| alt=Preliminary_Surface_Power_System_Assessment.jpg| Preliminary Surface Power System Assessment]] <br /> <br /> = Mars Surface Power Generation and Energy Storage =<br /> <br /> == Surface Power Architecture Tree ==<br /> * There are two basic types of analyses that can be carried out:<br /> **Equal power analysis: all systems provide the same (constant) power output at any point in time<br /> **Equal energy analysis: all systems provide the same usable energy per day (for photovoltaic systems this means increased power generation during the day)<br /> <br /> [[Image:Surface_Power_Architecture_Tree.jpg| thumb|center|upright=2.5| alt=Surface_Power_Architecture_Tree.jpg| Surface Power Architecture Tree]] <br /> <br /> == Modeling ==<br /> *Created model for a Mars solar array based on following major requirements:<br /> **Array must be sized for end-of-life power generation capabilities<br /> **Array must be sized to provide the required power during the year’s minimum incident solar energy period<br /> *Model Assumptions:<br /> **On Mars, optical depth of 0.4 (equivalent to hazy skies)<br /> **Tracking arrays at both locations are multi-axis and keep incident flux perpendicular to array over the day<br /> **Nighttime power of 20 kW, with daytime power enforced when sun is 12 degrees above the horizon<br /> **Mars analysis done for an equatorial location (actually not optimal location for solar power on Mars):<br /> ***Optimal location at 31° N, with a minimum of 6.57(kW-h/m^2/sol) and 49% daylight/sol for a period of 100 sols <br /> ***Northern latitudes better than corresponding southern latitude<br /> <br /> [[Image:Daily_Solar_Incidence_Energy_Levels.jpg| thumb|center|upright=2.5| alt=Daily_Solar_Incidence_Energy_Levels.jpg| Daily Solar Incidence Energy Levels]] <br /> <br /> ===Inputs===<br /> *Minimum solar energy<br /> *Eclipse Time<br /> *Daytime/nighttime power req.<br /> *Power distribution eff.<br /> *Solar array eff.<br /> *Degradation per year<br /> *Array lifetime<br /> *Optical depth<br /> *Latitude<br /> *Array packing density<br /> *Battery type<br /> <br /> ===Outputs===<br /> *Array area<br /> *System mass<br /> *System volume<br /> <br /> == Results ==<br /> <br /> [[Image:Mass_Specific_Power.jpg| thumb|center|upright=2.5| alt=Mass_Specific_Power.jpg| Mass Specific Power]] <br /> <br /> [[Image:Volume_Specific_Power.jpg| thumb|center|upright=2.5| alt=Volume_Specific_Power.jpg| Volume Specific Power]] <br /> <br /> == Other Considerations for Large Solar Array Fields on Mars ==<br /> ===Deployment time===<br /> *Considered a 10,000 m^2 rollout array field which will provide 63kW average power for about 100kW daytime power<br /> *Assume array blankets are 2m wide for easy storage and handling by two astronauts<br /> *Assume each blanket weighs 100lbs again for easy handling<br /> *With 0.06 kg/m^2 expected array density, need only 14 blankets total<br /> *Assume astronauts can unroll array at a walking speed of 1m/s, requires only 3hrs for unrolling<br /> *Most time will be needed for unloading positioning and hookup, if assume 1hr for this for each array, total deployment time *approximately 17 work hours for 2 crew<br /> ===Power delivery during deployment===<br /> *If we are conservative and say deployment takes 1 week, we need either a 10kW RTG or fuel cell system to provide 10kW power over the week<br /> *RTG system would be approximately 1200kg and 0.6 m^3<br /> *If use RFC, need 2400kg system with volume 8.4 m^3<br /> <br /> == Future Work ==<br /> *Reassess architecture options in MinMars colony context. Previous power analysis for shorter round trip mission. <br /> *Operations considerations such as dust removal and maintenance.<br /> *Dust storm power generation.<br /> <br /> == Issues to be resolved ==<br /> *RFC performance may be significantly reduced compared to our assumptions<br /> **300 Wh/kg or less<br /> **Could possibly be enhanced by generating oxygen for RFC in-situ (~ 25% of RFC mass)<br /> *Effect of wind speed on roll-out arrays<br /> **Would they be blown away?<br /> *Degradation, dust removal<br /> *Robotic deployment<br /> <br /> = Surface Power Architecture Analysis Follow-up =<br /> <br /> == Areas of Revision ==<br /> *Regenerative fuel cell performance<br /> **Original Energy Density<br /> ***~700 Wh/kg<br /> **Revised Energy Density<br /> ***~250 Wh/kg<br /> *Wind considerations<br /> **Found that a wind speed of 7.35 m/s would in fact lift the solar array off the surface.<br /> **Altered conceptual array design to include Kevlar areas equal to 10% of the total array area to provide space for Martian rock placement for weighing down the array. <br /> **9.2 kg/m^2 of rock is needed in the 10% Kevlar regions to secure the array against the top recorded Mars wind of 25 m/s.<br /> **The major effect of this consideration is increased deployment time.<br /> *Latitude considerations<br /> **Ran model for multiple latitudes to show change in performance based on location.<br /> **Optimal location at 31° N, with a minimum of 6.57(kW-h/m^2/sol) and 49% daylight/sol for a period of 100 sols.<br /> **Northern latitudes better than corresponding southern latitude. <br /> <br /> == Updated Results==<br /> <br /> [[Image:Mass_Specific_Power_vs_Latitude.jpg| thumb|center|upright=2.5| alt=Mass_Specific_Power_vs_Latitude.jpg| Mass Specific Power versus Latitude]] <br /> <br /> [[Image:Volume_Specific_Power_vs_Latitude.jpg| thumb|center|upright=2.5| alt=Volume_Specific_Power_vs_Latitude.jpg| Volume Specific Power versus Latitude]] <br /> ==Effects on Deployment Time==<br /> *Considered the 100kW average power system located at the equator.<br /> **Requires a 25,000 m^2 rollout array field due to addition of the Kevlar areas.<br /> **Assume array blankets are 2m wide for easy storage and handling by two astronauts<br /> **Assume each blanket weighs 80lbs again for easy handling<br /> **With 0.07 kg/m^2 expected array density, need only 18 blankets total<br /> **Assume astronauts can unroll array at a walking speed of 1m/s, requires only 7hrs for unrolling<br /> **Time will be needed for unloading positioning and hookup, if assume 1hr for this for each array this adds 18hrs<br /> **In addition to this rocks must be placed in the Kevlar areas. Assume Kevlar areas are 1ft in length and the complete 2m width. Need 5.6kg of rock in each area. There are 225 of these Kevlar areas per array so a total of 4050 of these areas. Assuming 2 rocks are needed per area to secure the 2 sides of the array this requires 8100 rocks to be placed. If 30 seconds is needed to pick and place a rock this will take 33.75hrs for 2 crew.<br /> *Total deployment time is then 66hrs for 2 crew members <br /> *Power delivery during deployment:<br /> **We see that deployment gives 0.76 kW per man hour, therefore we only need 13.2 man hours to reach a capability of 10 kW which is enough for minimal stay alive power.<br /> **If you are conservative and neglect this and say full deployment and initial usefulness takes 1 week, we need either a 10kW RTG or fuel cell system to provide 10kW power over the week<br /> **RTG system would be approximately 1200kg and 0.6 m^3<br /> **If use RFC, need 2400kg system with volume 8.4 m^3<br /> *Sensitivity of total deployment time to different factors:<br /> **Sensitivity to array area=0.99<br /> **Sensitivity to walking time=0.96<br /> **Sensitivity to rock placement time=0.97<br /> **Sensitivity to off-load and hookup time=0.965<br /> **We see that the total deployment time is most sensitive to walking time so the design should be sure to make the unrolling of the array by astronauts in suits easy</div>

Arthurguest