A2.1 Reference Mission 1.0 Launch Strategy
A2.1.3 Modified Launch Strategy
A2.2 Elimination of Initial Habitat Flight
A3.0 System Design Improvements
A3.1 Incorporation of TransHab Improvements
A3.2.1 In-Situ Resource Utilization
A3.3 Transportation System Improvements
A4.0 Summary of Reference Mission Version 3.0
A5.1 Solar Electric Propulsion
A5.1.1 Electric Propulsion Mission Concept
A5.1.2 Electric Vehicle Concepts
A5.2 Aerocapturing the TransHab
A5.3 Bimodal Nuclear Thermal Rocket (NTR) Propulsion
5.3.1 Bimodal NTR Mission Concept
5.3.2 All Propulsive" Bimodal NTR Option Using TransHab
5.3.3 "LOX-Augmented" NTR Option
5.3.4.2 Strategies and Technology Challenges
5.3.4.3 Combination Lander Scenario
Figure A2-1 Cargo and Piloted Vehicles for Reference Mission Version 1.0
Figure A2-2 Reference Mission Version 1.0 Mission Sequence
Figure A2-3 Mars Surface Lander and Habitat Aeroshells for Version 1.0
Figure A2-4 Habitat Repackaging Strategy
Figure A2-5 Historical Space Habitat Pressurized Volume
Figure A2-6 Mars Surface Inflatable Habitat Concept
Figure A3-1 Payload Capability to 407 km
Figure A3-2 Magnum Launch Vehicle
Figure A3-3 Schematic of solid core NTR turbopump and power cycle
Figure A3-4 NTR stage and aerobraked Mars payload for Version
Figure A3-5 Aeroassist Study Results for Version 3.0
Figure A3-6 Entry and Landing Parachute Study Results for Version 3.0
Figure A3-7 Launch and Packaging Configurations for Version 3.0
Figure A4-1 Reference Mission Sequence for Version 3.0
Figure A5-2 SEP Crew Taxi Concepts
Figure A5-3 Conceptual Solar Electric Propulsion Vehicle
Figure A5-4 Launch manifest for the Solar Electric Propulsion Vehicle Concept
Figure A5-5 Potential Transhab Aerobrake Configurations
Figure A5-6 Schematic "Bimodal" NTR System
Figure A5-7 "Bimodal" NTR Transfer Vehicle Option
Figure A5-8 All Propulsive Bimodal NTR Carrying TransHab
Figure A5-9 Three-Magnum Combination Lander Scenario
Figure A5-10 Three-Magnum Combination Lander Launch Packages
Figure A5-11 Combination Lander Concept on Mars Surface
Figure A5-12 Three-Magnum Split Mission Scenario
Figure A5-13 Three Magnum Split Mission Launch Packages
Figure A5-14 Solar Irradiation at Mars
Table A3-1 Mass Reduction Benefits from the Transhab Study
Table A3-2 ISRU System Breakdown for Version 3.0
Table A3-3 Power System Improvements for Version 3.0
Table A3-4 Science Manifest for Version 3.0
Table A3-5 Launch Vehicle Requirements
Table A3-6 Payload Capability to 407 km
Table A4-1 Payload Mass Evolution from Version 1.0 to Version 3.0
Table A4-2 Earth Return Vehicle Mass Scrub for Version 3.0
Table A4-3 Cargo Lander Mass Scrub for Version 3.0
Table A4-4 Piloted Lander Mass Scrub for Version 3.0
Table A5-1 Comparison of "Bimodal" NTR to Reference Mission Version 3.0