1. We Are Closer to Mars Today Than We Have Ever Been…

2. Aerojet Rocketdyne Capabilities Can Provide the Needed Propulsion and Power Technology 2 1940’s 1950’s1960’s1970’s1980’s1990’s2000’s2010’s Aerobee First Production Launcher Apollo SPS First Human Rated Lunar Vehicle Voyager Furthest, Longest Life Spacecraft Viking First Mars Lander NERVA NRX/EST First Nuclear Flight Type Rocket Engine SNAP 10A First Production Space Nuclear Fission Power NEAR First Asteroid Lander Cassini First Spacecraft to Orbit Saturn Messenger First Spacecraft to Orbit Mercury New Horizons First Pluto Flyby AEHF First USA Hall Thruster Flight MMRTG First Multi- mission Radioisotope Mars Science Lab Deepest Throttling Monoprop Engine Saturn V Largest Production Human Rated Rocket Engines JATO First Jet Assisted Take-off from an Aircraft Carrier Polaris First Submarine Launched ICBM First Solid Ballistic Missile Atlas V SRB Largest US Monolithic Solid Rocket Motor Telstar First Flight of a Hydrazine Arcjet NTP LEU Concept SEP Demo Surface Power Concept

3. Some Capabilities Areas AR is Working F UTURE C APABILITIES A RE N EEDED T O O PEN THE S OLAR S YSTEM TO H UMAN E XPLORATION AND S ETTLEMENT AT M ARS 3 Today’s Capabilities  No Heavy Lift −Many flights −In-space assembly  Chemical Propulsion Only −Long trip times to Mars −Very large mass to Earth orbit −Limited split mission benefit  Solar and Radioisotope Power −Limited maximum power capability and budgets Future Capabilities In-work  Heavy lift (SLS) Boost & Upper-stage  Solar Electric Propulsion  Nuclear power & propulsion  Deep Space Habitats  Life Support (H2O, Food)  Radiation Protection  Crew & Cargo Landers  ISRU-Resource Utilization  Deep-space High Thrust

4. Foundational Capabilities Needed for Mars 4 Going to Mars with humans requires a diverse set of “tools” Mars Descent Lander Mars Ascent Vehicle Ref: B. Drake/NASA image with modification per CR Joyner Ascent Vehicle ISRU* influenced Large EDL & Surface Habitat ISRU* influenced Transit Habitat In-Space Propulsion Earth to Mars to Earth Solar Electric 100 to 200 kWe Cargo 4 crew for 1000 days Orion Space Launch System Earth and Near Earth 4 Crew 21 Days < 12 km/s 70 & 130 t EUS Large shroud Mars Orbit to Surface High Thrust Crew ISRU=In-Situ Resource Utilization – discussed later*

5. Some Mars Architectures Options Being Considered 5 LRO LEO Phobos Orbit Elliptical Mars Orbit LGA LEO=Low Earth Orbit LRO=Lunar Retrograde Orbit LGA=Lunar Gravity Assist Yr=Year SEP=Solar Electric Propulsion Mars Stay 300-500 days In Orbit or Surface Earth to Mars Crew 300+ days Mars to Earth 180+ days High & Low Thrust Hybrid Combined High Thrust Earth to Mars Cargo 1200 days Earth to Mars Crew 180+ days Mars to Earth 300+ days SEP Pre-positions Cargo 6 -12 SLS ~2 SLS Launches per Yr 1 Mars Mission per 2 Yrs

6. Architecture Studies AR examined utility of SEP for logistics of deep space exploration dating back into the early 2000’s –HRT program supporting lunar logistics – 2005 –Augustine committee – 2008 –Cis-lunar tugs – 2010 –HLPT study - 2011 –Waypoint cis-lunar logistics - 2012 Current work examining SEP cargo vehicle power level trades –Updates to HLPT using SLS –Trades on departure orbit and power level Future Work –LDRO starting orbits to Mars –No Mars entry spiral –Multiple tier approach Example Copernicus run showing SEP trajectory Approved for Public Release

7. Affordable Crew Transportation Options If 6 month transfer times are required –LOX/methane with ISRU –LOX/H2 with long-term cryo storage –Nuclear thermal propulsion with long-term cryo storage Least number of launches per Mars expedition If longer crew transfer times are acceptable then storable chemical + SEP becomes an option –Potential benefit of commonality between cargo and crew propulsion systems 7 C HEMICAL PROPULSION OPTIONS ARE HIGH TRL BUT REQUIRE MORE LAUNCHES WITH IN - SPACE ASSEMBLY – CONCERNS ARE ISRU OR LT CRYO - STORAGE N UCLEAR T HERMAL P ROPULSION IS LOWER TRL AND REQUIRES LT CRYO STORAGE C HEMICAL PROPULSION OPTIONS ARE HIGH TRL BUT REQUIRE MORE LAUNCHES WITH IN - SPACE ASSEMBLY – CONCERNS ARE ISRU OR LT CRYO - STORAGE N UCLEAR T HERMAL P ROPULSION IS LOWER TRL AND REQUIRES LT CRYO STORAGE

8. Nuclear Thermal Propulsion Twice the Isp of LOX/H2; about 60% the best chem launch mass Safety and regulatory issues drive cost Key affordability drivers: –Overall DDT&E program approach –Fuel selection drives security, system complexity and testing costs –Thrust class impacts testing cost and number of NTRs/mission 8 A COMBINED SPLIT M ARS ARCHITECTURE (SEP ~100 KW E CARGO ) HELPS NTP AFFORDABILITY AND HELPS THRUST DOWNSIZING NO BIG ENGINES WITH BIG TEST FOOTPRINTS U SE AS MUCH OFF - SHELF TECHNOLOGY AS POSSIBLE F ROM “D ETERMINING A N A FFORDABLE M ARS M ISSION C APABLE NTP T HRUST S IZE ”, BY R. J OYNER ET AL.; NETS, F EBRUARY 2015 A COMBINED SPLIT M ARS ARCHITECTURE (SEP ~100 KW E CARGO ) HELPS NTP AFFORDABILITY AND HELPS THRUST DOWNSIZING NO BIG ENGINES WITH BIG TEST FOOTPRINTS U SE AS MUCH OFF - SHELF TECHNOLOGY AS POSSIBLE F ROM “D ETERMINING A N A FFORDABLE M ARS M ISSION C APABLE NTP T HRUST S IZE ”, BY R. J OYNER ET AL.; NETS, F EBRUARY 2015

9. How Do We Get Sustained Survivability at Mars Use Evolutionary Approach … 9

10. Cis-Lunar Habitats for Proving Ground Missions in 2020’s Approved for Public Release Source: Thales Alenia Space Source: NASA Habs prove out systems required for Mars transfers Missions for Orion/SLS in 2020’s of progressively longer duration

11. A Progression of Cis-Lunar Missions Using the SLS Block 1B configuration and Orion Many options for pressurized volume Key to habs is what goes inside ECLSS, Biological experiments, Radiation protection, etc. Duration can be increased by adding elements Logistics support via commercial model - SEP plays well

12. Key Factors in Cis-Lunar Mission Plans Progress toward Mars readiness Maintain cadence that keeps public / political interest Stay within budget guidelines No detours / dead-ends / blind alleys Reuse is a “plus” –learn from what we have done on ISS and shuttle

13. SLS Launch Configurations 13

14. Notional Cis-Lunar Mission Progression Earth 202520262024 LEO (407km circ) 2023 20222021 2020 202720282029 LDRO (70,000km) Lunar Surface 20 – 30 days 30 – 60 days 60 – 90 days Telerobotics 90 – 120 days Lunar Sorties (BYOLL) SLS Cadence of 1 per year EuropaSEP Resupply Mars First Mars Cargo Launches

15. Logistics for Cis-Lunar Habs Study results for cis-lunar habitat logistics show significant savings for cargo delivery using SEP Additional modules can also be delivered to build hab capability Cargo can be delivered using commercial or international LVs Approved for Public Release

16. Conclusions Split Cargo / Crew Architecture provides large cost savings for early Mars campaign –Can transfer approximately 80% of required assets by mass –Saves 60% of total campaign cost when compared to earlier DRMs Power level of SEP for cargo can be reduced to 150 – 200 kWe –20 mT – 40 mT payloads can be delivered in less than 3 years Modular SEP approach allows for scaling, extensibility, and economies of scale Early demonstration of SEP and Deep Space Habitat capabilities can be accomplished via (a) cis-lunar mission(s) Approved for Public Release