Oh, Thank Heaven for 7-Eleven: Fueling Up in Space with In-Situ Resource Utilization ASTE-527 Final Presentation Riley Garrett

Mission Context – Lunar Excavator Colorado School of Mines 1 Carnegie Mellon

Mission Context – Water Ice Deposits on the Moon 600 million tons of water ice 2 Permanently shadowed areas exist in the Moon’s deep craters

Mission Context – Lunar Propellant Purdue University 3 Aluminum makes up 13% of the mass of lunar highland regolith ALICE powered rocket -Thrust levels above 650 lb with Isp of 210 s during test flight

Rationale for In-Situ Lunar Propellant Production – Better Performance Examples of Propellant Depot Impact 4 Current PerformancePerformance With Depot Lunar Missions Landed Mass Surface Payload 18 tons 2 tons 51 tons 35 tons GTO Mission Delta IV H Atlas V tons 9 tons 35 tons 23 tons GSO Mission Delta IV H Atlas V tons 4 tons 18 tons 10 tons Interplanetary Mission Delta IV H Atlas V tons 7 tons 20 tons 15 tons

Saturn V with Propellant Depot Saturn V Launch Vehicle 5 Mass, tons Weight at Lift-off3200 Translunar Payload, total 54 CM/SM propellant mass 20 LEM propellant mass 12 % payload mass which was propellant 59.3% Using propellant depot means Saturn V does not need to launch 32 tons of propellant…delta-V for TLI (10.8 km/s) can be nearly be achieved with just the first 2 stages

LEO125,000 kg GTOTBD Fairing Diameter 8.38 m Price in millions $769 LEO50,000 kg GTO9,650 kg Fairing Diameter 5.2 m Price in millions $78 50 metric tons dry = 125 metric tons wet with using depots 6 A launch vehicle can be much smaller at 1/10th the cost

Assumptions and ground rules Robotic Precursors Lead the Way… …to a more Permanent Human Presence 7

7-Eleven Space Mission Concept – Land a Rover on the Moon and Re-launch using only In-Situ Resources Robotic Precursor Mission to Demonstrate a Factory for Processing Lunar Material for Rocket Propellant 8 Search – Land - Drive – Drill - Dig - Analyze - Extract - Mix - Load - Launch

7-Eleven Space Mission Architecture - Launch Vehicle

7- Eleven Space Mission Architecture – Trajectory and Landing Site

7-Eleven Space Mission Architecture – Mission Operations and Systems 1. Soil Sampling, 2. Landing, 3. Mining and Excavation, 4. Production and Refinement, 5. Loading and Launching

7-Eleven Space Mission Architecture - Spacecraft Lander Rover 9 Dig and Drill Excavate 7 Eleven

7-Eleven Space Mission Architecture – Spacecraft Instruments Extraction 10 – Mixer – Loader - Launch anorthosite Melt - quench - leech alumina electrolysis + cryolite aluminumNano-aluminum ALICE Pulse Plasma

Merits and Limitations Mission Merits Demonstrates technology sooner rather than later. Engages mission architects and planners in alternate propellant sources. Engages the public in another rover based mission (which they like). Meet program needs in terms of cost and scale. Demonstrates appropriate technology, at an appropriate scale. Shows Congress and NASA heads what to expect from ISRU and propellant depots. Proves the technology. Mission Limitations Is the mission scalable to meet larger propellant demands? Can the mission be extended for other resource extractions such as water and oxygen? Does a solid propellant meet the propulsion requirements for enough spacecraft to make it worthwhile?

Future Studies Developing re-startable ALICE solid propellant loading techniques for spacecraft station-keeping in GEO Improve specific impulse of ALICE solid propellant Oxygen and hydrogen production methods for liquid propulsion systems Silane production for rocket engines on Mars since it can burn using carbon dioxide as an oxidizer Extending propellant production methods for ISRU on NEO or Mars Proposed Mars sample and return mission using in-situ produced propellant 11

References html off.pdfhttp:// off.pdf and-affordable-moon-base/ and-affordable-moon-base/ beyondapollo.blogspot.com