On Orbit Refueling: Supporting a Robust Cislunar Space Economy

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Melanie Patterson
6 years ago
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2 Atlas V Launch History ULA s Vision: Unleashing Mankind s Potential in Space ULA is developing the enabling transportation system for a Self Sustaining Space Economy Delta IV March

3 Customers National Security Space Civil Space Human Launch Global Positioning System (GPS) Intelligence, Surveillance and Reconnaissance Robotic Exploration and Science Mars Science Laboratory Pluto New Horizons Commercial Space Increasing Our Knowledge of the Earth and Its Climate Earth Imagery Commercial Communication Geostationary Operational Environmental Satellite (GOES) Cloudsat Cargo Crew 4 March

4 4 March ULA Launches

5 4 March Cislunar 1000 Vision

6 4 March Cislunar 1000 Vision

7 GEO Cislunar Econosphere NEO V=3.77 V= V in (km/s) LEO V=1.40 V=0.65 V=2.52 V=4.33 EML1 LLO V=1.90 ETO V=9.53 LEO ISS Remote Sensing Commercial Station Communication Space Control Debris mitigation Science R&D Tourism Manufacturing Propellant Transfer Data Servers 4 March GEO Observation Communication Space Control Debris Mitigation Space Solar Power Repair Station Satellite Life extension Harvesting High Earth Orbit Science / Astronomy Communication Link Way Station Propellant Depots Repair Station Lunar Solar Power Sat Manufacturing Planetary Defense Existing market / Emerging market \ Future market Lunar Surface Science/ Astronomy Lunar Observatory Human Outpost Tourism Mining Oxygen/Water Regolith Rare Earth Elements HE3 Manufacturing Fuel Depots Solar Power to Earth

8 Cislunar Transportation System ACES Fueled with LO2 and LH2 propellant provided from: Earth Moon Asteroids XEUS 4 March Reusable Transportation Avoids Earth s Deep Gravity Well

9 Lunar Water Water at Lunar poles Cold Traps in Craters ~10B mt per pole Fuel, Water, Oxygen Lunar Reconnaissance Orbiter Credit: LRO Camera Team Paul Spudis 4 March Credit: Chris Meaney / NASA 2008

10 Lunar Water Extraction Power Tower on Crater Rim Beam power to crater floor Sublimate ICE Collect and liquefy Electrolyze water Liquefy and store LH2 & LO2 Resource Prospector Griffin Lander Shackleton Crater 4 March Credit: NASA/Zuber, M.T. et al., Nature, 2012

11 Transportation Refueling Nodes L1 Provides logical propellant staging node Assessable from NEO s and lunar surface Can distribute propellant to any Earth orbit Good staging location for distant missions Lunar surface Make propellant for ascent transportation GEO V=3.77 V= NEO V in (km/s) LEO V=1.40 V=0.65 V=2.52 V=4.33 EML1 LLO V=1.90 ETO V= March

depots Zero-G cryo fluid management Zero Boil off Storage

12 Historic On-Orbit Refueling Paradigm On-orbit refueling is historically associated with: Large scale, permanent propellant depots Zero-G cryo fluid management Zero Boil off Storage Historic Refueling Architectures Present Insurmountable Barriers 4 March

13 Simple On-Orbit Refueling Node Produce LO2 & LH2 Electrolyze water Liquefy GO2 and GH2 Store LO2 and LH2 Thermally Isolate & Sun Shields Settled propellant management LH2 >100 mt Propellant Distribute LO2 & LH2 Pressure fed transfer No-vent-fill LO2 4 March Single Launch Emplacement

Transportation Enabling Technologies Integrated

Cryogenics Power > No Main batteries Reaction

Enables Service Module Flexibility On Orbit

IVF Module Internal Combustion Engine Prototype IVF

14 Transportation Enabling Technologies Integrated Vehicle Fluids Integrated Vehicle Fluids & Cryogenics Power > No Main batteries Reaction control > No Hydrazine Pressurization > No Helium Enables Service Module Flexibility On Orbit Refueling Reusable ACES throughout cislunar space IVF Module Internal Combustion Engine Prototype IVF Module H2/O2 Thrusters 4 March On-Orbit Refueling Reduced to LO2 and LH2

15 Transportation Enabling Technologies: Cryo Fluid Management CRYOTE 3 at NASA MSFC Initiate CRYOTE CRYOTE Light 4 March CRYOTE 1 built CRYOTE 1 LN2 Test CRYOTE No Vent Fill CRYOTE 3 Tank Delivery CRYOTE 3 Cryo Test CRYOTE 3 IVF Test CRYOTE Grande CRYOTE 3 Long Duration

16 Distributed Launch Vulcan Earth Escape GSO or Lunar Orbit Lunar Surface Delta HLV 11 mt 7.4 mt - Single Launch 14 mt 10 mt 3.8 mt Distributed Launch 30 mt 24 mt 12 mt 4 March Propellant Launch Initial Step to Upper Stage Reuse Payload Launch

17 XEUS ACES + Mission Kit Electric LH2 & LO2 pumps LH2/LO2 Thruster Landing GN&C Landing struts XEUS Cargo Ascender or Cargo Module 4 March

Propellant Tank ACES/XEUS & Payload Propellant Transfer Enables Large Scale

18 Lunar Surface Cargo Mission 4) Lunar Orbit Insertion And Descent 1) Launch 2) Refuel ACES 5) XEUS Terminal Descent 3) Trans-Lunar Injection ACES & Propellant Tank ACES/XEUS & Payload Propellant Transfer Enables Large Scale Lunar Infrastructure Science Propellant production Manufacturing Habitation 4 March

19 Cost of Resources ($/kg) GEO Costs of Resource in Cislunar Space LEO EML1 LLO $35k/kg $20k $15k $10k $5k $0k $0.001k/kg Earth Cost From Earth Cost From the Moon (or Asteroid) Cost From Earth Utilizing Beyond Earth Propellant LEO GTO GSO L1 Moon $0.5k/kg 4 March

20 Standing on the Threshold of Robust Cislunar Economy Solar Power Station ALPHA Credit: John C. Mankins 4 March

21 4 March

Abstract #1754. English. French. Author(s) and Co Author(s) Resources in the cislunar marketplace. To follow. No abstract title in French

Abstract #1754. English. French. Author(s) and Co Author(s) Resources in the cislunar marketplace. To follow. No abstract title in French 4/26/2017 CIM TPMS Abstract #1754 English Resources in the cislunar marketplace To follow French No abstract title in French No French resume Author(s) and Co Author(s) Mr. GEorge Sowers (UnknownTitle)