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In-Situ Resource Propellant Production and ERV Launch Systems

This preliminary design analysis explores the considerations, methods, and advantages of in-situ propellant production for future ERV launch systems, including the Sabatier process, water electrolysis, and the Zirconia cell process. The comparison of different propellant options and launch system technologies is also discussed.

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In-Situ Resource Propellant Production and ERV Launch Systems

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  1. AAE450In-Situ Resource Propellant Productionand ERV launch systemsAdam ButtPreliminary Design Analysis1/23/01

  2. Overview • In-situ Propellant Production Considerations: • Method of production • Type of fuel/oxidizer to be produced • Necessary ingredients that need to be brought from Earth • ERV Launch system • Necessary power requirements

  3. Method of Production • Sabatier Process CO2+4H2  CH4+2H2O • Water Electrolysis H2O  1/2O2+H2 • Rocket Propulsion 1/2CH4+O2 CO2+H2O Picture from JPL – Advanced Propulsion Concepts website

  4. Method of Production • Zirconia Cell Process CO2  CO + O2 • Rocket Propulsion CO + 1/2O2  CO2 Picture from JPL – Advanced Propulsion Concepts website

  5. Method of Production • Another consideration is the production of Methanol, CH3CH, via an in-situ method (with a catalyst). CO + H2 CH3OH + H2O • Rocket Propulsion CH3OH + 3/2O2  CO2+2H2O

  6. Sabatier/H20 Electrolysis Advantages CH4/O2 combustion capable of producing high Isp~350sec Exothermic reaction that creates water as a side product Disadvantages Must bring and store sizeable amount of H2 from Earth Doesn’t produce adequate amounts of O2 Zirconia Cell Process Advantages All fuel and propellant produced from in-situ resources Excess O2 can be produced Disadvantages CO/O2 combustion relatively low Isp~240sec Greater overall volume requirements(?) Production Method Comparison

  7. Propellant Comparison • Graphs generated with NASA TEP code

  8. ERV Launch System Comparison • CO/O2 Rocket – Low Isp~240sec, but all propellant can be produced in-situ • CH4/O2 Rocket – Higher Isp~350sec, H2 must be brought from Earth • NERVA derived/CH4 (Nuclear Engine for Rocket Vehicle Applications) – Theoretical Isp~900sec, H2 must be brought from Earth • Note that all the above technologies have not been developed on the large, heavy-lift launch scale. Also the Nuclear engine has never been flight tested

  9. Future Work • More in-depth study into various propellant advantages and disadvantages. Also various in-situ techniques and their power/mass/volume/cost comparisons • Matlab code to determine necessary components to be brought from Earth to support various types of in-situ propellant production, based on delta V to return to Earth.

  10. Classes Propulsion AAE372, AAE439, AAE539 Management Managerial Accounting-Cost/Benefit Analysis Other Proficiencies AutoCad SurfCam CNC Model Building Skills

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