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Lunar Lander Propulsion System 100 g, 10 kg and Arbitrary payload cases Thaddaeus Halsmer Thursday, March 12, 2009

Lunar Lander Propulsion System 100 g, 10 kg and Arbitrary payload cases Thaddaeus Halsmer Thursday, March 12, 2009 Propulsion System Sizes, Performance and Power requirements Propulsion system cost estimate Designed 10 kg payload hopper engines

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Lunar Lander Propulsion System 100 g, 10 kg and Arbitrary payload cases Thaddaeus Halsmer Thursday, March 12, 2009

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  1. Lunar Lander Propulsion System 100 g, 10 kg and Arbitrary payload cases ThaddaeusHalsmer Thursday, March 12, 2009 Propulsion System Sizes, Performance and Power requirements Propulsion system cost estimate Designed 10 kg payload hopper engines Worked jointly with SaadTanvirto complete propulsion system sizing codes for all three payload cases Thaddaeus Halsmer, Propulsion

  2. (4) ** numbers on this page are a result of engine sizing scripts written by SaadTanvir & myself. Credit must also be given to John Aitchison for its integration into the Ops trajectory code and many iterations to produce final sizing (3) (1) (2) Stick is 6.5 feet high, same as a standard doorway Thaddaeus Halsmer, Propulsion

  3. 1) Propulsion system costs • Not including R&D/Testing to meet reliability requirements • Assumed $10000/kg Integration/manufacturing cost • Propulsion System Power Requirements • Power for fluid control systems Thaddaeus Halsmer, Propulsion

  4. Additional prop system size and performance info Thaddaeus Halsmer, Propulsion

  5. Engine Dimension diagrams for previous slide Dch,h Lch,h Dch Lch Lnoz Lnoz,h Dnoz Dnoz,h Main Engine Dimensions Hopper Engine Dimensions Thaddaeus Halsmer, Propulsion

  6. HV01 10 kg payload Fluid System Diagram High Pressure Helium Tank SV01 SV05 SV03 SV04 REG CK01 SV02 CK02 RV01 MOV F01 H2O2 Tank HV02 Thaddaeus Halsmer, Propulsion

  7. 100 g, & Arbitrary payload Fluid System Diagram HV01 High Pressure Helium Tank SV01 REG CK01 SV02 CK02 RV01 MOV F01 H2O2 Tank HV02 Thaddaeus Halsmer, Propulsion

  8. References: Fluid control component price source: [1] Reid, Bryan, (personal communication, February 2009), Sr. Director, Aerospace Business Development, Marotta Controls Inc., Montville, New Jersey Hybrid Rocket Engine Design: [2] Heister, S. D., (Personal communication, January 2009), Professor of Propulsion, Purdue University School of Aeronautics and Astronautics, Armstrong Hall Rm. 3331, West Lafayette, IN [3] Humble, R.W., Henry, G. N., Larson, W. J., “Space Propulsion Analysis And Design,” 1st ed., McGaw Hill, 1995 [4] Sutton, G. P., Biblarz, O., “Rocket Propulsion Elements,” 7th ed., Wiley-Interscience Publication, 2001 [5] Caravella Jr., J. R., Heister, S. D., Wernimont, E. J., “Characerization of Fuel Regression in a Radial Flow Hybrid Rocket,” JOURNAL OF PROPULSION AND POWER, Vol. 14, No. 1, January-February 1998 [6] Casalino, L., Pastrone, D., “Optimal Design of Hybrid Rocket Motors for Launchers Upper Stages,” 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 21-23 July 2008, Hartford, CT Thaddaeus Halsmer, Propulsion

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