1. AAE450 Spring 2009 Lunar Lander Propulsion System 100 g, 10 kg and Arbitrary payload cases Thaddaeus Halsmer Thursday, March 12, 2009 1.Propulsion System Sizes, Performance and Power requirements 2.Propulsion system cost estimate 3.Designed 10 kg payload hopper engines 4.Worked jointly with Saad Tanvir to complete propulsion system sizing codes for all three payload cases Thaddaeus Halsmer, Propulsion

2. AAE450 Spring 2009 Thaddaeus Halsmer, Propulsion 2 (2) (3) (4) (1) Table 1 Engine performance parameters Engine No.Payload case/DescriptionF_max/min [N]tb [s] 110 kg/hop engine 2x192 (avg.)134.5 2100 g/main engine1100/110198.6 310 kg/main engine1650/165190.4 4Arbitrary/main engine27000/2700250.2 Table 2 Engine dimensions Engine No.Height [m]D_chamber [m]D_nozzle [m] 10.270.070.11 20.610.270.20 30.800.320.23 42.160.920.94 Stick is 6.5 feet high, same as a standard doorway ** numbers on this page are a result of engine sizing scripts written by Saad Tanvir & 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. AAE450 Spring 2009 Thaddaeus Halsmer, Propulsion 3 1) Propulsion system costs Not including R&D/Testing to meet reliability requirements Assumed $10000/kg Integration/manufacturing cost Table 4 Power requirement from OTV/Lander stage separation through lunar landing payload casePower required not to exceed [watts] 100 g124 10 kg148 Arbitrary275 2)Propulsion System Power Requirements Power for fluid control systems

4. AAE450 Spring 2009 Thaddaeus Halsmer, Propulsion 4 Table A1 Thrust chamber and nozzle key dimensions SymbolDescription100 g10 kgArbitrary D_oxspherical oxidizer tank diameter, [m]0.470.540.67 D_Hespherical Helium tank diameter, [m]0.370.420.52 D_chmain engine chamber diameter, [m]0.270.320.92 L_chmain engine chamber length, [m]0.320.470.82 L_nozmain engine nozzle length, [m]0.290.331.34 D_nozmain engine nozzle exit diameter, [m]0.200.230.94 D_ch, hophopper engine chamber diameter, [m]--0.07-- L_ch, hophopper engine chamber length, [m]--0.47-- L_noz, hophopper engine nozzle length, [m]--0.16-- D_noz, hophopper engine nozzle exit diameter, [m]--0.11-- Table A2 Engine performance parameters SymbolDescription100 g10 kgArbitrary F_memax/min main engine thrust [N]1100/1101650/16527000/2700 F_hopperAverage hopper engine thrust [N]--192-- Isp_meAverage main engine Isp [s]320 Isp_hopperAverage hopper engine Isp [s]--333-- P_chmax/min chamber pressure [psi]300/30 Ae/Atnozzle area ratio100 Additional prop system size and performance info

5. AAE450 Spring 2009 Main Engine Dimensions D ch D noz L noz L ch D ch,h D noz,h L noz,h L ch,h Hopper Engine Dimensions Thaddaeus Halsmer, Propulsion 5 Engine Dimension diagrams for previous slide

6. AAE450 Spring 2009 Thaddaeus Halsmer, Propulsion 6 SV01 SV02 High Pressure Helium Tank HV01 REG CK01 CK02 MOV F01 H 2 O 2 Tank HV02 RV01 SV04 SV03SV05 10 kg payload Fluid System Diagram

7. AAE450 Spring 2009 SV01 SV02 High Pressure Helium Tank HV01 REG CK01 CK02 MOV F01 H 2 O 2 Tank HV02 RV01 100 g, & Arbitrary payload Fluid System Diagram Thaddaeus Halsmer, Propulsion 7

8. AAE450 Spring 2009 Thaddaeus Halsmer, Propulsion 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,” 1 st ed., McGaw Hill, 1995 [4] Sutton, G. P., Biblarz, O., “Rocket Propulsion Elements,” 7 th 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,” 44 th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 21-23 July 2008, Hartford, CT 8