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Dana Lattibeaudiere February 7, 2008 New Code Developments. New Code: ma_thrust.m. More outputs: => Structures nozzle diameters/lengths, engine masses, pressures of oxidizer and fuel tanks, fuel and oxidizer mass flows Assumptions: Theoretical hybrid engine Pc estimated
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Dana LattibeaudiereFebruary 7, 2008New Code Developments AAE 450 Spring 2008
New Code: ma_thrust.m • More outputs: => Structures • nozzle diameters/lengths, engine masses, pressures of oxidizer and fuel tanks, fuel and oxidizer mass flows • Assumptions: • Theoretical hybrid engine • Pc estimated • Conical shaped nozzles, 12 deg • Tank Pressure: no P_dynamic, P_throttle AAE 450 Spring 2008
Sample Output: • Tvac = 44.48 kN • Nozzle Diameter = 2.016 m • Engine mass = 43.84 kg • Nozzle length = 4.387 m • Pressure fuel = Pressure Ox = 1.73E6 Pa Future Work • Integrate code • CAD AAE 450 Spring 2008 Propulsion
Backup Slides AAE 450 Spring 2008 Propulsion
References • Humble, R. W., Henry, G. N., Larson, W. J., “Liquid Rocket Propulsion Systems,” Space Propulsion Analysis and Design, 1st ed., Vol. 1, McGraw-Hill, New York, NY, 1995, pp. 206-211, pp. 216-217, pp. 224. • Humble, R. W., Henry, G. N., Larson, W. J., “Hybrid Rocket Propulsion Systems,” Space Propulsion Analysis and Design, 1st ed., Vol. 1, McGraw-Hill, New York, NY, 1995, pp. 426-431. AAE 450 Spring 2008
Humble, R. W., Henry, G. N., Larson, W. J., “Appendix B: Thermochemical Data for Selected Propellants,” Space Propulsion Analysis and Design, 1st ed., Vol. 1, McGraw-Hill, New York, NY, 1995, pp. 701-702, pp. 705-706, pp 711-712. • Lara, Michael R., “Star 37XFP,” ATK Tactical Propulsion and Controls Division., Elkton, MD, Apr. 2007. AAE 450 Spring 2008
Mingchu, Gu, and Guoqiu, Liu, “The Oxygen/Hydrogen Rocket Engine For Long March Vehicle," AIAA Paper 95-2838, Jul. 1995. • Sutton, George P., Biblarz, Oscar, Rocket Propulsion Elements, 7th ed., Wiley, New York, NY, 2001. • Wade, Mark., “RD-161-1,” 1997-2007.[http://www.astronautix.com/engines/rd1611.htm. Accessed 1/22/08.] AAE 450 Spring 2008