Dana Lattibeaudiere March 27, 2008 Propulsion Code Outputs (Thanks Stephen Bluestone, John Beasley, Nicole Wilcox) Mass Deviations – Solids Project Logo.

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Presentation transcript:

Dana Lattibeaudiere March 27, 2008 Propulsion Code Outputs (Thanks Stephen Bluestone, John Beasley, Nicole Wilcox) Mass Deviations – Solids Project Logo (Thanks Steve Shurn, Jayme Zott, CJ Hiu, Stephen Bluestone, Jun Kanehara, Danielle Yaple, Amanda Briden) AAE 450 Spring 2008

Engine Performance Characteristics 200g Launch Vehicle Stage 1 Stage 2 Stage 3 Vacuum Thrust [N] 34,045 8,783 625.0 Mass Flow [kg/s] 10.69 2.738 0.1942 Burn time [s] 136.8 207.7 191.9 Propellant Mass [kg] 1,462 566.6 37.26 Exit Area [m^2] 0.5430 0.0400 0.0030 Exit Pressure [Pa] 2,821 11,454 Nozzle Length [m] 1.704 0.4645 0.1239 Engine mass [kg] 96.94 51.53 8.40 Pressure of ox, fuel tanks [MPa] 2.07 6.00 AAE 450 Spring 2008

Engine Performance Characteristics 1 kg Launch Vehicle Stage 1 Stage 2 Stage 3 Vacuum Thrust [N] 21,436 6,052 743.4 Mass Flow [kg/s] 6.730 1.880 0.2310 Burn time [s] 140.8 179.2 195.3 Propellant Mass [kg] 947.9 336.9 45.09 Exit Area [m^2] 0.3422 0.0278 0.00340 Exit Pressure [Pa] 2,821 11,454 Nozzle Length [m] 1.352 0.3856 0.1352 Engine mass [kg] 72.62 36.44 9.534 Pressure of ox, fuel tanks [MPa] 2.07 6.00 AAE 450 Spring 2008

Engine Performance Characteristics 5 kg Launch Vehicle Stage 1 Stage 2 Stage 3 Vacuum Thrust [N] 75,073 15,257 692.4 Mass Flow [kg/s] 23.57 4.74 0.22 Burn time [s] 174.9 213.0 178.4 Propellant Mass [kg] 4,123 1,009 38.37 Exit Area [m^2] 1.198 0.0700 0.0030 Exit Pressure [Pa] 2,821 11,454 Nozzle Length [m] 2.530 0.6122 0.1304 Engine mass [kg] 193.5 75.72 8.560 Pressure of ox, fuel tanks [MPa] 2.07 6.00 AAE 450 Spring 2008

Standard Deviations Propellant Weight Variations Burning Rate Can range from 0.08 – 0.12% Recommended: 0.12% Burning Rate Difficult to experimentally determine Thermochemical and combustion processes Temperature and erosion Recommended: 1% AAE 450 Spring 2008 <2> 5

Book, E., and Bratman, H., "Using Compilers to Build Compilers," Systems Development Corp., SP-176, Santa Monica, CA, Aug. 1960. Gnoffo, P. A., "An Upwind-Biased, Point-Implicit Relaxation Algorithm for Viscous, Compressible Perfect-Gas Flows," NASA TP-2953, Feb. 1990. Book, E., and Bratman, H., "Using Compilers to Build Compilers," Systems Development Corp., SP-176, Santa Monica, CA, Aug. 1960. Gnoffo, P. A., "An Upwind-Biased, Point-Implicit Relaxation Algorithm for Viscous, Compressible Perfect-Gas Flows," NASA TP-2953, Feb. 1990. References Heister, S., D., Davis, R., J., “Predicting Burning Time Variations in Solid Rocket Motors,” Journal of Propulsion and Power, Vol. 8, No. 3, 1992, pp. 564-565. Humble, R. W., Henry, G. N., Larson, W. J., “Solid Rocket Motors,” Space Propulsion Analysis and Design, 1st ed., Vol. 1, McGraw-Hill, New York, NY, 1995, pp. 327-331. Sutton, G., P., “Solid Propellant Rocket Fundamentals,” Rocket Propulsion Elements, 7th ed., Vol. 1, Wiley, New York, NY, 2001, pp. 434. Tsohas, John, AAE 450 class, Purdue University, West Lafayette, IN, 2/18/08. AAE 450 Spring 2008