Dana Lattibeaudiere March 27 2008 Propulsion Code Outputs

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 200 g Launch Vehicle Stage 1 Vacuum Thrust [N] Mass Flow [kg/s] Burn time [s] Propellant Mass [kg] Exit Area [m^2] Exit Pressure [Pa] Nozzle Length [m] Engine mass [kg] Pressure of ox, fuel tanks [MPa] Stage 2 Stage 3 34, 045 10. 69 136. 8 1, 462 0. 5430 8, 783 2. 738 207. 7 566. 6 0. 0400 625. 0 0. 1942 191. 9 37. 26 0. 0030 2, 821 1. 704 96. 94 11, 454 0. 4645 51. 53 11, 454 0. 1239 8. 40 2. 07 6. 00 AAE 450 Spring 2008

Engine Performance Characteristics 1 kg Launch Vehicle Vacuum Thrust [N] Mass Flow [kg/s] Burn time [s] Propellant Mass [kg] Exit Area [m^2] Stage 1 Stage 2 Stage 3 21, 436 6. 730 140. 8 947. 9 0. 3422 6, 052 1. 880 179. 2 336. 9 0. 0278 743. 4 0. 2310 195. 3 45. 09 0. 00340 2, 821 1. 352 72. 62 2. 07 11, 454 0. 3856 36. 44 6. 00 11, 454 0. 1352 9. 534 6. 00 Exit Pressure [Pa] Nozzle Length [m] Engine mass [kg] Pressure of ox, fuel tanks [MPa] AAE 450 Spring 2008

Engine Performance Characteristics 5 kg Launch Vehicle Stage 1 Stage 2 Stage 3 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 2. 07 6. 00 Vacuum Thrust [N] Pressure of ox, fuel tanks [MPa] AAE 450 Spring 2008

Standard Deviations § Propellant Weight Variations – 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>

Gnoffo, P. A. , "An Upwind-Biased, Point-Implicit Relaxation Algorithm for Viscous, Co References § Heister, S. , Davis, R. , J. , “Predicting Burning Time Variations in Solid Rocket Motors, ” Journal of Propulsion and Power, Vol. 8, No. 3, 1992, pp. 564565. § Humble, R. W. , Henry, G. N. , Larson, W. J. , “Solid Rocket Motors, ” Space Propulsion Analysis and Design, 1 st ed. , Vol. 1, Mc. Graw-Hill, New York, NY, 1995, pp. 327 -331. § Sutton, G. , P. , “Solid Propellant Rocket Fundamentals, ” Rocket Propulsion Elements, 7 th 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