1. 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

2. 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

3. 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
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

4. 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

5. 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

6. Book, E., and Bratman, H., "Using Compilers to Build Compilers," Systems Development Corp., SP-176, Santa Monica, CA, Aug
Gnoffo, P. A., "An Upwind-Biased, Point-Implicit Relaxation Algorithm for Viscous, Compressible Perfect-Gas Flows," NASA TP-2953, Feb
Book, E., and Bratman, H., "Using Compilers to Build Compilers," Systems Development Corp., SP-176, Santa Monica, CA, Aug
Gnoffo, P. A., "An Upwind-Biased, Point-Implicit Relaxation Algorithm for Viscous, Compressible Perfect-Gas Flows," NASA TP-2953, Feb
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
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
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