1 AAE 450 Spring 2008 Stephen Bluestone March 20, 2008 Propulsion Final Presentation Slides 1

2 Engine Sizing  The amount of propellant required for each rocket/stage was determined in Model Analysis  Inert mass fraction, f inert, was optimized between the structures and propulsion groups for final design

3 Engine Cost  Cost of Engines calculated from equations based on mass flow, thrust, and dry weight  Cost equations are extrapolated from historical values Payload1 st Stage Engine Cost 2 nd Stage Engine Cost 3 rd Stage Engine Cost Total Engine Cost 200g$679,720$263,690$79,930$1,023,340 1kg$634,090$209,930$86,860$930,880 5kg$1,138,700$339,700$80,900$1,559,300

4 Historical Failure Probability  U.S. Solid Rocket Systems (Failures/Attempts) –6 / 412 (1.4%) Failures between –19 / 3382 (0.56%) Failures between  Solid Propulsion Failure Rates (Failures/Attempts) –Upper Stage /10000 –Monolithic /10000 –Segmented /10000 –Total /10000 AAE 450 Spring 2008 Propulsion – Propellants

5 Catastrophic Failure  Historically Solid Rocket failure results in catastrophic failure 37% of the time (19 solid failures, 7 were catastrophic) [ ] 1  Solid Rocket Failure Rate (Failures/Attempts) –Failure , 56/10000 –Catastrophic Failure ,21/10000 AAE 450 Spring 2008 Propulsion - Propellants

6 References  Nieroski, John S., and Friedland, Edward I., “Liquid Rocket Engine Cost Estimating Relationships,” AIAA Paper , July  Humble, Ronald W., Henry, Gary N., Larson, Wiley J. “Hybrid Rocket Propulsion Systems,” Space Propulsion Analysis and Design, 1 st ed. revised, Primis, New York, 1995  Chang, I-Shih., Tomei, Edmardo Joe., “Solid Rocket Failures in World Space Launches.” AIAA Paper , Joint Propulsion Conference and Exhibit, 41st, Tuscon, Az, July 10-13, 2005  Sauvageu, Donald R., Allen, Brian D., “Launch Vehicle Historical Reliability.” AIAA AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 34th, Cleveland, OH, July 13-15, 1998