Title
College - Author 1
College of Engineering
Department - Author 1
Aerospace Engineering Department
Degree Name - Author 1
BS in Aerospace Engineering
Date
6-2010
Primary Advisor
Dianne DeTurris, College of Engineering, Aerospace Engineering Department
Abstract/Summary
This project involves the re-design, manufacturing, and testing of the Cal Poly Space System’s 4th iteration of an M-class 98mm hybrid rocket motor. This motor utilizes hydroxyl-terminated polybutadiene as fuel with liquid nitrous oxide as the oxidizer. Modeling and analysis was conducted on a 12 port self-impinging swirl injector and fuel manufacturing to improve performance. Several hot and cold flow tests were conducted to validate the analysis and predict performance values. Test results included two test fires resulting in an average of 212 lbf of thrust for 6 seconds with an Isp of 160 seconds and an average thrust of 260 lbf of thrust for 6 seconds with an Isp of 200 seconds. Analytical models predicted a thrust of 225 lbf for 6 seconds with an Isp of 180 seconds.
URL: https://digitalcommons.calpoly.edu/aerosp/22
Included in
Aerodynamics and Fluid Mechanics Commons, Propulsion and Power Commons, Systems Engineering and Multidisciplinary Design Optimization Commons