Abstract
A design of experiments was conducted to explore the regression rate performance of aluminized hybrid rocket fuels in gaseous oxygen. Mass flux, pressure, diameter, and aluminum content were varied independently in a 2-level, full factorial, 16-run experiment design. The least important 4 tests were run first so that any adjustments could be made as the device became better characterized with this setup and these propellants. This resulted in an effective set of data over orthogonal parameter spaces that led to a model depending on the mass flux, the diameter, and the aluminum loading, while showing pressure to be of no effect.
Original language | English (US) |
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Title of host publication | 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 |
Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
ISBN (Print) | 9781624105111 |
State | Published - Jan 1 2017 |
Event | 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 - Atlanta, Georgia Duration: Jul 10 2017 → Jul 12 2017 |
Other
Other | 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017 |
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Country/Territory | Georgia |
City | Atlanta |
Period | 7/10/17 → 7/12/17 |
All Science Journal Classification (ASJC) codes
- General Engineering