Date of Award
2015
Document Type
Thesis
Degree Name
Master of Science in Engineering (MSE)
Department
Mechanical and Aerospace Engineering
Committee Chair
Robert A. Frederick, Jr.
Committee Member
David Lineberry
Committee Member
Gabe Xu
Subject(s)
Hybrid propellant rockets., Rocket engines--Combustion.
Abstract
Hybrid rocket motors suffer from low regression rates when compared to traditional solid rocket motors. This work investigates the regression rate of a mixed oxidizer hybrid motor using a fuel-rich solid grain with and without gaseous oxygen as an oxidizer. The approach consisted of static testing of 15 motors to determine average pressures and regression rates. Ballistic analysis used an optimization sequence to determine a regression rate model using a linear combination of solid and hybrid models. Average regression rates were observed from 0.083 to 0.213 in/s, and predicted at a range from 0.102 to 0.222 in/s with good agreement between the test and ballistic analysis results. The pressure exponents calculated were 0.531 from test data and 0.585 from the ballistic analysis. The calculated oxidizer flux exponent was 2.85 for the tests investigated. Combustion instabilities were observed during hybrid testing.
Recommended Citation
Mascaro, Michael D., "Regression rate determination of a gas generator hybrid rocket motor with GOX" (2015). Theses. 151.
https://louis.uah.edu/uah-theses/151