Date of Award
2021
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
Jason T. Cassibry
Subject(s)
Rockets (Aeronautics)--Ramjet engines, Solid propellant rockets--Combustion
Abstract
This research develops a methodology for quantifying the uncertainties in key experimentally determined performance parameters for two solid fuel ramjet propellants in a connected pipe ramjet using the Monte Carlo Method. The performance parameters include characteristic velocity, characteristic velocity efficiency, thrust, specific impulse, and vacuum specific impulse. The burning rate equations and their uncertainty intervals were also calculated. Burning rate equations were constructed with terms in air flux and air temperature. The uncertainty intervals were found to be 4% - 5.1% at the test points. The burning rates were found to be accurate within ± 7.7%. Uncertainties in the performance parameters ranged from 16% - 37%. The dominant uncertainties were the nozzle throat diameter, which was affected by slag, and the combustor pressure. Recommendations for test procedures could lower uncertainty by up to 64% for the nozzle and by up to 45% for the combustor pressure.
Recommended Citation
Hankins, William Jarrett, "Assessment of performance parameter uncertainty of a solid fuel ramjet" (2021). Theses. 360.
https://louis.uah.edu/uah-theses/360