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.

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