Date of Award
2025
Document Type
Thesis
Degree Name
Master of Science (MS)
Department
Mechanical and Aerospace Engineering
Committee Chair
Robert Frederick
Committee Member
John Bennewitz
Committee Member
L. Dale Thomas
Research Advisor
Robert Frederick
Subject(s)
Solid propellants--Combustion, Ammonium perchlorate--Mechanical properties
Abstract
This thesis investigates the effect of ingredient variations on the burning rate of reduced smoke, low burning rate composite solid propellant. The effort focused on identical propellant formulations which presented significant burning rate differences correlated with the ammonium perchlorate (AP) source. A series of 1-gallon propellant mixes were prepared and tested utilizing both Manufacturer A and Manufacturer B ammonium perchlorate to investigate the propellant burning rate and pressure exponent shift anomaly and correlate those findings to the differing ingredient properties between the two AP lots. Each propellant mix was evaluated for burning rate utilizing subscale test motors and a scanning electron microscope characterized the raw AP and cast propellant surfaces. SEM images of the cast propellant surfaces showed cracking of the Manufacturer B AP indicating that the pressure exponent shift and burning rate increase observed could result from AP fracturing during propellant mixing.
Recommended Citation
Wallace, Erin Faith, "Ammonium perchlorate manufacturing effects on propellant burning rate" (2025). Theses. 779.
https://louis.uah.edu/uah-theses/779