Class
Article
College
College of Engineering
Department
Mechanical and Aerospace Engineering Department
Faculty Mentor
Nick Roberts
Presentation Type
Poster Presentation
Abstract
Solid rocket propellant typically contains the geometry of an extruded annulus. This propellant, when ignited, burns radially at a rate called the “burn rate”. This rate dramatically affects important motor performance characteristics such as pressure, thrust, and specific impulse. Each different mixture of solid rocket propellant has a sensitivity to initial propellant temperature. The relationship between burn rate and initial temperature sensitivity function are each determined experimentally. This literature review will analyze existing experimental data. The objective of the research is to see if there is a reliable way to predict the burning rate’s temperature sensitivity prior to obtaining new experimental data.
Location
Logan, UT
Start Date
4-12-2023 2:30 PM
End Date
4-12-2023 3:30 PM
Included in
Understanding and Minimizing the Effects of Propellant Mean Bulk Temperature Changes in Solid Rocket Motors
Logan, UT
Solid rocket propellant typically contains the geometry of an extruded annulus. This propellant, when ignited, burns radially at a rate called the “burn rate”. This rate dramatically affects important motor performance characteristics such as pressure, thrust, and specific impulse. Each different mixture of solid rocket propellant has a sensitivity to initial propellant temperature. The relationship between burn rate and initial temperature sensitivity function are each determined experimentally. This literature review will analyze existing experimental data. The objective of the research is to see if there is a reliable way to predict the burning rate’s temperature sensitivity prior to obtaining new experimental data.