The focus of this research is on the understanding and prediction of solid rocket propellant burn rates under various pressures. The experimental apparatus consists of a high-pressure Crawford burning chamber for which individual propellant strands are ignited and burn rates measured using high speed video and thermocouples. The goal of these activities is to compare measurements of burn-rates, temperature and flame structure to mathematical modeling.
Student Skill-Set Needed: junior or senior in MAE or equivalent level of classes
Compensation: Academic Credit
For further information on this opportunity, or to apply, contact:
Faculty Member: Paul E DesJardin
Department: Mechanical And Aerospace Engineering
Office: 318 Jarvis Hall