IGNITION AND COMBUSTION OF SOLID PROPELLANTS
Final rept. 1 Oct 1965-30 Sep 1966
UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING
Pagination or Media Count:
A model for the ignition response of solid propellants is presented, which predicts ignition behavior with respect to pressure and surface heat flux in qualitative agreement with experimental measurements. Surface regression is treated and a steady-state burning model is employed, which assumes equlibrium vaporization at the surface and a regression rate limited by the feedback flux. A method is developed and discussed for the determination of the net heat of gasification of a burning propellant. The critical pressure ratio for extinction by instantaneous depressurization, which is required for this method, is obtained by use of a rarefaction tube. Summaries are presented of a study of the PBAA and PBAA-AP decomposition reactions and of the results of measurement of propellant surface temperature during the ignition transient by detection of infrared emission from the surface.
- Combustion and Ignition
- Solid Rocket Propellants