Accession Number : AD0850965
Title : Ignition and Combustion of Solid Propellants.
Descriptive Note : Final rept. 1 Oct 67-30 Sep 68,
Corporate Author : UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING
Personal Author(s) : Baer, Alva D. ; Ryan, Norman W.
Report Date : 30 SEP 1968
Pagination or Media Count : 46
Abstract : The results are presented from a study of the ignition response of composite propellants to convective heat fluxes from high and low temperature gases. For gas temperatures below about 750C, the convective ignition data were in excellent agreement with results from thermal radiation tests. At higher convective gas temperatures, the ignition times were uniformly about 0.8 of the radiation and low-gas-temperature ignition times. It is postulated that feedback of energy or reactive species occurs from the hot gas in the thin convective boundary layers for the high temperature gas. Tests in which blackened composite propellant samples were ignited by radiant energy fluxes, ambient atmosphere being room-temperature air or air at 800-1350C, indicated no effect of the gas temperature on the time to first-flame. (Author)
Descriptors : (*SOLID ROCKET PROPELLANTS, COMBUSTION), (*COMPOSITE PROPELLANTS, IGNITION), CONVECTION(HEAT TRANSFER), HEAT OF COMBUSTION, HEAT FLUX, REACTION KINETICS, BURNING RATE, THERMAL CONDUCTIVITY.
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE