Accession Number : AD0851089
Title : Solid Propellant Combustion Gas Analysis Using a Micromotor Technique.
Descriptive Note : Final rept. Jan-Jun 68,
Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Personal Author(s) : Goshgarian, Berge B.
Report Date : MAR 1969
Pagination or Media Count : 20
Abstract : A system to provide analytical data on solid propellant combustion exhaust gases immediately after combustion is described. The system features a micromotor exhausting into a controlled-atmosphere chamber, a differentially pumped sampling system, and a high-resolution mass spectrograph for exhaust gas analysis. Concentrations of the gaseous combustion products such as NH3, HCl, and H2O decay on standing in the sampling chamber because of gas-phase reactions forming solids and gas reacting with or absorbing on the chamber walls. The experimental exhaust composition, determined within 30 seconds of propellant combustion, compares favorably with the thermodynamically predicted composition. The discharge of fuel-rich exhaust gases into air was found to result in a decrease of HCl with increasing time. (Author)
Descriptors : *EXHAUST GASES), (*SOLID ROCKET PROPELLANTS, (*COMBUSTION PRODUCTS, CHEMICAL ANALYSIS), CONTROLLED ATMOSPHERES, MASS SPECTROSCOPY, AMMONIA, WATER, HYDROCHLORIC ACID, GAS ANALYSIS.
Subject Categories : Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE