Solid Propellant Combustion Gas Analysis Using a Micromotor Technique.
Final rept. Jan-Jun 68,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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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
- Combustion and Ignition