Research on Solid Propellant Combustion Instability
Quarterly progress rept. no. 3, 1 Nov-31 Jan 1962
PRINCETON UNIV NJ GUGGENHEIM AEROSPACE PROPULSION LABS
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A fundamental study of the non-steady combustion of solid propellants with application to rocket instability is described. A polybutadieneacrylic acid composite propellant containing 80 ammonium perchlorate and 2 copper chromite has been developed for use in conjunction with an oscillator-driver described previously. The operating characteristics of the oscillator system including the propellant and the motor have been defined over a useful operating range. Windows for the observation of processes within the motor have been tested but were found to become obscured too quickly. The system is currently being modified to correct this deficiency. An analysis of the decay of entropy waves in burnt gases produced in an oscillating pressure field indicates that the waves will persist for sufficient times to be observable.
- Combustion and Ignition
- Solid Rocket Propellants