RESPONSE OF A BURNING PROPELLANT SURFACE TO EROSIVE TRANSIENTS.
Quarterly rept. no. 7, 1 Jul-30 Sep 67,
STANFORD RESEARCH INST MENLO PARK CALIF
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The formulation of an analytical model has been initiated, to clarify the gasdynamical mechanism by which the combustion mechanism, responding to pressure pulses induced by traveling shock waves in the chamber, interacts with the shock waves to produce combustion instability. The approach taken in this analysis is similar to that used to study the behavior of shock waves in shock tubes it differs in that it employs a modified surface boundary condition that accounts for the mass added by the combustion process. The nonlinear equations that describe the combustion model were programmed for numerical solution. The program will be used to predict the burning rate response of the combustion mechanism to steep-fronted pressure waves this calculation will provide the proper boundary conditions for the gasdynamical studies. Author
- Combustion and Ignition
- Solid Rocket Propellants