An Experimental Investigation of the Burning Rate of Propellant ANB 3066 under Oscillatory Pressure and Oscillatory Velocity Conditions.
Final scientific rept. Jun 72-Jun 73,
ROCKET PROPULSION ESTABLISHMENT WESTCOTT (ENGLAND)
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A program of work was conducted in order to measure the effects of oscillatory pressure and velocity at a frequency of 800 Hz upon the burning rate of ANB 3066. The burning rate was measured using a microwave interferometer method and also calculated from the pressuretime records of T-burner and KT-motor firings. An empirical relationship was derived which describes the burning rate under oscillatory and non-oscillatory conditions in terms of the average Mach number, the oscillatory pressure and the mean pressure at the propellant surface. Author
- Combustion and Ignition
- Solid Rocket Propellants