Combustion Transients of Solid Propellants.
UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING
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The report is largely a restatement of conclusions, with reference to previous publications for details. The areas of study reported are an evaluation of the hot-wire-ignition method for characterizing propellants the development and study of a gas-fueled analog of the solid-propellant T-burner a study of low frequency L combustion of L during a test a study of high frequency acoustic instability of solid propellants, both a T-burner and a radial-mode, radial-flow burner being used with the same propellants systems the development and evaluation of a technique for measuring the solid-propellant response function to external energy perturbations at the burning surface the measurement and evaluation of transient temperatures of propellant flames during rapid depressurization and a detailed characterization of the low-pressure-combustion phenomena for several different solid propellants including studies of the low-pressure deflagration limit, the electrical conductance near the surface, the extinguishment requirements, and spontaneous reignition. Author Modified Abstract
- Combustion and Ignition
- Solid Rocket Propellants