IGNITION AND COMBUSTION OF SOLID PROPELLANTS
Technical rept. 1 Oct 1961-30 Sep 1962
UTAH UNIV SALT LAKE CITY
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The response of several selected composite propellants subjected to surface heat fluxes was experimentally studied. The surface propellant samples were subjected to thermal-radiation heat fluxes from 1 to 13.5 calsec sq cm and convective heat fluxes from 30 to 100 calsec sq cm. Parallel theoretical studies, which were guided by the experimental results, have given a satisfactory explanation of the general character of the ignition process. The scope of this research work has been broadened to include several phases of the combustion of solid propellants.
- Electrical and Electronic Equipment
- Solid Rocket Propellants