Surface-Temperature Measurements of Solid Propellants During Ignition
Technical rept. Jun 1966-Jul 1967
UTAH UNIV SALT LAKE CITY DEPT OF CHEMICAL ENGINEERING
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Surface temperatures were measured on ammonium perchlorate propellants during ignition by convective heating by use of an infrared radiation sensor. This study was conducted in a shocktube apparatus, and air or nitrogen was used for heating the propellant samples. Heat fluxes were in the range of 30 to 80 calsq cmsec. Surface temperature histories measured on propellant samples with smooth blackened surfaces are in good agreement with predictions of a thermal ignition model that considers the key ignition reaction to be localized at the propellant surface. Surface roughness effects and sample transparency to thermal radiation result in difficulties in relating the infrared detector output to surface temperature.
- Combustion and Ignition
- Solid Rocket Propellants