Solid Propellant Combustion Modeling.
ROCKWELL INTERNATIONAL CORP MCGREGOR TEX ROCKETDYNE DIV
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The report covers the first 15 months of a continuing study on construction of a comprehensive mathematical model of composite solid propellant combustion, with emphasis on work during the past 12 months since reporting on the early efforts at the meeting last year. The liquid layer believed to exist on burning ammonium perchlorate has been treated in a manner similar to that described previously. Depth of penetration of a thermal wave is calculated and this value is multiplied by the surface area of oxidizer on the burning propellant surface. The surface is calculated in the computer program for use in other equations. Total volume of the liquid layer derived in this manner is then used to calculate the thermal contribution to surface temperature. Modified author abstract
- Combustion and Ignition
- Solid Rocket Propellants