The Effect of Oxidizer Particle Size Distribution on the Steady and Nonsteady Combustion of Composite Propellants.
PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING
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A theoretical analysis of the combustion of composite propellants with an emphasis on the heterogeneous effects is presented. The analysis based on the combination of a unique statistical treatment of the burning surface with a very comprehensive multiple flame type of physiochemical model for the combustion process. The analysis is divided into four parts the steady state burning rate, erosive burning rate, the pressure coupled response, and the velocity coupled response.
- Combustion and Ignition
- Solid Rocket Propellants