Accession Number : AD0723680

Title :   Combustion Termination of Solid Propellant Motors.

Descriptive Note : Interim rept.,

Corporate Author : BRIGHAM YOUNG UNIV PROVO UTAH DEPT OF CHEMICAL ENGINEERING

Personal Author(s) : Coates,R. L. ; Horton,M. D.

Report Date : APR 1971

Pagination or Media Count : 59

Abstract : An extensive analysis has been made of published characteristic chamber length instability data using a linearized form of the model. The steady-state burning rate exponent has been shown to be the most sensitive propellant parameter governing marginal stability conditions. Data for different propellants have been quantitatively compared with theoretically predicted marginal stability conditions. Comparison between the predicted and measured characteristic chamber lengths and frequencies versus operating pressure was found to be relatively good, and it is encouraging to note that the kinetic parameters found to correlate the characteristic chamber length instability data are of the same order of magnitude as those previously found to correlate extinguishment data. A device for measuring the effect of external thermal radiation on steady-state burning rates has been designed, fabricated, and assembled. (Author)

Descriptors :   (*SOLID ROCKET PROPELLANTS, *COMBUSTION), (*SOLID PROPELLANT ROCKET ENGINES, INTERIOR BALLISTICS), MATHEMATICAL MODELS, COMBUSTION CHAMBERS, PROPELLANT BURN OUT, BURNING RATE, OSCILLATION, STABILITY, NOZZLE AREA RATIO

Subject Categories : Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE