Accession Number : AD0753835

Title :   Non-Steady Combustion of Solid Propellants,

Corporate Author : PRINCETON UNIV N J DEPT OF AEROSPACE AND MECHANICAL SCIENCES

Personal Author(s) : Battista,R. A. ; Caveny,L. H. ; Summerfield,M.

Report Date : OCT 1972

Pagination or Media Count : 112

Abstract : Solid rocket performance during rapid pressure excursions differs greatly from predictions based on steady-state burning rate data. Rapid pressurization (150 to 250 kpsi/sec) following a sudden throat area decrease in a low L star combustor produces pressure overshoots of 10% and indicated burning rate overshoots in excess of 50%. A transient internal ballistics model was developed incorporating nonsteady continuity and energy equations for the chamber, nonsteady energy equation for the propellant condensed phase, and a modified Zeldovich heat feedback function for the propellant (which for the conditions considered is known to burn a thin quasi-steady reaction zone). Sensitivity analyses using the model indicate that accurate surface temperature and temperature sensitivity data are needed. (Author)

Descriptors :   (*SOLID ROCKET PROPELLANTS, *COMBUSTION), SOLID PROPELLANT ROCKET ENGINES, ROCKET NOZZLES, NOZZLE AREA RATIO, ROCKET PROPELLANT GRAINS, VARIABLE AREA NOZZLES, BURNING RATE, PYROLYSIS, MATHEMATICAL MODELS, COMPUTER PROGRAMS, INTERIOR BALLISTICS

Subject Categories : Combustion and Ignition
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE