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Accession Number:
AD0753835
Title:
Non-Steady Combustion of Solid Propellants,
Descriptive Note:
Corporate Author:
PRINCETON UNIV N J DEPT OF AEROSPACE AND MECHANICAL SCIENCES
Report Date:
1972-10-01
Pagination or Media Count:
112.0
Abstract:
Solid rocket performance during rapid pressure excursions differs greatly from predictions based on steady-state burning rate data. Rapid pressurization 150 to 250 kpsisec 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
Distribution Statement:
APPROVED FOR PUBLIC RELEASE