Accession Number:

AD0753835

Title:

Non-Steady Combustion of Solid Propellants,

Descriptive Note:

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:

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

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