Accession Number:

AD0735381

Title:

Micro-Rocket Impulsive Thrusters

Descriptive Note:

Final rept.

Corporate Author:

PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES

Report Date:

1971-11-01

Pagination or Media Count:

117.0

Abstract:

Light weight solid propellant motors which supply high thrusts greater than 500 lbf for durations on the order 0.010 sec. referred to as impulsive thrusters require special analysis of items such as internal ballistics, propellant combustion, ignition stimuli, exhaust plume envelope, and inert hardware. A survey of the rocket motor concepts revealed that the desired thrust versus time program can be achieved by internal burning grains and existing high burning rate composite propellants. The mathematical model for transient internal ballistics developed during the study can be applied to a wide range of high preformance rocket motors which experience rapid ignition and pressurization transients.

Subject Categories:

  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE