The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
Solid propellant rocket motor
1973-05-01
Sonstige
Keine Angabe
Englisch
NTIS | 1973
|NTIS | 1971
|Steerable Solid Propellant Rocket Motor
NTIS | 1964
|Miniature solid propellant rocket motor
NTIS | 1997
|A miniature solid propellant rocket motor
AIAA | 1997
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