A command method for thrust reduction and/or thrust termination of a solid-propellant rocket motor-called project Shavetail-was demonstrated successfully in flight by Jet Propulsion Laboratory. Thrust reduction is achieved by the separation of a portion of the nozzle to increase the throat area. The chamber pressure is lowered and motor continues to burn at a vernier level of thrust. At any time before motor burnout, upon command from guidance, thrust cancellation and motor separation from the payload are achieved by opening an orifice in the head end of the motor.
Payload Separation and Thrust Termination in A Solid-Propellant Rocket Motor
Institute of the Aerospace Sciences ; 21 , 5
1962-07-01
Miscellaneous
No indication
English
Payload separation and thrust termination in solid-propellant rocket motor
Engineering Index Backfile | 1962
|TECHNICAL NOTES - Thrust Termination Dynamics of Solid Propellant Rocket Motors
Online Contents | 2007
|Electrically operated propellant for solid rocket motor thrust management
European Patent Office | 2020
|