Command method for thrust reduction and/or thrust termination of rocket motor project Shavetail was demonstrated in flight by Jet Propulsion Laboratory; investigation of time-acceleration relationship of payload after motor separation, as function of effective orifice opening of thrust termination and pressure variation with time; analytical model and equations to predict parameters; capability for velocity control of payload is outlined; results are compared with flight-test data on axial acceleration of payload during thrust termination of Shavetail system.
Payload separation and thrust termination in solid-propellant rocket motor
Aerospace Eng
Aerospace Engineering ; 21 , n 5
1962
6 pages
Article (Journal)
English
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