Paper shows that upper limit exists for increase in nozzle area necessary to bring about combustion termination in rocket motor; two different criteria have been shown to govern required area change, namely, critical depressurization rate, and critical pressure, which is dependent on ratio of motor free volume to throat area free chamber/throat area; upper limit is consequence of steady-state mass conservation in chamber and is independent of either depressurization rate or free chamber/throat area criterion; data to support argument are presented.
Design procedures for combustion termination by nozzle area variation
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 3
1966
7 pages
Article (Journal)
English
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