Mathematical model is developed for accurately predicting interstage pressure time transient that exists during separation of 2 stages of solid propellant rocket system; system of equations, composed of mass, energy, and force balances for rocket chamber and interstage region, is solved simultaneously to yield predictions of time dependence of chamber temperature and pressure together with interstage pressure, temperature, and volume; sample calculations and prediction results for multistage rocket system.
Prediction of interstage pressure in multistage solid-propellant rocket systems
AIAA J
AIAA Journal ; 1 , n 10
1963
5 pages
Aufsatz (Zeitschrift)
Englisch
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