Abstract
A mathematical model has been developed for accurately predicting the interstage pressuretime transient that exists during the separation of two stages of a solid-propellant rocket system. The system of equations, composed of mass, energy, and force balances for the rocket chamber and interstage region, is solved simultaneously to yield predictions of the time dependence of chamber temperature and pressure together with interstage pressure, temperature, and volume. Sample calculations and prediction-results for a typical multistage rocket system are included.
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