Abstract
The synthesis of automatic controls for rocket engine systems requires information concerning the open loop frequency and transient response of such systems. This paper is concerned with the formulation of a mathematical model of a rocket engine system and the simulation of this model on an analog computer. Perturbation equations and computer circuit are developed for a pump-fed bipropellant system with turbine throttle valve area as the input variable. The frequency response of a typical system and the use of the computer model for estimating the effects of variations in the dimensions of interacting components on the frequency response are discussed.
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