Algorithm for Controlling a Spacecraft’s Engine with Preventing the Angular Momentum Accumulation

Abstract

An algorithm for controlling a multinozzle engine of a spacecraft operating in the cycle mode that makes it possible to vary the engine’s operation time and thrust in a wide range while accurately maintaining the desired mean thrust is presented. The results of simulation for an axial propulsion unit of the spacecraft consisting of four engines with the identical nominal thrust are presented. The application of the proposed algorithm for the propulsion unit arrangement indicated above makes it possible to prevent the accumulation of angular momentum about all three central axes of inertia of the vehicle simultaneously with producing a correction impulse, while maintaining the given mean thrust. A control algorithm is outlined and specific features of using the improved mathematical model of the engine’s operation in the cycle mode are described.