The Problem of Optimal Control of the Thrust Value of a Real Electro Rocket Engine

摘要

A study of the effectiveness of three methods for controlling the thrust value of the sustainer electric rocket engine (ERE) of an orbit-to-orbit transport vehicle is carried out. On board energy source for EPS is a solar battery. Two classical concepts of EPS with the adjustable and non adjustable thrust value and the engine with the adjustable piecewise-constant thrust are compared. On the examples of interorbital transfers, interesting from a practical point of view, it is confirmed in the numerical experiment the possibility for the engine of the third type of such control regime, which not much differs by the effectiveness from the optimal control of the engine with the adjustable thrust and retains the simplicity of implementation of a control law, inherent in classic relay control of an unregulated engine with the possibility of multiple switching on.