SELECTION OF UNIVERSAL PARAMETERS FOR A LOW-THRUST ENGINE DESIGNED TO MAINTAIN THE ORBIT OF AN EARTH SATELLITE.

The problem is considered of selecting the basic design parameters for a low-thrust ion-plasma jet engine. The multiple-purpose design of the engine assembly and the multiple-regime nature of carrying out each correction are taken into account. The problem is solved on the basis of the theory of optimum coverage with allowance for uncertain factors which affect the required level of thrust and the propellant consumption in correcting the orbit. Results are shown for the calculation of universal parameters for an engine designed to maintain low orbits of artificial earth satellites.