ABSTRACT

We consider the problem about realization interorbital transfer by spacecraft with propulsion of low thrust in central Newtonian field with maximal actual load. Traditional subdivision of the mentioned problem into parametric and dynamic parts results in various variational problems for controllable and uncontrollable propulsors. For comparison of efficiency of propulsors with constant and controllable thrust we determine dependence of delivered actual load on a complex parameter, which is defined by parameters of propulsor and characteristic velocity of maneuver or transfer with constant thrust during minimal time. It was shown that if electric rocket propulsion with cruise engine of space tug, which is intended for multiplex realization of regular transport operations with relatively large actual loads, then use of constructively more complicated controllable engines is unpractical.