INVESTIGATION OF A TERMINAL GUIDANCE SYSTEM FOR A SATELLITE RENDEZVOUS

A guidance scheme for the terminal phase of a satellite rendezvous operation is presented. The terminal phase is that part of the rendezvous operation during which the final velocity and position corrections are made, exclusive of the actual contact maneuvers. The initial relative position and velocity between the space vehicle and the satellite are assumed to result from the normal dispersion during powered phase and orbit injection of an inertially guided ballistic rocket launched from the earth. The analysis is based on a nominal maximum initial separation of 5000 m and a maximum relative velocity of 50 m/sec in an arbitrary direction. Thrust acceleration levels well above the tidal acceleration level are assumed. This permits the problem to be reduced to a free space case, with tidal acceleration entering as a relatively small perturbation. A relative coordinate system is used in the analysis. Guidance equations for an exponential type of homing are developed. This, of course, implies that variable thrust rocket motors are employed. The response, propellant consumption, and effects of tidal acceleration are presented in graphical form.