Optimization of the Proportional Navigation Law with Time Delay
The controlled relative motion of a spacecraft nearby an orbital station is considered. A rendezvous method used on active spacecraft is an algorithm of proportional navigation which is realized with some constant time delay.
The coefficient of the guidance law is considered as a control variable. The problem of choice of the mentioned coefficient which provides minimizing of rendezvous time, is analyzed. It is found that the optimal solution includes regular and singular control values both. The results of computer simulation are given.