METHOD OF CONTROL OVER SPACECRAFT CONVERGENCE WITH ORBITAL OBJECT DURING LONG-RANGE GUIDANCE
Annotation
A method of control over spacecraft during its long-range convergence with orbital object is considered. Angular movement dynamics of the spacecraft with a jet engine rigidly fixed on its body is taken into account. The current control action is calculated with consideration for the influence of noncentral gravitational field, the piecewise continuous jet engine operation, and restrictions on characteristic velocity. Values of equivalent coplanar motion parameters of the spacecraft used for calculations are predicted for the time of passage of the opposite point of the line of apsides. Results of computer simulations are presented to confirm the efficiency of the algorithms developed using the proposed method.
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