OPTIMIZATION OF CORRECTIVE SEQUENCES FOR INTERPLANETARY TERMINAL TRAJECTORIES
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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The effect an error velocity has on the hyper bolic transfer trajectory in the planets local gravity field is investigated. The number, direction, magnitude and position of the correction impses which optimally guide the spacecraft to a circular parking orbit is determined. The two approaches used are 1 a fixed and predetermined orbital radius 2 an allowable variation of orbital radii over a specified range. Forced geometric and dynamic programming correction sequences analyses are used. The results prove a geometrical correction sequence to be optimum. The corrective velocity sum is always less than 5 of the basic velocity sum.