Abstract
Far-range orbital maneuver is an important on-orbit operations phase during which TT&C provides measurement and tracking of both the servicer and customer until the former gets close to the latter. Then the servicer sensor captures the customer, which marks the beginning of proximity relative motion phase. Trajectory planning of far-range orbital maneuver is to optimize the orbital maneuver for the servicer under the constraints of time, fuel, and observation and control. The investigation on orbital maneuver generally employs impulse thrust method and finite continuous thrust method. Considering the advantage of the former in simplifying the problem and producing approximate results in preliminary design and demonstration, this chapter is mainly based on impulse thrust. On the basis of Lambert solution, the algorithms of GA and randomized A* tree expansion are adopted to address the multi-impulse orbital maneuver optimization problem respectively.
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