The invention relates to a spacecraft pulse maneuver optimization method considering collision avoidance, in particular to a spacecraft pulse maneuver optimization method considering collision avoidance. The invention belongs to the field of satellite orbit control. The objective of the invention is to solve the problem that the time for solving the optimal collision avoidance pulse of the spacecraft fuel by the existing method is long. The method comprises the following steps: step 1, based on a reachable domain envelope model, constructing a monopulse collision avoidance problem optimization model with fixed pulse time; step 2, based on the optimization model in the step 1, solving the minimum pulse of the spacecraft at a given collision avoidance moment by using a Newton iteration method; and step 3, carrying out one-dimensional search on the collision avoidance time in the step 2 to obtain the optimal collision avoidance time, and obtaining a minimum pulse with free collision avoidance time based on the optimal collision avoidance time.
一种考虑碰撞规避的航天器脉冲机动优化方法,本发明涉及考虑碰撞规避的航天器脉冲机动优化方法。本发明属于卫星轨道控制领域。本发明的目的是为了解决现有方法求解航天器燃料最优的碰撞规避脉冲时间较长的问题。过程为:步骤一、基于可达域包络模型,构建脉冲时间固定的单脉冲碰撞规避问题优化模型;步骤二、基于步骤一的优化模型,利用牛顿迭代方法求解给定避碰时刻下航天器最小脉冲;步骤三、对步骤二中的避碰时刻进行一维搜索,得到最优避碰时间,基于最优避碰时间得到避碰时间自由的最小脉冲。
Spacecraft pulse maneuver optimization method considering collision avoidance
一种考虑碰撞规避的航天器脉冲机动优化方法
2024-10-11
Patent
Electronic Resource
Chinese
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