远程导引变轨方案修正算法

Algorithm for Correcting Orbital Transfer Scheme of Long-Distance Guidance

为在实际摄动条件下由远程导引变轨方案初始设计结果实现追踪航天器与目标航天器的交会,提出了一种修正变轨方案。将初始多脉冲式变轨方案转换为有限推力式并作修正,取远程导引结束时刻追踪与目标航天器间的相对轨道要素为目标函数,采用J2,J3,J4解析轨道预报器对目标函数计算需要的轨道进行预报,以历次变轨开始时刻、结束时刻和推力方向为优化变量,用边界约束有限存储BFGS(L-BFGS-B)优化算法获得的最优解为修正后的变轨方案,可消除摄动模型误差。算例结果表明,经转换和修正所得有限推力式变轨方案能在实际摄动条件下实现追踪航天器与目标航天器的交会。

To implement the rendezvous between two spacecrafts by the initially designed scheme with long-distance guidance under real perturbation conditions, a modified orbital transfer scheme was put forward in this paper. The initial multi-impulse scheme was transformed into finite thrust scheme and was amended. The relative orbit elements between two spacecrafts at guidance finish time were served as object function. The orbit involving J2 ,J3 and J4 perturbation terms was propagated, which was used in the computation of the object function. The optimization variables were each beginning time, finish time and thrust direction. The optimal solution was obtained by using L-BFGS-B method so that the perturbation model error was corrected. The sample calculation showed that the corrected finite thrust scheme would realize tracing the spacecraft＇s rendezvous with target spacecraft under real perturbation conditions.