基于STK/X的远程导引变轨方案修正

Correction of Orbital Transfer Scheme of Long-distance Guidance Based on STK/X

远程导引多脉冲式变轨方案一般基于二体模型进行设计,设计结果存在摄动模型误差。当飞行时间较长时,由摄动模型误差带来的交会误差会达到上百公里甚至上千公里的量级,从而在实际摄动条件下难以实现追踪航天器和目标航天器的交会。采用L-BFGS-B优化算法,对初始的设计结果进行修正,以达到消除摄动模型误差的目的。优化过程中需要的真实摄动模型下的轨道预报,使用STK/X技术通过调用STK/Astrogator模块进行仿真得到。算例表明,初始设计的多脉冲式变轨方案经过修正后,能够在实际摄动条件下实现追踪航天器和目标航天器的交会。

Impulse transfer scheme of long - distance guidance is usually designed by using two - body model, but perturbation model error exists in the design result. When flight time is long, the rendezvous error caused by perturbation model error may reach hundreds of kilometers or thousands of kilometers, so the pursuit spacecraft is difficult to rendezvous with target spacecraft when under real perturbation conditions. By using L - BFGS - B optimal algorithm to correct the initial design result, the perturbation model error is eliminated. The spacecraft＇s ephemeris under real perturbation model used in optimization process is obtained by simulation using STK/Astrogator module via STK/X technology. Calculation case shows that the corrected transfer scheme can implement pursait spacecraft＇s rendezvous with target spacecraft under real perturbation conditions.