中文摘要：

根据目标飞行器轨道高度和追踪飞行器入轨轨道高度,给出了目标飞行器交会对接轨道初始相位的设计方法。针对目标飞行器交会对接轨道控制要求,建立了共面相位计算模型以及轨道相位、高度和圆化度的多目标参数求解模型。基于定轨误差、轨道控制误差和轨道预报误差的调相时间分析,制定了目标飞行器调相控制策略。仿真计算表明,实现的目标飞行器交会对接轨道满足要求,验证了调相控制量优化原则的正确性,并对标称共面与虚拟共面的共面时刻和共面相位进行了比较。所提出的计算模型、控制策略和分析方法适用于目标飞行器交会对接轨道设计和控制实施。

英文摘要：

According to the target spacecraft′s orbit height and the chaser spacecraft′s orbit height,the design method of the target′s initial phase for the rendezvous orbit was presented.The mathematical models of the target′s rendezvous orbit control were established,which included the model of the coplanar phase and the model of the multi-objective parameters to solve the target′s orbit phase,height and eccentricity.Based on the target′s phasing time analysis of orbit determination error,orbit control error and orbit prediction error,the strategy of the target′s phasing orbit maneuver was developed.Simulation results indicate that the target′s rendezvous orbit is obtained to meet the requirements of the objective orbit and the optimization principles of phasing control delta-velocity is verified.Even the difference of the normal coplanar and the virtual coplanar is compared.The proposed model,control strategy and analysis methods are applicable to the target′s rendezvous orbit design and control implementation.