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目标航天器相位调整机动的目的是为交会对接任务做准备,是一个非固定时间交会问题。从调相的基本原理出发,分析了大气阻力、升交点赤经漂移及轨道误差对相位角的影响,并将这些参数用于改进冲量对相位角影响的估算公式。将估算公式与数值积分相结合,从摄动轨道机动参数计算、调相方向选取与机动圈次选择三个方面改进相位调整策略。仿真结果表明:提出的相位调整策略可以稳定高效地获得摄动轨道机动参数,能够满足终端精度要求,相对于直接根据相位角偏差正负来选择调相方向的策略可以节省推进剂消耗。
The purpose of the target spacecraft phase maneuver is to prepare for the rendezvous and docking task, which is a non-regular rendezvous problem. Based on the basic principle of phase modulation, the influence of atmospheric drag, ascending drift and the orbit error on the phase angle are analyzed. These parameters are used to improve the estimation formula of the influence of the impulse on the phase angle. Combining the estimation formula and numerical integration, the phase adjustment strategy is improved from the following three aspects: calculation of maneuvering orbit maneuvering parameters, selection of phase modulation direction and selection of maneuvering coils. The simulation results show that the proposed phase adjustment strategy can obtain the perturbed orbit maneuver parameters stably and efficiently, which can meet the requirements of terminal precision. Compared with the method of selecting the phase modulation direction directly according to the positive and negative phase angle deviation, the propellant consumption can be saved.