CAJ | 학술논문

基于我国2天交会对接方案，通过合理减少定轨、变轨参数计算与指令上传及不可测控区域占用的飞行圈次，建立了5圈快速交会对接的调相变轨方案，采用四脉冲修正特殊点变轨算法进行求解。给出了满足调相段终端控制精度所需要的定轨精度，分析了追踪航天器入轨精度、追踪航天器入轨远地点高度、目标轨道高度、调相段终端瞄准点等参数对最优初始相位角范围的影响规律。简要分析了为获得需要的初始相位角，目标航天器的调相策略及追踪航天器可能的发射机会。
기우아국2천교회대접방안，통과합리감소정궤、변궤삼수계산여지령상전급불가측공구역점용적비행권차，건립료5권쾌속교회대접적조상변궤방안，채용사맥충수정특수점변궤산법진행구해。급출료만족조상단종단공제정도소수요적정궤정도，분석료추종항천기입궤정도、추종항천기입궤원지점고도、목표궤도고도、조상단종단묘준점등삼수대최우초시상위각범위적영향규률。간요분석료위획득수요적초시상위각，목표항천기적조상책략급추종항천기가능적발사궤회。
Based on the two-day profile of Chinese rendezvous and docking mission,a 5 -revolution short-rendezvous phasing strategy was proposed by cutting down the flight duration for orbit determination,computation of maneuver parameters and command uploading,and non-visible course of flight.This phasing strategy was solved by using the algorithm of four-impulse modified special-point maneuver.The required precision of orbit determination to meet the control precision at the end of phasing was obtained.Then,the optimal phase range and total velocity increment were analyzed.Further results show that the optimal phase range is affected by the target spacecraft’s orbit injection accuracy,the chaser’s orbit insert precision and apogee height,the target orbital altitude and the final desired target point of rendezvous phasing.Finally,in order to obtain the starting phase angle,both the target spacecraft’s phasing strategy and the chaser’s launch chances are analyzed for the short rendezvous mission.