平动点任务转移轨道中途修正研究

Research on Transfer Trajectory Correction Maneuvers for Libration Point Missions

平动点在深空探测中具有重要作用.由于发射中不可避免地会存在误差,平动点卫星往往需要考虑转移轨道的中途修正.本文从工程实用角度出发,根据以往平动点任务的中途修正经验,确定中途修正序列,综合以往文献对误差的处理,给出了误差的分布参数;将转移轨道中途修正问题转化为转移轨道设计问题,使用微分修正算法求解转移轨道中途修正问题;利用蒙特卡洛模拟给出统计性数据.仿真结果验证了方法的有效性.对于日地系110天类型的转移轨道,在95%的置信水平下,只需要78.0m/s的机动速度,即可以保证位置误差在66.1km之内.

Libration points play an important role in deep space exploration,due to the fact that they are ideal locations for spacecrafts with special purposes.Since there are always inevitable injection errors in the launch process,transfer trajectory correction maneuvers must be considered for libration point missions.From the view point of engineering development,firstly,transfer trajectory corrections sequence was determined on the basis of the experience of the past libration point missions, and the error models were concluded by summarizing previous studies of both home and abroad; then,the transfer trajectory correction problem was transformed into the transfer trajectory design problem and solved by the differential correction method.Simulation results show that the algorithm is very effective.For transfer trajectory with the flight time of 110 days in the Sun-Earth system, only 78.0m/s of maneuver velocity was needed to keep final position error below 66.1km on the confidence level of 95%.