Chang' E-2 Lunar Probe Orbit Determination and Support
Chang' E-2 Lunar Probe Orbit Determination and Support
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发表时间：
2013
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通讯作者：
Huang Yong
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作者：
Huang Yong
在嫦娥二号探测器上验证了直接奔月转移轨道和100 km高度绕月入轨机动等关键技术，并进行了日地拉格朗日点L2的扩展使命设计。针对轨道的新特点，提出了轨道使命设计和定轨策略。基于后处理的精密星历，对机动前的定轨和预报精度进行了评估，对机动后的定轨和预报精度进行了快速评估，根据入月前的定轨结果，近月3小时预报位置误差为1 km，速度误差为0.3m/s。对3种不同月球位场模型的定轨结果进行了比较，对测量残差和后处理星历的分析表明，SGM 100 h模型的残差均方根值最大。针对CE-2扩展使命，对不同类型的测量数据进行了定轨精度评估，并对基于pre-TCM精密星历的测量残差进行了分析，得到测距残差、时延残差和时延率残差的RMS分别为5 m、5 ns和1 ps/s。
Several key techniques are validated by Chang'E-2(CE-2),including the direct transfer trajectory to moon and the lunar orbit insertion maneuver at 100km altitude,etc.Then,an extended mission to sun-earth Lagrangian point L2 was carried out.For new characteristics of the trajectories,mission design and orbit determination strategy are presented.Based on post-processed precision ephemeris,the orbit determination and prediction accuracy of pre-maneuvers is evaluated and fast assessments of post-maneuvers are performed.Based on orbit determination results before lunar insertion,the 3-hour predicted position error of perilune is 1km and the velocity error is 0.3m/s.A comparison of the orbit determination results with 3 different lunar potential field models is presented.The analysis of measurement residuals and post-processed ephemerides shows that RMS of the residuals using SGM100h is the maximal of all.Furthermore,orbit determination accuracy of the different types of measurements is evaluated for CE-2 extended mission.Measurement residuals are analyzed based on pre-TCM precision ephemeris.The RMS of data residuals including ranging,time-delay and time-delay rate are respectively 5m,5ns and 1ps/s.