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Chang' E-2 Lunar Probe Orbit Determination and Support

DONG Guang-liang1,FAN Min1,LI Pei-jia2,HUANG Yong2 (1.Beijing Institute of Tracking and Telecommunications Technology,Beijing 100094,China; 2.Shanghai Astronomical Observatory,Chinese Academy of Sciences,Shanghai 200030,China)  
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.
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