Abstract
The article focuses on the orbit determination and tracking technology of CE-2 satellite. CE-2 satellite was injected into trans-lunar orbit directly by launch vehicle and captured by the Moon at perilune with altitude of 100 km. Orbit determination and accuracy estimation of CE-2 satellite is one key technology. Data process method and accuracy estimation of experimental data in X-band is another key technology. Considering the influence of momentum wheel unloading perturbation, an orbit determination strategy with shortening observation arc is put forward in order to improve the orbit accuracy. The estimation of accuracy of the injection position is given based on the satellite orbit and first trans-lunar midcourse correction. The estimation of accuracy of the lunar capture orbit is also given depending on overlap arc orbit determination. Based on the analysis of magnitude of perturbation, orbit determination strategy for CE-2 satellite lunar orbit is shown. The method of process deep space phase observation data in X-band is given. The noise of round-trip range data and DOR data in X-band is estimated. The noise of the experimental observation data in X-band is decreased obviously. CE-2 satellite entered the mission lunar orbit precisely under the control of the ground control center. Tracking technology and data process method in X-band can be used in future deep space exploration.
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