Research Of The Orbit Determination Algorithm About The Lunar Relay Satellite Constellation Supporting For The Rendezvous And Docking

To support future manned mission to the moon, relying solely on the deep spacestation can not completely cover and track the whole process of lunar orbit rendezvousand docking because of the moon’s shelter. Therefore, in order to provide theall-weather and continuous data relay communication and tracking service for the lunarorbit rendezvous and docking of human lunar exploration in the future, having toestablish the tracking and data relay satellite constellations like the near-earth orbit. Apreliminary study of the configuration of lunar relay satellite constellation at home andabroad have been carried out, on this basis and considering the less lunar relay satellitebe laid in the early lunar exploration, and this thesis focuses on how to use the singlelunar relay satellites guiding the lunar module to the vicinity of the service module anddetermining the relative status of the rendezvous and docking, and ultimately achievesthe purpose of support of the lunar orbit rendezvous and docking.To take advantage of the lunar relay satellite for tracking service, it first needs tomake use of the deep space station determining the orbit of lunar relay satellite. Thisthesis based on the ranging and velocimetry observations of deep space stationsresearches initial orbit determination algorithm with fg series least squares and orbitimproved algorithm, where the orbit improved algorithm includes the weighted leastsquares method in post-processing and the Kalman filter method in real-time processing;simulation results show that the initial orbit determination algorithm is able to provide areliable initial value, and taking advantage of the the orbit improved algorithm has theorbit determination accuracy of lunar relay satellite reach the position accuracy ofmeter-scale and the speed accuracy of centimeter per second level. Second, based on theprecise orbit of lunar relay satellite, researching the initial orbit determination algorithmwith ranging and velocimetry observations when the lunar module visible only with alunar relay satellite and with a lunar relay satellite and the service module at the sametime, and a large number of simulation is taken for the performance of the twoalgorithms; under the appropriate conditions of observation that these two algorithmsare able to provide the initial value of higher accuracy, and also analyzing the number of observed data and the size of sampling step impacting on these two algorithms. Lunarmodule will be guided to the vicinity of the service module by the above method, andfinally studying of using the angle and ranging and velocimetry observations ofrendezvous radar, based respectively on the absolute motion equation of the lunarmodule and the relative motion equation of rendezvous and docking, achieving thereal-time estimate of the relative motion of the rendezvous and docking with Kalmanfilter algorithm; through the large number of simulation shows that the estimatedaccuracy of relative status reaches the indicator in the closer approximation stage anddocking phase of rendezvous and docking.Based on the lunar relay satellite for the studying background, designing andresearching a complete set of orbit determination algorithm for the above three elementsin this thesis provides the reasonable and feasible programs for laying China’s lunarrelay satellite constellation and fully applying it to the lunar exploration mission in thefuture.