Optimized Design And Implementation Of The LRS Constellation

The LRS(Lunar Relay Satellite)constellation means the satellite constellation set uparound the moon orbits, which could offer uninterrupted services of trackingcommunication for the surface of the moon under specific lunar area tasks. The LRSconstellation could provide services of navigation&positioning for the astronauts,communications&relay for the exploration vehicles on the lunar surface, and orbitmeasuring&determination for the lunar orbiter. With the fast development of China’slunar science exploration and applied research, the requirement for this service isincreasing. The LRS relative to the earth’s ground station has incomparable advantage,which is China’s the first consideration in the major projects such as lunar explorationand manned lunar landing project in the future.This paper based on home and abroad in the lunar exploration’s experience,combined with the constellation program’s coverage performance (including coveragenumbers, average revisit time, time average gap, percent coverage, etc.),workperformance, chains performance, operation and maintenance, evaluation indicators,combined the principles for the design and basic method and evaluation method of LRS,using the theory of optimization method, cooperate with the STK(satellite tool kits)simulation, designing software of constellation optimization, and achieving theintegrated design optimization of satellite constellation system, the main content of thedissertation include:First, on adequate research to the LRS and the basic genetic algorithm, thisdissertation set up a method of the integrated design optimization of satelliteconstellation system, which maximum expanding the parameters of the system. Notonly includes the basic orbit parameters of satellite orbital elements and other possibleparameters. For the LRS, first of all, according to the demand, choose several roughlyconstellation configuration to meet mission requirements, and then according to theconstellation model to optimize several configuration parameters, this ensures that thegenerality of the model, and easy to find the optimal configuration.Secondly, on model of the LRS, the dissertation presented a improved GASAmethod, which is used to solve LRS problems. This method can solve multi-objective decision problems. In order to satisfy the different task requirements, this dissertationbasic performance evaluation of the principles, including the coverage performance,cost and link performance, etc.Finally, based on GASA algorithm and constellation model and evaluation criteria,in the back moon cover and the moon’s South Pole LRS aspects has carried on theoptimized design, and presents a result that hybrid algorithm is better than the basicgenetic algorithm on the satellite design. At last, according to the different missionrequirements and provide some different optimal design results.