Matching design of trajectory with Chang'e-6 mission and flight pratice of Queqiao-2 satellite
Queqiao-2 provides relay services in its overall life cycle for Chang'e-6,Chang'e-7,Chang'e-8,and Chang'e-4 missions,as well as lunar exploration missions from international cooperation.To meet the different relay needs of multiple launch windows and different flight phases of Chang'e-6 mission,the trajectory design method and process of the Queqiao-2 relay satellite to service the Chang'e-6 mission are introduced from the perspective of mission analysis.The adoption of a lunar elliptical sun-synchronous frozen orbit satisfies the requirements for communication range,coverage,launch windows,and orbital phase for the Chang'e-6 mission.Then the trajectory scheme and the control strategy adopted on each flight phase are optimized with minimum fuel constraint.A four-impulse joint optimization trajectory control strategy is employed to significantly alter the orbital ascending node,inclination and argument of perilune with few velocity increments.Finally,the status of the in-orbit flight and relay support for Chang'e-6 mission are shown respectively.For the first time internationally,Queqiao-2 has achieved a significant change of right ascension of the ascending node in lunar orbit by using a lunar low energy capture orbit,and close range and long arc relay of target on the far side of the moon by using the lunar large elliptical sun-synchronous and frozen orbit.The result shows that the in-orbit flight of Queqiao-2 is consistent with that of the design,which ensures the successful implementation of the Chang'e-6 lunar far-side sampling and return mission.The design method can provide a reference for the orbit design of deep space exploration missions.
Queqiao-2 relay satellitelunar large-elliptical frozen orbitsun synchronousflight and controllunar low energy capture orbi
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