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The accurate dynamic model of a solar wing is built on basis of its ground modal test, through which the method of the on-orbit load analysis of solar wing is put forward based on its flexible characteristics and modal synthesis hybrid coordinate dynamics modeling. The load analysis of the typical cases such as the orbit changing, module separating, and rendezvous and docking is calculated, the effect of the dynamic performance of the solar wing on the on-orbit load is analysed, and its maximum load is validated through the related test. The test results show that the research method is reasonable and valid, and can be extended to other types of solar wing load analysis. [ABSTRACT FROM AUTHOR]

Several key mechanic problems during the release and separation of the Chang' E-3 probe are revealed. The main risk points and influentical parameters of the separation process are given. The simulation model of the whole process of the release and separation is established by using ADAMS. Then the dynamic simulation and related experiment are carried out. The main risk points and influentical parameters of the two devices are identified, and the maximal landing boundary conditions of the lander is obtained, which provides basis and theoretical support for the release and separation of the two devices. [ABSTRACT FROM AUTHOR]