Research On Splicing Of The Condenser Of Space Solar Power Station And Mechanism Of Deployable Submodule

To solve the increasingly tense energy crisis,it is necessary to develop and utilize new renewable energy sources.With the development of aerospace technology,space solar power stations have become the current research hotspot.Considering the large size of space solar power station,its condenser system needs to be assembled by sub-modules in orbit.Deployable sub-module belongs to the large flexible body,its structure characteristics will influence the stability of condenser system.Therefore,it is of great practical significance to develop deployable sub-modules with large scale,light weight and high folding ratio,as well as docking interfaces with large tolerance and high stability.In this paper,the parameter index of the condenser are solved according to the efficiency of photoelectric conversion and optics law of the geometric.The method of constructing the Goldberg polyhedron to splice the sphere is proposed.Using D-H variation of coordinates method and the space surround circle method to obtain the spatial geometric coordinates of the submodule.The relationship between sphere radius and space surround circle radius is given.A variety of sub-modules are proposed,and the optimal sub-module scheme is optimized by the ratio of the stiffness and the ratio of the fundamental frequency.The material properties of the film were studied by tensile test,and the mechanical properties of the sub-module film structure were analyzed by the cooling method.The mathematical agent formulas is given by analyzing the influence factors by response surface theory.The formulas of rigidity and equivalent elastic modulus are derived by buckling analysis.Then analyzing sensitivity of thin-walled tube rigidity.The finite element model of the submodule has been established.The mechanical properties of the submodule were obtained and verified by the deformation compatibility equation.The influencing factors of sub-module rigidity are analyzed and giving the trend.The pre-stress criterion was established by the failure mode of the sub-module and designing the constraint condition.The structure parameters of the submodule are optimized by the function which the objective is the light weight and high rigidity.The detailed structure of deployable submodule and the structural parameters was designed.Then Printing the 3D model and finished the test.The submodule interface mechanism is designed by mechanical principle and finite element simulation.The docking interface was designed and then the test of docking and rigidity were completed.