The Dynamics Analysis Of Tethered Solar Power Satellite Subsystem

With the emergence of energy crisis,as well as the greenhouse effect,haze and other environmental problems become increasingly serious,people become more and more favored on the renewable and clean solar energy.It requires less on the environmental constraints,such as the weather or circadian rhythm.At the same time,the efficiency of solar energy utilization is enhanced through it.As one of the space power generation conceptions,Tethered solar power Satellite has a great advantage in the field of space solar power and its own structure.However,because the tether is prone to bending and deformation,and the area of flexible panel is very large,the dynamic behavior of the whole structure is more complex.Therefore,it is necessary to do dynamic simulation on the tethered solar power Satellite under the different complex external disturbance.Firstly,the development of tether satellite system and the recent research have been studied.It mainly analyzes the various simplified models of the whole structure and their advantages and disadvantages.Then,the characteristics of the flexible panel are analyzed,and the finite element model of the flexible panel is established.Dynamic analysis of the panel model is done and solved by the variable-step-length-Runge-Kutta method.Panel simply supported on four sides model is calculated by using the program,and the results are compared with the theoretical solution.Combined with the characteristics of tether,the finite element model of the flexible tether is established.Calculate the internal force of the flexible tether in orbit.Then,the finite element analysis of the whole system is carried out.The impact of the action time of 0.1s and the size of 15000 N perpendicular to the flexible panel is analyzed.It is mainly analyzed two different examples under the conditions by taking the same load.Based on the model of the tether with bushing force,the vibration module is used to analyze the vibration of the whole system,and the vibration mode and frequency response curve of the solar panel are obtained.Finally,the simulation model for the whole system of the tethered satellite is established in ANSYS,in which the flexible panel with honeycomb layer is modeled by equivalence principle.The coupling between the flexible tether and the panel is set reasonably.The displacement nephogram of the whole structure in the z direction is obtained by analyzing theresponse of the model under the effect of microgravity and solar pressure.Considering the complex external disturbance in the space environment,the time-varying impact of the whole structure is analyzed,and the influence of the main parameters on the calculation results is studied.