Heat Transfer Analysis And Thermally Induced Vibration Study Of Extensible Solar Cell Wings

Extensible solar cell wing has the advantages of small folding volume,light weight and so on.The wing in the case of a fully extended,big span,small stiffness and damping structure characteristics of the weak,and on-orbit working process,regularly to move out of the earth’s shadow area,the law of periodic change,because the temperature of the thermal radiation changes quickly,so the wing may be out of shape,so lead to cause the vibration.Thermally induced vibration may even lead to a significant decrease in the attitude accuracy of the spacecraft and the risk of stability changes,and even fail to complete the specified tasks.Therefore,it is necessary to explore the thermal analysis and thermally induced vibration of solar wings.In this paper,the thermal vibration of solar wing is attenuated and suppressed by using the heat-structure sequential coupling method.The main contents are as follows:First of all,this paper introduces the distribution of orbital zone and outer heat sources,according to the orbit parameters,calculate the three 900 km altitude of the sun radiation heat flux and total heat flux,heat transfer analysis,using the data from temperature difference derivative is analyzed in detail the decay time structure and the influence of the temperature difference and heat to the relationship between the vibration,the results show that the temperature difference of the derivative is the key parameter of structure vibration,and altitude difference directly affect the temperature reached steady state the time required to.Then,in order to reduce the sudden change of temperature difference,the influence on the structure was explored by changing the surface coating parameters and changing the structure size of the solar panel,and the attenuation time of temperature difference was used.Secondly,based on the Boley coefficient,the differences between the quasi-static responses of the incoming and outgoing shadow regions are analyzed by using two simplified spacecraft models,and the relationship between the quasi-static responses and the dynamic responses is discussed in the form of analytical solutions.Finally,the geometric model based on the wing,the stretchable solar cell wing to establish a detailed finite element model,the control variable method is adopted,and ignore the tension rope,guide lines and the influence of herringbone pointed,in view of the solar wing kinematics coupling constraints,the size of the front,factors such as altitude quasi static analysis,explore the root and the influence of the array,and focuses on the wing in all conditions,in the original model for reference,by changing the tension rope tensioning force,guidance force as well as the front,to study cause the vibration damping ratio of the size of the analysis result shows that:In terms of vibration response,attitude Angle response and thermal disturbance response,under the premise of full expansion,the thermal deformation and thermally induced vibration response can be greatly attenured by appropriately reducing steering force,tensioned force and increasing damping ratio.In this paper,the heat transfer analysis and thermal-induced vibration of the extensible solar cell wing are studied.The temperature difference,the derivative of temperature difference,vibration response,attitude Angle response and disturbance response are obtained,which provide reference and basis for the design of solar wing and the attenuation of thermal-induced vibration.