| The satellite is exposed in the space and suffers a lot from the space heat flux while transferring the heat into energy for itself.During attitude maneuver,the heat flux applied on the solar panel is changing all the time.As a result,the temperature gradient of the solar panel in the thickness direction is changing as well.According to the thermo-elasticity mechanics,thermal stress occurred.Thus,the thermally deformation of the solar panel and the rotation of the satellite are induced.What's worse,the satellite may lose its stability.This paper aims at establishing a rigid-flexible-thermal coupling dynamic model for the satellite-solar panel system under complex heat flux.Considering the influence of the thermal deformation and the rotation of the satellite,the thermal loads including the solar radiation flux,the earth-reflected heat radiation flux,earth-emitted heat radiation flux and the surface radiation are derived using the angle factor method.The finite element discrete heat conduct equations are derived from the equivalent integral weak form of the heat conduction,while the continuity condition of the temperature and the heat flux between the adjacent layers is taken into account.Considering the off axial effect of the composite solar panel,the off axial thermal strain was given,and the off axial stress was got according to the thermoelasticity mechanics.Using the hybrid coordinate formulation,the dynamic equations of satellite-solar panel system are derived based on Jourdan variational velocity principle.In addition,stability criterion of the solar panel can be obtained from the distribution of all the eigenvalues of linear system based on the Lyapunov's stability theory.Finally,dynamic simulations for the coupling system are conducted,and the stable region is given based on the stability criterion considering the influence of the attitude angle of the solar panel,damping coefficient,type of the heat flux and moment inertia of the satellite. |
PDF Full Text Request