Abstract: In this paper, the modeling, control and simulation technology is studied to improve the control performance of spacecraft with complex structures in multi physical field. Based on the absolute nodal coordinate formulation (ANCF), the thin plate element unifying the temperature and displacement field is given, which can avoid mismatch problem in the process of mapping two physical fields. On this basis, considering the variation law of material Poisson's ratio with temperature, a rigid flexible thermal dynamic model of spacecraft with the bidirectional coupling effects between the displacement field and temperature field is established. A high order control algorithm for active suppression of multiband disturbance is designed, achieving the index of control stability of flexible spacecraft with a moment of inertia of  better than 5e-6°/s under 8°/25s attitude maneuvering condition in mathematical simulation. Based on the three axis air flotation motion simulator, the flexible load simulator and the thermal radiation environment simulator, a full physics attitude control test platform with rigid flexible thermal coupling is constructed to calibrate the dynamic model in time domain, which verifies the engineering feasibility of the integrated simulation of finite element modeling and control.

Key words: complex spacecraft, multi physics coupled modeling, absolute nodal coordinate formulation, high order control, full physical experiment