Abstract: The disturbance induced by the rotation of dual axis flex solar wing is the important factor which impacts satellite attitude and pointing accuracy and stability of satellite precise payload. The flexible multibody system method based on recursive formulation is proposed to solve the dynamics problem induced by satellite dual axis flexible solar wing rotation. The satellite dynamics equations are established by considering orbit mechanics， satellite configuration， solar wing flexibility and solar array drive assembly and momentum wheels. As an example of a satellite with dual axis solar wing， the research on multibody dynamics simulation of satellite electromechanical coupling is developed， and the simulated attitude angle and angular velocity of satellite are compared with the corresponding telemetry data. The research shows that the simulated attitude angle and angular velocity of satellite agree well with the corresponding telemetry data， which proves the correctness of the model， The rotation of flexible dual axis solar wing will produce big disturbance torque and attitude angle， the control torque needs to be distributed to momentum wheel assembly for the accurate simulation results， and the disturbance torque of floating satellite caused by the rotation of solar wing was obtained by simulation， which can give the reference condition of ground test verification of solar wing rotation.