Modeling and Verification of in Orbit Dynamics and Attitude Control of Satellites with Dual Axis Solar Wings Based on Electromechanical Coupling Method

The disturbances generated by solar wings during orbital operation have the characteristics of dense distribution and complex characteristics in the low frequency region, which seriously affect the imaging quality and pointing accuracy of remote sensing satellites, as well as the stability of inter satellite links between communication satellites, and other important indicators. For satellites with high inclination orbits, the angle between sunlight and orbital plane can vary in the range of < 90°. In order to meet the power requirements of satellites, biaxial solar wings are mostly used to meet the solar-wing directional requirements. These solar wings have the characteristics of large centroid deviation from the axis of rotation and stepper motor drive. Their orbital rotation has obvious influence on the attitude and load direction of satellites, which is an important factor to be considered for such complex satellites. The disturbance caused by the rotation of the solar wing is an important factor affecting the accuracy of satellite attitude pointing. The two-axis solar wing has the characteristics of large centroid deviation from rotation axis and stepper motor drive. The rotation of solar wing in orbit disturbs the attitude of satellite greatly. According to the satellite in-orbit working environment, a flexible multi-body dynamics and control electromechanical coupling model for the whole satellite including satellite orbit, attitude control, momentum wheel and solar wing driving mechanism is established, which indicates the disturbance of satellite attitude direction during the solar wing in-orbit starting and running. The correctness of the model is verified by comparing with the on-orbit telemetry data. The research shows that the startup of the solar wing will directly cause the satellite attitude to flutter greatly, and compensation measures are required for high sensitivity loads. When the solar wing runs smoothly, the effect of solar wing rotation on satellite attitude pointing accuracy will be significantly reduced.