Rigid Flexible Coupling Dynamic Modeling Of Satellite With Solar Wings

In the design of spacecraft ignoring the influence of flexibility of spacecraft and its attachment brought a painful lesson in the development of human spacecraft. Reasonable in satellite dynamics modeling, it is necessary to consider the wing of the flexible structrue, to establish a more accurate model, so as to ensure the real effectiveness of satellite control system simulation.The dynamics analysis of flexible structure system need to use the flexible multi-body system dynamics modeling method. Flexible multi-body system dynamics has considered the impact of the elastic deformation of substructure or hinge point in the system. It is a combination of mechanics of rigid body, analysis mechanics, elastic vibration, structural dynamics and mathematics. This article will use mixed coordinates method in modeling, it succeeded in considering the coupling effect between elastic deformation and the large range of motion. This article uses the hybrid coordinate method for flexible multi-body system modeling with posture coordinates describing the satellite body movement and modal coordiantes describing the wing. The dynamic equation established by this method can describe the global motion and flexible attachment elastic movement at the same time, of which the relationship is given by coupled coefficientsIn the thesis of this article, dynamic modeling of spacecraft of central rigid body with flexible attachments is firstly made, and on this basis further derived the dynamic equations of satellites with a wing and two attachments. Then dynamic equations of satellites with a wing and two attachments are deduced. According to the foregoing method, finite element modal of a backgroud satellite is established, obtaining natural frequency, vibration mode and the coupling coefficient matrix with the hinge of different equivalent stiffness.