FLEXIBLE COUPLED DYNAMICS MODELING OF VARIABLE CONFIGURATION SPACECRAFT ORIENTED CONTROL

摘要

The communication satellite with large deployable antenna is a typical system which has the characteristics of alterable structure, configuration, parameter and centroid during the deployment of the antenna. In the paper, the flexible coupling dynamics equations are built based on modal synthesis-hybrid coordinate method, which can satisfy the requirement of the control system at both appendage level and the spacecraft level. Also, the flexible models of whole spacecraft with any configuration are obtained. An analysis simulation program is developed which has been verified by a typical example and inertial completion. The results show that this research would be practicable and effectual for designing the control system.