Deployable Method Of Flexible Structure Based On Spacecraft Formation With Cooperating Control

Currently, there are four basic deployable methods of lightweight flexible structure in space: projection deployable, inflation deployable, mechanical deployable and spin deployable. But the above four deployable methods both operate on a single satellite, then the size of that lightweight flexible structure is limited. As the aerospace industry develops, the need for bigger size is growing. Those deployable methods that operate on a single satellite can no longer meet the demand. We need to find a new reliability deployable method. So a new deployable method based on spacecraft formation with cooperating control is presented in this paper.The overall idea of this paper is deployment by the spacecraft formation with cooperating control drawing. This paper transforms deployable stabilization control of the lightweight flexible structure into cooperating control of spacecraft formation. This paper sees the impact of lightweight flexible structure on satellite as the disturbing force of spacecraft formation with cooperating control.First of all, this paper propose the simulation method of lightweight flexible structure in space based on fabric simulation technology. Modeling by Mass-Spring Model, then model forces are accomplished. The position and velocity of each particle next time are solved by explicit integral method. The additional deformation constraint is in order to avoid distortion and superelastic phenomenon.Secondly, building satellite formation dynamics model. The communication topology relationship between formation satellites is described based on graph theory. Satellite formation dynamics model is derived from the single satellite dynamics model. The condition of formation flying is determined by analyzing the analytical solution of dynamics model.Finally, the impact of lightweight flexible structure on satellite is treated as the disturbing force of spacecraft formation with cooperating control, then the control algorithm is proposed with control input constraints and energy optimization. And simulation experiment of the deployable method based on spacecraft formation with cooperating control is done with the simulation method of lightweight flexible structure.