簇状卫星姿态控制方程的通用建模方法

当前卫星通常都由一个中心刚体和其他挠性附件构成，每个挠性附件都与中心刚体直接相连，组成了一个簇状的刚柔耦合的多体系统。随着挠性附件的数目的不同，卫星系统的拓扑构型也将有所不同。即使对于同一颗卫星而言，在展开过程的不同阶段，卫星系统具有不同的拓扑构型。本文利用柔性多体系统动力学的单向递推组集方法，提出了一套通用的解决方案，以推导具有不同拓扑构型的簇状卫星的姿态控制方程，得出了姿态控制方程的系数矩阵。

A Universal Modeling Method of Attitude Control Equation for Clustered Satellites

Generally, a satellite comprises a central rigid body and other flexible appendages, which are connected with the main body directly and together form a system with a cluster shape consisting of both rigid and flexible bodies. Such a system will have different topological configurations if the quantity of flexible appendages is different. Even in a satellite of which the amount of appendages is already known, the topology is various when the satellite is in different expansion phases. In this paper, the forward recursive formulation for flexible multibody system is used to give a universal solution to obtain the attitude control equation for clustered satellites with different topological configurations. Then the coefficient matrix of the equation is obtained.