柔性航天器的模态综合-混合坐标动力学建模

针对由中心体和柔性附件组成的柔性航天器，采用混合坐标法，通过伪坐标形式的拉格朗日方程，建立了全柔性航天器的混合坐标动力学方程。建模中采用模态综合理论的方法，由航天器结构的弹性正则模态和静变形模态组成的模态集表示结构变形，以便更有效的将结构变形的影响引入到航天器的动力学模型中。文中用由盒形中心体和两帆板组成的假想航天器系统为例，以此系统的有限元动力学模型为基准，比较了采用弹性正则模态和静变形模态的模态综合建模和单纯采用弹性正则模态的常规建模时得到的系统特征频率，表明引入了静变形模态以后，所得到的动力学模型能更好反映柔性航天器的动力学特性。

Modal synthesishybrid coordinate dynamics modeling of flexible spacecrafts

Hybrid coordinate dynamic equations for flexible spacecrafts consisting of a central body and flexible appendages are derived by use of the hybrid coordinate method in terms of the Lagrange's equations in quasicoordinates. Introducing the technology of the modal synthesis theory, the structure deformation of the spacecraft is represented with elastic normal modes and static deformation modes to consider the influence of the structure deformation on the dynamic model more effectively. With a fictional flexible spacecraft consisting of a box and two plates as an example, the eigenfrequencies of the spacecraft model based on using elastic modes and static modes are compared with that based on using only elastic modes. It is shown that the introduction of static modes makes the derived dynamic equations more properly for capture of the dynamic characteristics of flexible spacecrafts.