一种考虑非线性形变的柔性航天器边界稳定控制方法

Boundary Stabilization of a Flexible Spacecraft Dynamical System with Geometric Nonlinearity

以空间连续变量描述的动力学模型为基础,考虑了大型柔性空间结构的整体刚体运动与局部弹性运动及位于结构边界的控制输入项的动力学耦合关系,建立了可以描述由几何非线性形变引起的动力学刚化现象的非线性动力学模型;再针对该耦合系统设计基于能量耗散方法的边界稳定控制器,利用布置在全柔性航天器两端的推力器和控制力矩陀螺,实现具有动力刚化特点的非线性自由边界弹性结构的边界稳定控制;通过数值仿真,给出全柔性航天器在边界控制作用下的动力学响应,以验证所设计的控制器的有效性。

A continuous spatial domain method is used when modeling the flexible spacecraft dynamics,taking into account the global large overall rigid-body motions and local elastic vibration with finite extension and bending,as well as the controlled inputs acting at boundaries,to exactly depict the strain hardening.Then,regarding thrusters and control moment gyros equipped at boundaries,a boundary damping algorithm based on dissipativity is proposed to stabilize the attitude and to damp out the vibration in presence of strain hardening.The result of numerical simulations shows the validity of the controller.