组合体航天器变拓扑过程中姿态稳定控制研究  

Attitude Stabilization Control of Compound Spacecraft in the Process of Changing Topologies

作　　者：李磊[1] 周军[1] 黄河[1] 张浩[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《计算机仿真》2015年第6期80-83,187,共5页Computer Simulation

摘　　要：在航天器姿态稳定性控制的研究中,由于空间站大型航天器需要通过多个航天器在轨组合完成,组合体航天器的结构在空间变化过程中,会引起质心和转动惯量等质量参数的大范围变化,从而给组合体的姿态带来较大的影响。针对组合体航天器变拓扑结构过程中的大质量参数变化的特点,研究了全程滑模变结构控制方法,实现了变拓扑结构的组合体姿态稳定。上述方法能有效克服外部干扰的影响,确保了整个系统的全局鲁棒性和稳定性,计算量小,易于工程实现。数学仿真表明,在空间站90°的转位过程中,核心舱的姿态控制在1.5°之内,证明了控制方案的有效性。Space station and other large spacecrafts are usually combined by many spacecrafts on - orbits. Mass parameters such as mass center and moment of inertia are changed with a large range in the process of compound spacecraft structure changing, which brings great influence on the attitude of compound spacecraft. Global sliding - model variable structure control approach is studied for the feature that the mass parameters are with a wide range of change and the proposed control scheme guarantees the attitude stabilization of the combination. The approach is not affected by the uncertain and external disturbance, and it ensures the global robustness and stability. Furthermore, the control approach has the advantage of less calculation, so that it is easy in engineering applications. A space station＇s 90° transposition process is simulated, which indicates that the attitude of core module can be controlled within 1.5° , and verifies the effectiveness of the proposed control scheme.

关 键 词：变拓扑结构 空间站转位 全程滑动模态 变结构控制 轨迹跟踪 

分 类 号：V44[航空宇航科学与技术—飞行器设计]