集群航天器构形重构滑模变结构控制方法  

Sliding mode variable structure control for fractionated spacecraft formation reconfiguration

作　　者：胡敏 曾国强[2] 

机构地区：[1]装备学院研究生院,北京101416 [2]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《飞行力学》2012年第5期444-447,453,共5页Flight Dynamics

基　　金：国家高技术研究发展计划基金资助(2010AA7026053)

摘　　要：针对大规模航天器集群飞行构形控制问题,提出了一种基于滑模变结构控制与改进人工势场法相结合的控制方法。集群航天器相对运动采用非线性动力学方程描述,人工势场法可以避免集群航天器之间的碰撞,滑模变结构控制对摄动干扰和模型不确定性具有鲁棒性,可以实现构形的精确控制。利用Lyapunov稳定性理论,证明了控制系统的全局渐进稳定性。通过仿真算例,验证了控制方法的可行性。To solve the control problem of large-scale spacecraft clustering flying, this paper proposes a formation reconfiguration control method based on improved artificial potential filed and sliding mode control technique. The nonlinear equation of relative motion dynamics was adopted, the enhanced artificial potential method was proposed to avoid collisions among the spacecraft, and the sliding mode variable structure control method was established for precise formation control in the presence of model and perturbations uncertainties. The global asymptotic stability was proved using Lyapunov stability theory. The numerical simulation results verify the effectiveness and feasibility of the proposed controller.

关 键 词：集群航天器 构形重构 滑模变结构控制 人工势场法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]