分导飞行器质心突变过程的稳定控制研究  

Stability control for mass center mutation of a post-boost vehicle

作　　者：丁保春[1] 谭峰[2] 段广仁[2] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073 [2]哈尔滨工业大学控制理论与制导技术研究中心,哈尔滨150001

出　　处：《哈尔滨工业大学学报》2007年第11期1803-1807,共5页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金资助项目(60474015);长江学者和创新团队发展计划资助项目

摘　　要：采用单位四元数方法建立了分导飞行器姿控系统的数学模型,对于飞行器在分导过程中出现的质心突变和惯性张量的变化进行了描述.基于Lyapunov方法给出了使闭环系统全局渐进稳定的控制律,特别考虑了惯性张量矩阵的时变特性和不确定项对于姿态系统稳定性的影响,给出了相应的控制器设计方法.对飞行器的大姿态转动及质心突变过程进行了非线性仿真.仿真结果表明,提出的控制方案可以实现对于分导飞行器质量剥离段和大角度姿态调整段的全局镇定,整个分导过程中姿态变化平稳,同时满足了对于控制力矩大小和变化率的要求.For a post-boost vehicle, the mathematic model of attitude system was established using the unitary quatemions. The variations of the inertia matrix and the position of the mass center caused by the separation of the warehouse and warheads were characterized in detail. A nonlinear feedback controller, which can globally asymptotically stabilize the closed-loop system, was proposed based on the Lyapunov approach. Specially, the time-varying characteristic and uncertainties of the inertia matrix were taken into consideration and correspond- ing controllers were brought forward. The controller proposed was applied to a post-boost vehicle. Nonlinear simulations were carried out for the process of large angle maneuver and the separation of the warehouse and warheads. The results show that the controller designed can successfully stabilize the attitude system during the angle maneuver and separation process. The attitude variables change smoothly on the whole trajectory and the constraints on the control inputs are satisfied at the same time.

关 键 词：分导飞行器 质心突变 时变惯性张量 LYAPUNOV方法 四元数 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]