基于不变流形的高超声速飞行器动态面控制

后德龙; 陈彬; 王青; 董朝阳

doi:10.13700/j.bh.1001-5965.2013.0673

基于不变流形的高超声速飞行器动态面控制

doi: 10.13700/j.bh.1001-5965.2013.0673

1.
北京航空航天大学飞行器控制一体化技术重点实验室, 北京 100191
2. 北京宇航系统工程研究所, 北京 100076
3. 北京航空航天大学飞行器控制一体化技术重点实验室, 北京 100191
4. 北京航空航天大学航空科学与工程学院, 北京100191

基金项目: 国家自然科学基金资助项目(61273083)

详细信息

作者简介:
后德龙(1988-),男,安徽芜湖人,博士生,dlh8855@163.com.

中图分类号: TP249;V448.22
计量
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- 被引次数: 0
出版历程
- 收稿日期: 2013-11-21
- 网络出版日期: 2014-11-20

Dynamic surface control for hypersonic vehicle based on invariant manifold

1.
Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Beijing Astronautics Systems Engineering Institute, Beijing 100076, China
3. Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
4. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对存在未知气动参数的吸气式高超声速飞行器纵向运动控制问题,提出一种基于不变流形的自适应动态面控制方法.通过合理假设将高超声速飞行器纵向模型分解为弹道倾角回路和速度回路,分别实现对弹道倾角和速度参考指令的跟踪.弹道倾角回路被表达为严反馈形式进行控制器设计.采用基于不变流形的自适应方法实现了对未知参数的估计.所提出的自适应动态面控制方案能保证未知参数估计误差全局一致稳定和闭环系统全局有界稳定,且估计器和控制器设计不存在耦合,因此参数设计更加容易.仿真结果验证了该控制方法在参数估计方面的显著优势和良好的闭环系统性能.
- 高超声速飞行器 /
- 跟踪控制 /
- 自适应估计 /
- 动态面控制 /
- 不变流形
Abstract: An adaptive dynamic surface control scheme based on invariant manifold was proposed for the longitudinal motion control problem of hypersonic vehicle. With reasonable hypothesis, the longitudinal dynamic model was separated into flight-path angle loop and velocity loop. Flight-path angle loop was formatted into parametric-strict-feedback form. The unknown parameters of the system were estimated based on the method of invariant manifold. The proposed dynamic surface control scheme can guarantee the global uniform stable of the error of estimation and the global boundedness of the closed system. The decoupled relationship between estimator and controller made the parameter tuning more easily than the traditional adaptive dynamic surface method. Simulation results validate the prominent improvement in parameters estimation and the good performance of the closed system.
- hypersonic vehicle /
- tracking control /
- adaptive estimate /
- dynamic surface control /
- invariant manifold

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参考文献(15)

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