宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (10): 1088-1096.doi: 10.3873/j.issn.1000-1328.2017.10.009

• 制导、导航、控制与电子 • 上一篇    下一篇

一种高超声速飞行器鲁棒自适应控制方法

余朝军，江驹，肖东，郑亚龙   

  1. 南京航空航天大学自动化学院，南京 211106
  • 收稿日期:2017-05-31 修回日期:2017-08-21 出版日期:2017-10-15 发布日期:2017-10-25
  • 基金资助:

    国家自然科学基金（61673209）；南京航空航天大学研究生创新基地（实验室）开放基金（kfjj20160318）;航空科学基金（2016ZA52009）；一院高校联合创新基金（CALT201603）

A Novel Robust Adaptive Control Scheme for Hypersonic Vehicles

YU Chao jun, JIANG Ju, XIAO Dong, ZHENG Ya long   

  1. College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106，China
  • Received:2017-05-31 Revised:2017-08-21 Online:2017-10-15 Published:2017-10-25

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摘要：

针对较强参数摄动情况下高超声速飞行器巡航段控制问题，提出一种基于主影响元素分析的鲁棒自适应控制方法。首先在飞行器具有未知参数情况下，使用符号计算工具对系统不确定量进行分离，实现不确定性的建模；进一步使用蒙特卡洛试验方法，确定不确定函数向量的主影响元素，对模型进行简化。然后在滑模控制的基础上，结合参数自适应估值和鲁棒补偿的方法，设计出飞行控制器，实现对未知参数的自适应估值以及对模型误差的补偿，并从理论上证明了系统的稳定性。仿真试验表明，在较大参数摄动情况下，文中所提方法依然可以保证系统的稳定性和跟踪性能。

关键词: 高超声速飞行器, 不确定性建模, 主影响元素分析, 鲁棒自适应控制

Abstract:

A robust adaptive control method based on main influence elements analysis is proposed for the hypersonic vehicles in strong parameter perturbations case during the cruise phase. Firstly, under the condition of parameter uncertainties, symbolic calculation tools are used to separate the uncertainty terms, and the uncertainty model is obtained. Furthermore, Monte Carlo method is implemented to determine the main influence elements of the uncertainty function vectors, the uncertainty model is simplified. Secondly, on the basis of the sliding mode control, a flight controller is designed combining the parameter adaptive estimation and robust compensation, then the stability of system is proved theoretically. Lastly, a detailed simulation experiment is carried out, which verifies that the flight controller can guarantee system stability and tracking performance even in case of large parameter perturbations.

Key words: Hypersonic vehicles, Uncertainty modeling, Main influence element analysis, Robust adaptive control

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