导弹增量式自适应容错控制系统设计

方艺忠; 陆宇婷; 韩拓; 胡庆雷

doi:10.13700/j.bh.1001-5965.2021.0454

导弹增量式自适应容错控制系统设计

doi: 10.13700/j.bh.1001-5965.2021.0454

方艺忠¹,
陆宇婷²,
韩拓^{2, 3},
胡庆雷^{2, 3, ,}

1.
北京航天长征飞行器研究所试验物理与计算数学国家重点实验室, 北京 100076
2.
北京航空航天大学自动化科学与电气工程学院, 北京 100083
3.
北航杭州创新研究院(余杭), 杭州 310023

基金项目:

国家自然科学基金 61960206011

北京市自然科学基金 JQ19017

浙江省自然科学基金 LD22E050004

详细信息

通讯作者:
胡庆雷, E-mail: huql_buaa@buaa.edu.cn

中图分类号: V249.1
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- 被引次数: 0
出版历程
- 收稿日期: 2021-08-11
- 录用日期: 2021-10-29
- 网络出版日期: 2022-05-20

Design of missile incremental adaptive fault tolerant control system

FANG Yizhong¹,
LU Yuting²,
HAN Tuo^{2, 3},
HU Qinglei^{2, 3
, ,}

1.
National Key Laboratory of Science and Technology on Test Physics & Numerical Mathematics, Beijing Institute of Space Long March Vehicle, Beijing 100076, China
2.
School of Automation Science and Electrical Engineering, Beihang University, Beijing 100083, China
3.
Beihang Hangzhou Innovation Institute Yuhang, Hangzhou 310023, China

Funds:

National Natural Science Foundation of China 61960206011

Beijing Municipal Natural Science Foundation JQ19017

Zhejiang Provincial Natural Science Foundation LD22E050004

More Information

Corresponding author: HU Qinglei, E-mail: huql_buaa@buaa.edu.cn

摘要

摘要:
导弹在实际飞行中存在气动参数不确定、执行机构故障等问题，从而对导弹飞行控制系统稳定性与操控能力造成严重影响。为此，设计一种增量式自适应容错控制方法，在实现导弹安全控制的同时，兼顾姿态控制算法时效性与可靠性。建立面向控制的三通道耦合姿态动力学模型；考虑系统不确定性和执行机构故障，基于增量式动态逆方法设计导弹被动容错控制律；基于自适应滑模控制与增量式动态逆方法，设计增量式动态逆自适应容错控制律，并对系统残差进行分析比较；通过某典型全弹道姿态跟踪任务，验证舵面故障下的姿态跟踪特性。仿真结果表明：所提方法在故障未知的情况下，能够保证飞行控制系统的鲁棒性与容错能力，实现导弹的安全可靠控制。
- 导弹 /
- 容错控制 /
- 增量式动态逆 /
- 鲁棒控制 /
- 执行机构故障
Abstract:
Aerodynamic parameter uncertainties and actuator failures in missile flight will severely affect the stability and operation of the flight system. Therefore, we investigate an incremental adaptive passive fault tolerant control method to ensure safe control in missile flight as well as effectiveness and reliability of the control algorithm. A control oriented coupled attitude dynamics model was presented. In order to avoid system uncertainties and actuator failures, a passive fault tolerant control law was designed based on incremental nonlinear dynamic inversion. An incremental nonlinear dynamic inversion-based adaptive fault tolerant control law was established by combining the adaptive sliding mode control method and the incremental nonlinear dynamic inversion approach. Meanwhile, the residual of the system was analyzed and compared. A typical full trajectory attitude tracking mission was conducted to verify the control performance under actuator faults. Simulation results show that the proposed system can ensure robustness and fault tolerance without the fault diagnosis knowledge, which could eventually achieve safe and reliable flight control.
- missile /
- fault tolerant control /
- incremental nonlinear dynamic inversion /
- robust control /
- actuator fault

HTML全文

图 1 无故障时仿真情况

Figure 1. Simulation results without faults

下载: 全尺寸图片幻灯片

图 2 偏差+失效+卡死故障时仿真情况

Figure 2. Simulation results with deviation, loss of efficiency and stuck faults

下载: 全尺寸图片幻灯片

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