不对称机翼损伤飞机特性分析与增量容错控制（先进飞行器安全控制专栏）

李煜; 陈家鑫; 李珂澄; 溫志湧; 李霓; 刘小雄

doi:10.7527/S1000-6893.2025.32501

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DOI: https://doi.org/10.7527/S1000-6893.2025.32501

不对称机翼损伤飞机特性分析与增量容错控制（先进飞行器安全控制专栏）

李煜 ,
陈家鑫 ,
李珂澄 ,
溫志湧 ,
李霓 ,
刘小雄

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1. 西北工业大学
2. 香港理工大学

收稿日期: 2025-07-01

修回日期: 2025-09-14

网络出版日期: 2025-09-18

基金资助

国家自然科学基金;国家自然科学基金;航空科学基金

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Analysis of aircraft characteristics with asymmetric wing damage and incremental fault-tolerant control

LI Yu ,
CHEN Jia-Xin ,
LI Ke-Cheng ,
WEN Zhi-Yong ,
LI Ni ,
LIU Xiao-Xiong

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Received date: 2025-07-01

Revised date: 2025-09-14

Online published: 2025-09-18

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摘要

为了提高机翼损伤飞机的安全飞行能力，本文开展了不对称机翼损伤对飞机气动和动力学特性的影响研究，并提出一种基于快速预定义时间的增量控制方法，以增强损伤飞机的稳定恢复能力和容错控制性能。首先，借助CFD软件分析了锯齿形和穿孔形机翼损伤对飞机气动特性的影响；其次，根据损伤影响特性，建立了不对称机翼损伤飞机的非线性六自由度动力学和动力学模型，研究了三种典型损伤飞机的配平策略，并根据配平实例探讨了其适用范围；随后，改进了现有预定义时间控制理论，进一步提升了闭环系统收敛速度，解决了收敛时间和用户设定时间不匹配以及收敛边界不可调的问题。在此基础上，基于快速预定义时间理论设计了增量容错控制器，并通过Lyapunov方法证明了闭环系统在机翼损伤下的稳定性和预定义时间收敛特性；最后，通过数字仿真和实时仿真实验验证了所设计增量轨迹容错控制器的有效性，并通过对比验证了其优越性。

关键词： 不对称机翼损伤; 损伤飞机配平; 快速预定义时间控制; 增量容错轨迹控制; 实时仿真实验

本文引用格式

李煜 , 陈家鑫 , 李珂澄 , 溫志湧 , 李霓 , 刘小雄 . 不对称机翼损伤飞机特性分析与增量容错控制（先进飞行器安全控制专栏）[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32501

Abstract

To enhance the flight safety of aircraft with wing damage, this paper investigates the aerodynamic and dynamic characteristics of asymmetric wing damage and proposes an incremental fault-tolerant control method based on an improved predefined-time theory. First, CFD calculations are conducted to analyze the effects of wing-tip truncation and perforation damage on aerodynamic performance. Based on the above aerodynamic characteristics, a six-degree-of-freedom nonlinear model of the aircraft with asymmetric wing damage is established. Three representative trim strategies are then analyzed, and their applicability is discussed through comparative case studies. Subsequently, the existing prede-fined-time control theory is improved to accelerate convergence and address the mismatch between theoretical convergence time and user-defined time. On this basis, an incremental fault-tolerant controller is developed for the damaged aircraft, and the stability and predefined-time convergence of the closed-loop system under wing damage are rigorously proven using Lyapunov theory. Finally, the effectiveness and superiority of the proposed incremental trajectory fault-tolerant control scheme are validated through both numerical simulations and real-time experiments.

Key words： Asymmetric wing damage; Trim strategy of damaged aircraft; Fast predefined-time control; Trajectory incremental fault-tolerant control; Real-time simulation experiments.

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