不对称机翼损伤飞机特性分析与增量容错控制

doi:10.7527/S1000-6893.2025.32501

Abstract

Abstract:

To enhance the flight safety of aircraft with wing damage， this paper investigates the effect of asymmetric wing damage on aerodynamic and dynamic characteristics of aircraft and proposes an incremental fault-tolerant control method based on an improved predefined-time theory， thereby improving stability recovery and fault-tolerant performance. First， the effects of wing-tip truncation and perforation damage on aerodynamic performance are analyzed using CFD software. Second， based on the aerodynamic characteristics of damage effects， a six-degree-of-freedom nonlinear model of the aircraft with asymmetric wing damage is established. Three representative trim strategies are then investigated， and their applicability is discussed through case studies. Subsequently， the existing predefined-time control theory is improved to accelerate closed-loop system convergence and address the mismatch between theoretical convergence time and user-defined time. On this basis， an incremental trajectory 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 simulation experiments.

Key words: asymmetric wing damage, trim strategy of damaged aircraft, fast predefined-time control, incremental trajectory fault-tolerant control, real-time simulation experiments

CLC Number:

V249.1

Yu LI, Jiaxin CHEN, Kecheng LI, Chi-Yung WEN, Ni LI, Xiaoxiong LIU. Characteristic analysis of aircraft with asymmetric wing damage and incremental fault-tolerant control[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(9): 532501.

Figures/Tables 22

Fig.1

Table 1

Variation of aircraft mass characteristics under different wing damages

类型	左侧机翼面积损失/%	质量m_d/ $k g$	$I x x$ / $(k g ∙ m 2)$	$I y y /$ $(k g ∙ m 2)$	$I z z$ / $(k g ∙ m 2)$	$I x y$ / $(k g ∙ m 2)$	$I x z$ / $(k g ∙ m 2)$	$I y z$ / $(k g ∙ m 2)$
正常情况	0	18.400	0.52	3.552	4.006	0	0.119 6	0
锯齿形损伤1	3.6	18.379	0.51	3.55	3.993	-0.005	0.119 7	1.88×10^-4
锯齿形损伤2	16.8	18.319	0.486	3.544	3.964	-0.016	0.119 9	6.91×10^-4
锯齿形损伤3	32.9	18.227	0.459	3.537	3.932	-0.029	0.120 3	0.001
锯齿形损伤4	47.5	18.086	0.429	3.531	3.894	-0.042	0.120 7	0.002
孔洞形损伤1	2.3	18.348	0.515	3.551	3.999	-0.002	0.119 7	2.49×10^-4
孔洞形损伤2	2.3	18.363	0.511	3.55	3.995	-0.004	0.119 8	2.66×10^-4
孔洞形损伤3	2.3	18.376	0.509	3.549	3.993	-0.005	0.119 7	2.12×10^-4

Table 1

Fig.2

Fig.3

Fig.4

Fig.5

Table 2

Limitations of actuators

执行机构	速率限制/（（°）·s^-1）	位置限制/（°）
$δ e$	［-60，60］	［-25，25］
$δ a$	［-80，80］	［-21.5，21.5］
$δ r$	［-120，120］	［-30，30］

Table 2

Table 3

Parameters of incremental trajectory fault-tolerant controller

组成	参数
FPTF	$m 1, m 3, m 5 = 0.8, n 1, n 3, n 5 = 1.3, T p f = 0.2, l ¯ 1 = 2, l ¯ 3 = 1.2, l ¯ 5 = 3$
容错控制器	$φ = 0.4, ζ = 0.1, m 2 = 0.5, n 2 = 1.8, m 4 = 1, n 4 = 3, m 6 = 0.9, n 6 = 1.5, m 7 = 0.8, n 7 = 2, m 8 = 0.8, n 8 = 2, T p 1 = 1, T p 2 = 1.5, T p 3 = 3.5, T p 4 = 3, T p 5 = 8$

Table 3

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Characteristic analysis of aircraft with asymmetric wing damage and incremental fault-tolerant control

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