基于历史维修数据的飞机结构疲劳当量载荷极值反演方法

doi:10.7527/S1000-6893.2025.33034

Abstract

Abstract:

Timely and effective maintenance of aircraft structures is essential for ensuring operational safety， reducing operating costs， and extending service life. However， in current engineering practice， aircraft structural maintenance is often accompanied by a lack of complete and reliable load data， which leads to inaccurate strength and fatigue assessments of in-service aircraft structures and severely restricts subsequent structural modification and redesign. To address this inverse problem of load prediction， this paper proposes an inversion method for the extreme value of aircraft structural equivalent fatigue load based on historical maintenance data. First， historical maintenance records of aircraft structures are statistically analyzed， and the statistical fatigue life is determined by incorporating confidence and reliability assessment methods. Then， a numerical simulation model of the aircraft structure is established to obtain the predicted fatigue life under given loading conditions. Finally， an optimization framework is constructed in which the absolute difference between the predicted fatigue life and the statistical fatigue life is minimized， with the extreme value of the structural equivalent fatigue load treated as the design variable. Through iterative optimization， the structural equivalent fatigue load extreme value that best matches the actual service loading condition is identified. To verify the effectiveness of the proposed method， an aircraft kicker plate angle is selected as a case study， and the inversion results are compared with experimental data obtained from component-level fatigue tests. The results show that the prediction error of the proposed method is within 10%， demonstrating higher accuracy than conventional life prediction approaches based directly on strain data. These results indicate that the proposed method enables accurate inversion of the extreme value of aircraft structural equivalent fatigue load and provides useful guidance for aircraft structural modification design.

Key words: structural strength, extreme value of structural equivalent fatigue load, load inversion, historical maintenance data, optimization design

CLC Number:

V214.4

Qiushi XIA, Lei HUANG, Xiaobo ZHANG, Yinghui ZUO, Wenzhao WANG, Honglun XIE, Kuo TIAN. An inversion method for extreme value of structural equivalent fatigue load of aircraft based on historical maintenance data[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(14): 233034.

Figures/Tables 12

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Fig.5

Table 2

Material properties of kicker plate angle［29］

材料属性	数值
弹性模量 E/MPa	70 329
泊松比 $ν$	0.3
强度系数 K/MPa	807
应变硬化指数 n	0.200
疲劳强度系数 $σ f'$ /MPa	1 014
疲劳强度指数 b	-0.110
疲劳延性系数 $ε f'$ /%	21
疲劳延性指数 c	-0.52
循环强度系数 $K'$ /MPa	685.73
循环硬化指数 $n'$	0.08

Table 2

Fig.6

Fig.7

Fig.8

Table 3

Life data of low cycle fatigue test for kicker plate angle

应变片	最大主应变 $ε$ /10^-6	疲劳寿命预测值/cycle	基于实测应变预测寿命/cycle	试验寿命/cycle	统计模型概率密度峰值/cycle
C1	8 208.4	2 542	1 370	2 830	2 320
C2	5 376.5		8 623	3 330
C3	3 661.0		99 041
C4	4 233.3		35 554	1 930
C5	4 020.6		50 452
C6	7 310.5		2 136	1 230
C7	5 658.6		6 646	1 930
C8	6 167.4		4 410	2 380

Table 3

Fig.9

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An inversion method for extreme value of structural equivalent fatigue load of aircraft based on historical maintenance data

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