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

夏秋实; 黄蕾; 张小波; 左迎荟; 王文照; 谢洪轮; 田阔

doi:10.7527/S1000-6893.2025.33034

航空学报 >

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DOI: https://doi.org/10.7527/S1000-6893.2025.33034

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

夏秋实 ,
黄蕾 ,
张小波 ,
左迎荟 ,
王文照 ,
谢洪轮 ,
田阔

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1. 大连理工大学
2. 南航股份公司工程技术分公司沈阳基地
3. 中国商飞上海飞机设计研究院

收稿日期: 2025-11-03

修回日期: 2025-12-30

网络出版日期: 2026-01-09

基金资助

国家自然科学基金;辽宁省人工智能领域科技创新项目;陕西省自然科学基础研究计划;辽宁省优秀青年基金;中央高校基本科研业务费

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

XIA Qiu-Shi ,
HUANG Lei ,
ZHANG Xiao-Bo ,
ZUO Ying-Hui ,
WANG Wen-Zhao ,
XIE Hong-Lun ,
TIAN Kuo

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Received date: 2025-11-03

Revised date: 2025-12-30

Online published: 2026-01-09

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摘要

对航空装备结构进行及时有效的维修，是保障装备安全性、降低运营成本、提升服役寿命的重要手段。然而，当前航空装备结构维修普遍存在载荷数据缺失问题，导致服役飞机结构强度评估不准，严重制约后续的结构改装设计。为解决载荷预测这一反问题，提出了一种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。首先，统计分析飞机结构历史维修记录，结合置信度和可靠度方法确定统计寿命；然后，建立飞机结构的仿真模型，计算得到结构疲劳寿命预测值；最后，建立最小化疲劳寿命预测值与统计寿命的绝对差值为目标、结构疲劳当量载荷极值为设计变量的优化框架，通过优化迭代获得最匹配实际受载的结构疲劳当量载荷极值。为验证方法有效性，以飞机角片结构为例开展验证，并将反演结果与试验数据进行对比。结果表明，该方法预测值与试验结果的误差在10%以内，相比基于应变数据直接预测寿命的方法具有更高精度，表明提出方法可实现飞机结构疲劳当量载荷极值精准反演，对于航空装备结构改装设计具有指导意义。

关键词： 结构强度; 疲劳当量载荷极值; 载荷反演; 历史维修数据; 优化设计

本文引用格式

夏秋实 , 黄蕾 , 张小波 , 左迎荟 , 王文照 , 谢洪轮 , 田阔 . 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[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.33034

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 simu-lation 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 statisti-cal fatigue life is minimized, with the extreme value of the equivalent fatigue load treated as the design variable. Through iterative optimization, the 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

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