基于多源数据驱动的机体结构航线运维优化技术研究

  • 朱林刚 ,
  • 陈普会
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  • 1. 南京航空航天大学航空学院
    2. 中国商飞上海飞机设计研究院
    3. 南京航空航天大学 航空宇航学院

收稿日期: 2025-09-16

  修回日期: 2025-10-23

  网络出版日期: 2025-10-24

Research on Structural Operation and Maintenance Optimizing Technology Based on Multi-source Data Driven

  • ZHU Lin-Gang ,
  • CHEN Pu-Hui
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Received date: 2025-09-16

  Revised date: 2025-10-23

  Online published: 2025-10-24

摘要

针对大型客机机体结构的预测性及视情维护需求,基于型号研制阶段飞行试验实测载荷、全机有限元内力、结构疲损评定、适航限制项目及其维护要求等多源工程数据,采用数据清洗、样本重构、数据建模、损伤累计及运维定制优化等方法,构建大型客机机体结构航线运维的多源数据融合驱动系统。通过国内某型大型客机实际应用,解决了机体结构航线视情维护相关数据建模精度及预测效率难点,实现机翼结构关重部位的单架次“飞参-载荷-应力-损伤”快速预测,通过单架次理论损伤与置信度95%实际损伤对比,初步评估可实现某机翼下壁板蒙皮对缝细节部位长桁孔边高频涡流重复检查间隔从5000架次增加至8091架次、蒙皮孔边高频涡流重复检查间隔从5500架次增加至8900架次。

本文引用格式

朱林刚 , 陈普会 . 基于多源数据驱动的机体结构航线运维优化技术研究[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32789

Abstract

To address the predictive and condition-based maintenance requirements for the airframe structures of large passenger aircraft, a multi-source data fusion-driven system for line maintenance has been developed. This system integrates engineering data from the type development phase, including flight test-measured loads, full-aircraft finite element internal forces, structural fatigue damage assessment, airworthiness limitation items, and their associated maintenance requirements. By employing methods such as data cleaning, sample reconstruction, data modeling, damage accumulation analysis, and maintenance customization optimization, the system enables comprehensive condition-based maintenance support. Through application on a specific domestic large passenger aircraft model, it has resolved key challenges in data modeling accuracy and prediction efficiency for airframe structure maintenance. The system achieves rapid single-flight prediction of "flight parameters-loads-stress-damage" for critical wing regions. Based on comparison between theoretical damage per flight and actual damage values at 95% confidence level, preliminary estimates indicate that the repeat inspection interval for high-frequency eddy current inspections can be extended as follows: from 5,000 to 8,091 flight cycles for stringer hole edges at the skin-stringer splice details of the lower wing panel, from 5,500 to 8,900 flight cycles for skin hole edges.

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