基于飞行实测数据的机身壁板改装结构疲劳寿命预测  

Fatiguelife Assessment of Fuselage Panel Modification based on Flight Measurement

作　　者：刘福文 黄博[1] 肖迎春[1] 杨宇[1] Liu Fuwen;Huang Bo;Xiao Yingchun;Yang Yu(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an,Shaanxi,710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,陕西西安710065

出　　处：《飞行器强度研究》2024年第3期54-59,共6页Aircraft Strength Research

摘　　要：在飞机机身壁板改装过程中,结构的疲劳性能发生了变化。为了确保改装结构的安全性和可靠性,需要对结构的疲劳寿命进行评估。本文采用疲劳细节额定值(DFR)法对改装结构进行疲劳寿命评估。首先通过在改装结构上安装光纤布拉格光栅(FBG)传感器,获取了飞行过程中的实测数据。然后通过有限元分析确定疲劳关键部位,将改装前的传感器测量数据转换为改装后疲劳关键部位的数据。最后计算疲劳关键部位的DFR值,并基于线性损伤累积准则评估了关键部位的疲劳寿命。根据最终的分析结果,确定了最危险部分及其寿命,为壁板改装方案的确定提供了依据。During the modification of aircraft fuselage panel,the fatigue performance of the structure changes.In order to ensure safety and reliability of commercial aircraft,the fatigue life assessment of the modified structure is required.In this paper,the detail fatigue rating method was used for fatigue assessment.The strain information of the modified structure during flight was obtained by installing fiber Bragg grating sensors.Through the finite element analysis,the fatigue critical parts were determined and the measured data before modification were converted into the data after modification.The detail fatigue ratings of the fatigue critical parts were calculated.The fatigue life of the critical parts was evaluated based on the linear fatigue damage cumulative rule.According to the results,the most critical part was determined,which provides a basis for the determination of the modification plan of the fuselage panel.

关 键 词：飞行实测 改装结构FBG DFR 疲劳寿命预测 

分 类 号：U46[机械工程—车辆工程]