Random Failure Model and Multi-element Damage Assessment of Long Endurance Aircrafts

doi:10.3969/j.issn.1004-132X.2021.22.002

China Mechanical Engineering ›› 2021, Vol. 32 ›› Issue (22): 2667-2672.DOI: 10.3969/j.issn.1004-132X.2021.22.002

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Random Failure Model and Multi-element Damage Assessment of Long Endurance Aircrafts

BAI Shuwei1;JIANG Nan2;TONG Mingbo3;CHANG Wenkui4

1.Shanghai Electro-Mechanical Engineering Institute,Shanghai,201109
2.Shanghai Aerospace Electronic Technology Institute,Shanghai,201109
3.College of Aerospace Engineering,Nanjing University of Aeronautics & Astronautics,Nanjing,210016
4.AVIC Aircraft Strength Research Institute,Xi'an,710065

Online:2021-11-25 Published:2021-12-09

长航时飞行器多元件随机失效模型与损伤评估

白树伟1;姜楠2;童明波3;常文魁4

1.上海机电工程研究所，上海，201109
2.上海航天电子技术研究所，上海，201109
3.南京航空航天大学航空学院，南京，210016
4.中国飞机强度研究所，西安，710065

通讯作者: 童明波（通信作者），男，1966年生，教授、博士研究生导师。研究方向为飞行器设计、金属疲劳损伤分析。E-mail:tongw@nuaa.edu.cn。
作者简介:白树伟，男，1994年生，工程师。研究方向为飞行器设计、损伤容限设计。E-mail:baishw@nuaa.edu.cn。
基金资助:
国家自然科学基金（51601175）；
航空科学基金（201928052009）

Abstract

Abstract: To evaluate the multi-element damages that occured during the aircraft services, a random failure model was established based on element fatigue characteristics, and the average behavior of widespread fatigue damages were calculated based on element failure life to determine the time for aircraft inspection and repair. The validity of the model was verified by a five-frame fuselage section example, and the influences of simulation times and distribution model on the repair time of multi-element damage structures were studied. According to the fatigue test results of the seven-frame fuselage section, multi-element damage assessment was performed, the structural inspection and repair time were given. The results show that the evaluation results are in good agreement with the calculation example data, and normal regression may better simulate structural failure characteristics.

Key words: widespread fatigue damage, multi-element damage, random failure model, fuselage frame, normal regression model

摘要： 为评估飞机服役过程中出现的多元件损伤，根据元件疲劳特性建立了随机失效模型，基于元件失效寿命计算广布疲劳损伤平均行为，从而确定飞机检查修理时刻。通过五隔框机身段算例验证所提模型的有效性，研究模拟次数及概率分布模型对多元件损伤结构检修时间的影响。根据七隔框机身段疲劳试验结果进行多元件损伤评估，给出结构检查修理时刻。结果表明，评估结果与算例数据吻合良好，正态回归模型能够更好地模拟结构失效特性。

关键词: 广布疲劳损伤, 多元件损伤, 随机失效模型, 机身框段

CLC Number:

V215.5

BAI Shuwei, JIANG Nan, TONG Mingbo, CHANG Wenkui. Random Failure Model and Multi-element Damage Assessment of Long Endurance Aircrafts[J]. China Mechanical Engineering, 2021, 32(22): 2667-2672.

白树伟, 姜楠, 童明波, 常文魁. 长航时飞行器多元件随机失效模型与损伤评估[J]. 中国机械工程, 2021, 32(22): 2667-2672.

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Random Failure Model and Multi-element Damage Assessment of Long Endurance Aircrafts

长航时飞行器多元件随机失效模型与损伤评估

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