长航时飞行器多元件随机失效模型与损伤评估

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

中国机械工程 ›› 2021, Vol. 32 ›› Issue (22): 2667-2672.DOI: 10.3969/j.issn.1004-132X.2021.22.002

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

出版日期:2021-11-25 发布日期:2021-12-09
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）

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

摘要/Abstract

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

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

中图分类号:

V215.5

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.

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.

参考文献

［1］奚蔚,赵剑军,姚卫星.广布疲劳损伤裂纹萌生寿命概率分布分析模型［J］.中国科技论文,2016,11(5):576-580.
XI Wei, ZHAO Jianjun, YAO Weixing. Analysis Model of Probability Distribution of Crack Initiation Life for Widespread Fatigue Damage［J］. Chinese Science and Technology Paper,2016,11(5):576-580.
［2］闫晓中,王生楠,黄汉超.飞机结构发生多处损伤的概率分析方法［J］.机械强度,2012,34(6):881-885.
YAN Xiaozhong, WANG Shengnan, HUANG Hanchao. Probability Analysis Method for Multiple Damages in Aircraft Structure［J］. Mechanical Strength, 2012, 34(6):881-885.
［3］雷晓欣,王生楠,詹福宇.飞机结构WFD发生的概率分析［J］.机械科学与技术,2011,30(11):1801-1804.
LEI Xiaoxin, WANG Shengnan, ZHAN Fuyu. Probability Analysis of WFD Occurrence in Aircraft Structure［J］. Mechanical Science and Technology, 2011, 30(11):1801-1804.
［4］徐武. 飞机结构多位置损伤分析的权函数法与剩余强度预测［D］.上海：上海交通大学,2012.
XU Wu. Weight Function Method and Residual Strength Prediction for Multi-position Damage Analysis of Aircraft Structure［D］. Shanghai:Shanghai Jiaotong University, 2012.
［5］AI Y,ZHU S P,LIAO D. Probabilistic Modeling of Fatigue Life Distribution and Size Effect of Components with Random Defects［J］. International Journal of Fatigue, 2019, 126:165-173.
［6］KIM J H, THANH C D, GOANGSEUP Z. Probabilistic Fatigue Integrity Assessment in Multiple Crack Growth Analysis Associated with Equivalent Initial Flaw and Material Variability ［J］. Engineering Fracture Mechanics, 2016, 156:182-196.
［7］周俊杰,王生楠.飞机机翼壁板紧固孔细节原始疲劳质量评估［J］.西北工业大学学报,2018,36(1):91-95.
ZHOU Junjie, WANG Shengnan. Evaluation of the Original Fatigue Quality of the Fastening Hole Details of the Aircraft Wing Panel［J］. Journal of Northwestern Polytechnical University,2018,36(1):91-95.
［8］管世民, 王生楠. 多裂纹结构中的多部位/多元件相互影响因子［J］. 航空工程进展, 2011, 2(4):437-443.
GUAN Shimin, WANG Shengnan. Multi-part/Multi-element Interaction Factors in a Multi-crack Structure［J］. Advances in Aeronautical Engineering, 2011, 2(4):437-443.
［9］王传胜,张建宇,鲍蕊.飞机结构多部位损伤发生的可能性分析［J］.北京航空航天大学学报,2006,32(8):899-902.
WANG Chuansheng, ZHANG Jianyu, BAO Rui. Possibility Analysis of Damage to Multiple Parts of Aircraft Structure［J］.Journal of Beijing University of Aeronautics and Astronautics, 2006,32(8):899-902.
［10］白树伟, 姜楠, 樊俊玲,等. 疲劳裂纹扩展前缘形貌分析及数值模拟［J］.科学技术与工程, 2019, 19(1):256-260.
BAI Shuwei, JIANG Nan, FAN Junling, et al. Analysis and Numerical Simulation of Fatigue Crack Propagation Front Edge［J］. Science Technology and Engineering, 2019, 19(1):256-260.
［11］薛景川, 弓云昭. 结构初始广布疲劳损伤发生预估的概率模型［C］∥第18届全国结构工程学术会议.北京,2009:597-600.
XUE Jingchuan, GONG Yunzhao. ProbabilisticModel for Predicting the Occurrence of Structural Initial Widespread Fatigue Damage［C］∥Proceedings of the 18th National Structural Engineering Conference. Beijing, 2009:597-600.
［12］WHITTAKER I C, BESUNER P M. A Reliability Analysis Approach to Fatigue Variability of Aircraft Structures［R］. Technical Report AFML-TR-69-65, 1969.
［13］WHITTAKER I C. Development of Titanium and Steel Fatigue Variability Model for Application of Reliability Analysis Approach to Aircraft Structures［R］. Boeing Co Renton Wa Commercial Airplane Group, 1972.
［14］HERNANDES F. Widespread Fatigue Damage Evaluation for Multiple Elements Based on Probabilistic Approach［C］∥ICAF 2019—Structural Integrity in the Age of Additive Manufacturing:Proceedings of the 30th Symposium of the International Committee on Aeronautical Fatigue. Krakow, 2019:308-318.
［15］赵永翔, 王金诺, 高庆. 确定有限疲劳可靠性数据良好假设分布的一种统一方法［J］.中国机械工程, 2001,12(12):24-28.
ZHAO Yongxiang, WANG Jinnuo, GAO Qing. A Unified Method for Determining the Distribution of Good Assumptions of Finite Fatigue Reliability Data［J］. China Mechanical Engineering, 2001,12(12):24-28.
［16］姚卫星.结构疲劳寿命分析［M］.北京:科学出版社, 2019:67-68.
YAO Weixing. Analysis of Structural Fatigue Life［M］. Beijing:Science Press, 2019:67-68.
［17］LIU Haitao. WFD Evaluation of a MED-susceptible Structure Based on the Test Data［C］∥A Review of Aeronautical Fatigue and Structural Integrity Research and Application in China. Krakow, 2019:58-59.

[1]	郑捷1;刘洋1,2;童明波1. 腐蚀环境对飞机梁结构连接件疲劳寿命和裂纹扩展的影响[J]. 中国机械工程, 2019, 30(17): 2129-2134.
[2]	程军圣, 袁毅, 喻镇涛, 袁辉. 考虑平均应力效应的Tovo-Benasciutti疲劳寿命预测模型[J]. 中国机械工程, 2015, 26(2): 196-199.
[3]	严一峰, 王长武, 常研. 基于DFR法的工程结构振动疲劳寿命评定[J]. 中国机械工程, 2013, 24(6): 760-764.
[4]	黄铭敏1, 2, 左敦稳2, 黎向锋2, 汪洪峰2, 王珉2. 四轮并列式起落架焊接主起轮轴受载模型及分析[J]. 中国机械工程, 2012, 23(17): 2071-2074.
[5]	高清振, 王耀华, 张晓南. 基于样本法的某型飞机救生机构振动疲劳寿命估算 [J]. 中国机械工程, 2011, 22(2): 162-165.
[6]	龙双丽, 聂宏, 王旭亮. 灰色模型在不确定性疲劳寿命预测中的研究 [J]. 中国机械工程, 2010, 21(9): 1093-1097.
[7]	钱文学;尹晓伟;由美雁;何雪浤;谢里阳;;. 基于多轴疲劳模型的轮盘低循环疲劳寿命预测[J]. J4, 2009, 20(07): 0-881.
[8]	谢里阳. 扩展式可靠性建模方法与四元统计模型 [J]. J4, 2009, 20(24): 2969-2973.
[9]	王旭亮;聂宏;. 考虑载荷加载顺序的模糊Miner理论研究[J]. J4, 2008, 19(22): 0-2724.
[10]	王旭亮;聂宏. 基于模糊理论的疲劳寿命估算方法[J]. J4, 2008, 19(17): 0-2049.
[11]	吴富强;姚卫星;. 一个新的材料疲劳寿命曲线模型[J]. J4, 2008, 19(13): 0-1637.
[12]	王明珠;姚卫星;孙伟;. 结构随机振动疲劳寿命估算的样本法[J]. J4, 2008, 19(8): 0-888,.

长航时飞行器多元件随机失效模型与损伤评估

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

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