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

作　　者：白树伟 姜楠 童明波[3] 常文魁[4] BAI Shuwei;JIANG Nan;TONG Mingbo;CHANG Wenkui(Shanghai Electro-Mechanical Engineering Institute,Shanghai,201109;Shanghai Aerospace Electronic Technology Institute,Shanghai,201109;College of Aerospace Engineering,Nanjing University of Aeronautics & Astronautics,Nanjing,210016;AVIC Aircraft Strength Research Institute,Xi'an,710065)

机构地区：[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　　处：《中国机械工程》2021年第22期2667-2672,共6页China Mechanical Engineering

基　　金：国家自然科学基金(51601175);航空科学基金(201928052009)。

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。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.

关 键 词：广布疲劳损伤 多元件损伤 随机失效模型 机身框段 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]