CAJ | 학술논문

针对飞机结构安全寿命分析中样本容量偏少的问题，综合考虑结构分散性和载荷分散性的飞机结构疲劳寿命是否服从对数正态分布或威布尔分布的情况，根据等损伤原理，将服役飞机实际飞行小时数等效转化为在同一试验载荷谱下的当量飞行小时数，以实现飞机结构试验疲劳寿命与服役使用数据的融合，采用随机右截尾情形下的极大似然估计方法估算疲劳寿命分布函数的参数，进行飞机结构安全寿命分析；最后以飞机结构疲劳寿命服从对数正态分布为例进行了算例分析，分析结果表明：在相同的可靠度和置信水平下，利用试验数据与服役使用数据融合方法可以显著增大样本容量，从而充分挖掘飞机结构可靠性的储备。
침대비궤결구안전수명분석중양본용량편소적문제，종합고필결구분산성화재하분산성적비궤결구피로수명시부복종대수정태분포혹위포이분포적정황，근거등손상원리，장복역비궤실제비행소시수등효전화위재동일시험재하보하적당량비행소시수，이실현비궤결구시험피로수명여복역사용수거적융합，채용수궤우절미정형하적겁대사연고계방법고산피로수명분포함수적삼수，진행비궤결구안전수명분석；최후이비궤결구피로수명복종대수정태분포위례진행료산례분석，분석결과표명：재상동적가고도화치신수평하，이용시험수거여복역사용수거융합방법가이현저증대양본용량，종이충분알굴비궤결구가고성적저비。
This paper mainly discusses how to reconcile the test results with the service data to solve fatigue safe-life of aircraft structure.Aimed at the fatigue life obedient to the Log-normal distribution or Weibull distribution,the service flying hours and test results can be reconciled directly to analyze the reliability for the aircraft structure.Aimed at the fatigue life disobedient to the Log-normal distribution or Weibull dis-tribution,the service hours can be transformed into the equivalent flying hours at the same test load spec-trum according to the equal damage to realize the fusion of the test data and the service data.The parame-ters of fatigue safe-life distribution function can be estimated by using the method of maximum likelihood function in accordance with the fusion data.The fatigue safe-life for aircraft structure is analyzed by using the estimated parameters and the fusion data.The result shows that the sample capacity is increased obvi-ously after the data fusion,and the life reserve of reliability is excavated adequately by adopting the meth-od of the fusion data under the conditions of the same reliability and confidence level.