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本文介绍了损伤容限分析流程,结合NASGRO裂纹扩展分析软件,给出机身壁板纵向搭接结构的裂纹扩展分析方法。概述中国民用航空规章CCAR25部和美国联邦航空条例FAR25部等各国的适航条例均明确规定,新研制的民用飞机必须按损伤容限设计,除非损伤容限无法实现。NASGRO软件由NASA、Southwest Research Institute等机构共同开发,FAA认可,并被全球航空宇航领域的客户广泛采用的一款断裂力学和疲劳裂纹扩展分析软件。本文把机身壁板纵向搭接结构的典型开裂模式,
In this paper, the damage tolerance analysis process is introduced. Combined with NASGRO crack propagation analysis software, the crack propagation analysis method of the longitudinal lap joint structure of fuselage panels is given. Overview China’s civil aviation regulations CCAR25 and the United States Federal Aviation Regulations FAR25 and other countries Airworthiness Regulations clearly stipulated that newly developed commercial aircraft must be designed to damage tolerance, unless the damage tolerance can not be achieved. NASGRO software was developed by NASA, Southwest Research Institute and other institutions, the FAA approved, and is widely used by customers worldwide aerospace crack mechanics and fatigue crack growth analysis software. In this paper, the fuselage longitudinal splice structure of the typical cracking mode,