民机APU安装系统损伤容限符合性方法研究  

Methods of Compliance for Damage Tolerance of Civil Aircraft APU Mount System

作　　者：张发富[1] 李翠超[2] 张强[1] 银未宏[1] 唐力[1] 

机构地区：[1]上海飞机设计研究院,上海201210 [2]上海交通大学,上海200240

出　　处：《装备制造技术》2016年第5期68-71,共4页Equipment Manufacturing Technology

摘　　要：近年来适航局方对FAR25.571条款的态度趋于严格,提出APU安装系统需按照FAR25.571(b)要求的损伤容限进行设计,这对新型飞机APU系统的研制带来较大的重量、进度和成本影响。为了解决这一分歧,对该条款和相关咨询通告进行了深入研究,对APU系统进行了安全性分析,统计了近二十年来APU系统相关的航线故障,并调研了以往机型的符合性方法和检查要求,以确定APU安装对FAR25.571的符合性方法。通过研究表明:APU安装系统结构失效不会对安全续航及着陆造成安全隐患,一般只通过疲劳分析和/或试验的方法保证其在整个飞机寿命期内不发生疲劳破坏,不需要基于裂纹扩展的损伤容限分析符合FAR25.571(b)条款。Recently,airworthiness authority has became more strictly toward FAR25.571 regulation,presented that APU mount system should be designed according to DT（damage tolerance） requirement for FAR 25.571（b）. This proposal has great influence on weight,schedule and cost of new aircraft APU system. In order to solve this disagreement and determine the APU mount system＇s method of compliance for FAR25.571. This regulations and relative advisory circular has been furtherresearched. Safety analysis to APU system has been conducted,statistic analysis of APU related aircraft safety hazard in the recent two decade has been completed,and former aircraft method of compliance and inspection requirement has been investigated. The result show that structural failure of APU mount system doesn＇t cause hidden danger to flight and landing. In general,only fatigue analysis and/or test is required to avoid fatigue rupture during airplane service life. Iit isn＇t required to conduct damage tolerance analysis based on crack growth for FAR25.571（b）.

关 键 词：损伤容限 疲劳分析 适航符合性方法 APU安装系统 主要结构件 安全性分析 

分 类 号：V221[航空宇航科学与技术—飞行器设计]