飞机疲劳失效适航规章演变历程回顾  

Evolution History of Airworthiness Regulations for Aircraft Structural Fatigue Designs

作　　者：林建鸿 王彬文[1] Lin Jianhong;Wang Binwen(AVIC Aircraft Strength Research Institute,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所,陕西西安710065

出　　处：《航空科学技术》2022年第3期39-51,共13页Aeronautical Science & Technology

摘　　要：为了保障飞机的使用安全,与结构疲劳失效相关的适航规章已经经历了70多年的演变过程。本文以历史时序为线索,回顾了相关的适航规章在不断吸取疲劳破坏事故经验教训的过程中逐步完善的演变历史,包括:进行以安全寿命理念的疲劳设计分析;通过全机结构疲劳试验来确定飞机的使用寿命;确立破损安全的设计理念并进行静强度试验验证;为兼顾减重和保障在役飞行安全而提出的损伤容限设计与试验验证;在设计寿命内,通过试验验证来保证不会发生广布疲劳损伤破坏;(6)确定有效限制寿命(LOV),以确保飞行安全。由此明确了飞机发生疲劳损伤的影响因素,不仅涉及材料的性能表征、制造和安装工艺,也与飞机的使用状态密切相关,明确指出满足适航规章要求的核心手段是采用积木式试验方法构建试验金字塔来完成飞机结构设计的适航认证。In order to secure the operation safety of aircraft,the airworthiness regulations related to fatigue and damage tolerance have been evaluated for more than 70 years.This paper reviews the evolution history of regulation through the time line,which are based on the investigation results for various aircraft accidents,including:Conducting fatigue design based on safe-life principle;Determining the aircraft fatigue life based on full-scale fatigue test;Introducing fail-safe fatigue design principle;Updating to damage tolerance design principle to combine both side requirements from safety and weight saving;Approvaling no widespread fatigue damage within the design service goal via validations by testing results;Determination of limit of validation(LOV).It is concluded that the influence factors for aircraft fatigue damages include the aspects of material character properties,machining/assembly processes,and operation histories.The key measurements to satisfy the requirements from airworthiness regulations is to establish the testing pyramids with building block approach,and touse the testing results to validate the aircraft structural designs.

关 键 词：疲劳失效 安全寿命 破损安全 损伤容限 广布疲劳损伤 有效限制寿命 适航认证 

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]