摘要
介绍了民用飞机复合材料主结构适航取证方法。该取证方法是基于试样和组合件试验支持的分析方法,符合FAA和EASA发布的指导条例。根据FAA新近发布的资讯通报AC20-107B,给出了复合材料主结构静强度、疲劳和损伤容限符合性方法需遵循的原则。最后给出了全尺寸复合材料部件静强度、疲劳和损伤容限试验流程。研究的复合材料主结构取证方法符合适航当局颁布的适航规章和咨询通报要求。
This paper presents the approach to certification of commercial aircraft primary composite structure. The approach to certification is based on analysis supported by coupon and component test evidence in compliance with guidelines issued by the FAA and EASA. Principles of certification method- ology on static strength, fatigue and damage tolerance for primary composite structure are given herein according to AC20-107B issued by FAA recently. The paper eventually provides executable flowchart of full-scale static strength, fatigue and damage tolerance component test. The approach developed here is complying with regulations and advisory circular published by airworthiness authority.
出处
《民用飞机设计与研究》
2011年第4期24-27,61,共5页
Civil Aircraft Design & Research
关键词
适航取证
静强度
疲劳
损伤容限
复合材料结构
Certification
static Strength
Fatigue
Damage Tolerance
Composite Structure
