飞机设计中发动机转子碎片非包容性设计
收稿日期: 2015-08-17
修回日期: 2015-12-01
网络出版日期: 2015-12-16
Design of uncontained engine rotor fragments failure during airplane design
Received date: 2015-08-17
Revised date: 2015-12-01
Online published: 2015-12-16
基于一种双发常规布局飞机进行飞机设计中发动机转子碎片非包容失效设计的研究,通过研究相关适航规章,以及相关咨询通告等文件,得出第3节到第7节所描述的对咨询通告AC20-128A适当裁剪的工程方法和步骤,并在实例机型设计中进行验证,缩短了飞机研制周期的同时,也表明在发动机转子碎片非包容失效事故发生后,飞机系统及机体结构等采取的设计措施、防范措施符合相关适航条例要求,也即结构剩余的强度、灾难性事件发生概率等满足AC20-128A第10条c中的定性和定量要求,表明该型实例飞机完全满足相关适航条例的要求,并获得中国民用航空局(CAAC)和美国联邦航空局(FAA)的认可。
陆入成 , 李先哲 , 李洋 , 胡文刚 , 滕超 . 飞机设计中发动机转子碎片非包容性设计[J]. 航空学报, 2016 , 37(1) : 351 -363 . DOI: 10.7527/S1000-6893.2015.0341
The design and analysis of uncontained engine rotor fragment failure is conducted based on a twin-engine normal layout airplane during airplane design.Engineering method and procedure described from section 3 to section 7,properly simplified from advisory circular AC20-128A,have been gained by studying related documents including airworthiness rules and advisory circulars,which have been used in an example airplane design progress as a dem-onstration.The airplane development circle time has been shortened by applying the engineering method and proce-dure.The results indicate that when the uncontained engine rotor fragment failure occurs,design and precautionary measures taken for systems and structures of this airplane comply with airworthiness rules,where residual structure strength and tragic failure probability comply with qualitative and quantitative requirements in section 10c of AC20-128A.This shows that the airplane complies with related airworthiness requirements,and the conformity has been accepted by Civil Aviation Administration of China(CAAC) and Federal Aviation Administration(FAA).
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