战斗机进气道结构声疲劳设计方法  

Acoustic fatigue design method for fighter inlet structure

作　　者：牟彬杰 蒋劲松[1] 杨堃 付焕兵 孟德虹[3] 金伟[1] Binjie MOU;Jinsong JIANG;Kun YANG;Huanbing FU;Dehong MENG;Wei JIN(AVIC Chengdu Aircraft Design&Research Institute,Chengdu 610091,China;Aircraft Strength Research Institute of China,Xi’an 710000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]航空工业成都飞机设计研究所,成都610091 [2]中国飞机强度研究所,西安710000 [3]中国空气动力研究与发展中心,绵阳621000

出　　处：《航空学报》2024年第14期258-269,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：先进战斗机S型进气道的内流场分离使进气道薄壁结构承受严重的振动噪声载荷,对进气道蒙皮及支撑结构的声疲劳寿命影响极大,增加了战斗机的维护维修成本。因此,S型进气道结构抗声疲劳动强度设计是新一代先进战斗机的设计难点。针对战斗机进气道结构声疲劳问题,从气动噪声预计、声振耦合动响应分析方法、进气道有限元快速建模方法以及结构声疲劳寿命预计等方向开展了系统的研究,建立了进气道抗声疲劳设计方法,并通过试验验证,分析结果与试验一致性良好,为战斗机进气道结构强度设计提供了有效的技术手段。The thin-walled structure of an advanced fighter inlet experiences severe vibration and noise loads due to the internal flow field separation in the S-shaped inlet,resulting in limited fatigue life of the inlet skin and supporting structure and thus increased maintenance cost.Therefore,the S-shaped inlet design against acoustic fatigue is a key challenge in the structural design of next-generation fighters.This study establishes a design method to combat inlet acoustic fatigue based on an analysis of the aerodynamic noise prediction method,the acoustic-vibration coupling analysis method,the fast finite element inlet modeling method,and acoustic fatigue life prediction.The proposed method is verified by experiments,with results demonstrating good agreement with the analysis results,and provides an effective technical means for the dynamics strength design of fighter inlet structures.

关 键 词：S型进气道 声疲劳 气动噪声预计 声振耦合 寿命预计 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]