摘要
对复合材料进气道进行结构材料一体化设计,可提高进气道结构整体性,减少紧固件数量,使其逐步替代常规金属进气道。复合材料的铺层多样,非对称性强,各材料强度极限差异较大,基于正交各向异性的设计准则难以精确预计损伤位置及承载能力。针对复合材料进气道初始损伤预测问题,以Hashin准则为初始损伤依据,通过有限元模拟复合材料进气道纤维、基体损伤演化过程,明确失效模式,确定薄弱部位,并开展强度分析。通过试验验证结果表明,建立的分析方法能准确预测复合材料进气道初始损伤部位及损伤对应的载荷值,可用于复合材料进气道强度设计验证中。
Composite intake ducts are designed with integrated structural materials to improve the overall integrity of the intake structure,reduce the number of fasteners,and replace conventional metal intake gradually.The composite materials of aircraft inlet have various forms,with asymmetry and differences in the strength limits of each material.Conventional analysis methods based on orthogonal anisotropy design criteria are difficult to accurately predict the damage location and bearing capacity.This paper focuses on the prediction of the initial damage in composite aircraft intake,using the Hashin criterion as the initial damage basis,through finite element simulation of the fiber and matrix damage evolution process of composite intake,the failure modes are clarified,the weak areas are identified,and the strength analysis is carried out.Through experimental verification,the results show that the analysis method established in this paper can accurately predict the initial damage location and corresponding load value of composite intake,which can be used in the strength design vertfication of composite intake.
作者
卜英格
邢华璐
BU Yingge;XING Hualu(Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)
出处
《飞机设计》
2025年第5期17-21,共5页
Aircraft Design
