摘要
某型直升机的主桨叶是金属桨叶构型,其金属大梁和后段件通过结构胶胶接在一起,若结构胶胶接强度不足,会造成后段件脱离,对直升机的飞行安全造成重大影响。为分析金属桨叶后段件与大梁的胶接强度,先计算桨叶受到的气动力、离心力等载荷,然后构建有限元分析模型,获得在正常工作状态下桨叶后段件与大梁胶接处胶层的应力分布情况,检验该处结构胶的强度是否满足使用要求。
The main blade of a certain type of helicopter is a metal blade configuration,and the metal girder and the rear part are bonded together by structural adhesive.If the structural adhesive bonding strength is insufficient,the rear part will be separated,which has a great impact on the flight safety of the helicopter.In order to analyze the adhesive strength between the rear section of the metal blade and the girder,the aerodynamic force,centrifugal force and other loads subjected to the blade were first calculated,and then the finite element analysis model was constructed to obtain the stress distribution of the adhesive layer at the adhesive joint between the rear section of the blade and the girder under normal working conditions,and to check whether the strength of the structural adhesive there meets the application requirements.
作者
潘永福
何水莲
姜天增
PAN Yongfu;HE Shuilian;JIANG Tianzeng(Changhe Aircraft Industries(Group)Corporation Ltd.,Jingdezhen 333000)
出处
《现代制造技术与装备》
2024年第9期66-69,共4页
Modern Manufacturing Technology and Equipment
关键词
胶接强度
金属桨叶
有限元分析
直升机
bonding strength
metal blades
finite element analysis
helicopter
