摘要
根据机翼设计及材料工程力学性能要求,基于给定的机翼外形设计并制造了一种满足工程应用要求的全复合材料整体模压成型机翼结构。通过有限元仿真分析和工程静力学试验方法对该机翼结构进行了全面验证,有限元仿真分析结果与工程静力学试验结果吻合良好,满足复合材料工程力学许用值要求及机翼最大变形不大于半翼展长8%的刚度设计需求,该机翼的力学承载性能得到了充分验证。
According to the requirements of wing design and the engineering mechanical properties of materials,this paper designs and manufactures a kind of wing structure made of the integral molding of all-composite materials which meets the requirements of engineering application based on the shape of the given wing.This paper comprehensively verifies the structure of the wing by the methods of finite element simulation analysis and engineering statics tests.The results of finite element simulation analysis are well consistent with the results of engineering statics tests,which satisfies the requirement of the engineering mechanical allowable value of composite materials and the stiffness design requirement that the maximum deformation of the wing is not more than the 8%of the span length of the half wing.The mechanical bearing capacity of the wing has been fully verified.
作者
蒋建军
何利军
何建
赵琛
JIANG Jianjun;HE Lijun;HE Jian;ZHAO Chen(Aviation Military Representative Office of Army Equipment Department in Beijing Area,Beijing,100012 China;Seahawk General Aviation Equipment Co.,Ltd.,Beijing,100018 China;Aviation Military Representative Office of Army Equipment Department in Zhuzhou Area,Zhuzhou,Hunan Province,412000 China;Aviation Military Representative Office of Army Equipment Department in Harbin Area,Harbin,Heilongjiang Province,150060 China)
出处
《科技资讯》
2024年第1期98-101,共4页
Science & Technology Information
关键词
复合材料
大后掠机翼
整体成型
有限元分析
力学试验
Composite materials
Highly swept-back wing
Integral molding
Finite element method
Mechanical test