复合材料整体成型大后掠机翼设计与验证研究  

Research of the Design and Verification of Highly Swept-Back Wings Based on the Integral Molding of Composite Materials

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)

机构地区：[1]陆军装备部驻北京地区航空军事代表室,北京100012 [2]海鹰航空通用装备有限公司,北京100018 [3]陆军装备部驻株洲地区航空军事代表室,湖南株洲412000 [4]陆军装备部驻哈尔滨地区航空军事代表室,黑龙江哈尔滨150060

出　　处：《科技资讯》2024年第1期98-101,共4页Science & Technology Information

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.

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 

分 类 号：V279[航空宇航科学与技术—飞行器设计]