某型四座电动飞机复合材料机翼剪切性能试验与分析  

Testing and Analysis on Shear Properties of Composite Wing of a Four-seater Electric Aircraft

作　　者：杨康 李东辉[1,2] 郭义林 马刚[1,2] 耿昊 李群芳 薛继佳 YANG Kang;LI Donghui;GUO Yilin;MA Gang;GENG Hao;LI Qunfang;XUE Jijia(Design department,Liaoning General Aviation Academy,Shenyang 110136,China;Liaoning Key Laboratory of General Aviation,Shenyang Aerospace University,Shenyang 110136,China;Liaoning Rui-xiang General Aircraft Manufacturing Co.,Ltd,Shenyang 110136,China)

机构地区：[1]辽宁通用航空研究院设计部,沈阳110136 [2]沈阳航空航天大学辽宁通用航空重点实验室,沈阳110136 [3]辽宁锐翔通用飞机制造有限公司,沈阳110136

出　　处：《材料导报》2021年第S01期485-488,共4页Materials Reports

摘　　要：为了验证某型四座电动飞机复合材料机翼结构强度是否满足适航规定(CCAR 23-R3《正常类、实用类、特技类和通勤类飞机适航规定》)要求,本工作对该复合材料机翼的翼梁、翼肋、蒙皮、前缘、后缘的布局和铺层等结构形式,以及机翼与机翼、机翼与机身的连接形式进行了研究分析,建立了四座电动飞机全机有限元数值分析模型,并计算了在适航规定要求的限制剪切载荷下,复合材料机翼的变形和应力分布情况,最后通过全机静力试验验证了有限元模拟结果的准确性。结果表明:有限元分析和试验结果有较好的一致性;该电动飞机复合材料机翼的结构设计形式,满足适航所规定的结构强度要求。In order to verify whether the structural strength of the composite wing of a four-seater electric aircraft meets the airworthiness requirements(CCAR 23-R3 airworthiness requirements for normal,practical,special effects and commuting aircraft),this paper have studied and analyzed the structural of the composite wing,include the layout and ply of the wing beam,rib,skin,leading edge and trailing edge,and the connection form of wing-wing,wing-fuselage.And the deformation and the strain distribution of the composite wing under the limited shear load were calculated by established the finite element model of the four-seater electric aircraft.Finally,the accuracy of the finite element analysis results have been verified by the static testing of the whole aircraft.The results show that the results of the finite element analysis and the static testing were in good agreement,and the structural design of the composite wing met the structural strength requirements of the airworthiness.

关 键 词：四座电动飞机 复合材料机翼 静力试验 有限元分析 CCAR 23-R3 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]