复合材料水平尾翼的后梁铺层优化研究  

Lamination optimization research on the rear spar of a composite horizontal tail

作　　者：刘嘉 吴江 张夫恩 吴道明[1,2] LIU Jia;WU Jiang;ZHANG Fuen;WU Daoming(Chongqing Aerospace Polytechnic,Chongqing 400021,China;College of Materials Science and Engineering,Chongqing University,Chongqing 400021,China)

机构地区：[1]重庆航天职业技术学院,重庆400021 [2]重庆大学材料科学与工程学院,重庆400021

出　　处：《复合材料科学与工程》2023年第11期78-83,共6页Composites Science and Engineering

基　　金：重庆市教委科学技术研究计划项目(KJQN202203009);重庆市教委科技项目(KJQN202003002)。

摘　　要：为有效降低水平尾翼的重量,合理布置铺层方式,提高复合材料的利用效率,以某型复合材料水平尾翼为研究对象,借助专业分析软件Patran&Nastran建立了水平尾翼的有限元模型,校核了水平尾翼的静强度。设计制造了水平尾翼主承力结构试验件和试验夹具,并完成试验验证,试验结果表明二者应力分布基本一致,说明有限元模型是合理的。水平尾翼承受最大过载时,主承力件后梁最大应力远远小于材料许用值,以铺层厚度为设计变量,材料应力极限为约束对后梁铺层进行优化设计。结果表明:优化后的结构重量减轻了15.75%,且强度性能满足要求。In order to effectively reduce the weight of the horizontal tail,reasonably arrange the lay-up method and improve the utilization efficiency of the composite material,the finite element model of the horizontal tail was established with the help of professional analysis software Patran&Nastran,and the static strength of the horizontal tail was calibrated.Then the test piece and test fixture of the main bearing structure of the horizontal tail are designed and manufactured,and the test verification is completed.The test results show that the stress distribution of the two methods is basically the same,which shows that the finite element model is reasonable.When the horizontal tail is bearing the maximum inertia overload,the maximum stress value of the rear spar of the main load-bearing member is far less than the allowable value of the composite material.Taking the thickness of the layer as the design variable and the material stress limit as the constraint,the layout style of the rear spar is optimized.The results show that the weight of the optimized structure is reduced by 15.75%,and the strength performance meets the requirements.

关 键 词：水平尾翼 有限元分析 试验验证 后梁 铺层优化 复合材料 

分 类 号：TB332[一般工业技术—材料科学与工程]