某型无人机复合材料机翼大梁准等强度设计与有限元分析  

Quasi-Equal Strength Design and Finite Element Analysis for Composite Wing Beam of X UAV

作　　者：刘峰[1] 马佳[1] 张春[1] 喻辉[1] 

机构地区：[1]中国民用航空飞行学院航空工程学院,四川广汉618307

出　　处：《机械设计与制造》2015年第6期59-62,共4页Machinery Design & Manufacture

基　　金：国家自然科学基金民航联合基金重点项目(U1233202/F01);民航局科技项目重大专项(MHRD201240);中国民用航空飞行学院成果转化与创新基金项目(CJ2013-02);国家级大学生创新创业训练项目(201310624034)

摘　　要：以某型无人机复合材料机翼工字型大梁准等强度设计与优化为目标,研究了复合材料工字梁基于载荷分段的设计方法与铺层优化方法。计算了机翼大梁弯矩方程,采用等步长载荷包络方法给出了准等强度大梁的载荷分布,计算了缘条和腹板的内力方程。基于复合材料层合结构设计的基本原则,采用经典层合板理论对大梁进行了初步铺层设计。以结构强度、刚度、稳定性作为约束条件,综合考虑最小重量要求,在分段包络安全载荷作用下对工字梁铺层进行了分段优化设计。建立了工字梁的有限元模型,基于有限元分析结果校核了工字梁的强度、刚度和稳定性。研究结果表明:采用等步长载荷包络方法能够方便地计算非均布弯矩作用下机翼大梁的准等强度设计载荷;基于经典层合板理论进行工字梁铺层初步设计,建立工字梁有限元模型能够有效、快速地对工字型机翼大梁在分段包络安全载荷作用下的铺层进行分段优化设计,同时完成大梁的强度、刚度与稳定性校核;大梁结构减重可达29%;铺层设计时必须考虑受压缘条和受剪切腹板的稳定性问题,否则大梁根部高应力区会出现局部屈曲。Research on design and layer optimization method of an unmanned aerial vehicle composite I-beam is carried out based on load segmentation envelope method. The bending moment function of the wing I-beam is giver The load segmentation distribution of the semi equi-strength I-beam/s calculated using load envelope method with constant step width, The internal force functions of the strip and web of the beam are determinated. The initial layer structure of the beam is designed based on fundamental principles of laminate structure design and the classical laminated plate theory. The layer structure of the segmented beam is optimized under the segmented safety load envelope considering the strength, stiffness, stability and lowest--weight requirements. The finite element model of the beam is builL The strength, stiffness and stability of the beam are checked based on the results of finite element analysis. It is showed that it＇s very convenient to calculate the design safety load envelope of the semi equi-strength I-beam using load segmentation method with constant step widtb The layer structure optimization of the segmented I-beam can be done efficiently based on initial layer design using the classical laminated plate theory and finite element analysis. The weight of the beam can be cut down by 29%. The stability prablerns af the beam strip under compression and the web under shearing must be considered to avoid local bucklin at the beam root reion which is in high stress level

关 键 词：无人机 复合材料 机翼 工字梁 优化设计 有限元 

分 类 号：TH16[机械工程—机械制造及自动化] V215[航空宇航科学与技术—航空宇航推进理论与工程]