超轻复合材料机翼结构设计及成型技术研究  

RESEARCH ON THE TECHNOLOGY OF STRUCTURE DESIGN AND FORMING OF ULTRA-LIGHT COMPOSITE WING

作　　者：王凯[1] 熊晨曦 贺强[1] WANG Kai;XIONG Chen-xi;HE Qiang(Aviation Engineering Institute Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,广汉618307

出　　处：《复合材料科学与工程》2020年第4期72-78,共7页Composites Science and Engineering

基　　金：国家自然科学基金民航联合基金(民机复合材料结构维修基础理论与实验验证,U1233202);中国民航飞行学院面上项目(基于B/S模式的桌面式虚拟机务维修训练系统研究与实现,J2015-19)。

摘　　要：在给定外形与尺寸的机翼设计要求下,进行了机翼结构设计、工艺设计、产品制造及力学性能实验研究。采用有限元分析软件,对复合材料机翼进行静力学分析,提取了主承力结构,设计了内部骨架结构。提出了“工字梁+薄蒙皮+变厚度”的结构方案,并通过碳纤维复合材料铺层设计和聚甲基丙烯酰亚胺(PMI)泡沫设计,实现机翼内部的结构制造。研究了复杂外形零件模具的设计思路,设计了中央翼盒和机翼双模具。采用模压+共胶接成型工艺方法,设计了机翼成型工艺流程。通过这种方法成功制造了机翼,并进行了力学性能测试。最终制备的机翼表面质量和外形尺寸满足要求,实现了重量轻、载荷比重大的机翼设计与制造。证明了本文结构设计及成型方法的合理性与有效性。The paper seeks to address the techniques of structural design,technological design,product manufacturing and mechanical properties of the wing with given shape and size.By using finite element analysis software,the static analysis of composite wing was carried out,the main bearing structure was extracted,and the internal skeleton structure was designed.A structural scheme of"I-beam+thin skin+variable thickness"was put forward.Through the design of carbon fiber composite material and polymethacryl imide(PMI)foam,the structure of the wing was realized.The design idea of die for complex shape parts was studied,and the central wing box and wing die were designed.The process flow of wing forming was designed by molding process and co-bonding.Through this method,the wing was manufactured successfully and the mechanical properties were tested.Finally,the surface quality and shape size of the prepared wing meet the requirements,and the design and manufacture of the wing with light weight and heavy load ratio are realized.The rationality and validity of the structure design and forming method are proved.

关 键 词：超轻复合材料机翼 强度分析 结构设计 工艺流程 载荷/质量比 

分 类 号：TB332[一般工业技术—材料科学与工程]