复合材料科学与工程 ›› 2025, Vol. 0 ›› Issue (6): 101-108.DOI: 10.19936/j.cnki.2096-8000.20250628.014

• 工程应用 • 上一篇    下一篇

混杂复合材料大展弦比机翼结构特性研究

周杨, 王军利*, 李金洋, 张升, 王佳欢   

  1. 陕西理工大学 机械工程学院,汉中 723001
  • 收稿日期:2024-04-28 出版日期:2025-06-28 发布日期:2025-07-24
  • 通讯作者: 王军利(1977—),男,博士研究生,教授,硕士生导师,研究方向为机翼气动弹性设计,wjl503@126.com。
  • 作者简介:周杨(2000—),男,硕士研究生,研究方向为机翼结构特性设计。
  • 基金资助:
    陕西省重点研发计划项目(2023-YBGY-385);陕西省自然科学基础研究计划项目(2023-JC-YB-018);陕西理工大学2024年校级研究生创新基金项目(SLGYCX2408)

Research on structural characteristics of high aspect ratio wing made of hybrid composites

ZHOU Yang, WANG Junli*, LI Jinyang, ZHANG Sheng, WANG Jiahuan   

  1. School of Mechanical Engineering, Shaanxi University of Technology, Hanzhong 723001, China
  • Received:2024-04-28 Online:2025-06-28 Published:2025-07-24

摘要: 碳/玻混杂纤维复合材料的应用使机翼的可设计性大幅提升,在满足强度要求的情况下,在基体中编入一定比例的玻璃纤维可有效提高机翼热稳定性、隔热与绝缘性能。基于有限元软件Nastran对混杂纤维复合材料大展弦比机翼结构特性进行研究,讨论铺层混杂方式与混杂比例对混杂纤维复合材料大展弦比机翼模态特性、最大变形量、应力、应变与屈曲特性的影响。结果表明:混杂纤维复合材料的混杂方式与混杂比例对大展弦比机翼的结构特性均有影响,随着碳纤维铺层体积分数逐渐增大,机翼的结构性能也逐渐提升。机翼屈曲易发生于机翼翼根靠近后缘处的蒙皮,对起主承载作用的前梁或仅对易屈曲区域进行铺层优化设计均可以提高机翼的临界屈曲载荷,但前梁铺层优化设计还能大幅提高机翼整体结构承载能力,减小机翼最大变形量。

关键词: 混杂纤维复合材料, 铺层设计, 大展弦比机翼, 结构特性, 屈曲

Abstract: The application of carbon/glass hybrid fiber composites significantly enhances the design flexibility of wings. When meeting the strength requirements, incorporating a certain proportion of glass fibers into the matrix can effectively improve the thermal stability, insulation, and dielectric properties of the wings. Using the finite element software Nastran, we investigated the structural characteristics of high aspect ratio wings made from hybrid fiber composites. The study discusses the effects of different hybridization methods and ratios on the modal characteristics, maximum deformation, stress, strain, and buckling properties of the high aspect ratio wings. The results show that both the hybridization method and ratio significantly affect the structural characteristics of the high aspect ratio wings. As the volume fraction of carbon fiber plies increases, the structural performance of the wings improves. Buckling tends to occur in the skin near the trailing edge at the wing root. Optimizing the ply design of the main load-bearing spar or only the regions prone to buckling can increase the critical buckling load of the wing. However, optimizing the ply design of the spar significantly enhances the overall load-bearing capacity of the wing and reduces the maximum deformation.

Key words: hybrid fiber composite, layer design, high aspect ratio wing, structural characteristics, buckling

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