Journal of Zhejiang University-SCIENCE A

, Volume 20, Issue 10, pp 781–793

Structural design and analysis of a composite wing with high aspect ratio

• Yu-shan Meng
• Li Yan
• Wei Huang
• Tian-tian Zhang
• Zhao-bo Du
Article

Abstract

Wings with large aspect ratio have large bending moment and torque, so the poor flexural and torsional stiffness are noteworthy. The application of composite materials in wing structure can improve the performance of wing. In the design process of the wing with high aspect ratio, the design parameters of the wing are preliminarily set. Then, the wing configuration is determined according to the force characteristics referring to the indexes of the Predator unmanned aerial vehicle (UAV), and on the basis of the composite material mechanics and finite element theory, the finite element model of the wing is designed as well. Next, we carry out the aerodynamic analysis in FLUENT. At last, we use ANSYS Composite Pre/Post (ACP) module to establish the static analysis of the wing, and two improvement schemes are proposed to deal with the problem that the wing with high aspect ratio would encounter.

Key words

Composite High-aspect-ratio wing Structural design Finite element static analysis

大展弦比复合材料机翼结构设计与分析

摘要

创新点

1. 通过流固耦合的方法对大展弦比机翼进行气动 仿真和有限元静力分析; 2. 针对大展弦比机翼产 生的大变形现象, 提出增加机翼外挂或在翼尖处 增加翼尖小翼的方法进行改进.

方 法

1. 通过数值仿真建立机翼的有限元模型, 并对机 翼进行气动分析; 2. 通过流固耦合, 将在FLUENT 中的气动力加载到有限元静力分析模块进行分 析; 3. 通过Workbench 中的ACP 复合材料专用模 块, 对复合材料结构进行铺层.

结 论

1. 综合考虑刚度、强度以及减重效果, 确定12 mm 为本文大展弦比复合材料机翼的最佳蒙皮厚度; 2. 利用增加外挂的方法减小机翼大变形时, 当外 挂重心位置在机翼重心线前 15%时机翼变形减 小的程度最大; 3. 在翼尖处增加高度为300 mm 的翼尖小翼时机翼变形减小程度最大. 4. 在相同 受载情况下, 相比于金属材料机翼, 复合材料机 翼结构能够有效减小机翼的翼尖最大位移和最 大应力.

V22

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© Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2019

Authors and Affiliations

• Yu-shan Meng
• 1
• Li Yan
• 1
Email author
• Wei Huang
• 1
• Tian-tian Zhang
• 1
• Zhao-bo Du
• 1
1. 1.College of Aerospace Science and EngineeringNational University of Defense TechnologyChangsha, HunanChina