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This research paper presents a detailed investigation into the design and analysis of the internal structure of a fixed-wing Vertical Take-Off and Landing (VTOL) UAV using composite materials, specifically unidirectional carbon fiber and woven carbon fiber, in comparison to traditional materials such as aluminum 6061, aluminum 7075, and titanium. Using Finite Element Analysis (FEA) and Computational Fluid Dynamics (CFD), the study evaluates the performance and structural integrity of these materials. The results demonstrate significant advantages of using composite materials in UAV wing structures, including weight reduction, enhanced strength, and improved aerodynamic efficiency.

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Design and Analysis of Composite Wing Structures for Fixed-Wing VTOL UAV

  • 会议论文

  • 发表日期：

    2026年

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  • Nitish Sharma,
  • Manish Kumar Chauhan,
  • Niraj Kumar,
  • Sahil

摘要

This research paper presents a detailed investigation into the design and analysis of the internal structure of a fixed-wing Vertical Take-Off and Landing (VTOL) UAV using composite materials, specifically unidirectional carbon fiber and woven carbon fiber, in comparison to traditional materials such as aluminum 6061, aluminum 7075, and titanium. Using Finite Element Analysis (FEA) and Computational Fluid Dynamics (CFD), the study evaluates the performance and structural integrity of these materials. The results demonstrate significant advantages of using composite materials in UAV wing structures, including weight reduction, enhanced strength, and improved aerodynamic efficiency.