Structural analysis of an unmanned aerial vehicle wing made of composite materials


Authors

DOI:

https://doi.org/10.22517/23447214.24535

Keywords:

wing design, composites, aeronautic structures, finite element analysis

Abstract

Composite materials are widely used in aerospace applications due to their good mechanical properties such as low density and good resistance, due to their versatility it is possible to design different configurations making it difficult to find the optimal option. The objective of this work is to compare different laminates on the wing surface, the advantage of using structural elements such as spars and ribs, also to see the influence on the results of different load simplifications. In the study, the finite element analysis technique is used to find the best characteristics regarding resistance, deformation, and failure modes under the established conditions. The analysis showed that the best load simplification is a decreasing distributed load along the pressure center, the best surface laminate is [45/0/0/45] with carbon fiber cloth with a maximum displacement of 15.27 mm, the spar presented a 29.6% decrease in maximum displacement and the ribs did not represent a significant change in the structural response.

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Author Biography

Octavio Andrés González-Estrada, Universidad Industrial de Santander

Profesor planta Escuela de Ing. Mecánica Universidad Industrial de Santander

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Published

2021-09-30

How to Cite

González-Estrada, O. A., León Becerra, J. S., Correa-Rivera, A. F., Martínez, M. del J., & Rodríguez Ferreira, J. G. (2021). Structural analysis of an unmanned aerial vehicle wing made of composite materials. Scientia Et Technica, 26(03), 278–289. https://doi.org/10.22517/23447214.24535

Issue

Vol. 26 No. 03 (2021): Julio-Septiembre

Section

Mecánica

License

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