Structural Analysis of an Unconventional Hybrid Control Surface of a Morphing Wing

Date

2014-11-03

Author

Arslan, Pınar
Uğur, Kalkan
Harun, Tıraş
İlhan Ozan, Tunçöz
Yosheph, Yang
Gürses, Ercan
Şahin, Melin
Özgen, Serkan
Yaman, Yavuz

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In this study, design and analysis of a new unconventional hybrid trailing edge control surface of an unmanned aerial vehicle (UAV) wing is presented. The hybrid trailing edge control surface is composed of a compliant material and a composite material and designed by using CATIA® V5-6R2012 package program. The stiffness difference between compliant and composite parts provides the deflection of control surface and an effective camber. The required number and the location of servo motors needed to deflect control surface effectively were compared by considering the desired shape of the control surface, weight and torque optimization. The servo motor forces that gave the desired shape of the control surface were determined in-Vacuo condition by using ANSYS®v14.0 Workbench package program to perform finite element analysis (FEA). Then, the structural analysis of the control surface is performed under the aerodynamic loads which were taken from a similar study. [1] Finally, in order to demonstrate that the design is realizable, it is shown that the servo motors can fit within the control surface.

URI

https://hdl.handle.net/11511/76487

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

P. Arslan et al., “Structural Analysis of an Unconventional Hybrid Control Surface of a Morphing Wing,” 2014, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/76487.