Decamber Morphing Concepts by Using a Hybrid Trailing Edge Control Surface

Date

2015-09-01

Author

Yaman, Yavuz
Yang, Yosheph
Arslan, Pinar
Kalkan, Ugur
Tiras, Harun
Gürses, Ercan
Şahin, Melin
Özgen, Serkan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

98
views

0
downloads

The idea of morphing is drawing extensive attention in aerospace technologies. Several different approaches like span, camber, twist, and sweep are finding applications. In this work, the concept of a trailing edge control surface which is capable of performing decamber morphing is explained. The upper and lower parts of the control surface undergo different chordwise elongations and the difference between these displacements gives rise to either camber or decamber morphing. The necessary force is achieved by the help of servo actuators. During the design, the structural analyses were done to determine the best viable options for the number of servo actuators, the location of the servo actuators, and the material properties used in the control surface. The control surface was designed of aluminum, composite and compliant materials hence was called a hybrid one. The structural analyses were conducted by using ANSYS (R) Workbench v14.0 package program. After finding the best viable design, which was made for in vacuo condition, the proposed design was also verified under the simulated aerodynamic loading. The aerodynamic loads were obtained from CFD analyses which were done with SU2 V3.2.3 open-source flow solver.

Subject Keywords

Camber morphing, Hybrid control surface, Structural analysis, Finite element method

URI

https://hdl.handle.net/11511/36033

Journal

AEROSPACE

DOI

https://doi.org/10.3390/aerospace2030482

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Modeling of the dynamic delamination of L-shaped unidirectional laminated composites Gozluklu, Burak; Çöker, Demirkan (2012-03-01) One of the widely used geometrically complex parts in advanced commercial aircraft is the L-shaped composite. Due to the sharp curved geometry, interlaminar opening stresses are induced and delamination occurs under considerable mode-mixities in L-shaped beams. Dynamic phenomena during delamination initiation and propagation of L-shaped beams are investigated using dynamic (explicit) finite element analysis in conjunction with cohesive zone methods. The 2-D model consists of 24 plies of unidirectional CFRP ...
Kinematic synthesis of flight control systems for light aircrafts Yaman, Yavuz; Soylemez, E (2002-01-01) In this paper, kinematic synthesis of a planar flight control system mechanism has been conducted for a light aircraft designed and built by TAL To achieve a simple construction, the four-bar linkages are used in the synthesis. Freudenstein's Method and Bloch's Method are utilized for analytical three and four bar position syntheses respectively. A case study of an elevator flight control system is presented.
Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing Gürses, Ercan; Yang, Yosheph; Arslan, Pinar; Kalkan, Ugur; Tıraş, Harun; Şahin, Melin; Özgen, Serkan; Yaman, Yavuz (2017-05-01) In this article, the design and analysis of a hybrid trailing edge control surface of an unmanned aerial vehicle are presented. The structural design was performed to increase and decrease the camber of the control surface to match selected airfoil profiles. The design was first analyzed with the help of finite element method to assess the morphing capability. The morphed control surface was then analyzed aerodynamically and comparisons with the original target profiles were made. According to the aerodynam...
COMPARATIVE STRUCTURAL OPTIMIZATION STUDY OF COMPOSITE AND ALUMINUM HORIZONTAL TAIL PLANE OF A HELICOPTER Arpacıoğlu, Bertan; Kayran, Altan (2019-11-11) This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS ...
Electromagnetic Scattering from Obstacles in the Near Field Region of Electrically Large Arrays Cetin, Ramazan; Aydın Çivi, Hatice Özlem; Nepa, Paolo; Manara, Giuliano (2009-09-18) In this paper, an efficient method for the analysis of electromagnetic scattering/radiation from the obstacles nearby electrically large array antennas, with nonuniform excitation, is proposed. The approach is based on the combination of a ray field representation of electrically large arrays and a DFT (Discrete Fourier Transform) based representation of array current distribution. Proposed method is applied to a 2D problem: Radiation of a linear array of 2N+1 infinitely long current elements with tapered c...

Citation Formats

Y. Yaman et al., “Decamber Morphing Concepts by Using a Hybrid Trailing Edge Control Surface,” AEROSPACE, pp. 482–504, 2015, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/36033.