Synthesis, Analysis, and Design of a Novel Mechanism for the Trailing Edge of a Morphing Wing

Download

index.pdf

Date

2018-12-11

Author

Şahin, Harun Levent
Yaman, Yavuz

Metadata

Show full item record

Item Usage Stats

288
views

82
downloads

In the design and analysis of morphing wings, several sciences need to be integrated. This article tries to answer the question, “What is the most appropriate actuation mechanism to morph the wing profile?” by introducing the synthesis, analysis, and design of a novel scissor-structural mechanism (SSM) for the trailing edge of a morphing wing. The SSM, which is deployable, is created via a combination of various scissor-like elements (SLEs). In order to provide mobility requirements, a four-bar linkage (FBL) is assembled with the proposed SSM. The SSM is designed with a novel kinematic synthesis concept, so it follows the airfoil camber with minimum design error. In this concept, assuming a fully-compliant wing skin, various types of SLEs are assembled together, and emergent SSM provide the desired airfoil geometries. In order to provide the required aerodynamic efficiency of newly-created airfoil geometries and obtain pressure distribution over the airfoil, two-dimensional (2D) aerodynamic analyses have been conducted. The analyses show similar aerodynamic behavior with the desired NACA airfoils. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed, and the required torque to drive the newly-developed SSM is estimated as feasible.

Subject Keywords

Morphing wings, Kinematic synthesis, Kinematic analysis, Scissor-structural mechanisms, Scissor-like elements, Aerodynamic analysis, Dynamic force analysis

URI

https://hdl.handle.net/11511/28441

Journal

Aerospace

DOI

https://doi.org/10.3390/aerospace5040127

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Morphing wings and control surfaces: A new approach in aircraft design Yaman, Yavuz (2017-07-05) This paper details the fully morphing wings and control surfaces. The idea of morphing is particularly attractive in aircraft technologies. Various approaches like span increase, camber increase and/or decrease, twist, and sweep are finding extensive applications in aeronautical structures.
Synthesis, analysis and design of a novel mechanism for the trailing edge of a morphing wing Şahin, Harun Levent; Yaman, Yavuz; Department of Aerospace Engineering (2018) In this thesis, synthesis, analysis and design of a novel scissor-structural mechanism (SSM) with a four-bar (FB) linkage for the trailing edge of a morphing wing has been presented. The SSM, which is deployable, is created via combination of various scissor-like elements (SLEs). In order to provide mobility requirements, a FB linkage is assembled to the proposed SSM. The FB linkage is synthesized and optimized in order to give the structure required torque with a complete rotation. The SSM is designed with...
Design, Modelling and Analysis of Morphing Airfoils Köksal, Buğra; Şahin, Melin; Uzol, Oğuz; Department of Aerospace Engineering (2023-1) This study presents the design, finite element (FE) modeling and analysis of a morphing airfoil using pressure-actuated cell structures. It is aimed that the selected baseline airfoil should be capable of changing its profile to morph into a target airfoil profile. To achieve this goal, first, a NACA 0012 airfoil with a 500 mm chord and 8 mm x 8 mm outer cross-section is obtained in Altair® HyperWorks environment as a baseline airfoil. Following this, the cell actuators responsible for morphing are designed...
MODELING OF THE HAWKMOTH WING AND ITS IMPLEMENTATION IN A FOUR-BAR FLAPPING WING MECHANISM Ökmen, Aytek Altuga; Kurtuluş, Dilek Funda; Arıkan, Kutluk Bilge; Department of Aerospace Engineering (2022-2) The main aim of this study is to accurately model the wing of a hawkmoth (Manduca sexta) to implement it in a flapping wing mechanism for a micro aerial vehicle (MAV). The wing is first modeled in ANSYS/SpaceClaim then the model is verified by performing modal analysis on the finite element model (FEM) of the wing in ANSYS/Mechanical. Grid refinement study is performed on the FEM. Results of the modal analysis of the modeled wing are compared to literature results and it is seen that both results are ...
Design and analysis of an equipment rack structure of a medium transport aircraft Yalçın, Mehmet Efruz; Yaman, Yavuz; Department of Aerospace Engineering (2009) In this study, equipment rack structure for a medium transport aircraft was designed and finite element analysis of this design was performed. The equipment rack structure, which was designed for a modernization project, was positioned and dimensions were determined by regarding the geometry of primary structures of the aircraft. The structure was designed such that it satisfies the pre-defined margin of safety values. Design of the structure was prepared in Unigraphics, and the finite element modeling and ...

Citation Formats

H. L. Şahin and Y. Yaman, “Synthesis, Analysis, and Design of a Novel Mechanism for the Trailing Edge of a Morphing Wing,” Aerospace, 2018, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/28441.