Design and Analysis of a Novel Mechanism for the Morphing of Trailing Edge of an Aircraft Wing

Şahin, Harun Levent; Yaman, Yavuz

doi:10.1051/matecconf/201818804001

Cited by 3 publications

(6 citation statements)

References 12 publications

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“…At low loads, a very prominent phenomenon is the so-called "Indentation Size Effect" (ISE), due to imperfection in tip geometry. This effect may cause deviations in the accurate measurement of hardness values [46].…”

Section: Nanomechanical Characterizationmentioning

confidence: 99%

“…With the power of the computer, the above design procedure can be expedited by perturbing the design parameters. The obtained SSMs can be compared by their errors, and the final SSM that best matches both the baseline and target curves can be selected [41,46]. Such a type of error, which originates in the design, is named "design error" and can be defined as:…”

Section: Synthesis and Design Of Scissor-structural Mechanismsmentioning

confidence: 99%

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8th EASN-CEAS Workshop on Manufacturing for Growth and Innovation

Kontis¹,

Pantelakis²

2019

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Professor Kontis is a world-leading authority in aerodynamics, wind tunnel testing, flow control, shock physics, and diagnostics. He has published 108 journal articles, 1 book on shock waves (2 volumes, published by Springer), 6 book chapters, and 176 conference papers focusing on both fundamental scientific research and practical engineering applications. He is regularly invited to publish his conference papers in Special Issues of prestigious journals. He has received continuous EPSRC funding since 2001; other sources of funding include Royal Society, EU, Nuffield Foundation, USAF, USNavy, JSPS, and the industry. He has raised over £13.5M in external funding in the last 10 years, including over 60 separate collaborative projects with industrial partners-a testament to the industrial applicability of his work. The new developed methodologies are now being adopted by industry and universities worldwide. He has given 57 invited presentations and keynote lectures to peer-reviewed conferences and international advanced schools in the USA,

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Section: Nanomechanical Characterizationmentioning

confidence: 99%

Section: Synthesis and Design Of Scissor-structural Mechanismsmentioning

confidence: 99%

8th EASN-CEAS Workshop on Manufacturing for Growth and Innovation

Kontis¹,

Pantelakis²

2019

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Section: Synthesis and Design Of Scissor-structural Mechanismsmentioning

confidence: 99%

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

Şahin

Yaman

2018

Aerospace

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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.

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“…The wing and the control surfaces studied here are those of [6]. As an example only those with SLE number = 10 are studied.…”

Section: Design Aerodynamic Modelling and Analysis Of Ssms For Chordmentioning

confidence: 99%

“…In this paper, the dynamic force analysis of a novel morphing wing trailing edge structure with various configurations of airfoil shapes are conducted. First of all, a SSM is synthesized which satisfies baseline and target airfoil shapes [6]. Then, the aerodynamic analyses of airfoil configurations are performed in 2D by XFOIL, which predicts the pressure distribution over the airfoil which can be integrated to calculate the required torque [7].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Force Analysis of a Novel Mechanism for Chord and Camber Morphing Wing Under Aerodynamic Loading

2018

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In this paper, the dynamic force analysis of a novel deployable mechanism, called as scissor-structural mechanism (SSM), for active camber and chord morphing have been presented. The mechanism is created via combination of several scissor-like-elements (SLEs). With a novel kinematic synthesis concept, various types of scissor-like-elements are assembled together to provide the desired airfoil geometries. The types (translational, polar), the number of scissor-like-elements, their orientations with respect to centerline of the airfoil and their distribution frequencies over the chord length are the design parameters, which allow designers to achieve all the possible geometric shapes. With the assumption of an existing fullycompliant wing skin, it is possible to adjust the wing profile to various desired airfoil geometries. With the help of developed computer routine, the mechanism is generated which yields the minimum possible design error. After the selection of mechanism, the position, velocity and acceleration analyses of the mechanism have been done. In order to prove aerodynamic efficiency of newly created airfoil geometries and obtain pressure distribution over the airfoil, 2D aerodynamic analyses have been done with the package program XFOIL. The flow characteristics used for the analysis are determined by the flight envelope of a generic UAV. Obtained pressure distribution is applied as the lumped force on the joints. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed in order to estimate the required torque to drive the synthesized mechanism.

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Design and Analysis of a Novel Mechanism for the Morphing of Trailing Edge of an Aircraft Wing

Cited by 3 publications

References 12 publications

8th EASN-CEAS Workshop on Manufacturing for Growth and Innovation

8th EASN-CEAS Workshop on Manufacturing for Growth and Innovation

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

Dynamic Force Analysis of a Novel Mechanism for Chord and Camber Morphing Wing Under Aerodynamic Loading

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