Concepts for morphing airfoil sections using bi-stable laminated composite structures

Diaconu, Cezar G.; Weaver, Paul M.; Mattioni, Filippo

doi:10.1016/j.tws.2007.11.002

Cited by 232 publications

(103 citation statements)

References 23 publications

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“…It is potentially suitable for a wide variety of systems, such as morphing aircraft (Yokozeki et al, 2006;Diaconu et al, 2008;Schultz, 2008), deployable structures (Lei & Yao, 2010) and mechanical switches. The studies of multi-stable structures reported in open literatures are dominated by the bi-stable unsymmetric composite laminates (Jun & Hong, 1992 Hyer, 1998;Maenghyo et al,1998;Hufenbach et al, 2002Hufenbach et al, , 2006Ren, & Parvizi-Majidi, 2003Gigliotti et al, 2004;Dai et al 2007;Etches etal., 2009).…”

Section: Conception Of Multi-stable Structuresmentioning

confidence: 99%

Finite Element Analysis of Multi-stable Structures

Dai¹,

Li²

2012

Finite Element Analysis - From Biomedical Applications to Industrial Developments

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Section: Conception Of Multi-stable Structuresmentioning

confidence: 99%

Finite Element Analysis of Multi-stable Structures

Dai¹,

Li²

2012

Finite Element Analysis - From Biomedical Applications to Industrial Developments

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“…), and several morphing structures have been investigated [9][10][11][12][13][14][15][16][17]. Most of the researches are within conceptual studies, numerical simulation without experimental demonstration, development of partial prototype, or demonstration using micro air vehicles.…”

Section: Introductionmentioning

confidence: 99%

Development of Variable Camber Morphing Airfoil Using Corrugated Structure

Yokozeki

Sugiura

Hirano

2014

Journal of Aircraft

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“…In particular, many researchers have studied the unique characteristics of bi-stability and snap through the unbalanced [0 , 90 ] composite laminate with either piezoelectric or shaped memory alloys (SMA) actuation. [7][8][9][10] However, the aerodynamic forces could be greater than the force required to snap a bi-stable composite skin from one state to another. 6) In addition, factors such as the ply angle are not well understood.…”

Section: Introductionmentioning

confidence: 99%

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

Bourchak

Dobah

2014

Trans. Japan Soc. Aero. S Sci.

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Design of morphing wings is being considered as a potential way to improve aircraft performance. Composite materials are identified as suitable candidates to achieve some of the future morphing capabilities of aircraft wings. In this work, a morphing airfoil is designed and manufactured using a woven carbon fiber reinforced plastic (CFRP) composite material and a vacuum bagging technique. The layup arrangement and stacking sequence are chosen for maximum out-of-plane deflection under the applied actuation force using finite element analysis (FEA) and composite plate bending experiments. Additionally, manual actuation loads are applied simultaneously at various feasible locations on the airfoil top surface. The morphed airfoil new shape is studied using a JavaFoil airfoil analysis program to investigate its aerodynamic characteristics in terms of lift vs. angle of attack and lift-to-drag ratio vs. angle of attack. It is found that the numbers and locations of actuation forces depend on the flight envelope stage (e.g., take-off and cruising). In general, four factors are identified to have significant effects on the maximum deflection and consequently the ease of the airfoil to morph. These factors are the ply angles, the unbalanced stacking sequence, and the number of actuation forces and their location along the airfoil skin.

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Concepts for morphing airfoil sections using bi-stable laminated composite structures

Cited by 232 publications

References 23 publications

Finite Element Analysis of Multi-stable Structures

Finite Element Analysis of Multi-stable Structures

Development of Variable Camber Morphing Airfoil Using Corrugated Structure

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

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