Evaluating the Impact of Morphing Technologies on Aircraft Performance

Bowman, Jason C.; Sanders, Brian; Weisshaar, Terrence A.

doi:10.2514/6.2002-1631

Cited by 116 publications

(58 citation statements)

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“…In this case, large and distributed deformation of specific parts of the wing body are achieved by generating proper internal forces ( . In order to reach this objective, leading and trailing edges have to be designed to withstand the external loads and undertake dramatic deformations, following the selected flight regime requirements ( Ref 7,8). Large displacement capabilities associated with load bearing capacities is the paradox which the smart or adaptive structure systems have to overcome in order to provide a reliable alternative to classical devices.…”

Section: Introductionmentioning

confidence: 99%

A Novel SMA-based Concept for Airfoil Structural Morphing

Barbarino

Pecora

Lecce

et al. 2009

J. of Materi Eng and Perform

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The adaptive structures concept is of great interest in the aerospace field because of the several benefits which can be accomplished in the fields including noise reduction, load alleviation, weight reduction, etc., at a level in which they can be considered as compulsory in the design of future aircraft. Improvements in terms of the aerodynamic efficiency, aeroelastic behavior, stability, and manoeuvrability performance have already been proved through many international studies in the past. In the family of the Smart Materials, Shape Memory Alloys (SMA) seem to be a suitable solution for many static applications. Their high structural integrability in conjunction with actuation capabilities and a favorable performance per weight ratio, allows the development of original architectures. In this study, a morphing wing trailing edge concept is presented; morphing ability was introduced with the aim of replacing a conventional flap device. A compliant rib structure was designed, based on SMA actuators exhibiting structural potential (bearing external aerodynamic loads). Numerical results, achieved through a FE approach, are presented in terms of trailing edge induced displacement and morphed shape.

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Section: Introductionmentioning

confidence: 99%

A Novel SMA-based Concept for Airfoil Structural Morphing

Barbarino

Pecora

Lecce

et al. 2009

J. of Materi Eng and Perform

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“…Due to power requirements of actuators to change the shape of the wings, wing morphing methods were largely abandoned [1]. Recently, flexible and morphing wing research and technology has renewed interest, and promises to greatly enhance performance of aircraft [2], [3]. A continuous morphing design can achieve a greater variety of desired wing shapes and more precise camber control while simultaneously reducing friction and discontinuities introduced by traditional actuators such as rudders and flaps.…”

Section: Introductionmentioning

confidence: 97%

A model based feedback controller for wing-twist via piezoceramic actuation

Ray

Batten

Singler

2011

Proceedings of the 2011 American Control Conference

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In this paper we present a model for a rubber plate with piezoceramic actuators to represent a bioinspired flexible wing. Using a Galerkin based finite element approximation to the system, we compute a linear quadratic based tracking control for piezoelectric actuators placed along both leading and trailing edges. Using these piezoceramic devices, we demonstrate the effectiveness of model based feedback control in achieving a desired wing tip position; this modified shape is analogous to aircraft roll moment generation via wing twist.

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“…The Global Hawk, and therefore the LRN1015, has more advanced flaps, but plain flaps are sufficient for this initial investigation. The flap was hinged at 70% chord, 50% relative height, and deflected over the interval [6 • , 4…”

Section: Maneuver Comparison Of Flap Versus Camber-controlledmentioning

confidence: 99%

Use of XFOIL in design of camber‐controlled morphing UAVs

Lafountain

Cohen

Abdallah

2012

Comp Applic In Engineering

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ABSTRACT:The standard curriculum for Aerospace Engineering students at the University of Cincinnati includes AEEM361 Integrated Aircraft Engineering. The goal of this course is to instruct students in the tools and methodology of aircraft design. The integrated aspects of aircraft design are underscored by introducing prejunior (between sophomore and junior) students to the state-of-the-art morphing technology, inspired by bat and bird flight, which can enable an aircraft to adapt its shape to best suit the flight condition thereby enhancing mission performance. In this article, we present the development of unique software tools, which provide undergraduates an opportunity to design airfoils for morphing aircraft. Morphing is introduced in the form of "on demand" camber as well as sweep change with the aim of improving aerodynamic efficiency for a multiobjective (several design points) mission profile. The Global Hawk UAV mission in general and its LRN1015 airfoil in particular is in focus due to the relative long mission times spent at the two different flight conditions, namely high-speed dash and low-speed loiter. We are using several tools to virtually simulate a morphing wing including XFOIL to perform fast and relatively accurate two-dimensional steady-flow simulations of different morphed configurations using a camber-controlled morphed wing to maneuver. In this article we detail AeroMorph, the educational MATLAB-based tool developed for design of a camber-controlled morphing of airfoils with the aim of improving aerodynamic efficiency and exploration of the basic relationships between flap deflection and airfoil morphing based on a camber change.

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Evaluating the Impact of Morphing Technologies on Aircraft Performance

Cited by 116 publications

References 0 publications

A Novel SMA-based Concept for Airfoil Structural Morphing

A Novel SMA-based Concept for Airfoil Structural Morphing

A model based feedback controller for wing-twist via piezoceramic actuation

Use of XFOIL in design of camber‐controlled morphing UAVs

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