Validation of a smart structural concept for wing-flap camber morphing

Pecora, Rosario; Amoroso, Francesco; Amendola, Gianluca; Concilio, Antonio

doi:10.12989/sss.2014.14.4.659

Cited by 42 publications

(16 citation statements)

References 13 publications

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“…Assuming incompressible flow, the strip pressure coefficient distribution depends only on the local angle of attack given by Equation (5). It must be observed that the local value of the pressure coefficient difference between the lower and upper surfaces also depends on the 11 chord-wise position where it is calculated.…”

Section: B the Numerical Solution Proceduresmentioning

confidence: 99%

“…Morphing wings were used to adapt the wing span and airfoil camber [1]- [2], the winglet's cant and toe angles [3], to replace conventional high-lift devices [4]- [5], or even the conventional control surfaces [6]. However, the technology is still in the early stages of development, its technological readiness level is still very low, and only a few 3 concepts have sufficiently progressed to reach wind tunnel testing, and even fewer have actually been flight tested [7].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Analysis of the Aerodynamic Performance of a Morphing Wing-Tip Demonstrator Using a Novel Nonlinear Vortex Lattice Method

Gabor

Koreanschi

Botez

et al. 2016

34th AIAA Applied Aerodynamics Conference

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Section: B the Numerical Solution Proceduresmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Analysis of the Aerodynamic Performance of a Morphing Wing-Tip Demonstrator Using a Novel Nonlinear Vortex Lattice Method

Gabor

Koreanschi

Botez

et al. 2016

34th AIAA Applied Aerodynamics Conference

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“…A first remarkable distinction within the adaptive systems can be made according to two macro-groups of interest: mechanized and compliant architectures. The first one implements morphing through rigid roto-translation of linkages interconnected by kinematic chains, [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. The sizing is led so that each kinematic sub-component withstands the external stresses foreseen in the real operating conditions; the actuators and the transmission lines must allow the correct kinematic behavior of the system, ensuring the achievement of target shape-configurations.…”

Section: Introductionmentioning

confidence: 99%

Electro-Actuation System Strategy for a Morphing Flap

et al. 2018

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Within the framework of the Clean Sky-JTI (Joint Technology Initiative) project, the design and technological demonstration of a novel wing flap architecture were addressed. Research activities were carried out to substantiate the feasibility of morphing concepts enabling flap camber variation in compliance with the demanding safety requirements applicable to the next generation green regional aircraft. The driving motivation for the investigation on such a technology was found in the opportunity to replace a conventional double slotted flap with a single slotted camber-morphing flap assuring similar high lift performances—in terms of maximum attainable lift coefficient and stall angle—while lowering emitted noise and system complexity. The actuation and control logics aimed at preserving prescribed geometries of the device under variable load conditions are numerically and experimentally investigated with reference to an ‘iron-bird’ demonstrator. The actuation concept is based on load-bearing actuators acting on morphing ribs, directly and individually. The adopted un-shafted distributed electromechanical system arrangement uses brushless actuators, each rated for the torque of a single adaptive rib of the morphing structure. An encoder-based distributed sensor system generates the information for appropriate control-loop and, at the same time, monitors possible failures in the actuation mechanism. Further activities were then discussed in order to increase the TRL (Technology Readiness Level) of the validated architecture.

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“…In the current paper, it is described how the modification of wing load distribution could be tailored to achieve wing-root bending moment alleviation as a sudden increase of aerodynamic loads occurs (gust or rapid manoeuvers). The morphing aileron is made of three-segmented ribs assembled into a finger-like architecture (Pecora et al, 2014), connected through longitudinal spars to guarantee a suitable torsional rigidity. The actuation system is completely integrated within the structural body.…”

Section: Introductionmentioning

confidence: 99%

Preliminary design of an adaptive aileron for next generation regional aircraft

Amendola¹,

Dimino²,

Concilio³

et al. 2017

jtam

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Design of morphing wings at increasing TRL is common to several research programs worldwide. They are focused on the improvement of their performance that can be expressed in several ways, indeed: aerodynamic efficiency optimization, fuel consumption reduction, COx and NOx emission reduction and so on, or targeted to overcome the classical drawbacks related to the introduction of a novel technology such as system complexity increase and management of certification aspects. The Consortium for Research and Innovation in Aerospace in Quebec (CRIAQ) lunched project MD0505 that can be inserted in this crowded frame. The target of this cooperation, involving Canadian and Italian academies and a research centre, is the development of a camber "morphing aileron" integrated on an innovative full scale wing tip of the next generation regional aircraft. This paper focuses on the preliminary design and the numerical modeling of its architecture. The structural layout is, at the beginning, described in detail and furthermore, a finite element (FE) model of the entire aileron architecture is assessed and used to verify the structural integrity under prescribed operational conditions.

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Validation of a smart structural concept for wing-flap camber morphing

Cited by 42 publications

References 13 publications

Analysis of the Aerodynamic Performance of a Morphing Wing-Tip Demonstrator Using a Novel Nonlinear Vortex Lattice Method

Analysis of the Aerodynamic Performance of a Morphing Wing-Tip Demonstrator Using a Novel Nonlinear Vortex Lattice Method

Electro-Actuation System Strategy for a Morphing Flap

Preliminary design of an adaptive aileron for next generation regional aircraft

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