Toward the bi-modal camber morphing of large aircraft wing flaps: the CleanSky experience

Pecora, Rosario; Amoroso, Francesco; Magnifico, Marco

doi:10.1117/12.2218415

Cited by 13 publications

(13 citation statements)

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“…With this regard relatively high Technology Readiness Level (TRL) projects, targeting current industrial airliners at true scale, were undertaken. The European research programs SARISTU 8 and CleanSky 9 have work packages dealing with morphing wing trailing edge devices, Dimino et al (2016) and Pecora et al (2016). Another trailing edge morphing concept, called Adaptive Compliant Trailing Edge, was developed by NASA in cooperation with FlexSys Inc. 10 This concept features an adjustable structure which can be actively deformed.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of a hybrid morphing wing with active open loop vibrating trailing edge by time-resolved PIV and force measures

Jodin

Motta

Scheller

et al. 2017

Journal of Fluids and Structures

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et al.. Dynamics of a hybrid morphing wing with active open loop vibrating trailing edge by Time-Resolved PIV and force measures.This is an author-deposited version published in: http://oatao.univ-toulouse.fr/ Eprints ID: 16095Open Archive Toulouse Archive Ouverte (OATAO)OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. Keywords:Morphing Smart materials Wind tunnel experiments Vortex breakdown Harmonic forcing a b s t r a c t A quantitative characterization of the effects obtained by high frequency-low amplitude trailing edge actuation is presented. Particle image velocimetry, pressure and aerodynamic forces measurements are carried out on a wing prototype equipped with shape memory alloys and trailing edge piezoelectric-actuators, allowing simultaneously high deformations (bending) in low frequency and higher-frequency vibrations. The effects of this hybrid morphing on the forces have been quantified and an optimal actuation range has been identified, able to increase lift and decrease drag. The present study focuses more specifically on the effects of the higher-frequency vibrations of the trailing edge region. This actuation allows manipulation of the wake turbulent structures. It has been shown that specific frequency and amplitude ranges achieved by the piezoelectric actuators are able to produce a breakdown of larger coherent eddies by means of upscale energy transfer from smaller-scale eddies in the near wake. It results a thinning of the shear layers and the wake's width, associated to reduction of the form drag, as well as a reduction of predominant frequency peaks of the shear-layer instability. These effects have been shown by means of frequency domain analysis and Proper Orthogonal Decomposition.

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Section: Introductionmentioning

confidence: 99%

Dynamics of a hybrid morphing wing with active open loop vibrating trailing edge by time-resolved PIV and force measures

Jodin

Motta

Scheller

et al. 2017

Journal of Fluids and Structures

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“…The articulated mechanism for flap camber morphing was designed with reference to the most severe load condition expected in service; from an accurate comparison of the solicitations induced by more than 20 different load cases, the enveloping limit condition was found as the climb case related to uncambered flap deployed at 35°, δflap = 35°, flight speed V∞ = 95.2 m/s, angle of attack = 6°, sea level and max zero fuel weight. The highest resisting hinge torque (HT = 150 Nm) occurred in correspondence of the hinge axis connecting blocks B2 and B3, indicated with H3 in Figure 11 [17]. This led to the choice of such resistant hinge torque as the designing one for all the actuation kinematic mechanism.…”

Section: Target Shapes and Specificationsmentioning

confidence: 98%

“…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%

“…Fewer actuators are typically required to control the morphing process which expected benefit expected at system level drives the definition of additional mass, volume, force, and power required by the actuation system. In force of this consideration, it naturally follows that the adoption of mechanized structures becomes quite mandatory when dealing with large aircraft applications [3,4,6,8] and/or when multi-modal morphing functionalities have to be assured, [17]. European research projects such as JTI (Joint Technology Initiative)-Clean Sky [2] and GRA-ITD (Green Regional Aircraft-Integrated Technological Demonstration) have been important occasions to demonstrate technological achievements to be integrated into future green open-rotor aircraft (EASA, European Aviation Safety Agency, CS-25 category, [37]).…”

Section: Introductionmentioning

confidence: 99%

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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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“…Recently, different EU projects, such as SADE and SAR-ISTU, started from Monner's work to design a portion of a full-scale morphing droop nose composed of two main parts: a compliant skin and a rigid kinematic mechanism obtained by an integrate design [10]. Other projects also concerned the development of morphing flap [11,12] and morphing trailing edge [13,14] devices for the load control in both high-speed and low-speed conditions.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Shape Design and Validation of an Advanced High-Lift Device for a Regional Aircraft with Morphing Droop Nose

Gaspari

Moëns

2019

International Journal of Aerospace Engineering

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In the present work, the aerodynamic shape design of an advanced high-lift system for a natural laminar flow (NLF) wing, based on the combination of a morphing droop nose and a single slot trailing edge flap, is presented. The paper presents both the aerodynamic design and optimization of the NLF wing and the high-lift configuration considering the mutual effects of both flap devices. Concerning the morphing droop nose (DN), after defining the parameterization techniques adopted to describe the geometry in terms of morphing shape and flap settings, the external configuration is obtained by an aerodynamic shape optimization procedure able to meet geometrical constraints and the skin structural requirements due to the morphing. The final performance assessment of the three-dimensional high-lift configurations is performed by high-fidelity aerodynamic analyses. The design procedure is applied to a twin-prop regional aircraft equipped with a natural laminar flow wing. The morphing droop nose is compatible with an NLF wing that requires the continuity of the skin and, at the same time, extends the possibilities to improve the performances of the class of regional aircraft which usually are not equipped with conventional leading edge devices. Additionally, the morphing technology applied to the flap allows the design of a tracking system fully integrated inside the airfoil geometry, leading to a solution without external fairings and so with no extra friction drag penalty for the aircraft.

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Toward the bi-modal camber morphing of large aircraft wing flaps: the CleanSky experience

Cited by 13 publications

References 14 publications

Dynamics of a hybrid morphing wing with active open loop vibrating trailing edge by time-resolved PIV and force measures

Dynamics of a hybrid morphing wing with active open loop vibrating trailing edge by time-resolved PIV and force measures

Electro-Actuation System Strategy for a Morphing Flap

Aerodynamic Shape Design and Validation of an Advanced High-Lift Device for a Regional Aircraft with Morphing Droop Nose

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