Distributed actuation concepts for a morphing aileron device

Amendola, Gianluca; Dimino, Ignazio; Magnifico, Marco; Pecora, Rosario

doi:10.1017/aer.2016.64

Cited by 40 publications

(22 citation statements)

References 9 publications

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“…The external structure is made up of segmented aluminum-alloy skin embedding standard gap-filler, as shown in Fig The ribs' kinematic is based on a oscillating glyph mechanism which transforms the actuator shaft rotation into a rib deflection by means of a leverage directly linked to the rib plate. This mechanism has been theoretically studied in [12], [13] and it has the advantage to exhibit an increasing torque amplification factor as the rib-morphing angle rises [13]. Further details on the actuation system are shown in Fig.…”

Section: Morphing Aileron Architecturementioning

confidence: 99%

“…8) tailored for assessment of its dynamic behavior;  FE model of the morphing aileron ( Fig. 10) characterized by refined mesh specifically conceived for detailed stress analysis (further detail on the model in [13]) and properly updated by means of Ground Vibration Test (GVT) [17]. The complete test article finite-element model was generated in MSC-PATRAN®, and real eigenvalue extraction was performed, according to MSC-NASTRAN® SOL 103 protocol [16], by means of Lanczos Method in the frequency range of interest ([0 Hz; 80 Hz]) with eigenvectors normalized to the maximum value [16].…”

Section: A Structural Modelmentioning

confidence: 99%

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Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Rea¹,

Pecora²,

Amoroso³

et al. 2018

IJMERR

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In last decades, several research programs were founded worldwide to exploit the potentialities of the morphing concepts, especially to improve aerodynamic efficiency, and so reduce fuel consumption. Among these, the CRIAQ MDO-505 project represents the first joined research program between Canadian and Italian academies, research centers and leading industries. The aim of the project is to design, manufacture and tests in wind tunnel facilities a morphing wing tip for a Bombardier-type aircraft controlled by electric actuators and pressure sensors. In such framework, the authors intensively worked on the flutter clearance demonstration of the wind tunnel wing model equipped with a full-scale variable-camber aileron driven by load-bearing electro-mechanical actuators. Rational approaches were implemented in order to simulate the effects induced by variations of aileron actuator's stiffness on the aeroelastic behavior of the wing. Reliable models were properly implemented to enable fast aeroelastic analyses covering several configuration cases in order to prove clearance from any dynamic instability (flutter) up to 1.2 times the maximum flow speed expected during Wind Tunnel Tests. Finite-element models were properly developed in order to obtain and implement wing model modal parameters (modes shapes, frequencies, generalized masses, damping) in SANDY®, an in-house developed code, that was used for the definition of the coupled aerostructural model as well as for the solution of aeroelastic stability equations by means of theoretical modes association in frequency domain. Obtained results were finally arranged in a diagram showing trend of the flutter speed with respect to changes in control surface harmonic covering a wide range of values for the stiffness of the aileron (external) actuator.  Index Terms-morphing aileron, aeroelasticity, flutter, aeroelastic stability, variable camber, active ribs, smart structures, FEM.I.

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Section: Morphing Aileron Architecturementioning

confidence: 99%

Section: A Structural Modelmentioning

confidence: 99%

Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Rea¹,

Pecora²,

Amoroso³

et al. 2018

IJMERR

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show abstract

“…It is based on the classical quick-return mechanism, also referred to as oscillating glyph kinematics that (Fig. 7) is widely discussed and was validated by Amendola et al (2016). Figure 7 shows the main structural components of the glyph kinematic system.…”

Section: Actuation Systemmentioning

confidence: 99%

“…The complete system is made of commercial elements: actuators, kinematics, linear guides and all the other devices are in fact available on the market. The implemented architecture is a slight modification of the so-called quick-return mechanism (Amendola et al, 2016). In this paper, the aileron structure is sized with respect to the designated load chosen among the most critical operative ones.…”

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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“…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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Distributed actuation concepts for a morphing aileron device

Cited by 40 publications

References 9 publications

Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Aeroelastic Stability Analysis of a Wind Tunnel Wing Model Equipped with a True Scale Morphing Aileron

Preliminary design of an adaptive aileron for next generation regional aircraft

Electro-Actuation System Strategy for a Morphing Flap

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