Aeroelastic stability analysis of a large civil aircraft equipped with morphing winglets and adaptive flap tabs

Pecora, Rosario; Amoroso, Francesco; Noviello, Maria Chiara; Dimino, Ignazio; Concilio, Antonio

doi:10.1117/12.2300173

Cited by 6 publications

(7 citation statements)

References 10 publications

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“…From the aeroelastic standpoint, the tab behaves as a large aileron and detrimental flutter instability may arise from the coupling of the first wing bending mode with the tab harmonic (elastic oscillation of the tab around its hinge axis). Aeroelastic analyses based on numerical models [38,39] proved however that the flap tab design was safe from the flutter stand point considering also the functioning of the electric line feeding the actuators; in order to give experimental evidence of this result, ground resonance tests were carried out to validate the flap dynamic model used for theoretical flutter analyses. This validation was performed by correlating numerical and experimental generalized parameters related to the only flap mode proved to be relevant for flutter stability [39]: the tab harmonic at powered actuators.…”

Section: Dynamic Testmentioning

confidence: 99%

“…Aeroelastic analyses based on numerical models [38,39] proved however that the flap tab design was safe from the flutter stand point considering also the functioning of the electric line feeding the actuators; in order to give experimental evidence of this result, ground resonance tests were carried out to validate the flap dynamic model used for theoretical flutter analyses. This validation was performed by correlating numerical and experimental generalized parameters related to the only flap mode proved to be relevant for flutter stability [39]: the tab harmonic at powered actuators. The flap was suspended to a test rig through soft springs in order to reproduce a free-free condition, Figure 23; all the actuators were shut down.…”

Section: Dynamic Testmentioning

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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Section: Dynamic Testmentioning

confidence: 99%

Section: Dynamic Testmentioning

confidence: 99%

Electro-Actuation System Strategy for a Morphing Flap

et al. 2018

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“…The first one is a multifunctional adaptive flap, capable of different ways of working within the same architecture and the same physical realization, all congruent with the morphing and the adaptive structure definition, [ 26 ], to meet different flight phases necessities (cruise, take-off, and landing, maneuver). The second system is an adaptive winglet, [ 27 , 28 ], and is made of the main body with external independent multi-tab systems capable of working both synchronously and asynchronously, for performance adaption among different flight phases (take-off, cruise), and for load alleviation purposes. Finally, the third one implements a full-embedded SMA torque tube for twist adaptation of a full-scale rotorcraft blade for matching both hovering and cruise needs, [ 29 ].…”

Section: Introductionmentioning

confidence: 99%

A Preliminary Technology Readiness Assessment of Morphing Technology Applied to Case Studies

Miceli¹,

Ameduri

Dimino

et al. 2023

Biomimetics

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In an innovative system, it is essential to keep under control the crucial development phases, which should consider several aspects involving, for instance, the modeling or the assessment of suitable analytical representations. Aiming to pursue a final demonstration to verify the actual capability of an engineering idea, however, some fundamental elements may have been partially considered. Many projects state the initial and final technology readiness level based on the famous scale introduced by the US National and Aeronautics Space Administration (NASA) many years ago and now widespread in many fields of technology innovation. Its nine-step definition provides a high-level indication of the maturity of the observed innovative system. Trivially, the resolution of that macroscopic meter is not made for catching advancement details, but it rather provides comprehensive information on the examined technology. It is, therefore, necessary to refer to more sophisticated analysis tools that can show a more accurate picture of the development stage and helps designers to highlight points that deserve further attention and deeper analysis. The risk is to perform a very good demonstration test that can miss generality and remain confined only to that specific experimental campaign. Moving on to these assumptions, the authors expose three realizations of theirs concerning aeronautic morphing systems, to the analysis of a well-assessed Technology Readiness Level instrument. The aim is to define the aspects to be further assessed, the aspect to be considered fully mature, and even aspects that could miss some elementary point to attain full maturation. Such studies are not so frequent in the literature, and the authors believe to give a valuable, yet preliminary, contribution to the engineering of breakthrough systems. Without losing generality, the paper refers to the 2.2 version of a tool set up by the US Air Force Research Laboratory (AFRL), and NASA, with the aim to standardize the evaluation process of the mentioned nine-step TRL.

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“…The flutter and divergence characteristics of a large civil aircraft with morphing winglets and adaptive flap tabs were systemically examined to assess the robustness and safety of adoption in the real structure. 6 Hu et al 7 paid more attention to the nonlinear aeroelastic characteristics of a folding wing with cubic connection stiffness in the quasi-steady condition and during the morphing process, and variable motion types, such as chaos motion, were observed in the numerical calculation. Flutter and divergent speeds significantly changed during the transition between take-off, climb, cruise and loiter phases of a fully morphing wing studied by € Unlu¨soy and Yaman.…”

Section: Introductionmentioning

confidence: 99%

Transonic flutter characteristics of an airfoil with morphing devices

Guo

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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An investigation into transonic flutter characteristic of an airfoil conceived with the morphing leading and trailing edges has been carried out. Computational fluid dynamics (CFD) is used to calculate the unsteady aerodynamic force in transonic flow. An aerodynamic reduced order model (ROM) based on autoregressive model with exogenous input (ARX) is used in the numerical simulation. The flutter solution is determined by eigenvalue analysis at specific Mach number. The approach is validated by comparing the transonic flutter characteristics of the Isogai wing with relevant literatures before applied to a morphing airfoil. The study reveals that by employing the morphing trailing edge, the shock wave forms and shifts to the trailing edge at a lower Mach number, and aerodynamic force stabilization happens earlier. Meanwhile, the minimum flutter speed increases and transonic dip occurs at a lower Mach number. It is also noted that leading edge morphing has negligible effect on the appearance of the shock wave and transonic flutter. The mechanism of improving the transonic flutter characteristics by morphing technology is discussed by correlating shock wave location on airfoil surface, unsteady aerodynamics with flutter solution.

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Aeroelastic stability analysis of a large civil aircraft equipped with morphing winglets and adaptive flap tabs

Cited by 6 publications

References 10 publications

Electro-Actuation System Strategy for a Morphing Flap

Electro-Actuation System Strategy for a Morphing Flap

A Preliminary Technology Readiness Assessment of Morphing Technology Applied to Case Studies

Transonic flutter characteristics of an airfoil with morphing devices

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