Experimental validation of a true-scale morphing flap for large civil aircraft applications

Pecora, Rosario; Amoroso, Francesco; Arena, Maurizio; Noviello, Maria Chiara; Rea, Francesco

doi:10.1117/12.2259878

Cited by 7 publications

(9 citation statements)

References 9 publications

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“…Starting from the reference aero-loads related to the most severe working conditions expected in service, [ 30 ], the morphing flap device was designed according to an articulated engineering process compliant with CS-25 requirements and industrial standards [ 30 , 31 ]. To properly monitor the process, three revision gates were placed at the end of the conceptual, preliminary, and advanced design phases (critical concept review, preliminary design review, and critical design review).…”

Section: A Short Description Of the Analyzed Morphing Systemsmentioning

confidence: 99%

“…The goodness of the adopted structural solutions as well as of the actuation and control strategy were successfully proved by means of full-scale static, functionality, and dynamic tests, Figure 4 , [ 30 ]. Relying upon the outcomes of the dynamic tests, a thorough assessment of the flap impacts on aircraft aeroelastic stability was also addressed, showing the absence of any flap-induced flutters also in case of flap malfunctions (jamming) and/or free plays, [ 31 ]. In parallel, the aerodynamic improvements brought by the device at aircraft level were successfully demonstrated by means of large-scale wind tunnel test, fairly reproducing flap’s low speed (take-off and landing) and high-speed (cruise) operative conditions.…”

Section: A Short Description Of the Analyzed Morphing Systemsmentioning

confidence: 99%

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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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Section: A Short Description Of the Analyzed Morphing Systemsmentioning

confidence: 99%

Section: A Short Description Of the Analyzed Morphing Systemsmentioning

confidence: 99%

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

Miceli¹,

Ameduri

Dimino

et al. 2023

Biomimetics

View full text Add to dashboard Cite

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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%

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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“…Functionality tests were carried out to validate the flap morph ing capabilities [17]. The open loop law presented in Tab le 4 was imp lemented in a DriveManager® software environment to explo it the ability of the control devices to respond to a digital logic with various inputs by the X4 terminal ( Figure 21).…”

Section: Functionality Testmentioning

confidence: 99%

Description of Position Control Laws for Functionality Test of a Bi-modal Morphing Flap

Noviello¹,

Rea²,

Arena³

et al. 2018

IJMERR

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Modern aerospace research programs are increasingly focusing on structural design strategies based on the adaptive wing philosophy. Morphing wing technologies are being studied because they can be used to maximize the aerodynamic efficiency, maneuverability, and load control effectiveness under different flight conditions. As one of the most important research projects in Europe, the JTI Green Regional Aircraft (GRA) focused on the design and demonstration of a true-scale morphing flap applicable to the natural laminar flow (NLF) wing of a 130seat EAS A CS 25 category reference aircraft. The authors worked on developing an appropriate actuation and control system to enable flap bi-modal operational modes. In the deployed configuration, the overall camber morphs during takeoff and landing for high-lift performances. In the stowed configuration, the flap trailing edge (nearly 10% of the local chord) is deflected upwards an d downwards to improve the wing aerodynamic efficiency during cruising. Tailored control units were programmed according to a proper digital logic control law based on LTI DriveManager® software. Flap functionality tests showed that the obtained morphed shapes had an excellent correlation with the design target geometries.

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Experimental validation of a true-scale morphing flap for large civil aircraft applications

Cited by 7 publications

References 9 publications

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

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

Electro-Actuation System Strategy for a Morphing Flap

Description of Position Control Laws for Functionality Test of a Bi-modal Morphing Flap

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