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Dr. Antonio Concilio
Department of Adaptive Structures, Centro Italiano Ricerche Aerospaziali; 81043 Capua (CE), Italy

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Research Keywords & Expertise

0 Piezoelectrics
0 Shape Memory Alloys
0 Smart Materials
0 Structural Health Monitoring
0 smart structures

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Smart Materials
Shape Memory Alloys
smart structures
Morphing Structures
Structural Health Monitoring
noise and vibration control
Adaptive structures
Deployable structures
Adaptive wings
Piezoelectrics
shape memory polymers

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Journal article
Published: 15 April 2021 in Applied Sciences
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Morphing aeronautical systems may be used for a number of aims, ranging from improving performance in specific flight conditions, to keeping the optimal efficiency over a certain parameters domain instead of confining it to a single point, extending the flight envelope, and so on. An almost trivial statement is that traditional skeleton architectures cannot be held as a structure modified from being rigid to deformable. That passage is not simple, as a structure that is able to be modified shall be designed and constructed to face those new requirements. What is not marginal, is that the new configurations can lead to some peculiar problems for both the morphing and the standard, supporting, elements. In their own nature, in fact, adaptive systems are designed to contain all the parts within the original geometry, without any “external adjoint”, such as nacelles or others. Stress and strain distribution may vary a lot with respect to usual structures and some particular modifications are required. Sometimes, it happens that the structural behavior does not match with the common experience and some specific adjustment shall be done to overcome the problem. What is reported in this paper is a study concerning the adaptation of the structural architecture, used to host a winglet morphing system, to make it accomplish the original requirements, i.e., allow the deformation values to be under the safety threshold. When facing that problem, an uncommon behavior of the finite element (FE) solver has been met: the safety factors appear to be tremendously dependent on the mesh size, so as to raise serious questions about the actual expected value, relevant for the most severe load conditions. On the other side, such singularities are more and more confined into single points (or single lines), as the mesh refines, so to evidence somehow the numerical effect behind those results. On the other side, standard engineering local methods to reduce the abovementioned strain peaks seem to work very well in re-distributing the stress and strain excesses to the whole system domain. The work does not intend to give an answer to the presented problem, being instead focused on describing its possible causes and its evident effects. Further work is necessary to detect the original source of such inconsistencies, and propose and test operative solutions. That will be the subject of the next steps of the ongoing research.

ACS Style

Salvatore Ameduri; Ignazio Dimino; Antonio Concilio; Umberto Mercurio; Lorenzo Pellone. Specific Modeling Issues on an Adaptive Winglet Skeleton. Applied Sciences 2021, 11, 3565 .

AMA Style

Salvatore Ameduri, Ignazio Dimino, Antonio Concilio, Umberto Mercurio, Lorenzo Pellone. Specific Modeling Issues on an Adaptive Winglet Skeleton. Applied Sciences. 2021; 11 (8):3565.

Chicago/Turabian Style

Salvatore Ameduri; Ignazio Dimino; Antonio Concilio; Umberto Mercurio; Lorenzo Pellone. 2021. "Specific Modeling Issues on an Adaptive Winglet Skeleton." Applied Sciences 11, no. 8: 3565.

Journal article
Published: 09 March 2021 in Applied Sciences
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Aircraft winglets are well-established devices that improve aircraft fuel efficiency by enabling a higher lift over drag ratios and lower induced drag. Retrofitting winglets to existing aircraft also increases aircraft payload/range by the same order of the fuel burn savings, although the additional loads and moments imparted to the wing may impact structural interfaces, adding more weight to the wing. Winglet installation on aircraft wing influences numerous design parameters and requires a proper balance between aerodynamics and weight efficiency. Advanced dynamic aeroelastic analyses of the wing/winglet structure are also crucial for this assessment. Within the scope of the Clean Sky 2 REG IADP Airgreen 2 project, targeting novel technologies for next-generation regional aircraft, this paper deals with the integrated design of a full-scale morphing winglet for the purpose of improving aircraft aerodynamic efficiency in off-design flight conditions, lowering wing-bending moments due to maneuvers and increasing aircraft flight stability through morphing technology. A fault-tolerant morphing winglet architecture, based on two independent and asynchronous control surfaces with variable camber and differential settings, is presented. The system is designed to face different flight situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed, along with the expected aerodynamic performance and the actuation systems’ integration in the winglet surface geometry. Such a device was designed by CIRA for regional aircraft installation, whereas the aerodynamic benefits and performance were estimated by ONERA on the natural laminar flow wing. An active load controller was developed by PoliMI and UniNA performed aeroelastic trade-offs and flutter calculations due to the coupling of winglet movable harmonics and aircraft wing bending and torsion.

ACS Style

Ignazio Dimino; Giovanni Andreutti; Frédéric Moens; Federico Fonte; Rosario Pecora; Antonio Concilio. Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft. Applied Sciences 2021, 11, 2439 .

AMA Style

Ignazio Dimino, Giovanni Andreutti, Frédéric Moens, Federico Fonte, Rosario Pecora, Antonio Concilio. Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft. Applied Sciences. 2021; 11 (5):2439.

Chicago/Turabian Style

Ignazio Dimino; Giovanni Andreutti; Frédéric Moens; Federico Fonte; Rosario Pecora; Antonio Concilio. 2021. "Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft." Applied Sciences 11, no. 5: 2439.

Review article
Published: 01 September 2020 in Chinese Journal of Aeronautics
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SARISTU was a big cooperation project granted by the European Commission, 7th Framework Programme, carried out between 2011 and 2015. It dealt with smart aeronautic structures, both morphing and sensored; its main target was to demonstrate the feasibility of designing, manufacturing and operating in representative environment, instrumented structures. Till now, it represents the major effort carried out within the European Union on the development of adaptive architectures for air systems. Inside that big activity, the realization of an Adaptive Trailing Edge Device (ATED) for wing camber adaptations aimed at compensating the weight reduction following the fuel consumption during cruise was addressed. It made the core of investigations target variable geometry aircraft components together with two other analyses concerning the development of shape-changing winglet and droop nose. ATED activities were conducted by the Italian Aerospace Research Centre (CIRA) in tight cooperation with the University of Napoli, “Federico II”, who coordinated a group of 12 different partners from 8 different nations (France, Germany, Greece, the Netherlands, Israel, Spain, Turkey, and Italy). In this paper, an integral synthesis of that work is reported, with a focus on the definition and realization of the components of the presented device. The publication is in fact meant as the first part of a series that is aimed at overviewing the whole adaptive trailing edge development, till wind tunnel tests execution. Such a concise report is a critical and harmonized review of what have been performed by many colleagues spread all over Europe, all of which are duly recalled in the reported bibliography where the reader may access more detailed information and descriptions. In detail, the paper starts with a general introduction of the concept and its aims, to move to the specs definition immediately after. Then, it deals with a short but comprehensive description of the main ATED components: structural skeleton, skin, actuation and sensing systems. It is worth remarking that the paragraph dedicated to the body frame includes some discussion about aeroelastic assessment and manufacture, seen as complementation for a complete assessment of the design constraints.

ACS Style

A. Concilio; I. Dimino; R. Pecora. SARISTU: Adaptive Trailing Edge Device (ATED) design process review. Chinese Journal of Aeronautics 2020, 34, 187 -210.

AMA Style

A. Concilio, I. Dimino, R. Pecora. SARISTU: Adaptive Trailing Edge Device (ATED) design process review. Chinese Journal of Aeronautics. 2020; 34 (7):187-210.

Chicago/Turabian Style

A. Concilio; I. Dimino; R. Pecora. 2020. "SARISTU: Adaptive Trailing Edge Device (ATED) design process review." Chinese Journal of Aeronautics 34, no. 7: 187-210.

Journal article
Published: 12 April 2020 in Applied Sciences
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This paper presents a cross-correlation function-based method applied to a spatially shifted differential strain readout vectors using distributed sensors under backscattering random noise and impact excitations. Structural damage is generated by low/medium energy impact on two aeronautical 24-ply CFRP (carbon fiber reinforced plastic) stiffened panels. Two different drop impact locations, two different sensor layouts and two different post-impact solicitations are provided for a skin-stringer debonding detection and length estimation. The differential signal with respect to an arbitrarily selected grounding is used. Then the effects of noise filtering are evaluated post-processing the differential signal by cross-correlating two strain vectors having one sensor gauge position lag. A Rayleigh backscattering sensing technology, with 5 mm of spatial resolution, is used to log the strain map. The results show a good coherence with respect to the NDI (nondestructive inspection) performed by ultrasonic C-scan (an ultrasonic imaging system) flaw detector.

ACS Style

Monica Ciminello; Natalino Daniele Boffa; Antonio Concilio; Bernardino Galasso; Fulvio Romano; Ernesto Monaco. Damage Detection of CFRP Stiffened Panels by Using Cross-Correlated Spatially Shifted Distributed Strain Sensors. Applied Sciences 2020, 10, 2662 .

AMA Style

Monica Ciminello, Natalino Daniele Boffa, Antonio Concilio, Bernardino Galasso, Fulvio Romano, Ernesto Monaco. Damage Detection of CFRP Stiffened Panels by Using Cross-Correlated Spatially Shifted Distributed Strain Sensors. Applied Sciences. 2020; 10 (8):2662.

Chicago/Turabian Style

Monica Ciminello; Natalino Daniele Boffa; Antonio Concilio; Bernardino Galasso; Fulvio Romano; Ernesto Monaco. 2020. "Damage Detection of CFRP Stiffened Panels by Using Cross-Correlated Spatially Shifted Distributed Strain Sensors." Applied Sciences 10, no. 8: 2662.

Journal article
Published: 20 September 2019 in Aerospace
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The application of morphing wing devices can bring several benefits in terms of aircraft performance, as the current literature shows. Within the scope of Clean Sky 2 AirGreen 2 European project, the authors provided a safety-driven design of an adaptive winglet, through the examination of potential hazards resulting from operational faults, such as actuation chain jamming or links structural fails. The main goal of this study was to verify whether the morphing winglet systems could comply with the standard civil flight safety regulations and airworthiness requirements (EASA CS25). Systems functions were firstly performed from a quality point of view at both aircraft and subsystem levels to detect potential design, crew and maintenance faults, as well as risks due to the external environment. The severity of the hazard effects was thus identified and then sorted in specific classes, representative of the maximum acceptable probability of occurrence for a single event, in association with safety design objectives. Fault trees were finally developed to assess the compliance of the system structures to the quantitative safety requirements deriving from the Fault and Hazard Analyses (FHAs). The same failure scenarios studied through FHAs have been simulated in flutter analyses performed to verify the aeroelastic effects due to the loss of the actuators or structural links at aircraft level. Obtained results were used to suggest a design solution to be implemented in the next loop of design of the morphing winglet.

ACS Style

Maria Chiara Noviello; Ignazio Dimino; Antonio Concilio; Francesco Amoroso; Rosario Pecora. Aeroelastic Assessments and Functional Hazard Analysis of a Regional Aircraft Equipped with Morphing Winglets. Aerospace 2019, 6, 104 .

AMA Style

Maria Chiara Noviello, Ignazio Dimino, Antonio Concilio, Francesco Amoroso, Rosario Pecora. Aeroelastic Assessments and Functional Hazard Analysis of a Regional Aircraft Equipped with Morphing Winglets. Aerospace. 2019; 6 (10):104.

Chicago/Turabian Style

Maria Chiara Noviello; Ignazio Dimino; Antonio Concilio; Francesco Amoroso; Rosario Pecora. 2019. "Aeroelastic Assessments and Functional Hazard Analysis of a Regional Aircraft Equipped with Morphing Winglets." Aerospace 6, no. 10: 104.

Research article
Published: 12 July 2019 in Journal of Intelligent Material Systems and Structures
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Active blade twist is an option to increase helicopter performance, for instance moving its condition from hovering to cruise. Shape memory alloys give the possibility of realizing compact devices, with high energy density. Several devices have been proposed in literature, showing limitations in terms of effectiveness and necessary room. In this article, the capability of a shape memory alloy torque tube to induce a certain twist law along the blade, while preserving its integrability within the structure, has been exploited. The study refers to a complex theoretical model, made of different specialized modules. In detail, transmitted twist action by the shape memory alloy actuators, aerodynamic effects caused by the induced geometrical change, inertial impact following the motor system integration, and system layout influence on the blade response have been taken into account. Through this model, a parametric investigation has been organized to highlight the importance of selected design variables. Tube thickness, mass, and length have been considered. Two different configurations have been initially taken into account, distinguished for the twist transmission mode and their outline. In the first hypothesis, a pre-stressed wire system converts tensile stress into a rotary action. In the second sketch, a pre-twisted solid tube connects two different stations of the blade, transmitting relative rotation. After the first trade-off, the second architecture has been selected for further analysis, focusing on its performance in terms of net transmitted twist, aerodynamic effects, while paying attention to a proper mass balance. In the chosen approach, the actuator has been installed at the torsion center. A finite element model has been used to validate the assessed analytical representation and has permitted establishing the applicability domain. Apart elastic forces, acting both in the shape memory alloys and the blade components, centrifugal forces have been taken into account by considering an increased stiffness of the reference structural element. Aerodynamic forces have been evaluated after the target configuration has been reached; helicopter trim has been considered to this purpose. The researchers aim at developing this concept by integrating the reverse action of the aerodynamic field and evaluating the importance of the actuator position along the chord. The research herein presented has been carried out within the SABRE project, project ID 723491, gratefully funded by the European Union within the Horizon 2020 program.

ACS Style

Salvatore Ameduri; Antonio Concilio. A shape memory alloy torsion actuator for static blade twist. Journal of Intelligent Material Systems and Structures 2019, 30, 2605 -2626.

AMA Style

Salvatore Ameduri, Antonio Concilio. A shape memory alloy torsion actuator for static blade twist. Journal of Intelligent Material Systems and Structures. 2019; 30 (17):2605-2626.

Chicago/Turabian Style

Salvatore Ameduri; Antonio Concilio. 2019. "A shape memory alloy torsion actuator for static blade twist." Journal of Intelligent Material Systems and Structures 30, no. 17: 2605-2626.

Journal article
Published: 27 June 2019 in Actuators
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The work at hand focuses on the modeling, prototyping, and experimental functionality test of a smart actuator based on shape memory polymer technology. Particular attention is paid to the specific modeling approach, here conceived as an effective predictive scheme, quick and, at the same time, able to face those nonlinearity aspects, strictly related to the large displacements shape memory polymers usually undergo. Shape memory polymer composites (SMPCs) may play a critical role for many applications, ranging from self-repairing systems to deployable structures (e.g., solar sails, antennas) and functional subcomponents (e.g., pliers, transporters of small objects). For all these applications, it is very important to have an effective tool that may drive the designers during the preliminary definition of the main parameters of the actuation system. For the present work, a SMPC plate sample has been conceived and realized in view of aerospace applications. An external fibre optic sensor has been then fixed with special adhesive. The temperatures needed for the activation of the Shape Memory Polymer (SMP) and strain storing have been provided by a thermo-gun and complete load–unload cycles, including strain storing, have been performed. Experimental displacements and strains have been used to validate a dedicated predictive theoretical approach, suited for laminates integrated with SMP layers.

ACS Style

Salvatore Ameduri; Monica Ciminello; Antonio Concilio; Fabrizio Quadrini; Loredana Santo. Shape Memory Polymer Composite Actuator: Modeling Approach for Preliminary Design and Validation. Actuators 2019, 8, 51 .

AMA Style

Salvatore Ameduri, Monica Ciminello, Antonio Concilio, Fabrizio Quadrini, Loredana Santo. Shape Memory Polymer Composite Actuator: Modeling Approach for Preliminary Design and Validation. Actuators. 2019; 8 (3):51.

Chicago/Turabian Style

Salvatore Ameduri; Monica Ciminello; Antonio Concilio; Fabrizio Quadrini; Loredana Santo. 2019. "Shape Memory Polymer Composite Actuator: Modeling Approach for Preliminary Design and Validation." Actuators 8, no. 3: 51.

Journal article
Published: 19 February 2019 in Aerospace
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Nature has many striking examples of adaptive structures: the emulation of birds’ flight is the true challenge of a morphing wing. The integration of increasingly innovative technologies, such as reliable kinematic mechanisms, embedded servo-actuation and smart materials systems, enables us to realize new structural systems fully compatible with the more and more stringent airworthiness requirements. In this paper, the authors describe the characterization of an adaptive structure, representative of a wing trailing edge, consisting of a finger-like rib mechanism with a highly deformable skin, which comprises both soft and stiff parts. The morphing skin is able to follow the trailing edge movement under repeated cycles, while being stiff enough to preserve its shape under aerodynamic loads and adequately pliable to minimize the actuation power required for morphing. In order to properly characterize the system, a mock-up was manufactured whose structural properties, in particular the ability to carry out loads, were also guaranteed by the elastic skin. A numerical sensitivity analysis with respect to the mechanical properties of the multi-segment skin was performed to investigate their influence on the modal response of the whole system. Experimental dynamic tests were then carried out and the obtained results were critically analysed to prove the adequacy of the adopted design approaches as well as to quantify the dissipative (high-damping) effects induced by the rubber foam on the dynamic response of the morphing architecture.

ACS Style

Maurizio Arena; Christof Nagel; Rosario Pecora; Oliver Schorsch; Antonio Concilio; Ignazio Dimino. Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin. Aerospace 2019, 6, 22 .

AMA Style

Maurizio Arena, Christof Nagel, Rosario Pecora, Oliver Schorsch, Antonio Concilio, Ignazio Dimino. Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin. Aerospace. 2019; 6 (2):22.

Chicago/Turabian Style

Maurizio Arena; Christof Nagel; Rosario Pecora; Oliver Schorsch; Antonio Concilio; Ignazio Dimino. 2019. "Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin." Aerospace 6, no. 2: 22.

Journal article
Published: 13 December 2018 in Actuators
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The work at hand focuses on an adaptive system aimed at improving the soundproof performance of car door seals at specific regimes (cruise), without interfering with the conventional opening and closing operations. The idea addresses the necessity of increasing seal effectiveness, jeopardized by aerodynamic actions that strengthen as the speed increases, generating a growing pressure difference between the internal and the external field in the direction of opening the door, and then deteriorating the acoustic insulation. An original expansion mechanism driven by a shape memory alloy (SMA) wire was integrated within the seal cavity to reduce that effect. The smart material was activated (heated) by using the Joule effect; its compactness contributed to the realization of a highly-integrable and modular system (expanding cells). In this paper, the system development process is described together with the verification and validation activity, aimed at proving the functionality of the realized device. Starting from industrial requirements, a suitable solution was identified by considering the basic phenomenon principle and the allowable design parameters. The envisaged system was designed and its executive digital mock-up (CAD, computer-aided design) was released. Prototyping and laboratory tests showed the reliability of the developed numerical models and validated the associated predictions. Finally, the system was integrated within the reference car. To demonstrate the insulation effect, the experimental campaign was carried out in an anechoic room, achieving significant results on the concept value.

ACS Style

Salvatore Ameduri; Angela Brindisi; Monica Ciminello; Antonio Concilio; Vincenzo Quaranta; Marco Brandizzi. Car Soundproof Improvement through an SMA Adaptive System. Actuators 2018, 7, 88 .

AMA Style

Salvatore Ameduri, Angela Brindisi, Monica Ciminello, Antonio Concilio, Vincenzo Quaranta, Marco Brandizzi. Car Soundproof Improvement through an SMA Adaptive System. Actuators. 2018; 7 (4):88.

Chicago/Turabian Style

Salvatore Ameduri; Angela Brindisi; Monica Ciminello; Antonio Concilio; Vincenzo Quaranta; Marco Brandizzi. 2018. "Car Soundproof Improvement through an SMA Adaptive System." Actuators 7, no. 4: 88.

Preprint
Published: 29 October 2018
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The work at hand focuses on an adaptive system aimed at improving the soundproof performance of car door seals at specific working regimes (cruise), without interfering with the conventional open-closure operations. The idea addresses the necessity of increasing the seal effectiveness, jeopardized by aerodynamic actions more and more important as the speed increase, generating a pressure difference between the internal and the external filed, in the direction of opening the door. To recover this effect, an expanding mechanism was integrated within the seal cavity, driven by an SMA actuator. The material was activated (heated) by Joule effect; its compactness, intrinsic of smart materials, contributed to arrive to a final system characterized by a high level of integrability (expanding cells). In this paper, the development process is described together with the verification activity, aimed at proving the functionality of the realized device. Starting from the industrial requirements, the most appropriate solution was identified highlighting the working principle and the main design parameters involved. Then, the envisaged system was designed and its executive digital mock up (CAD) was released. Prototyping and laboratory validation showed the reliability of the numerical models and the associated predictions. On this basis, the integration task within the actual reference car was faced. To demonstrate the isolation effect of the proposed system, an experimental campaign was finally organized in an anechoic room, achieving significant results on the concept value.

ACS Style

Salvatore Ameduri; Angela Brindisi; Monica Ciminello; Antonio Concilio; Vincenzo Quaranta; Marco Brandizzi. Car Soundproof Improvement Through an SMA Adaptive System. 2018, 1 .

AMA Style

Salvatore Ameduri, Angela Brindisi, Monica Ciminello, Antonio Concilio, Vincenzo Quaranta, Marco Brandizzi. Car Soundproof Improvement Through an SMA Adaptive System. . 2018; ():1.

Chicago/Turabian Style

Salvatore Ameduri; Angela Brindisi; Monica Ciminello; Antonio Concilio; Vincenzo Quaranta; Marco Brandizzi. 2018. "Car Soundproof Improvement Through an SMA Adaptive System." , no. : 1.

Conference paper
Published: 01 June 2018 in 2018 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace)
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It is presented here the concept and the preliminary design of an On-Board Weight and Balance System, intended to provide a regional aircraft pilot with the actual values of the aircraft weight and center of gravity position. The system is based on the use of fiber optic sensors, integrated within the landing gear and able to measure the strain induced by the overall vehicle take-off weight, including fuel and payload (passengers and luggage).

ACS Style

A. Brindisi; S. Ameduri; A. Concilio; M. Ciminello; M. Leone; A. Iele; M. Consales; A. Cusano. Preliminary Design of an Innovative Aircraft Weight & Balance Measurement System Based on Fiber Optic Sensors. 2018 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace) 2018, 11 -14.

AMA Style

A. Brindisi, S. Ameduri, A. Concilio, M. Ciminello, M. Leone, A. Iele, M. Consales, A. Cusano. Preliminary Design of an Innovative Aircraft Weight & Balance Measurement System Based on Fiber Optic Sensors. 2018 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace). 2018; ():11-14.

Chicago/Turabian Style

A. Brindisi; S. Ameduri; A. Concilio; M. Ciminello; M. Leone; A. Iele; M. Consales; A. Cusano. 2018. "Preliminary Design of an Innovative Aircraft Weight & Balance Measurement System Based on Fiber Optic Sensors." 2018 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace) , no. : 11-14.

Journal article
Published: 12 April 2018 in The Aeronautical Journal
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A new wing-tip concept with morphing upper surface and interchangeable conventional and morphing ailerons was designed, manufactured, bench and wind-tunnel tested. The development of this wing-tip model was performed in the frame of an international CRIAQ project, and the purpose was to demonstrate the wing upper surface and aileron morphing capabilities in improving the wing-tip aerodynamic performances. During numerical optimisation with ‘in-house’ genetic algorithm software, and during wind-tunnel experimental tests, it was demonstrated that the air-flow laminarity over the wing skin was promoted, and the laminar flow was extended with up to 9% of the chord. Drag coefficient reduction of up to 9% was obtained when the morphing aileron was introduced.

ACS Style

R.M. Botez; Andreea Koreanschi; O.S. Gabor; Y. Tondji; M. Guezguez; J.T. Kammegne; Teodor Lucian Grigorie; D. Sandu; Y. Mebarki; M. Mamou; F. Amoroso; Rosario Pecora; L. Lecce; G. Amendola; Ignazio Dimino; Antonio Concilio. Numerical and experimental transition results evaluation for a morphing wing and aileron system. The Aeronautical Journal 2018, 122, 747 -784.

AMA Style

R.M. Botez, Andreea Koreanschi, O.S. Gabor, Y. Tondji, M. Guezguez, J.T. Kammegne, Teodor Lucian Grigorie, D. Sandu, Y. Mebarki, M. Mamou, F. Amoroso, Rosario Pecora, L. Lecce, G. Amendola, Ignazio Dimino, Antonio Concilio. Numerical and experimental transition results evaluation for a morphing wing and aileron system. The Aeronautical Journal. 2018; 122 (1251):747-784.

Chicago/Turabian Style

R.M. Botez; Andreea Koreanschi; O.S. Gabor; Y. Tondji; M. Guezguez; J.T. Kammegne; Teodor Lucian Grigorie; D. Sandu; Y. Mebarki; M. Mamou; F. Amoroso; Rosario Pecora; L. Lecce; G. Amendola; Ignazio Dimino; Antonio Concilio. 2018. "Numerical and experimental transition results evaluation for a morphing wing and aileron system." The Aeronautical Journal 122, no. 1251: 747-784.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Antonio Concilio; Ignazio Dimino; Leonardo Lecce; Rosario Pecora. Preface. Morphing Wing Technologies 2018, 1 .

AMA Style

Antonio Concilio, Ignazio Dimino, Leonardo Lecce, Rosario Pecora. Preface. Morphing Wing Technologies. 2018; ():1.

Chicago/Turabian Style

Antonio Concilio; Ignazio Dimino; Leonardo Lecce; Rosario Pecora. 2018. "Preface." Morphing Wing Technologies , no. : 1.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Ignazio Dimino; Gianluca Amendola; Rosario Pecora; Antonio Concilio; André Gratias; Martin Schueller. On the Experimental Characterization of Morphing Structures. Morphing Wing Technologies 2018, 683 -712.

AMA Style

Ignazio Dimino, Gianluca Amendola, Rosario Pecora, Antonio Concilio, André Gratias, Martin Schueller. On the Experimental Characterization of Morphing Structures. Morphing Wing Technologies. 2018; ():683-712.

Chicago/Turabian Style

Ignazio Dimino; Gianluca Amendola; Rosario Pecora; Antonio Concilio; André Gratias; Martin Schueller. 2018. "On the Experimental Characterization of Morphing Structures." Morphing Wing Technologies , no. : 683-712.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Gianluca Amendola; Ignazio Dimino; Antonio Concilio; Rosario Pecora; Francesco Amoroso; Maurizio Arena. Morphing Aileron. Morphing Wing Technologies 2018, 547 -582.

AMA Style

Gianluca Amendola, Ignazio Dimino, Antonio Concilio, Rosario Pecora, Francesco Amoroso, Maurizio Arena. Morphing Aileron. Morphing Wing Technologies. 2018; ():547-582.

Chicago/Turabian Style

Gianluca Amendola; Ignazio Dimino; Antonio Concilio; Rosario Pecora; Francesco Amoroso; Maurizio Arena. 2018. "Morphing Aileron." Morphing Wing Technologies , no. : 547-582.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Antonio Concilio; Ignazio Dimino; Monica Ciminello; Rosario Pecora; Francesco Amoroso; Marco Magnifico. An Adaptive Trailing Edge. Morphing Wing Technologies 2018, 517 -545.

AMA Style

Antonio Concilio, Ignazio Dimino, Monica Ciminello, Rosario Pecora, Francesco Amoroso, Marco Magnifico. An Adaptive Trailing Edge. Morphing Wing Technologies. 2018; ():517-545.

Chicago/Turabian Style

Antonio Concilio; Ignazio Dimino; Monica Ciminello; Rosario Pecora; Francesco Amoroso; Marco Magnifico. 2018. "An Adaptive Trailing Edge." Morphing Wing Technologies , no. : 517-545.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Marco Bellucci; Maria Chiara Noviello; Francesco Amoroso; Rosario Pecora; Ignazio Dimino; Antonio Concilio. Stress Analysis of a Morphing System. Morphing Wing Technologies 2018, 451 -488.

AMA Style

Marco Bellucci, Maria Chiara Noviello, Francesco Amoroso, Rosario Pecora, Ignazio Dimino, Antonio Concilio. Stress Analysis of a Morphing System. Morphing Wing Technologies. 2018; ():451-488.

Chicago/Turabian Style

Marco Bellucci; Maria Chiara Noviello; Francesco Amoroso; Rosario Pecora; Ignazio Dimino; Antonio Concilio. 2018. "Stress Analysis of a Morphing System." Morphing Wing Technologies , no. : 451-488.

Book chapter
Published: 01 January 2018 in Morphing Wing Technologies
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ACS Style

Antonio Concilio; Leonardo Lecce. Historical Background and Current Scenario. Morphing Wing Technologies 2018, 3 -84.

AMA Style

Antonio Concilio, Leonardo Lecce. Historical Background and Current Scenario. Morphing Wing Technologies. 2018; ():3-84.

Chicago/Turabian Style

Antonio Concilio; Leonardo Lecce. 2018. "Historical Background and Current Scenario." Morphing Wing Technologies , no. : 3-84.

Conference paper
Published: 01 October 2017 in 2017 IEEE SENSORS
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A FO based ring patch sensor has been developed for load identification applications. The transducer is made of glass/epoxy composite material. The ability of composite material to integrate optical fibres is exploited. Fibres are allocated in different layers and in single or multi loop, this allows to reconstruct the applied loads. In this work a Finite Element approach has been used to simulate a transducer working under tensile and bending loads and extrapolate different deformation fields through a fiber optic circular path. Then the numerical results have been compared with the experimental outcomes performed by using FBGs array opportunely located inside the circular path.

ACS Style

Salvatore Ameduri; Paolo Bettini; Monica Ciminello; Antonio Concilio. Ring patch sensor based on FBG array for normal and bending load recognition. 2017 IEEE SENSORS 2017, 1 -3.

AMA Style

Salvatore Ameduri, Paolo Bettini, Monica Ciminello, Antonio Concilio. Ring patch sensor based on FBG array for normal and bending load recognition. 2017 IEEE SENSORS. 2017; ():1-3.

Chicago/Turabian Style

Salvatore Ameduri; Paolo Bettini; Monica Ciminello; Antonio Concilio. 2017. "Ring patch sensor based on FBG array for normal and bending load recognition." 2017 IEEE SENSORS , no. : 1-3.

Proceedings article
Published: 28 September 2017 in Structural Health Monitoring 2017
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In composite aeronautical structures at the stiffener terminations, the carried loads are transferred to the skin, making vital the design of the run-out region. Hence, improved structural health monitoring methods are required. The observations showed that failure initiates in the flange close to the tip in many operational cases, causing an almost full disconnection from the skin. This paper presents a simple methodology for skin-stringer de-bonding detection by using distributed fibre optic sensors and first order statistics. The proposed technique is based on the deviation comparison between a baseline set of measurements (irrespectively of the healthy state) and the current structural response. The assessed datasets are then processed in order to provide normalbased statistical features, an appropriate threshold limit and a damage index for each sensor. The algorithm points then out the positions where the possibility of the existence of a damage is maximum.

ACS Style

Bernardino Galasso; Monica Ciminello; Francesca Maria Pisano; Antonio Concilio. Statistical Based Features Vector for Skin-stringer Debonding Detection. Structural Health Monitoring 2017 2017, 1 .

AMA Style

Bernardino Galasso, Monica Ciminello, Francesca Maria Pisano, Antonio Concilio. Statistical Based Features Vector for Skin-stringer Debonding Detection. Structural Health Monitoring 2017. 2017; ():1.

Chicago/Turabian Style

Bernardino Galasso; Monica Ciminello; Francesca Maria Pisano; Antonio Concilio. 2017. "Statistical Based Features Vector for Skin-stringer Debonding Detection." Structural Health Monitoring 2017 , no. : 1.