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Dr Ignazio Dimino graduated with honors in Aeronautical Engineering at the University of Palermo, Italy, in 2004. He earned his Ph.D. in Aeronautics from Imperial College of London, UK. He was also visiting researcher at Center of Acoustics and Vibration of Penn State University, State College, PA US. Currently, he is the Head of the Adaptive Structures Technologies unit at the Italian Aerospace Research Centre (CIRA) and Project Manager in the field of Smart Structures. In 2015, within the EU-funded SARISTU project, he was involved in the wind tunnel test campaign in Russia of the first true-scale morphing wing ever delivered in Europe. He joined also the Italian/Canadian team of the CRIAQ MDO-505 project supervising the design and testing of a morphing aileron. From 2016, he is responsible of the Morphing Technology stream of the Clean Sky 2 Green Regional Aircraft IADP and board member of the Airgreen 2 PMO managing the Technologies Review and Demonstrations. Dimino is author of about eighty peer reviewed papers on adaptive structures and co-author of two books. In 2014, Dr Dimino received the “Best paper Award” at the 3AF/CEAS conference "Greener Aviation: Clean Sky breakthroughs and worldwide status” in Brussels. In 2016 and 2019, he served as program committee member and chairman of the Greener Aviation conference in Brussels, organized by the 3AF Association Aéronautique et et Astronautique de France.
This work proposes a systematic topology optimization approach for simultaneously designing the morphing functionality and actuation in three-dimensional wing structures. The actuation was modeled by a linear-strain-based expansion in the actuation material. A three-phase material model was employed to represent structural and actuating materials and voids. To ensure both structural stiffness with respect to aerodynamic loading and morphing capabilities, the optimization problem was formulated to minimize structural compliance, while the morphing functionality was enforced by constraining a morphing error between the actual and target wing shape. Moreover, a feature-mapping approach was utilized to constrain and simplify the actuator geometries. A trailing edge wing section was designed to validate the proposed optimization approach. Numerical results demonstrated that three-dimensional optimized wing sections utilize a more advanced structural layout to enhance structural performance while keeping the morphing functionality better than two-dimensional wing ribs. The work presents the first step towards the systematic design of three-dimensional morphing wing sections.
Peter Dørffler Ladegaard Jensen; Fengwen Wang; Ignazio Dimino; Ole Sigmund. Topology Optimization of Large-Scale 3D Morphing Wing Structures. Actuators 2021, 10, 217 .
AMA StylePeter Dørffler Ladegaard Jensen, Fengwen Wang, Ignazio Dimino, Ole Sigmund. Topology Optimization of Large-Scale 3D Morphing Wing Structures. Actuators. 2021; 10 (9):217.
Chicago/Turabian StylePeter Dørffler Ladegaard Jensen; Fengwen Wang; Ignazio Dimino; Ole Sigmund. 2021. "Topology Optimization of Large-Scale 3D Morphing Wing Structures." Actuators 10, no. 9: 217.
This work proposes a systematic topology optimization approach to simultaneously design the morphing functionality and actuation in three-dimensional wing structures. The actuation is assumed to be a linear strain-based expansion in the actuation material and a three-phase material model is employed to represent structural and actuating materials, and void. To ensure both structural stiffness with respect to aerodynamic loading and morphing capabilities, the optimization problem is formulated to minimize structural compliance while morphing functionality is enforced by constraining a morphing error between actual and target wing shape. Moreover, a feature mapping approach is utilized to constrain and simplify actuator geometries. A trailing edge wing section is designed to validate the proposed optimization approach. Numerical results demonstrate that three-dimensional optimized wing sections utilize a more advanced structural layout to enhance structural performance while keeping morphing functionality than two-dimensional wing ribs. The work presents the first step towards systematic design of three-dimensional morphing wing sections.
Peter Dørffler Ladegaard Jensen; Fengwen Wang; Ignazio Dimino; Ole Sigmund. Topology Optimization of Large-Scale 3D Morphing Wingstructures. 2021, 1 .
AMA StylePeter Dørffler Ladegaard Jensen, Fengwen Wang, Ignazio Dimino, Ole Sigmund. Topology Optimization of Large-Scale 3D Morphing Wingstructures. . 2021; ():1.
Chicago/Turabian StylePeter Dørffler Ladegaard Jensen; Fengwen Wang; Ignazio Dimino; Ole Sigmund. 2021. "Topology Optimization of Large-Scale 3D Morphing Wingstructures." , no. : 1.
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.
Salvatore Ameduri; Ignazio Dimino; Antonio Concilio; Umberto Mercurio; Lorenzo Pellone. Specific Modeling Issues on an Adaptive Winglet Skeleton. Applied Sciences 2021, 11, 3565 .
AMA StyleSalvatore 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 StyleSalvatore Ameduri; Ignazio Dimino; Antonio Concilio; Umberto Mercurio; Lorenzo Pellone. 2021. "Specific Modeling Issues on an Adaptive Winglet Skeleton." Applied Sciences 11, no. 8: 3565.
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.
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 StyleIgnazio 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 StyleIgnazio 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.
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.
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 StyleMaria 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 StyleMaria 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.
As a key enabler for future aviation technology, the use of servo electromechanical actuation offers new opportunities to transition innovative structural concepts, such as biomimicry morphing structures, from basic research to new commercial aircraft applications. In this paper, the authors address actuator integration aspects of a wing shape-changing flight surface capable of adaptively enhancing aircraft aerodynamic performance and reducing critical wing structural loads. The research was collocated within the Clean Sky 2 Regional Aircraft Demonstration Platform (IADP) and aimed at developing an adaptive winglet concept for green regional aircraft. Finite Element-based tools were employed for the structural design of the adaptive device characterized by two independent movable tabs completely integrated with a linear direct-drive actuation. The structural design process was addressed in compliance with the airworthiness needs posed by the implementation of regional airplanes. Such a load control system requires very demanding actuation performance and sufficient operational reliability to operate on the applicable flight load envelope. These requirements were met by a very compact direct-drive actuator design in which the ball recirculation device was integrated within the screw shaft. Focus was also given to the power-off electric brake necessary to block the structure in a certain position and dynamically brake the moveable surface to follow a certain command position during operation. Both the winglet layout static and dynamic robustness were verified by means of linear stress computations at the most critical conditions and normal mode analyses, respectively, with and without including the integrated actuator system.
Ignazio Dimino; Federico Gallorini; Massimiliano Palmieri; Giulio Pispola. Electromechanical Actuation for Morphing Winglets. Actuators 2019, 8, 42 .
AMA StyleIgnazio Dimino, Federico Gallorini, Massimiliano Palmieri, Giulio Pispola. Electromechanical Actuation for Morphing Winglets. Actuators. 2019; 8 (2):42.
Chicago/Turabian StyleIgnazio Dimino; Federico Gallorini; Massimiliano Palmieri; Giulio Pispola. 2019. "Electromechanical Actuation for Morphing Winglets." Actuators 8, no. 2: 42.
When dealing with adaptive lifting surfaces, the level of complexity of the structural design naturally increases as a consequence of the augmented functionality of the resulting system. Specifically, an adaptive structure ensures a controlled and fully reversible transition from a baseline shape to a set of different configurations, each one characterized by different external loads and transmission paths of the internal stresses. The Consortium de recherche et d’innovation en aérospatiale au Québec (CRIAQ) MD0-505 research project, born from an efficient transatlantic cooperation among Italian and Canadian academic departments, research centers, and leading companies, suggests a possible solution to more stringent government requirements on emissions and safety: an innovative morphing aileron implemented to increase both structural stability and the in-cruise load control, was designed, manufactured, and tested. The aim of this article is to predict the aero-servo-elastic impact of a true-scale prototype on a regional aircraft, following an experimental test campaign and the development of a well-correlated finite-element model of the device. A detailed trade-off flutter analysis was performed by means of SANDY, an in-house code, in compliance with European Aviation Safety Agency (EASA) CS-25 airworthiness requirements and referring—initially—to nominal aileron functioning. Furthermore, a sensitivity investigation was carried out to assess the dynamic stability of the adaptive aileron, verifying the flutter clearance in the presence of critical scenarios related to malfunctions of the actuation system. Safety values for the aileron control harmonic were investigated looking at potential certification and industrialization issues.
Maurizio Arena; Rita Palumbo; Rosario Pecora; Francesco Amoroso; Gianluca Amendola; Ignazio Dimino. Flutter Clearance Investigation of Camber-Morphing Aileron Tailored for a Regional Aircraft. Journal of Aerospace Engineering 2019, 32, 04018146 .
AMA StyleMaurizio Arena, Rita Palumbo, Rosario Pecora, Francesco Amoroso, Gianluca Amendola, Ignazio Dimino. Flutter Clearance Investigation of Camber-Morphing Aileron Tailored for a Regional Aircraft. Journal of Aerospace Engineering. 2019; 32 (2):04018146.
Chicago/Turabian StyleMaurizio Arena; Rita Palumbo; Rosario Pecora; Francesco Amoroso; Gianluca Amendola; Ignazio Dimino. 2019. "Flutter Clearance Investigation of Camber-Morphing Aileron Tailored for a Regional Aircraft." Journal of Aerospace Engineering 32, no. 2: 04018146.
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.
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 StyleMaurizio 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 StyleMaurizio 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.
By introducing the progresses on Morphing currently achieved within the European Project “AIRGREEN2”, in Clean-Sky 2 GRA platform, this work presents a review of the research step forwards accomplished in the last decade by three Italian Partners largely active in the field: the Italian Aerospace Research Centre, the University of Naples “Federico II” and the Politecnico of Milano. A chronologic overview is at first presented, revisiting the research programs and the achieved results; an organic development path has been then built, starting from low TRL achievements up to arrive at the most complete technical accomplishments, characterized by a high level of integration and targeting specific aerospace applications.
Salvatore Ameduri; Antonio Concilio; Ignazio Dimino; Rosario Pecora; Sergio Ricci. AIRGREEN2 - Clean Sky 2 Programme: Adaptive Wing Technology Maturation, Challenges and Perspectives. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation 2018, 1 .
AMA StyleSalvatore Ameduri, Antonio Concilio, Ignazio Dimino, Rosario Pecora, Sergio Ricci. AIRGREEN2 - Clean Sky 2 Programme: Adaptive Wing Technology Maturation, Challenges and Perspectives. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation. 2018; ():1.
Chicago/Turabian StyleSalvatore Ameduri; Antonio Concilio; Ignazio Dimino; Rosario Pecora; Sergio Ricci. 2018. "AIRGREEN2 - Clean Sky 2 Programme: Adaptive Wing Technology Maturation, Challenges and Perspectives." Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation , no. : 1.
Aircraft wing design optimization typically requires the consideration of many competing factors accounting for both aerodynamics and structures. To address this, research on morphing aircraft has shown its potential by providing large benefits on aircraft performance. In particular, by adapting wing lift distribution, morphing winglets are capable to improve aircraft aerodynamic efficiency in off-design conditions and reduce wing loads at critical flight points. For those reasons, it is expected that these devices will be applied to the aircraft of the very next generation. In the study herein presented, a preliminary failure analysis and structural design of a morphing winglet are presented. The research is collocated within the Clean Sky 2 Regional Aircraft IADP, a large European programme targeting the development of novel technologies for the next generation regional aircraft. The safety-driven design of the proposed kinematic system includes a thorough examination of the potential hazards associated with the system faults, by taking into account the overall operating environment and functions. The mechanical system is characterized by movable surfaces sustained by a winglet skeleton and completely integrated with a devoted actuation system. Such a load control device requires sufficient operational reliability to operate on the applicable flight load envelope in order to match the needs of the structural design. One of the most critical failure modes is assessed to get key requirements for the system architecture consistency. Possible impacts of the defined morphing outline on the FHA analysis are investigated. The structural design process is then addressed in compliance with the demanding requirements posed by the implementation on regional airplanes. The layout static robustness is verified by means of linear stress analyses at the most critical conditions, including possible failure scenarios. Results focus on the assessment of the device static and dynamic structural response and the preliminary definition of the morphing system kinematics, including the integrated actuator system.
Ignazio Dimino; Salvatore Ameduri; Antonio Concilio. Preliminary Failure Analysis and Structural Design of a Morphing Winglet for Green Regional Aircraft. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation 2018, 1 .
AMA StyleIgnazio Dimino, Salvatore Ameduri, Antonio Concilio. Preliminary Failure Analysis and Structural Design of a Morphing Winglet for Green Regional Aircraft. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation. 2018; ():1.
Chicago/Turabian StyleIgnazio Dimino; Salvatore Ameduri; Antonio Concilio. 2018. "Preliminary Failure Analysis and Structural Design of a Morphing Winglet for Green Regional Aircraft." Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation , no. : 1.
Future aircraft wing technology is rapidly moving toward flexible and morphing wing concepts capable to enhance aircraft wing performance in off-design conditions and to reduce operative maneuver and gust loads. However, due to the reduced stiffness, increased mass, and increased degree of freedom (DOF), such mechanical systems require advanced aeroelastic assessments since the early design phases; this appears crucial to properly drive the design of the underlying mechanisms since the conceptual phase by mitigating their impact on the whole aircraft aeroelastic stability. Preliminary investigations have shown that the combined use of adaptive flap tabs and morphing winglets significantly improves aircraft aerodynamic performance in climb and cruise conditions by the order of 6%. Additionally, by adapting span-wise lift distributions to reduce gust solicitations and alleviate wing root bending moment at critical flight conditions, significant weight savings can also be achieved. Within the scope of Clean Sky 2 Airgreen 2 project, flutter and divergence characteristics of a morphing wing design integrating adaptive winglets and flap tabs are discussed. Multi-parametric flutter analyses are carried out in compliance with CS-25 airworthiness requirements (paragraph 25.629, parts (a), (b), (c) and (d)) to investigate static and dynamic aeroelastic stability behavior of the aircraft. The proposed kinematic systems are characterized by movable surfaces, each with its own domain authority, sustained by a structural skeleton and completely integrated with EMA-based actuation systems. For that purpose, a sensitivity analysis was performed taking into account variations of the stiffness and inertial properties of the referred architectures. Such layouts were reduced to a stick-equivalent model which properties were evaluated through MSC-NASTRAN-based computations. The proprietary code SANDY 4.0 was used to generate the aero-structural model and to solve the aeroelastic stability equations by means of theoretical modes association in frequency domain. Analyses showed the presence of critical modal coupling mechanisms in nominal operative conditions as well as in case of system malfunctioning or failure. Design solutions to assure clearance from instabilities were then investigated. Trade-off flutter and divergence analyses were finally carried out to assess the robustness of the morphing architectures in terms of movable parts layout, mass balancing and actuators damping.
Maria Chiara Noviello; Ignazio Dimino; Francesco Amoroso; Antonio Concilio; Rosario Pecora. Preliminary Assessment of Morphing Winglet and Flap Tabs Influence on the Aeroelastic Stability of Next Generation Regional Aircraft. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation 2018, 1 .
AMA StyleMaria Chiara Noviello, Ignazio Dimino, Francesco Amoroso, Antonio Concilio, Rosario Pecora. Preliminary Assessment of Morphing Winglet and Flap Tabs Influence on the Aeroelastic Stability of Next Generation Regional Aircraft. Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation. 2018; ():1.
Chicago/Turabian StyleMaria Chiara Noviello; Ignazio Dimino; Francesco Amoroso; Antonio Concilio; Rosario Pecora. 2018. "Preliminary Assessment of Morphing Winglet and Flap Tabs Influence on the Aeroelastic Stability of Next Generation Regional Aircraft." Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation , no. : 1.
Aircraft industry is by now deeply involved in technological breakthroughs bringing innovative frameworks, in which the morphing systems constitute the most promising scenario. These systems are taking a remarkable role among the unconventional solutions for the improvement of performance in the operating conditions. The application of morphing devices involves a combination among structural and aerodynamic analyses, actuation requirements, weight assessment and flight control performance. The research project CRIAQ-MDO505, Canadian-European cooperation project on smart technologies, has investigated morphing structures potential through the design and the manufacturing of a variable camber aileron tailored to CS-25 category aircraft applications. This paper is especially focused on the most considerable results able to validate the conceptual design: functionality, ground vibration and wind tunnel tests outcomes have been discussed. The ailerons typically constitute crucial elements for the aerodynamic forces equilibrium of the wing. Therefore, compared to the traditional architectures, the need of studying the dynamic performance and the following aeroelastic impact is, in the specific case of servo-actuated variable-shaped systems, higher. Relying upon the experimental evidence within the present research, the issue appeared concerns the critical importance of considering the dynamic modelling of the actuators in the design phase of a smart device. The higher number of actuators and mechanisms involved makes de facto the morphing structure much more complex. In this context, the action of the actuators has been modelled within the numerical model of the aileron: the comparison between the modal characteristics of numerical predictions and testing activities has shown a high level of correlation. Moreover, the compliance of the device with the design morphing shapes has been proved by wind tunnel test. The outcomes are expected to be key insights for future designers to better comprehend the dynamic response of a morphing aileron, primary knowledge for flutter and failure analyses.
Maurizio Arena; Francesco Amoroso; Rosario Pecora; Gianluca Amendola; Ignazio Dimino; Antonio Concilio. Numerical and experimental validation of a full scale servo-actuated morphing aileron model. Smart Materials and Structures 2018, 27, 105034 .
AMA StyleMaurizio Arena, Francesco Amoroso, Rosario Pecora, Gianluca Amendola, Ignazio Dimino, Antonio Concilio. Numerical and experimental validation of a full scale servo-actuated morphing aileron model. Smart Materials and Structures. 2018; 27 (10):105034.
Chicago/Turabian StyleMaurizio Arena; Francesco Amoroso; Rosario Pecora; Gianluca Amendola; Ignazio Dimino; Antonio Concilio. 2018. "Numerical and experimental validation of a full scale servo-actuated morphing aileron model." Smart Materials and Structures 27, no. 10: 105034.
Within Green Regional Aircraft (GRA), a JTI Integrated Technology Development (ITD) program, an acoustically treated flap (called lined-flap), has been assessed. The design of such a lined-flap, conceived as a low-noise high-lift device, has been optimized through a suitable evolutionary algorithm that refers to an acoustic finite element (FE) model. An original turbulent empirical model has been implemented to estimate the noise, generated by the trailing edge and scattered by the wing body. A semiempirical model has instead supported the design process, relating the acoustic impedance to structural and materials properties. The capability of the proposed system has been finally checked within devoted wind tunnel test experiments.
Mattia Barbarino; Ignazio Dimino; Antonio Concilio. Numerical and Experimental Assessment of the Linflap Technology for Regional Aircraft Noise Reduction. Flinovia—Flow Induced Noise and Vibration Issues and Aspects-II 2018, 131 -145.
AMA StyleMattia Barbarino, Ignazio Dimino, Antonio Concilio. Numerical and Experimental Assessment of the Linflap Technology for Regional Aircraft Noise Reduction. Flinovia—Flow Induced Noise and Vibration Issues and Aspects-II. 2018; ():131-145.
Chicago/Turabian StyleMattia Barbarino; Ignazio Dimino; Antonio Concilio. 2018. "Numerical and Experimental Assessment of the Linflap Technology for Regional Aircraft Noise Reduction." Flinovia—Flow Induced Noise and Vibration Issues and Aspects-II , no. : 131-145.
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.
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 StyleR.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 StyleR.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.
Variation of trailing edge camber proved to be one of the easiest and most effective ways to modify aerofoil shape to match different aircraft operational weights, with benefits approaching 3% of fuel savings or, equivalently, range extension. This is particularly the case of commercial planes, where both initial take-off conditions (because of the unpredictable payload or the specific required mission – transfer flight, for instance) and in-flight states (for the kerosene consumption) can undergo significant differences. Several studies (like the European Research Programs SARISTU or JTI-GRA) demonstrated that the most sensible region for installing an adaptive trailing edge system for those aims is towards the wing tip. This is unfortunately a very delicate area where usually ailerons are deployed and where significant mass insertions could affect the aeroelastic response with some risks of instabilities. Furthermore, the volume available are really limited so that the installation of a fully embedded system is challenging. Moving from the experience taken in many former projects as the cited ones, the authors faced the problem of installing a fully integrated adaptive trailing edge system within the existing structural skeleton of a reference aileron and defined a design strategy to take into account the aeroelastic modifications due to the installation of such a device. Besides, the architecture preserved the original function of that control surface so that it could work as a standard aileron (classical rigid tab movement) with the augmented function of a deformable, quasi-static shape. In this sense, the proposed system exhibited a double functionality: a conventional rigid aileron with augmented shape modification capability plus a continuous, slow change of the trailing edge, occurring during flight for compensating aircraft weight variation. The research was carried out within the Italian-Canadian program MDO-505 and led to the realisation of a multifunctional aileron with two operational motor systems (one for the classical aileron working and the other for the morphing enforcement), completely integrated so that no external element was visible or affected the aerodynamics of the wing. The manufacture of this device was possible thanks to the development of a suitable design process that allowed taking into account both the structural and the aeroelastic response of the integrated architecture. This system was part of an adaptive wing section that was completed with the realisations made by the ETS of Montreal, the Quebecoise Consortium for Aerospace Research and Innovation (CRIAQ) and the IAR-NRC, supported by Bombardier and Thales Canada. The joint demonstrator was tested in the wind tunnel at the NRC facilities in Ottawa and gave confirmation of the aerodynamic, aeroelastic and structural predictions. The paper that is herein presented deals therefore with the design process and the manufacture of an adaptive trailing edge,...
Gianluca Amendola; Ignazio Dimino; Rosario Pecora; Francesco Amoroso; Leonardo Lecce; Antonio Concilio. Technological demonstration of an adaptive aileron system. Bioinspiration, Biomimetics, and Bioreplication VIII 2018, 10593, 1059304 .
AMA StyleGianluca Amendola, Ignazio Dimino, Rosario Pecora, Francesco Amoroso, Leonardo Lecce, Antonio Concilio. Technological demonstration of an adaptive aileron system. Bioinspiration, Biomimetics, and Bioreplication VIII. 2018; 10593 ():1059304.
Chicago/Turabian StyleGianluca Amendola; Ignazio Dimino; Rosario Pecora; Francesco Amoroso; Leonardo Lecce; Antonio Concilio. 2018. "Technological demonstration of an adaptive aileron system." Bioinspiration, Biomimetics, and Bioreplication VIII 10593, no. : 1059304.
Aeronautic and aerospace engineering is recently moving in the direction of developing morphing wing devices, with the aim of making adaptable the aerodynamic shapes to different operational conditions. Those devices may be classified according to two different conceptual architectures: kinematic or compliant systems. Both of them embed within their body all the active components (actuators and sensors), necessary to their operations. In the first case, the geometry variation is achieved through an augmented classical mechanism, while in the second case the form modification is due to a special arrangement of the inner structure creating a distributed elastic hinges arrangement. Whatever is the choice, novel design schemes are introduced. Then, it is almost trivial to conclude that standard methods and techniques cannot be applied easily to these innovative layouts. In other words, because new architectures are produced, the former construction paradigms cannot be maintained as they are but shall be somehow transformed and assimilated by the design engineers’ community. In the meantime, the realization process should go on and morphing elements shall be realized, irrespectively of the full maturity of the associated concepts. Therefore, if optimization methods are important for the better exploitation of usual constructions, they become absolutely necessary for the technological demonstration of the capability of such breakthrough systems. In fact, standing their aim of improving the effectiveness of the aircraft flight and reducing then its overall weight, mass impact plays a fundamental role. Promised benefits could completely vanish if the added should overcome the saved weight! In the study herein presented, the design process of a morphing winglet is reported. The research is collocated within the Clean Sky 2 Regional Aircraft IADP, a large European programme targeting the development of novel technologies for the next generation regional aircraft. The ultimate scope concerns the definition of an adaptive system for alleviating the gust loads and possibly modifying the wing load distribution in the sense of minimizing the attachment momentum (the parameter that governs the wing sizing). The proposed kinematic system is characterized by movable surfaces, each with its own domain authority, sustained by a winglet skeleton and completely integrated with a devoted actuation system. Preliminary aeroelastic investigations did already establish the robustness of the referred structural layout. This paper summarizes the activities relating to the optimization of the envisaged morphing system architecture. Moving from a standard configuration, a process is carried out to identify the lighter adaptive layout that can bear the external and internal loads without experiencing excessive stress levels for its safe operation. The most severe loads are taken into account for this process, as provided by the industrial partner, showing the reliability of the proposed solution on-board of a standard commercial aircraft. The optimization process produces interesting, sometime surprising, results that promise to reduce the weight impact of the structural skeleton for more than 40% with exclusive reference to the regions undergoing the optimization process. Such figure reduces to 15% if the complete structure is taken into account, and 12% if the skin contribution is included. The innovative outcomes are discussed in detail. Results are verified with a dedicated study that proves the consistency of the procedure and the trustworthiness of the computations.
Antonio Concilio; Marco Lo Cascio; Alberto Milazzo; Ignazio Dimino; Gianluca Amendola; Maurizio Arena. Optimization design process of a morphing winglet. Bioinspiration, Biomimetics, and Bioreplication VIII 2018, 10593, 1059305 .
AMA StyleAntonio Concilio, Marco Lo Cascio, Alberto Milazzo, Ignazio Dimino, Gianluca Amendola, Maurizio Arena. Optimization design process of a morphing winglet. Bioinspiration, Biomimetics, and Bioreplication VIII. 2018; 10593 ():1059305.
Chicago/Turabian StyleAntonio Concilio; Marco Lo Cascio; Alberto Milazzo; Ignazio Dimino; Gianluca Amendola; Maurizio Arena. 2018. "Optimization design process of a morphing winglet." Bioinspiration, Biomimetics, and Bioreplication VIII 10593, no. : 1059305.
The in-flight control of the wing shape is widely considered as one of the most promising solutions to enhance the aerodynamic efficiency of the aircraft thus minimizing the fuel burnt per mission ([1]-[26]). In force of the fallout that the implementation of such a technology might have on the greening of the next generation air transport, ever increasing efforts are spent worldwide to investigate on robust solutions actually compliant with industrial standards and applicable airworthiness requirements. In the framework of the CleanSky2, a research program in aeronautics among the largest ever founded by the European Union, the authors focused on the design and validation of two devices enabling the camber-morphing of winglets and flaps specifically tailored for EASA CS-25 category aircraft ([29]). The shape transition was obtained through smart architectures based on segmented (finger-like) ribs with embedded electromechanical actuators. The combined actions of the two smart systems was conceived to modulate the load distribution along the wing while keeping it optimal at all flight conditions with unequalled benefits in terms of lift-over-drag ratio increase and root bending moment alleviation. Although characterized by a quasi-static actuation, and not used as primary control surfaces, the devices were deeply analysed with reference to their impact on aircraft aeroelastic stability. Rational approaches were adopted to duly capture their dynamics through a relevant number of elastic modes; aeroelastic coupling mechanisms were identified in nominal operative conditions as well as in case of systems’ malfunctioning or failure. Trade off flutter and divergence analyses were finally carried out to assess the robustness of the adopted solutions in terms of movable parts layout, massbalancing and actuators damping.
Rosario Pecora; Francesco Amoroso; Ignazio Dimino; Antonio Concilio; Maria Chiara Noviello. Aeroelastic stability analysis of a large civil aircraft equipped with morphing winglets and adaptive flap tabs. Active and Passive Smart Structures and Integrated Systems XII 2018, 10595, 105950L .
AMA StyleRosario Pecora, Francesco Amoroso, Ignazio Dimino, Antonio Concilio, Maria Chiara Noviello. Aeroelastic stability analysis of a large civil aircraft equipped with morphing winglets and adaptive flap tabs. Active and Passive Smart Structures and Integrated Systems XII. 2018; 10595 ():105950L.
Chicago/Turabian StyleRosario Pecora; Francesco Amoroso; Ignazio Dimino; Antonio Concilio; Maria Chiara Noviello. 2018. "Aeroelastic stability analysis of a large civil aircraft equipped with morphing winglets and adaptive flap tabs." Active and Passive Smart Structures and Integrated Systems XII 10595, no. : 105950L.
Gianluca Amendola; Ignazio Dimino; Antonio Concilio; Rosario Pecora; Francesco Amoroso; Maurizio Arena. Morphing Aileron. Morphing Wing Technologies 2018, 547 -582.
AMA StyleGianluca Amendola, Ignazio Dimino, Antonio Concilio, Rosario Pecora, Francesco Amoroso, Maurizio Arena. Morphing Aileron. Morphing Wing Technologies. 2018; ():547-582.
Chicago/Turabian StyleGianluca Amendola; Ignazio Dimino; Antonio Concilio; Rosario Pecora; Francesco Amoroso; Maurizio Arena. 2018. "Morphing Aileron." Morphing Wing Technologies , no. : 547-582.
Antonio Concilio; Ignazio Dimino; Monica Ciminello; Rosario Pecora; Francesco Amoroso; Marco Magnifico. An Adaptive Trailing Edge. Morphing Wing Technologies 2018, 517 -545.
AMA StyleAntonio Concilio, Ignazio Dimino, Monica Ciminello, Rosario Pecora, Francesco Amoroso, Marco Magnifico. An Adaptive Trailing Edge. Morphing Wing Technologies. 2018; ():517-545.
Chicago/Turabian StyleAntonio Concilio; Ignazio Dimino; Monica Ciminello; Rosario Pecora; Francesco Amoroso; Marco Magnifico. 2018. "An Adaptive Trailing Edge." Morphing Wing Technologies , no. : 517-545.
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 StyleMarco 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 StyleMarco 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.