Prof. Rosario Pecora Profile

Prof. Rosario Pecora

Assistant Professor at Univ degli Studi di Napoli Federico II

SPIE Involvement:

Author

Area of Expertise:

Aircraft Structures , Aeroelasticity , Morphing Adaptive Structures , Smart Structures , Dynamics of Structures , Smart Materials

Profile Summary

Master degree in Aeronautical Engineering and Ph.D. in Transport Engineering awarded by the University of Naples “Federico II” on 2002 and 2005. Assistant Professor of Aircraft Structures Stability and Lecturer of Advanced Aircraft Structures at the same University since 2011. He has worked for many aircraft manufacturing companies (including but to limited to ATR, ALENIA AERMACCHI, BOMBARDIER, PIAGGIO AEROINDUSTRIES) and research centers as technical advisor for loads, aeroelasticity, aircraft structures design and certification (EASA CS-23,-25 standards). His research activity is mainly focused on aero-servo-elasticity of unconventional structural systems, structures dynamics and smart structures while covering leading roles in major European and extra-European projects (CAPECON, Clean Sky GRA, SARISTU, CRIAQ-MDO505, Cleans Sky 2). He is author of several scientific papers, editor of a book on morphing wing technologies for large civil airplanes and designed inventor of European and US patents on SMA-based architectures for morphing wing trailing edge.

Publications (15)

Proceedings Article | 22 March 2021 Presentation + Paper

Presentation + Paper

Design of a morphing test-article for large-scale, high-speed wind tunnel tests of an adaptive wing flap

Rosario Pecora, Francesco Amoroso, Mürüvvet Sinem Sicim

Proceedings Volume 11588, 1158808 (2021) https://doi.org/10.1117/12.2580861

KEYWORDS: Wind measurement, Aerodynamics, CFD analysis

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Large efforts are currently being spent in Europe for the maturation of innovative technologies enabling the application of morphing systems on next-generation civil transport aircraft. Running along with the CleanSky2 platform, the AirGreen2 project aims to evolve the proofs of concept addressed during the CleanSky program into true-scale demonstrators for a more comprehensive validation of morphing architectures both on the ground and in flight. In this challenging framework, research activities have been carried out to design a novel multi-modal camber morphing flap for the enhancement of the aerodynamic performances of a new-generation regional aircraft. Referring to CFD analyses, very relevant benefits in terms of CLmax increase and stall angle delay were proved to be achievable by properly morphing the camber of the flap; the extra-lift produced by flap cambering resulted more than adequate to allow for takeoff and landing at a single flap deployment angle, in turn much lower than those required by a standard flap in both settings. As a side positive effect, a dramatic simplification of the flap deployment system was shown to be practicable, together with the adoption of fairing-less (no-drag) solutions with flap tracks fully embedded into the wing. In addition, wing aerodynamic efficiency in cruise was demonstrated to be enhanced by locally morphing the tip of the flap still exposed to the aerodynamic flow in flap-retracted configuration. The design and validation of the smart architecture enabling the different morphing modes required for low speed (take-off / landing) and high speed (cruise) conditions, consisted of a complex process involving both wind tunnel and ground tests. To increase the relevance of the wind tunnel test campaign, a large scale-factor (1:3) was selected for the test-article, in combination with the realization of the very same Mach numbers expected in flight. Standing the un-scalability of the flap architecture conceived for ground tests and flight operations, a very challenging design was faced for the test article, in order to define a totally new morphable system (Fig.1), assuring the same functionalities of the true-scale device. The path followed to accomplish this task has been outlined in this work, with emphasis on adopted design philosophy, implemented methodologies, and technological solutions.

Proceedings Article | 19 May 2020 Paper

Paper

Aircraft morphing systems: elasticity of selected components and modelling issues

A. Concilio, I. Dimino, R. Pecora, M. Arena

Proceedings Volume 11376, 113760M (2020) https://doi.org/10.1117/12.2560161

KEYWORDS: Modeling, Kinematics, Actuators, Aerodynamics, Numerical simulations, Performance modeling, Aerospace engineering, Skin, Complex systems, Lead, Smart structures

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Morphing is an increasingly investigated topic in aeronautics due to the performance improvements brought by aerodynamic shapes adaptivity on large aircraft. Being aerodynamics mainly driven by geometry, a structure that can modify its shape may achieve tremendous capability enhancement, especially if its operating scenario is wide. However, the implementation of morphing structures leads to many issues that still need to be properly solved to make the technology fully operative in real application scenarios. For instance, additional DOFs generate systems with increased modal density and then with more complex aeroelastic behaviour, and premature onset of dynamic instabilities. The authors of the present paper have dealt with this problem in other publications, in cooperation with several colleagues, and interesting results are available in literature, to some extent. In this general framework, there are peculiar aspects that only recently have started to catch the attention of the scientific community. Among those, a particular one is the objective of the present work, referring to the numerical simulation strategy of adaptive devices. The kinematic system at the basis of a wide class of morphing structures is driven by an actuation chain, which gives an important contribution to the already cited aeroelastic behaviour. For safety-critical embedded subsystems, it is crucial to detect potential failures and predict their impacts since the early design stages. Now, kinematic components significantly affecting the structural dynamics, as torsion bars and bearings, are assumed rigid in the traditional simulation strategy. If such a concept may be supposed valid for standard layouts (as in the case of flap, ailerons and other moveable systems), it cannot be held for architectures integrating hundreds of those mechanical parts. This work addresses preliminary investigations on systematic analyses carried out on detailed simulations of selected components of aircraft morphing structures, trying to evaluate the effects of elasticity of bearings and hinged connections on the global dynamic response.

Proceedings Article | 21 March 2019 Paper

Paper

Effect of hinge elasticity on morphing winglet mechanical systems

Antonio Concilio, Ignazio Dimino, Rosario Pecora, Maurizio Arena, Salvatore Ameduri

Proceedings Volume 10967, 1096711 (2019) https://doi.org/10.1117/12.2514356

KEYWORDS: Kinematics, Modeling, Aerodynamics, Actuators, Skin, Aerospace engineering, Systems modeling, System integration, Electromechanical design, Additive manufacturing

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Proceedings Article | 21 March 2019 Presentation + Paper

Presentation + Paper

Flutter analysis of a large civil aircraft in case of free-plays and internal failures of morphing wing flaps mechanical systems

Rosario Pecora, Francesco Amoroso, Ignazio Dimino, Antonio Concilio

Proceedings Volume 10967, 109670Y (2019) https://doi.org/10.1117/12.2514251

KEYWORDS: Aerodynamics, Actuators, 3D modeling, Control systems, Numerical analysis, Aerospace engineering, Electromechanical design, New and emerging technologies, Smart structures

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The adoption of mechanical systems represents a very promising solution to realistically enable wing-camber morphing for large civil aircraft. These systems implement the change of shape through the relative motion of parts usually interconnected by means of hinges, and therefore, without any morphing-induced elastic deformation of the load carrying structure; conversely to what happens in compliant structures, the energy provided by the actuation system is here spent to counteract only the external aerodynamic loads which are in turn dependant on shape, speed and flight altitude. Apart of the more effective use of the available power, the mechanical systems show a higher level of technological maturity and readiness for flight thanks to their higher robustness, reliability and maintainability, as well as in force of their similarity with conventional airworthy architectures already in flight. On the other hand, the use of multiple-hinges connections imposes a careful analysis of the effects induced by any degradation of their mechanical performance leading to overall system malfunction or local failures. 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 a camber-morphing flap specifically tailored for EASA CS-25 category aircraft. The shape transition is obtained through a smart architecture based on segmented (finger-like) ribs with embedded electromechanical actuators. Three large tabs were located at the flap trailing edge to actively control the shape of the wing in cruise and to optimize the aerodynamic load distribution along the span. Aeroelastic phenomena related to these flap components were duly addressed since the very preliminary design stage in order to avoid the maturation of a potentially unstable architecture; rational approaches compliant with applicable airworthiness requirements were implemented to properly model and investigate the aeroelastic behaviour of the flap tabs in nominal working conditions. Finally, free plays and internal failures were accurately simulated and their effects on the aeroelastic stability of the aircraft were duly investigated in order to assess the robustness of the conceived tabs as well as of the embedded mechanical subsystems driving their motion.

Proceedings Article | 27 March 2018 Paper

Paper

Technological demonstration of an adaptive aileron system

Gianluca Amendola, Ignazio Dimino, Antonio Concilio, Rosario Pecora, Francesco Amoroso, Leonardo Lecce

Proceedings Volume 10593, 1059304 (2018) https://doi.org/10.1117/12.2297083

KEYWORDS: Aerodynamics, Actuators, Skin, Kinematics, Computer aided design, Manufacturing, Wind measurement, Aerospace engineering, Prototyping, Interfaces

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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, installed within the existing aileron system of a wing segment, to undergo wind tunnel tests. The resulting device considers the definition of the kinematic structural system, the development of the integrated actuator system, their integration and the assessment of their static and dynamic structural response, and the verification of a safe aeroelastic behavior. Numerical and experimental results are presented, achieved in lab and wind tunnel environments.

Proceedings Article | 16 March 2018 Paper

Paper

Control strategy of an electrically actuated morphing flap for the next generation green regional aircraft

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

Proceedings Volume 10595, 105950K (2018) https://doi.org/10.1117/12.2296424

KEYWORDS: Embedded systems, Smart materials, Control systems design, Distributed computing, Actuators, Image segmentation, Logic, Shape analysis, Aerodynamics, Prototyping

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Proceedings Article | 16 March 2018 Paper

Paper

Feasibility studies for the installation of Plasma Synthetic Jet Actuators on the skin of a morphing wing flap

Maurizio Arena, Matteo Chiatto, Francesco Amoroso, Rosario Pecora, Luigi de Luca

Proceedings Volume 10595, 105950M (2018) https://doi.org/10.1117/12.2300512

KEYWORDS: Actuators, Electromagnetism, Skin, Control systems, Plasma, Aerodynamics, Power supplies, Electrodes, Electromagnetic coupling, Magnetism

Read Abstract +

A morphing structure can be considered as the result of the synergic integration of three main systems: the structural system, based on reliable kinematic mechanisms or on compliant elements enabling the shape modification, the actuation and control systems, characterized by embedded electromechanical actuators and robust control strategies, and the sensing system, usually involving a network of sensors distributed along the structure to monitor its state parameters. Technologies with ever increasing maturity level are adopted to assure the consolidation of products in line with the aeronautical industry standards and fully compliant with the applicable airworthiness requirements. In the framework of the CleanSky2, one of the largest research projects ever funded by the European Union, a novel multi-modal camber morphing flap was conceived for the enhancement of the aerodynamic performances of the next generation green regional aircraft. Thanks to different morphing modes, the shape of the flap can be suitably adapted in order to preserve an optimal configuration as the aircraft trim parameters change according to the specific flight phase (take-off, climb, cruise, descent, landing). To further improve the benefits brought by such technology on the wing aerodynamic efficiency, an active flow control system based on plasma synthetic jet (PSJ) actuators was investigated for a potential installation on the upper skin of the flap. PSJ actuators, or Sparkjets, are able to produce very high jet velocities, without the aid of any moving parts, affecting the structure of the flow-field to be controlled and allowing a positive variation of the aerodynamic forces on the aircraft, with a modest power consumption. This work is focused on the two main aspects related to the feasibility of PSJ actuators integration into the adaptive flap skin: the thermal and electromagnetic interferences of the actuators with the other electronic equipment of the flap. Experimental measurements were carried out to characterize the thermal and the electromagnetic fields induced by the operating device into the surrounding structure. A simplified test article was designed and manufactured to support all experimental activities while being fairly representative of the actual PSJ-skin assembly. Test results allowed for a definition of the safety-critical areas for the installation of flap actuation, control and sensing systems.

Proceedings Article | 15 March 2018 Presentation + Paper

Presentation + Paper

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

R. Pecora, F. Amoroso, M. Noviello, I. Dimino, A. Concilio

Proceedings Volume 10595, 105950L (2018) https://doi.org/10.1117/12.2300173

KEYWORDS: Aerodynamics, Actuators, Control systems, 3D modeling, Aerospace engineering, Modulation, Safety, Matrices, Modeling

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Proceedings Article | 4 April 2017 Paper

Paper

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

R. Pecora, F. Amoroso, M. Arena, M. C. Noviello, F. Rea

Proceedings Volume 10166, 101660L (2017) https://doi.org/10.1117/12.2259878

KEYWORDS: Prototyping, Safety, Control systems, Aerospace engineering, Manufacturing, Actuators, Computer programming, Skin, Kinematics, Aerodynamics, Sensors

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Within the framework of the JTI-Clean Sky (CS) project, and during the first phase of the Low Noise Configuration Domain of the Green Regional Aircraft – Integrated Technological Demonstration (GRA-ITD, the preliminary 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, 130- seats with open rotor configuration. 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. Studies and tests were limited to a portion of the flap element obtained by slicing the actual flap geometry with two cutting planes distant 0.8 meters along the wing span. Further activities were then addressed in order to increase the TRL of the validated architecture within the second phase of the CS-GRA. Relying upon the already assessed concept, an innovative and more advanced flap device was designed in order to enable two different morphing modes on the basis of the A/C flight condition / flap setting: Mode1, Overall camber morphing to enhance high-lift performances during take-off and landing (flap deployed); Mode2, Tab-like morphing mode. Upwards and downwards deflection of the flap tip during cruise (flap stowed) for load control at high speed. A true-scale segment of the outer wing flap (4 meters span with a mean chord of 0.9 meters) was selected as investigation domain for the new architecture in order to duly face the challenges posed by real wing installation. Advanced and innovative solutions for the adaptive structure, actuation and control systems were duly analyzed and experimentally validated thus proving the overall device compliance with industrial standards and applicable airworthiness requirements.

Proceedings Article | 4 April 2017 Presentation + Paper

Presentation + Paper

Preliminary aeroelastic assessment of a large aeroplane equipped with a camber-morphing aileron

Rosario Pecora, Francesco Amoroso, Rita Palumbo, Maurizio Arena, Gianluca Amendola, Ignazio Dimino

Proceedings Volume 10166, 101660E (2017) https://doi.org/10.1117/12.2260008

KEYWORDS: Embedded systems, Prototyping, Safety, Aerospace engineering, Actuators, Aerodynamics, Neodymium, Skin, Control systems, Finite element methods, Failure analysis

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Proceedings Article | 20 April 2016 Paper

Paper

Experimental characterization of an adaptive aileron: lab tests and FE correlation

Gianluca Amendola, Ignazio Dimino, Francesco Amoroso, Rosario Pecora

Proceedings Volume 9803, 98034P (2016) https://doi.org/10.1117/12.2219187

KEYWORDS: Smart structures, Aerodynamics, Control systems, Design for manufacturability, Manufacturing, System integration, Actuators, Kinematics, Skin, Aerospace engineering, Finite element methods, Prototyping

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Proceedings Article | 20 April 2016 Paper

Paper

Numerical design of an adaptive aileron

Gianluca Amendola, Ignazio Dimino, Antonio Concilio, Marco Magnifico, Rosario Pecora

Proceedings Volume 9803, 98032A (2016) https://doi.org/10.1117/12.2219167

KEYWORDS: Smart structures, Prototyping, Structural design, Complex systems, Finite element methods, Servomechanisms, Actuators, Skin, Kinematics, Aerospace engineering, Bismuth, Modeling

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The study herein described is aimed at investigating the feasibility of an innovative full-scale camber morphing aileron device. In the framework of the “Adaptive Aileron” project, an international cooperation between Italy and Canada, this goal was carried out with the integration of different morphing concepts in a wing-tip prototype. As widely demonstrated in recent European projects such as Clean Sky JTI and SARISTU, wing trailing edge morphing may lead to significant drag reduction (up to 6%) in off-design flight points by adapting chord-wise camber variations in cruise to compensate A/C weight reduction following fuel consumption. Those researches focused on the flap region as the most immediate solution to implement structural adaptations. However, there is also a growing interest in extending morphing functionalities to the aileron region preserving its main functionality in controlling aircraft directional stability. In fact, the external region of the wing seems to be the most effective in producing “lift over drag” improvements by morphing. Thus, the objective of the presented research is to achieve a certain drag reduction in off-design flight points by adapting wing shape and lift distribution following static deflections. In perspective, the developed device could also be used as a load alleviation system to reduce gust effects, augmenting its frequency bandwidth. In this paper, the preliminary design of the adaptive aileron is first presented, assessed on the base of the external aerodynamic loads. The primary structure is made of 5 segmented ribs, distributed along 4 bays, each splitted into three consecutive parts, connected with spanwise stringers. The aileron shape modification is then implemented by means of an actuation system, based on a classical quick-return mechanism, opportunely suited for the presented application. Finite element analyses were assessed for properly sizing the load-bearing structure and actuation systems and for characterizing their dynamic behavior. Obtained results are reported and widely discussed.

Proceedings Article | 16 April 2016 Presentation + Paper

Presentation + Paper

KRISTINA: Kinematic rib-based structural system for innovative adaptive trailing edge

R. Pecora, F. Amoroso, M. Magnifico, I. Dimino, A. Concilio

Proceedings Volume 9801, 980107 (2016) https://doi.org/10.1117/12.2218516

KEYWORDS: Kinematics, Aerodynamics, Aerospace engineering, Skin, Analytical research, Structural design, Smart materials, Aircraft structures, Smart structures, Actuators, Foam, Computer aided design, Safety, Aluminum, Finite element methods

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Proceedings Article | 16 April 2016 Presentation + Paper

Presentation + Paper

Toward the bi-modal camber morphing of large aircraft wing flaps: the CleanSky experience

R. Pecora, F. Amoroso, M. Magnifico

Proceedings Volume 9801, 980106 (2016) https://doi.org/10.1117/12.2218415

KEYWORDS: Aerodynamics, Control systems, Manufacturing, Aerospace engineering, Aircraft structures, Smart structures, Actuators, Kinematics, Skin, Silicon, Chemical elements, Shape analysis, Motion analysis

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Proceedings Article | 1 November 2007 Paper

Paper

Wing chamber control architectures based on SMA: numerical investigations

Silvestro Barbarino, Salvatore Ameduri, Rosario Pecora

Proceedings Volume 6423, 64231E (2007) https://doi.org/10.1117/12.779397

KEYWORDS: Shape memory alloys, Aerodynamics, Actuators, Chemical elements, Aluminum, Computer architecture, Temperature metrology, 3D modeling, Aerospace engineering, Smart materials

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Showing 5 of 15 publications

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