The Italian Aerospace Research Center

Capua, Italy

The Italian Aerospace Research Center

Capua, Italy
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Iuliano E.,The Italian Aerospace Research Center
Springer Tracts in Mechanical Engineering | Year: 2016

The chapter proposes the application of surrogate-based optimization to the efficient design of aeronautical configurations. The surrogate model consists of the Proper Orthogonal Decomposition of computed aerodynamic flow fields and Radial Basis Functions interpolation to reconstruct the aerodynamic flow at any unknown design vector. The surrogate model is coupled to an evolutionary algorithm to globally explore the design space. Several adaptive sampling strategies are proposed, either objective-driven (i.e. aimed at improving the fitness function) or error-driven (i.e. aimed at reducing the prediction error of the surrogate model globally). The proposed methodology is applied to the design optimization of a two-dimensional airfoil in multi-point transonic conditions. The results of different training strategies are critically discussed and compared. © 2016, Springer International Publishing Switzerland.


Iuliano E.,The Italian Aerospace Research Center
Aerospace Science and Technology | Year: 2017

The paper proposes the combination of physics-based surrogate models, adaptive sampling of the design space and evolutionary optimization towards the solution of aerodynamic design problems. The Proper Orthogonal Decomposition is used to extract the main features of the flow field and Radial Basis Function networks allow the surrogate model to predict the target response over the entire design space. In order to train accurate and usable surrogates, ad hoc in-fill criteria are provided which smartly rank and select new samples to enrich the model database. The solution of two aerodynamic benchmark problems is proposed within the framework of the AIAA Aerodynamic Design Optimization Discussion Group. The two benchmark problems consist respectively in the drag minimization of the RAE 2822 airfoil in transonic viscous flow and of the NACA 0012 airfoil in transonic inviscid flow. The shape parameterization approach is based on the Class-Shape Transformation (CST) method with a sufficient degree of Bernstein polynomials to cover a wide range of shapes. Mesh convergence is demonstrated on single-block C-grid structured meshes. The in-house ZEN flow solver is used for Euler/RANS aerodynamic solution. Results show that, thanks to the combined usage of surrogate models and adaptive training in an evolutionary optimization framework, optimal candidates may be located even with limited computational resources with respect to plain evolutionary approaches and similar standard methodologies. © 2017 Elsevier Masson SAS


Botez R.M.,École de Technologie Supérieure of Montreal | Koreanschi A.,École de Technologie Supérieure of Montreal | Gabor O.S.,École de Technologie Supérieure of Montreal | Mebarki Y.,National Research Council Canada | And 8 more authors.
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting | Year: 2017

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 was done in the frame of an international CRIAQ project, and the purpose was to demonstrate the upper surface morphing and aileron morphing capabilities in improving the wing tip aerodynamic performances. During numerical optimization with ‘in-house’genetic algorithm software, and during wind tunnel experimental tests, it was demonstrated that the air flow laminar state was extended and drag coefficient reduction were obtained. © 2017 by Ruxandra Mihaela Botez,Koreanschi Andreea,Oliviu Sugar Gabor.


Dimino I.,the Italian Aerospace Research Center | Concilio A.,the Italian Aerospace Research Center | Schueller M.,Fraunhofer Institute for Electronic Nano Systems | Gratias A.,Fraunhofer Institute for Electronic Nano Systems
Proceedings of SPIE - The International Society for Optical Engineering | Year: 2013

A key technology to enable morphing aircraft for enhanced aerodynamic performance is the design of an adaptive control system able to emulate target structural shapes. This paper presents an approach to control the shape of a morphing wing by employing internal, integrated actuators acting on the trailing edge. The adaptive-wing concept employs active ribs, driven by servo actuators, controlled in turn by a dedicated algorithm aimed at shaping the wing cross section, according to a pre-defined geometry. The morphing control platform is presented and a suitable control algorithm is implemented in a dedicated routine for real-time simulations. The work is organized as follows. A finite element model of the uncontrolled, non-actuated structure is used to obtain the plant model for actuator torque and displacement control. After having characterized and simulated pure rotary actuator behavior over the structure, selected target wing shapes corresponding to rigid trailing edge rotations are achieved through both open-loop and closed-loop control logics. © 2013 SPIE.


Dimino I.,The Italian Aerospace Research Center | Flauto D.,University of Palermo | Diodati G.,The Italian Aerospace Research Center | Concilio A.,The Italian Aerospace Research Center | Pecora R.,University of Naples Federico II
Recent Patents on Mechanical Engineering | Year: 2014

Shape control of adaptive wings has the potential to improve aircraft aerodynamic performance during cruise. In recent years, several patents have been issued for inventions in the field of morphing wings, using hydraulic, electromechanical or smart material-based actuation concepts and architectures. In the framework of SARISTU project (EU-FP7), the joint integration of different conformal morphing concepts in a laminar wing is investigated to improve aircraft performance through a 6% drag reduction, with a positive effect on fuel consumption and required take-off fuel load. An innovative seamless morphing wing incorporating a gapless morphing leading edge, a morphing trailing edge and a wingtip active trailing edge is developed to pursue optimal wing geometry for any flight condition. This paper proposes a state of the art technology to design the actuation system of a morphing trailing edge, consisting of a flexible outer skin and an internal driving mechanism. Focus is given to the modeling and analysis of the morphing actuation, and its integration in the seamless flexible trailing edge control surface. The actuation system is driven by servo rotary actuators and it is designed and established to control the wing trailing edge in order to obtain pre-defined airfoil shapes maximizing wing aerodynamic efficiency. The actuation concept relies on a quick-return mechanism driven by load-bearing actuators controlling the morphing ribs individually. The actuation system is both analytically and numerically addressed. To validate the design, experiments are then carried out with the purpose of estimating the control movement functions suitable for single airfoil camber variations. The morphing rib kinematics including the actuation system is designed to withstand operational pressure loads and actuation forces. © 2014 Bentham Science Publishers.


Dimino I.,The Italian Aerospace Research Center | Concilio A.,The Italian Aerospace Research Center | Pecora R.,University of Naples Federico II
24th AIAA/AHS Adaptive Structures Conference | Year: 2016

In morphing structures, actuation is a key system for general aircraft-level functions. Similarly to the demonstration of safety compliance applied to aircraft control surfaces, novel functions resulting from the integration of a morphing device (ATED), imposes a detailed examination of the associated risks. Because of the concept novelty, literature references for a safe design of a morphing trailing edge device are hard to be found. The safety-driven design of ATED requires a thorough examination of the potential hazards resulting from operational faults involving either the actuation chain, such as jamming, or the external interfaces, such as loss of power supplies and control lanes. In this work, a study of ATED functions is qualitatively performed at both subsystem and aircraft levels to identify potential design faults, maintenance and crew faults, as well as external environment risks. The severity of the hazard effects is determined and placed in specific classes, indicative of the maximum tolerable probability of occurrence for a specific event, resulting in safety design objectives. A fault tree is finally produced to evaluate the impact of actuation kinematics on specific aspects of ATED morphing operation and reliability. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved.


Angelino C.V.,The Italian Aerospace Research Center | Cicala L.,The Italian Aerospace Research Center | De Mizio M.,The Italian Aerospace Research Center | Leoncini P.,The Italian Aerospace Research Center | And 4 more authors.
Lecture Notes in Computer Science (including subseries Lecture Notes in Artificial Intelligence and Lecture Notes in Bioinformatics) | Year: 2013

This paper presents a new low-complexity H.264 encoder, based on x264 implementation, for Unmanned Aerial Vehicles (UAV) applications. The encoder employs a new motion estimation scheme which make use of the global motion information provided by the onboard navigation system. The results are relevant in low frame rate video coding, which is a typical scenario in UAV behind line-of-sight (BLOS) missions. © 2013 Springer-Verlag.


Dimino I.,The Italian Aerospace Research Center | Vitiello P.,The Italian Aerospace Research Center | Aliabadi F.M.H.,Imperial College London
Recent Patents on Mechanical Engineering | Year: 2013

Sound radiation from vibrating panels plays a crucial role in the study of interior noise in transportation vehicles. In recent years, several patents have been issued for inventions in the field of sound reduction technologies to mitigate aircraft noise. This work presents a theoretical analysis and simulations to investigate sound transmission through plate-like multi wall structures. An analytical model is developed to predict sound transmission through infinite-sized triple panel partitions placed in a rigid baffle, from a viewpoint of practical noise control. A numerical procedure is also developed to evaluate the transmission characteristics of finite partitions due to an incident diffuse field. The method is based on a hybrid FEM/Rayleigh methodology and utilizes numerically calculated sound transmission loss of flat multi panel partitions and box like cavities with idealized boundary conditions. Two simplifying assumptions are made: the surrounding medium is air and the radiated sound power is calculated by an array of discrete elemental radiators. Several examples are presented to demonstrate the accuracy of the proposed approach. A theoretical performance analysis is finally carried out on a triple panel partition representative of a more complex triple wall aircraft-type window. The testbed design, used for this study, is guided by an effort to quantify sound insulation capabilities of aircraft windows with a specific focus on passenger's protection against noise transmitted through fuselage panels. © 2013 Bentham Science Publishers.


Paletta N.,The Italian Aerospace Research Center | Cristillo D.,The Italian Aerospace Research Center | Belardo M.,The Italian Aerospace Research Center | Marino A.,The Italian Aerospace Research Center | Pecora M.,The Italian Aerospace Research Center
Latin American Journal of Solids and Structures | Year: 2016

This paper presents a methodology for the conceptual design of a Maneuver Load Control system taking into account the airframe flexibility. The system, when switched on, is able to minimize the bending moment augmentation at a wing station near the wing root during an unsteady longitudinal maneuver. The reduction of the incremental wing bending moment due to maneuvers can lead to benefits such as improved pay-loads/gross weight capabilities and/or extended structural fatigue life. The maneuver is performed by following a desired vertical load factor law with elevators deflections, starting from the trim equilibrium in level flight. The system observes load factor and structural bending through accelerometers and calibrated strain sensors and then sends signals to a computer that symmetrically actuates ailerons for reducing the structural bending and elevators for compensating the perturbation to the longitudinal equilibrium. The major limit of this kind of systems appears when it has to be installed on commercial transport aircraft for reduced OEW or augmented wing aspect-ratio. In this case extensive RAMS analyses and high redundancy of the MLC related sub-systems are required by the Certification Authority. Otherwise the structural design must be performed at system off. Thus the unique actual benefit to be gained from the adoption of a MLC system on a commercial transport is the fatigue life extension. An application to a business aircraft responding to the EASA Certification Specifications, Part 25, has been performed. The aircraft used for the numerical application is considered only as a test casestudy. Most of design and analysis considerations are applicable also to other aircraft, such as unmanned or military ones, although some design requirements can be clearly different. The estimation of the fatigue life extension of a structural joint (wing lower skinstringer), located close to the wing root, has been estimated by showing the expected benefit to be gained from the adoption of such a maneuvering load control system. © 2016, Latin American Journal of Solids and Structures. All rights reserved.


Iuliano E.,The Italian Aerospace Research Center | Quagliarella D.,The Italian Aerospace Research Center
53rd AIAA Aerospace Sciences Meeting | Year: 2015

The paper proposes the application of evolutionary-based optimization coupled with physics-based and adaptively-trained surrogate model to the solution of two aerodynamic benchmark problems defined within the AIAA Aerodynamic Design Optimization Discussion Group. The benchmark problems are represented respectively by the drag minimization of the RAE 2822 airfoil in transonic viscous flow and of the NACA 0012 airfoil in transonic inviscid flow. The shape parameterization approach consists of the Class-Shape Transformation (CST) method with a sufficient degree of Bernstein polynomials to cover a wide range of shapes. Mesh convergence is demonstrated on single-block C-grid structured meshes. The in-house ZEN ow solver is used for Euler/RANS aerodynamic solution. Results show that, thanks to the combined usage of surrogate models and intelligent training, optimal candidates may be located in the design space even with limited computational resources with respect to brute force optimization approaches. © 2015 by Emiliano Iuliano. Published by the American Institute of Aeronautics and Astronautics, Inc.

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