Prof. Massimo Viscardi Profile

Prof. Massimo Viscardi

at University of Naples Federico II

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Author

Publications (7)

Proceedings Article | 28 March 2018 Presentation + Paper

A modified Shunted Switch Architecture (SSSA) for active vibration control

Massimo Viscardi, Maurizio Arena, Monica Ciminello

Proceedings Volume 10595, 1059508 (2018) https://doi.org/10.1117/12.2296421

KEYWORDS: Switches, Active vibration control, Control systems, Sensors, Stochastic processes

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Proceedings Article | 27 March 2018 Paper

Experimental technologies comparison for strain measurement of a composite main landing gear bay specimen

Massimo Viscardi, Maurizio Arena, Monica Ciminello, Michele Guida, Carosena Meola, Pietro Cerreta

Proceedings Volume 10599, 105990N (2018) https://doi.org/10.1117/12.2296420

KEYWORDS: Fiber Bragg gratings, Composites, Digital image correlation, Thermography, Aerospace engineering, Infrared imaging, Infrared radiation, Failure analysis, Computer aided design, Sensors

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Proceedings Article | 27 March 2018 Paper

Piezoresistive strain sensing of carbon nanotubes-based composite skin for aeronautical morphing structures

Massimo Viscardi, Maurizio Arena, Giuseppina Barra, Luigi Vertuccio, Monica Ciminello, Liberata Guadagno

Proceedings Volume 10599, 105991C (2018) https://doi.org/10.1117/12.2295938

KEYWORDS: Composites, Epoxies, Sensors, Carbon, Resistance, Fiber Bragg gratings, Skin, Carbon nanotubes, Nanocomposites, Aerospace engineering

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Nowadays, smart composites based on different nano-scale carbon fillers, such as carbon nanotubes (CNTs), are increasingly being thought of as a more possible alternative solution to conventional smart materials, mainly for their improved electrical properties. Great attention is being given by the research community in designing highly sensitive strain sensors for more and more ambitious challenges: in such context, interest fields related to carbon nanotubes have seen extraordinary development in recent years. The authors aim to provide the most contemporary overview possible of carbon nanotube-based strain sensors for aeronautical application. A smart structure as a morphing wing needs an embedded sensing system in order to measure the actual deformation state as well as to “monitor” the structural conditions. Looking at more innovative health monitoring tools for the next generation of composite structures, a resin strain sensor has been realized. The epoxy resin was first analysed by means of a micro-tension test, estimating the electrical resistance variations as function of the load, in order to demonstrate the feasibility of the sensor. The epoxy dogbone specimen has been equipped with a standard strain gauge to quantify its strain sensitivity. The voltamperometric tests highlight a good linearity of the electrical resistance value as the load increases at least in the region of elastic deformation of the material. Such intrinsic piezoresistive performance is essentially attributable to the re-arrangement of conductive percolating network formed by MWCNT, induced by the deformation of the material due to the applied loads. The specimen has been prepared within this investigation, to demonstrate its performance for a future composite laminate typical of aerospace structures. The future carbon-fiber sensor can replace conventional metal foil strain gauges in aerospace applications. Furthermore, dynamic tests will be carried out to detect any non-reversible changes to the sensing response.

Proceedings Article | 27 March 2018 Paper

Impact detection method for composite winglets based on neural network implementation

Massimo Viscardi, Maurizio Arena, Pasquale Napolitano

Proceedings Volume 10599, 105990Q (2018) https://doi.org/10.1117/12.2296571

KEYWORDS: Neural networks, Composites, Structural health monitoring, Algorithm development, Inspection, Sensors, Detection and tracking algorithms, Finite element methods, Aerospace engineering, Safety

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Proceedings Article | 16 August 2001 Paper

Multifunctional system for active noise control and damage detection on a typical aeronautical structure

Leonardo Lecce, Massimo Viscardi, Giuseppe Zumpano

Proceedings Volume 4327, (2001) https://doi.org/10.1117/12.436531

KEYWORDS: Sensors, Actuators, Intelligence systems, Control systems, Damage detection, Skin, Distributed interactive simulations, Vibration control, Environmental sensing, Denoising

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The present work relates to the assessment and testing of a multifunctional intelligent system, based upon the use of piezoelectric devices, devoted both to the active noise and vibration control and to damage detection f the structure. In the control application, the piezoelectric devices (in form of patches) play the role of actuators; their induced secondary vibration field has the target to reduce the primary one through a specific control algorithm and system. In the health monitoring application, the piezo devices play both the roles of actuators and sensors. In fact the developed technique is primarily based upon the evaluation and comparison of the structure Frequency Response Functions (FRF) that intrinsically contains all the information regarding the structural properties whose change may be correlated with incipient damages. The aforementioned application were investigated and experimentally assessed with good results with reference to a typical partial fuselage structure (three frames, eight stringers and the skin panels: 1.2 m x 1.7 m). On the noise control application side, a height sensors/height actuators control architecture was then assessed and experimentally tested whose results may be synthesized in a 30 dB vibration level reduction at sensors locations and more than 20 dB of reduction of the associated noise field. In the optic of a multifunctional intelligent system, the aforementioned set of piezo's was decided to be used also for health monitoring application. As a preliminary activity, an extensive monitoring was performed on the integer structure to verify the sensibility of the system and the stability of the defined Damage Index (DI) in respect to environmental factor not related to structural real modification. To verify the sensibility of the technique to reveal and locate a typical shear clip damage, a set of rivets were successively cut in the area surrounding the frame shear clip, and relative FRF's were acquired and relative DI calculated. The analysis of the data showed a good sensibility of the system to identify the presence of a damage with maximum values of the DI in the sensor closest to the damage location and with an absolute value of the index growing up with damage extension.

Proceedings Article | 31 March 1998 Paper

Damage identification and location on a typical aeronautical structure

Luca Napolitano, Paolo Fedele, Massimo Viscardi, Leonardo Lecce

Proceedings Volume 3397, (1998) https://doi.org/10.1117/12.305040

KEYWORDS: Sensors, Actuators, Signal processing, Damage detection, Nondestructive evaluation, Safety, Inspection, Modal analysis, Spectrum analysis, Computer simulations

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Proceedings Article | 26 April 1996 Paper

Active vibration control by piezoceramic actuators on a jet aircraft partial frame structure

Leonardo Lecce, Massimo Viscardi, Stefania Cantoni

Proceedings Volume 2779, (1996) https://doi.org/10.1117/12.237040

KEYWORDS: Actuators, Active vibration control, Sensors, Control systems, Vibration control, Artificial neural networks, Aircraft structures, Ferroelectric materials, Acoustics, Intelligence systems

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