Cira Italian Aerospace Research Center

Capua, Italy

Cira Italian Aerospace Research Center

Capua, Italy
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Toscano C.,Cira Italian Aerospace Research Center | Lenzi F.,IMAST Scarl
Civil-Comp Proceedings | Year: 2010

In this work, specific viscoelastic materials characterized by different complex modulus have been selected, embedded and co-cured into the graphite/epoxy structure composites in order to study the impact behaviour of the obtained structures. Therefore, an impact test campaign at the same energy has been performed on the embedded panels as well as on simple graphite/epoxy laminates. The effects of the impact have been examined via Non Destructive Testing (NDT) using the Ultrasound Pulse-Echo technique, and by optical microscopy analysis, then the results have been compared. The presented work allows to establish that the impact behaviour of graphite/epoxy laminates could be highly influenced by the presence of damping layers. In particular the damping layers seems to strongly limit the damaged area, effectively reducing the inter-lamina damage propagation. © Civil-Comp Press, 2010.

Scordamaglia V.,University of Reggio Calabria | Sollazzo A.,Cira Italian Aerospace Research Center | Mattei M.,The Second University of Naples
IFAC Proceedings Volumes (IFAC-PapersOnline) | Year: 2012

This paper presents the application of an H ∞ control technique to the control of a HAPD (High Altitude Performance Demonstrator) aircraft having redundant surfaces. The interaction of the controlling moments and forces with the aircraft flexible modes requires a careful use of the control resources in the frequency domain also considering that aerodynamic surface deflections are limited in amplitude and angular rates. A fixed structure H ∞ control problem design, inspired by the classical minimum norm allocation control approach, is formulated and solved in terms of Linear Matrix Inequalities. Numerical simulations on the full nonlinear model of the HAPD including flexibility modes are carried out to show the effectiveness of the proposed technique on the whole flight envelope which is covered using a parameter dependent formulation of the linearized model plants. © 2012 IFAC.

Riccio A.,Cira Italian Aerospace Research Center | Giordano M.,CNR Institute of Composite and Biomedical Materials | Zarrelli M.,CNR Institute of Composite and Biomedical Materials
Journal of Composite Materials | Year: 2010

In this article, a simplified linear analysis-based approach to simulate the delamination growth initiation in stiffened composite panels, suitable as preliminary design and optimization tool implemented into a finite element code, is presented. The proposed approach is based on the determination of the delamination buckling and on the evaluation of the energy released during the delamination propagation by means of eigenvalue and linear static analyses. Stiffened composite panels with circular embedded bay delaminations, under compression loads, were adopted as a benchmark to test the simulation capabilities of the method. Obtained results, in terms of delamination growth initiation load and energy release rate distributions along the delamination front, have been compared to nonlinear results obtained by the virtual crack closure technique and experimental data for preliminary validation purposes. Comments and considerations upon the applicability of this methodology are, finally, provided with particular focus on delamination sizes and locations within the considered structural elements. © The Author(s), 2010.

Amoroso F.,University of Naples Federico II | Pecora R.,University of Naples Federico II | Ciminello M.,Cira Italian Aerospace Research Center | Concilio A.,Cira Italian Aerospace Research Center
Smart Structures and Systems | Year: 2015

Today, as railways increase their capacity and speeds, it is more important than ever to be completely aware of the state of vehicles fleet's condition to ensure the highest quality and safety standards, as well as being able to maintain the costs as low as possible. Operation of a modern, dynamic and efficient railway demands a real time, accurate and reliable evaluation of the infrastructure assets, including signal networks and diagnostic systems able to acquire functional parameters. In the conventional system, measurement data are reliably collected using coaxial wires for communication between sensors and the repository. As sensors grow in size, the cost of the monitoring system can grow. Recently, auto-powered wireless sensor has been considered as an alternative tool for economical and accurate realization of structural health monitoring system, being provided by the following essential features: On-board micro-processor, sensing capability, wireless communication, auto-powered battery, and low cost. In this work, an original harvester device is designed to supply wireless sensor system battery using train bogie energy. Piezoelectric materials have in here considered due to their established ability to directly convert applied strain energy into usable electric energy and their relatively simple modelling into an integrated system. The mechanical and electrical properties of the system are studied according to the project specifications. The numerical formulation is implemented with in-house code using commercial software tool and then experimentally validated through a proof of concept setup using an excitation signal by a real application scenario. Copyright © 2015 Techno-Press, Ltd.

Ciminello M.,Cira Italian Aerospace Research Center | Ameduri S.,Cira Italian Aerospace Research Center | Concilio A.,Cira Italian Aerospace Research Center | Flauto D.,University of Palermo | Mennella F.,University of Naples Federico II
Smart Structures and Systems | Year: 2015

An original sensor system based on Fiber Bragg Gratings (FBG) for the strain monitoring of an adaptive wing element is presented in this paper. One of the main aims of the SARISTU project is in fact to measure the shape of a deformable wing for performance optimization. In detail, an Adaptive Trailing Edge (ATE) is monitored chord- and span-wise in order to estimate the deviation between the actual and the desired shape and, then, to allow attaining a prediction of the real aerodynamic behavior with respect to the expected one. The integration of a sensor system is not trivial: it has to fit inside the available room and to comply with the primary issue of the FBG protection. Moreover, dealing with morphing structures, large deformations are expected and a certain modulation is necessary to keep the measured strain inside the permissible measure range. In what follows, the mathematical model of an original FBG-based structural sensor system is presented, designed to evaluate the chord-wise strain of an Adaptive Trailing Edge device. Numerical and experimental results are compared, using a proof-of-concept setup. Further investigations aimed at improving the sensor capabilities, were finally addressed. The elasticity of the sensor structure was exploited to enlarge both the measurement and the linearity range. An optimisation process was then implemented to find out an optimal thickness distribution of the sensor system in order to alleviate the strain level within the referred component. Copyright © 2015 Techno-Press, Ltd.

Meola C.,University of Naples Federico II | Toscano C.,Cira Italian Aerospace Research Center
Materials | Year: 2014

It is a fact that the presence of porosity in composites has detrimental effects on their mechanical properties. Then, due to the high probability of void formation during manufacturing processes, it is necessary to have the availability of non-destructive evaluation techniques, which may be able to discover the presence and the distribution of porosity in the final parts. In recent years, flash thermography has emerged as the most valuable method, but it is still not adequately enclosed in the industrial enterprise. The main reason of this is the lack of sufficient quantitative data for a full validation of such a technique. The intention of the present work is to supply an overview on the current state-of-the-art regarding the use of flash thermography to evaluate the porosity percentage in fiber reinforced composite materials and to present the latest results, which are gathered by the authors, on porous carbon fiber reinforced polymer laminates. To this end, several coupons of two different stacking sequences and including a different amount of porosity are fabricated and inspected with both non-destructive and destructive testing techniques. Data coming from non-destructive testing with either flash thermography or ultrasonics are plotted against the porosity percentage, which was previously estimated with the volumetric method. The new obtained results are a witness to the efficacy of flash thermography. Some key points that need further consideration are also highlighted. © 2014 by the authors.

Toscano C.,Cira Italian Aerospace Research Center | Toscano C.,University of Naples Federico II | Meola C.,University of Naples Federico II | Iorio M.C.,University of Naples Federico II | Carlomagno G.M.,University of Naples Federico II
Advances in Optical Technologies | Year: 2012

The ever wide use of composite materials in the aeronautical industry has evidenced the need for development of ever more effective nondestructive evaluation methodologies in order to reduce rejected parts and to optimize production costs. Infrared thermography has been recently enclosed amongst the standardized non destructive testing techniques, but its usefulness needs still complete assessment since it can be employed in several different arrangements and for many purposes. In this work, the possibility to detect slag inclusions and porosity is analyzed with both lock-in themography and pulse thermography in the transmission mode. To this end, carbon-fiber-peinforced polymers different specimens are specifically fabricated of several different stacking sequences and with embedded slag inclusions and porosity percentages. As main results, both of the techniques are found definitely able to reveal the presence of the defects above mentioned. Moreover, these techniques could be considered complementary in order to better characterize the nature of the detected defects. © 2012 C. Toscano et al.

Riccio A.,The Second University of Naples | Raimondo A.,The Second University of Naples | Borrelli R.,Cira Italian Aerospace Research Center | Mercurio U.,Cira Italian Aerospace Research Center | And 2 more authors.
Applied Composite Materials | Year: 2014

In this paper, a numerical study has been carried out on skin delamination and skin-stringer debonding growth in a composite wing-box under compressive loading conditions. The adopted numerical models use the Virtual Crack Closure Technique to simulate the inter-laminar damage evolution and the numerical analyses have been performed by means of the FEM code ABAQUS and B2000++. The obtained numerical results have been assessed and compared each other in terms of delaminated area evolution, delamination growth initiation load and strain distributions. In order to investigate the effectiveness of the adopted numerical platforms in predicting the evolution of inter-laminar damages, comparisons with experimental data, in terms of load displacement curves and strains in the debonding area, have been also introduced. © 2013 Springer Science+Business Media Dordrecht.

Cembalo A.,Cira Italian Aerospace Research Center | Pisano F.M.,Cira Italian Aerospace Research Center | Romano G.,Cira Italian Aerospace Research Center
Proceedings - 2012 6th International Conference on Complex, Intelligent, and Software Intensive Systems, CISIS 2012 | Year: 2012

For years, businessmen made use of ad-hoc technologies in order to analyze huge amount of data related to the domain of interest, aiming at extracting relevant information to elaborate successful company strategies. Such technologies focused essentially on the structured data. In particular Data Warehousing systems represent the decision support systems on which academia and industry focused their attention. It is believed that "about 80% of the information of any organization is contained in unstructured and semi-structured documents"[1], so limiting the analysis to only the structured data, as it has been done so far, is likely to lose a high percentage of potentially useful knowledge. Since text is the primary mean to disseminate information and knowledge, it is necessary to introduce concepts related to text-oriented Business Intelligent and Document Warehousing systems, which could have many useful applications in industries or large domains. In this paper we present a prototype application of a Document Warehousing system, highlighting challenges and solutions for each phase of its lifecycle. The prototype is related to Security and Prevention domain and it is built with a set of open-source tools whose features and limitations are highlighted. As we currently know, organization and setting of the fundamental elements of a Document Warehouse system lifecycle, are issues which have not been deepened yet. Furthermore until now, we have not find an application of Document Warehousing, which has been implemented integrating the open-source tools which we use to implement our prototype yet. © 2012 IEEE.

Gardi R.,Cira Italian Aerospace Research Center | Del Vecchio A.,Cira Italian Aerospace Research Center | Marino G.,Cira Italian Aerospace Research Center | Russo G.,Cira Italian Aerospace Research Center
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 | Year: 2011

SHARK (Sounding Hypersonic Atmospheric Re-entering 'Kapsule') is a small capsule designed and realized by CIRA. It was launched on March the 26th 2010 on board the European Space Agency sounding rocket MAXUS 8 flight. During the ascent parabola, the capsule was released and successfully executed its 15 minutes ballistic flight and then reentered in the atmosphere and landed. The aim of the project was to prove the possibility to set up a low cost experimental space platform and execute a re-entry test flight by dropping a capsule from a sounding rocket. Since CIRA is investigating new technologies for the re-entry and in particular new ceramic materials for sharp thermal protection systems (TPS), this flight opportunity has been chosen to test in a real flight an UHTC (Ultra High Temperature Ceramic) component, machined from scraps of previous ground tests executed in the Plasma Wind Tunnel SCIROCCO. The paper describes the mission genesis and development, the design and the subsystems of the capsule and then shows the first results from the preliminary analysis of the recorded data. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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