Alenia Aeronautica

Napoli, Italy

Alenia Aeronautica

Napoli, Italy
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Zammit Mangion D.,University of Malta | Becouarn L.,Thales Alenia | Dominici J.,Thales Alenia | Fabbri M.,Alenia Aeronautica | Bader J.,Diehl Aerospace
11th AIAA Aviation Technology, Integration,and Operations (ATIO) Conference, including the AIAA Balloon Systems Conference and 19th AIAA Lighter-Than-Air Technology Conference | Year: 2011

This paper presents a cockpit display concept that proposes to make use of rear-projection technology to generate a single, seamless end-to-end display on the aircraft's main instrument panel, extending to the front of the central pedestal in its central section. In this way, a greater percentage of the area than that currently utilized on state-of-the-art aircraft can be employed productively for human machine interaction. Although this paper focuses on commercial and business jet aircraft, the concept could be adapted to other platforms such as military aircraft or helicopters. It eliminates the limitation of functional compartmentalization introduced by the physical limitations of the individual displays and employs multi-touch capability over the whole display surface, thus affording the pilots with enhanced display and input functionality, which may then form the basis of new cockpit HMI concepts. The paper also discusses a simple concept of use to illustrate the salient capabilities of the single interactive display concept. © 2011 by The ODICIS Consortium. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.

Guida M.,University of Naples Federico II | Marulo F.,University of Naples Federico II | Meo M.,University of Bath | Russo S.,Alenia Aeronautica
International Journal of Impact Engineering | Year: 2013

The objective of this paper was to design, manufacture and test a composite leading edge, without ribs, able to satisfy birdstrike requirements specified by certification authorities. The leading edge configuration was validated through an extensive campaign of experimental tests performed firstly on small sample to determine the mechanical properties [1], then through the analysis and testing of a small representative structures of the wing leading edge [2,3]. The explicit finite element software MSC.Dytran® [4] was chosen for the numerical investigation and a validated simulation methodology was developed to predict the birdstrike scenario. The evaluation of numerous birdstrike scenarios allowed an improved design efficiency and safety and led to a significant reduction of certification costs. The most important achievement was a ribless wing leading edge made of FML, aluminium and honeycomb able to satisfy the birdstrike resistance test specified by the Federal Aviation Regulation [5]. This configuration allowed a considerable reduction in weight and manufacturing costs. © 2012 Elsevier Ltd. All rights reserved.

Guida M.,University of Naples Federico II | Marulo F.,University of Naples Federico II | Meo M.,University of Bath | Russo S.,Alenia Aeronautica
Mechanics of Advanced Materials and Structures | Year: 2012

The work is based on the experimental activities developed to investigate the behavior of fiber metal laminate (FML) materials used for very critical structural components, such as leading edge panels that must satisfy a series of requirements defined in terms of structural resistance, applying impact loads at different speeds, arising, for example, from birdstrike on wing leading edge. The experimental tests have been carried out on some panels manufactured by Alenia Aeronautica in the context of a national project, that had the aim to identify the material that defines the best solution in terms of weight and performance to realize a leading edge that was able to be resistant at the birdstrike requirements. The first part of work presents an extensive campaign of tests performed to determine stiffness and strength properties on FML (trade name GLARE). The experiments considered the static tests useful to determine the stress-strain curve; the dynamic tests at different strain rates, and different impact tests to evaluate the threshold energy that correspond to a visible impact damage on the coupon. Subsequently, several tests were performed on two different types of joints that were mechanically tested to determine strength properties at a different strain rate. In the second part of this work, the experimental tests have been reproduced numerically with the aim of validating models able to correctly simulate the phenomenon in question, obtaining a satisfactory numerical-experimental correlation. In the present work the guidelines for the future development of similar numerical models have been traced and advantages and disadvantages of birdstrike modeling have been highlighted and numerical activities allowed to define the parameters of the material and to improve the design rules for a leading edge subjected to the birdstrike. © Taylor and Francis Group, LLC.

Iaccarino P.,University of Naples Federico II | Leone C.,University of Naples Federico II | Durante M.,University of Naples Federico II | Caprino G.,University of Naples Federico II | Lamboglia A.,Alenia Aeronautica
Journal of Sandwich Structures and Materials | Year: 2011

Three-point bending tests in the elastic domain were carried out on sandwich specimens with the facings made of unidirectional T800H/3900-2 laminates, and the core of a soft and thin viscoelastic layer, varying the slenderness ratio. A closed-form formula available in the literature, developed for sandwich beams with thick facings, was used to predict the rigidities in flexure, adopting three different methods for the calculation of the shear rigidity. The best results were obtained by the classical sandwich theory, which provided reasonably good correlation with the experimental results, slightly overestimating the actual values. A finite element model consisting of three layers, made of standard CQUAD4 and CHEXA8 elements for facings and core, respectively, was developed, accurately predicting beam bending behavior. From the numerical results, the inability of classical sandwich theory to correctly estimate the bending rigidity is correlated with the through-the-thickness shear deformation of facings, not accounted for in the analysis. © The Author(s) 2010.

Campanile G.,Alenia Aeronautica | Prisco A.,Alenia Aeronautica | Squillace A.,University of Naples Federico II | Bitondo C.,University of Naples Federico II | And 5 more authors.
Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications | Year: 2011

The effect of process parameters on mechanical and microstructural properties of AA 2139 T8 joints produced by friction stir welding (FSW) was analysed by means of statistical tools. Three different parameters were taken into account: angular speed (>), welding speed (v -a), and plunging depth (p); each of them was varied on three levels. Forces and temperatures achieved during the welding were monitored and analysed for all joints. An accurate microstructural analysis was performed: the occurrence of some remarkable defects, typical of FSW, such as tunnel or lack of penetration, was related to actual process parameters adopted. The extension of each FSW characteristic zone was measured and the main grain dimension within each of these zones was measured. The mechanical properties of the joints were evaluated by means ofVickers microhard- ness measurements and tensile tests at room temperature. It was observed that the joint welded with lowest angular speed, highest welding speed, and greatest plunging depth attained the best performances. The statistical data treatment allowed providing a numerical model capable of predicting the mechanical performances of joints.

Bitondo C.,University of Naples Federico II | Prisco U.,University of Naples Federico II | Squillace A.,University of Naples Federico II | Giorleo G.,University of Cagliari | And 3 more authors.
International Journal of Material Forming | Year: 2010

This work investigates the influence of the Friction Stir Welding (FSW) parameters on the mechanical properties AA 2198 T3 welds. For this purpose, a full-factorial experimental design was conducted. The observed responses are ultimate tensile strength (UTS) and yield strength (YS). The factors under investigation are tool rotational speed (N) and welding feed (Va). In order to estimate the influence of the heat transfer transient phase on the mechanical properties of the weld, besides these classical welding parameters, a position parameter defining the relative distance of the specimens from the welding run-in and run-out is considered. Analysis of variance (ANOVA), main effect plot and desirability function technique were used to determine the significant parameters and set the optimal level for each parameter. A regression equation was derived to predict each output characteristic. © 2010 Springer-Verlag France.

D'Errico V.,Alenia Aeronautica | Fico M.,Alenia Aeronautica | Franco G.,IBM
ACM International Conference Proceeding Series | Year: 2011

The complexity of market pushes organizations and individuals to amplify their knowledge in both directions of generalization and specialization to face market opportunities. However it is very difficult, even for a large organization, to plan the equilibrium of competencies in terms of knowledge and behaviours needed inside a particular market. We propose a business model of a distributed network of partners, organizations and individuals, and a knowledge based management system to dynamically find and maintain the equilibrium between generalization and specialization while organizations in the business model work on opportunities. In meantime we depict, as a part of the system, the processes to face with the problem of knowledge protection towards competitors. Such a distributed network of partners will be the best way to face both the problems of generalization/specialization and knowledge sharing/protection. The paper details roles and other items of the K-based management System in the designed framework.

Feminella F.,Alenia Aeronautica | Dell'Osso M.,Simmel Difesa Spa
SAE International Journal of Aerospace | Year: 2011

This paper presents a model of semi-quantitative analysis for risks and their associated impact caused by aeronautical suppliers in charge of specific work-packages (WP). Considering that many approaches to supply chain risk evaluation are qualitative (consequently subjective) and restricted to few functional areas of the supplier, the paper defines fifteen areas of functionality (production, finance, quality human resources etc.) for the supplying company. It then identifies specific risks for each area and measures them through predictive indicators. Therefore, taking in account the WP characteristics (size, technology, delivery and quality constraints, etc.), drivers are defined to evaluate the impact associated with each risk. The model is applied to the case of a supplier delivering structural parts. Finally, contingency actions to overcome the identified risks are illustrated and discussed. © 2011 SAE International.

Iannone M.,Alenia Aeronautica
AIP Conference Proceedings | Year: 2010

Cooling rate of semicrystalline thermoplastic (PEEK) based composite parts has been assessed by means of a thermal flow model. Cold tool thermoforming was found suitable for thin parts, but the use of a preheated tool is suggested. Cooling rate is critical for automated lay-up; consequently the optimization of this technique requires the use of a complex apparatus, able to provide both heating of the part during lay-up and a control of the cooling rate. Alternatively a modified cooling rate vs. crystallinity behavior of the material must be achieved. © 2010 American Institute of Physics.

Caprino G.,Alenia Aeronautica | Lopresto V.,Alenia Aeronautica | Riccio M.,Alenia Aeronautica | Leone C.,Alenia Aeronautica
Applied Composite Materials | Year: 2012

Low-velocity impact tests were carried out on sandwich plates having CFRP facings and thin rubbery core. Two types of cores, differing in the material nature and thickness, were used. For comparison, similar tests were performed on the monolithic laminate. Various impact parameters, among which indentation, first failure energy, perforation energy, absorbed energy and maximum contact force, were analyzed, to highlight the effect of the core on the material response. The influence of the core on the macroscopic behaviour of the panels was quite limited, except in the elastic phase, where the lower stiffness of the sandwich configurations resulted in a higher energy at first failure. More relevant differences were found from the study of failure modes, carried out combining ultrasonic C-scan and a limited number of microscopic observations. In particular, in correspondence of the energy for barely visible impact damage, besides considerable facing-core debonding, both the facings of the sandwich structures exhibited fibre breakage at their back side. © 2011 Springer Science+Business Media B.V.

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