Belsanti L.,European Commission - Joint Research Center Ispra |
Belsanti L.,National Research Council Italy |
Forchin E.,Agusta Westland |
Stifanese R.,National Research Council Italy |
And 2 more authors.
Metallurgia Italiana | Year: 2016
Coating systems protect metal substrates from environmental corrosion attack. However, although having good performances, the presence of specific metal ions in their composition represents a potential source of environmental contamination. The necessity to conciliate corrosion protection with environmental impact is, thereby, primary. This work was designed to study the performance of low environmental impact conversion coatings (surface pre-treatment and high-solids epoxy primer), such as those free from hexavalent chromium (Cr VI), layered on different substrates of aluminium alloy [Al 7075 (T6) unclad and Al 2024 (T3) unclad] widely used in aerospace applications. Substrate surfaces were first treated by environmentally friendly Cr-free products. Successively, on pre-treated substrates, high-solids, chromate-free epoxy primer was applied. The capability to protect substrates from corrosion phenomena was evaluated following exposure of 4 groups of samples to in situ marine atmosphere at the Genoa Experimental Marine Station (G.EM.S.) of C.N.R.-I.S.MAR., located in the port of Genoa, for 8, 16, and 24 months and in accordance with UNI EN ISO 8565:1997 Standard. Accelerated degradation of conversion coating was also studied by electrochemical impedance spectroscopy. To characterize the coating systems, the interface metal substrate/conversion coating, sections from different samples were submitted to microscope techniques. The experimental results reported in this paper give useful information regarding the protective power against substrate corrosion of some Cr-free conversion coatings that have, as compared to traditional Cr VI containing products, a lower impact on workers' health and on the environment.
Karachalios E.,Research and Product Design |
Vrettos C.,Research and Product Design |
Marioli-Riga Z.,Research and Product Design |
Bisagni C.,Polytechnic of Milan |
And 3 more authors.
International Journal of Structural Stability and Dynamics | Year: 2010
Prediction of the buckling behavior of structures is of great interest in the aerospace industry, and extensive research is taking place worldwide in that area. The current work concerns numerical simulation of the collapse test of a closed stiffened composite box subjected to compression followed by torsion. Numerical simulation is performed and the results are correlated with experimental findings. The objective is to validate the numerical model and detect any deficiencies of the modeling procedure. For this purpose, a series of quantities numerically predicted are directly compared with experimental ones: strains, displacements, deformation plots and loaddisplacement curves. The physical test article also contains artificial stringerskin debondings realized via Teflon film inserts. The energy release rates are calculated at the debonding front using the virtual crack closure technique. The FE model is slightly stiffer than the actual structure but the numerical results are at a reasonable level of agreement with the experimental data. © 2010 World Scientific Publishing Company.
Martarelli M.,Biomedical University of Rome |
Santolini C.,Marche Polytechnic University |
Perazzolo A.,Agusta Westland |
Castellini P.,Marche Polytechnic University
Conference Proceedings of the Society for Experimental Mechanics Series | Year: 2012
Damping and loss factor assessment of high damped materials is a challenging task addressed in the past by several researchers, one of the most important is H. Oberst who defined a standard method to tackle the issue. In this paper a sandwich beam composed of two aluminium layers separated by the damping material has been studied. First the beam made only of aluminium layer has been tested and then the composite beam has been assembled by using as damping layer a sheet of styrene-butadiene rubber (SBR). The highly damped behaviour of the test sample makes the test very difficult; great care must be taken in the setting up the test itself. In particular the excitation system has been studied in depth by comparing the results obtained with a traditional non-contact impact test and an electro-dynamic system. Being the impact excitation invasive as well when considering light structures as the object under test, a non-contact electro-magnetic system has been developed in order to limit the influence of the excitation device on the structure behaviour. © The Society for Experimental Mechanics, Inc. 2012.
Pappada S.,Consorzio CETMA |
Salomi A.,Consorzio CETMA |
Montanaro J.,Consorzio CETMA |
Montanaro J.,University of Salento |
And 3 more authors.
Aerospace Science and Technology | Year: 2015
In this work, the experimental and numerical study of induction welding devoted to the fabrication of a composite stiffened panel, representative of a typical aeronautic sub-component, is presented. Athermoplastic matrix composite, polyphenylene sulfide(PPS) reinforced with carbon fibers, is used. The influence of the fundamental process parameters, such as generator power, distance between induction coil and laminate, coil geometry and laminate lay-up on the heating rate and the heat distribution was analyzedapplying finite element simulations. The model was validated through the comparison of experimental and model results obtained in static experiments. Optimized parameters for composites welding were found out, and the mechanical properties of the welded joints were evaluated by single lap shear and pull-offexperiments. Finally, a prototype panel made of a flat laminate stiffened with four "L" shaped stringers is fabricated by continuous induction welding, exploiting modeling and experimental results. A C-scan of the panel was also performed. © 2015 Elsevier Masson SAS. All rights reserved.
Goulos I.,Cranfield University |
Pachidis V.,Cranfield University |
D'Ippolito R.,Lms International |
Stevens J.,National Aerospace Laboratory Netherlands |
Smith C.,Agusta Westland
Proceedings of the ASME Turbo Expo | Year: 2012
This work focuses on the development and application of a generic methodology targeting the design of optimum rotorcraft operations in terms of fuel burn, gaseous emissions and ground noise impact. An integrated tool capable of estimating the performance and emitted noise of any defined rotorcraft configuration within any designated mission has been deployed. A comprehensive and cost-effective optimization strategy has been structured. The methodology has been applied to two generic - baseline missions representative of current rotorcraft operations. Optimally designed operations for fuel burn, gaseous emissions and ground noise impact have been obtained. A comparative evaluation has been waged between the acquired optimum designs. The respective trade-off arising from the incorporation of flight paths optimized for different objectives has been quantified. Pareto front derived models for fuel burn and emitted noise have been structured for each mission. The Pareto models have been subsequently deployed for the design of operations optimized in a multidisciplinary manner. The results have shown that the proposed methodology is promising with regards to achieving simultaneous reduction in fuel burn, gaseous emissions and ground noise impact for any defined mission. The obtainable reductions are found to be dependent on the designated mission. Finally, the potential to design optimum operations in a multidisciplinary fashion using only a single design criterion is demonstrated. Copyright © 2012 by ASME.
Stevens J.,National Aerospace Laboratory Netherlands |
Smith C.,Agusta Westland |
Pachidis V.,Cranfield University |
Thevenot L.,Airbus |
D'Ippolito R.,NOESIS Solutions NV
41st European Rotorcraft Forum 2015, ERF 2015 | Year: 2015
This paper describes the work done by the Green Rotorcraft (GRC) Integrated Technology Demonstrator (ITD), the Sustainable And Green Engine (SAGE) ITD and the Technology Evaluator (TE) of the CleanSky Joint Technology Initiative (JTI). The GRC and SAGE ITD's are responsible for developing new (rotorcraft) technologies, whilst the TE has the distinctive role of assessing the environmental impact of these technologies at single flight (mission), airport and Air Transport System levels (ATS). Besides the trade-off work already performed by each individual GRC subproject (GRCi), a need has emerged to perform trade-off studies for the complete rotorcraft with various technologies applied to the generic rotorcraft classes. The assessments reported here have been performed by using a GRC-developed multidisciplinar/ simulation framework called Phoenix that comprises various computational modules. These modules include a rotorcraft performance code (EUROPA), an engine performance and emissions simulation tool (GSP or Turbomeca engine deck) and a noise prediction code (HELENA). Phoenix can predict the performance of a rotorcraft along a prescribed 4D trajectory offering a complete helicopter mission analysis. Two helicopter classes have been examined, being a Single Engine Light (SEL) configuration for passenger transport missions and a Twin Engine Heavy (TEH) configuration for Oil & Gas missions. The results of this study illustrate the potential that incorporated technologies possess in terms of improving such performance metrics as fuel burn, and CO2 and NOx emissions.
News Article | March 17, 2016
The controllers are supplied for use within the aviation and composites industries to provide temperature control for the manufacture and repair of adhesive bonded components. The Novatech HBC-4301A features ontrol of 1 to 6 heated zones, modular flexibility, inputs for up to 32 K or J type thermocouples, operation of two independent jobs from one unit, an adhesive maintenance program offering automatic adhesive cure time setting, vacuum and positive pressure monitoring and control, repair map design and simple configuration of the thermocouples/zones. This is the second set of equipment supplied to the IMP Group for use on the Cormorant (CH-149) Helicopter. Used for rectification of structure and windscreen replacements, the HBC-4301A is approved by the Agusta Westland/Finmeccanica Group to cover all aspects of repair on this aircraft. This story uses material from JRT, with editorial changes made by Materials Today. The views expressed in this article do not necessarily represent those of Elsevier.
Bianco-Mengotti R.,Agusta Westland |
Del Grande F.,Agusta Westland |
Ragazzi A.,Agusta Westland |
La Barbera A.,Agusta Westland |
Lo Coco G.,Agusta Westland
Annual Forum Proceedings - AHS International | Year: 2013
In 2011 AgustaWestland, in response to a specific Customer request, has conducted a ship trial campaign at sea to define a reference ship operation envelope. After this experimental campaign, an expansion in the SHOL envelope (Ship Helicopter Operating Limitations) was envisaged, implying another series of trials at sea, with all the associated project and schedule risks. It was therefore decided to complement the initial experimental data with a simulation campaign, consisting in an initial validation of the approach based on the flights, followed by the actual simulation of the expanded envelope. This paper describes the AW139 SHOL simulation campaign and illustrates the frameworkfor ship operations and the experimental tests, discussing in particular the methodology used to effectively setup -in a short timeframe-all the elements of the simulation process as well as lessons learned and future perspectives in this field. © 2013 by the American Helicopter Society International, Inc.
Schaeffer J.,Agusta Westland |
Colombo A.,Agusta Westland |
Belt D.,Agusta Westland |
Campbell K.,Agusta Westland |
Mattaboni M.,Agusta Westland
Annual Forum Proceedings - AHS International | Year: 2015
Transport Category Certification requires the ability to safely land or continue flight after an engine failure during all phases of flight. The maximum transport category gross weight is a key parameter that can strongly influence the success of an aircraft. Due to its unique configuration, the tiltrotor offers unique challenges and abilities for surviving an engine failure during its critical mission phase. Challenges include energy management and thrust maintenance for a low inertia, high disk-loading rotor. Unique capabilities include rapid acceleration due to tilting of the thrust vector via the nacelles, which is a powerful method of improving takeoff performance and ground clearance for continued flight after a single engine failure. With its fly by wire flight control system and integrated engine controls architecture, the AW609 offers an unparalleled ability to evaluate, tune, and improve transport category performance, specifically during the critical flight phases of takeoff and landing. This paper will summarize the development and initial evaluation of transport category performance on the AW609 tiltrotor. It includes a brief discussion of the control architecture, a summary of simulation correlation, and a summary of flight test findings. © 2015 by the American Helicopter Society International, Inc.
Bellussi E.,Agusta Westland
SAE Technical Papers | Year: 2015
This paper describes the AgustaWestland (AW) experience in the use of the results obtained with the HISS flight tests to support the civil ice clearance for rotorcraft. The use of the HISS, a US Army CH-47D Chinook fitted with a spray bar system providing a cloud where the helicopter can fly in icing conditions, allows stable and prolonged flight data, conditions extremely difficult to encounter during natural ice flights. The paper analyses the definition of the HISS test matrix, to optimize the points needed for system development and the points possibly usable during certification, in both normal and failure mode conditions. It is also shown how the HISS ice campaigns results can be assessed, and how they can be compared to the natural ice flights to validate them. Finally it is explained how the HISS results can be used, in addition to natural ice flights results, to support the certification. Copyright © 2015 SAE International.