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Vito De Pasquale
Image classification and data-mining of satellite images
Manolo Venturin, EnginSoft
Extracting and recognizing objects in satellite images is an important tool that enables exploitation of geographical data. Example of information that can be provided by these systems are land use, plant species, presence of water, safety, etc.
In this talk an efficient classification image system is presented and the possibilities that it provides are described. The developed method is based on a supervised data mining system (properly trained) with an automatic system of image features extraction.
The images classification process consists in the extraction of classes of information from a raster image composed of several bands . The resulting raster can be used to create thematic maps.
Coupled Approach to evaluate Gun Blast Induced Stress in Combat Systems
The present paper concerns the coupling between a commercial software package and the in-house tool GUNWave3D to determine the stress levels in the structures loaded by the blast wave emitted in ambient at the fire of a cannon-type weapon system. In fact, during combat systems firing the structures adjacent to a gun are typically subjected to the blast load due to the impingement and propagation of the shock waves expanding from the weapon muzzle. The first stage of the coupled approach foresees that the gun blast data are calculated by means of GUNWave3D. That tool is an empirical-analytical model based on scaling relationships that provides a fast and reasonable estimate of the main gun blast parameters upon structures in function of weapon characteristics and launch conditions taking also into account the asymmetric shape characterizing the gun blast wave. Successively, the calculated blast data are processed and passed to the LS-DYNA® software as input load in order to finally compute the structural response of the components of interest.
The application of the coupled approach is showcased through the development of a test case concerning a 30-mm gun whose muzzle blast quantities have been already validated in a previous published work. The proposed approach can thus be effectively employed in the design, optimization and retrofit of surface warship, aircraft and ground combat systems
Use Virtual Vibration Tests to Optimize Physical Shaker Tests
Physical tests are performed at various stages of the development cycle of a product — from prototype validation to product qualification. Although costly, there are growing demands for qualification tests like endurance vibration testing to be more representative of the real world. At the same time there are growing demands to assess the durability of these items based on FEA simulation.
In this presentation we will explain how to set up a CAE-based test and how to correlate the results with some physical measurements. Specific assumptions will be explained and some advantages of using virtual tests will be highlighted:
Reduce the number of prototypes needed
Investigate why a physical test fails and propose an optimal solution
Perform sensitivity analysis
Find out what the margins are at the end of a successful test
This presentation will therefore focus on explaining and showing how virtual tests can enrich the exploitation of physical tests.
EM lightning strike analysis to support aircraft certification
Electromagnetic environments such as those produced by lightning can cause failures on aircraft safe operation and even catastrophic effects if precautions are not taken. The risk is elevated for modern aircraft having an increased number of flight control, communication and guidance systems, and incorporating structures made of carbon-fiber composite (CFC).
Aircraft certification by testing with respect to different electromagnetic environments is both costly and time consuming. Today, electromagnetic (EM) field simulation offers the possibility to predict vulnerabilities to electromagnetic environments early in the design process and reduce the number of tests required for certification. Simulation may be used to assess the impact of changing a component at a later time in the product life cycle. As such EM simulation is ideally suited to complement testing.
In this talk the application of CST STUDIO SUITE® to simulate aircraft exposed to various electromagnetic environments will be presented. We will discuss the use of CST EM STUDIO® for lightning attachment zoning characterization and CST CABLE STUDIO® for indirect lightning effect analysis including coupling into cable harnesses systems.
Real life production and the use of products of higher complexity – such as Autonomous driving or related processes to Industry 4.0 – put a higher interlectual pressure onto development resources.
Multibody could cover historical mechanical and mechatronic requirements – Multiphysics - including taking into account programming algorithms- plus vice/versa optimization and statistics is the only strategy to support upcoming product development requirements.
Parasitic effects, that cause defects in proper / unproper use, can be identified and eliminated; Effects of use and wearout can be forecasted and included into an advance maintenance strategy. Driving objective is to specify the key to Zero Defect!
Assessment of RFID technology to track aeronautic components using the numerical methodology
The plant of Avio Aero in Brindisi carries out activities of MRO on aircraft engines. In this context, it is necessary to use an efficient system of identification and tracking, within the same plant, of the parts constituting the engine under revision and the equipment in use.
A methodology, under investigation, takes into account the use of a “smart tag” of identification based on RFID or similar technologies, enabling a multiple reading and an automated identification of the parties with respect to the access gaps or portable players.
The activity described in this work is focused on the numerical study of the electromagnetic interaction between RFID systems placed on parts to be tracked and the antennas mounted on the access gates.
The study has been carried out is through FEM numerical analysis by means of the ANSYS HFSS software. The whole system has been designed, including the footboards, parts to be traced and the multi-antenna system installed on the gate.
The objective of the analysis is the study of the electric field distribution on the planes of the footboards, in the real operating conditions of the reading system, as effect of the radio frequency propagation mechanism, introduced by the presence of the parts to be traced.
The results of the activity, expressed as contour plots of the electric field distributions, as a function of the its phase, have allowed to identify the shadow zones in which it could be difficult to read the tags associated with the parts to be traced.
The whole activity has therefore allowed to carry out a preliminary assessment of the performance of the RFID technology with respect to this application.
Space debris capture mechanism: Develop of design, simulation, and ground demonstrator
Gabriele Bombaci, Aviospace
Active removal of large space debris, such as the upper stages of elderly launch vehicles or the decommissioned satellites, constitutes a technological challenge which is so far well-known and recognized by all the main players of space business, both at institutional and at industrial level, as a required step to achieve significant progress towards a safer and cleaner space environment. To accomplish such objective, a non-collaborative rendez-vous and capture procedure, to be performed by a robotic spacecraft (namely “chaser”), is required.
The present activity is focus on a belts-based capture mechanism develop in the frame of CADET program. Dyna supports all phases of design, at the beginning for the flight systems and than for the ground system. In fact the activity ended with the construction of a laboratory where a scaled ground demonstrator was used to validate the performance of the capture mechanism and Dyna models. In particular LS-DYNA has been adopted in the following areas: study of the maneuvers of proximity between chaser (active spacecraft) and target (non-cooperative object), mechanical interaction between the two objects (exchange of forces, energy, accelerations, contact pressure), the development and optimization of mechanisms to perform the capture, assessment and verification of the dynamic behaviour during the deployment of extensible parts (arms, solar panels, deployable structures), design test environment on the ground, prediction and correlation of test data.
Numerical models tuning procedure: a general method for aircraft cooled components
Elena Campagnoli, Politecnico di Torino
In order to correctly simulate the fluid and thermal behavior of different aircraft components, the choice of the suitable numerical tools alone isn’t sufficient and so it must be combined with a good tuning procedure that, starting from the available experimental data, allows obtaining high accuracy numerical models.
In the past the authors, to accomplish the tuning, have identified a procedure that has been applied, with fairly good results, to the numerical model representing the Test Article of an experimental rig built to simulate, properly scaled, one stage of a LPT (Low Pressure Turbine). The aim of the present work is to definitely validate the pointed up procedure verifying, at the same time, how its use can be extended to others engine components. For this reason the tuning procedure has been applied to a different engine element, a rotating blade, having in common with the previous one only the need to be cooled during the operation, but with completely different geometrical features and, in addition, numerically simulated by using others software.
Heat Ventilation and Air Conditioning of a Greenhouse in Antarctica
L. Bucchieri, E. Mazzoleni | EnginSoft
M. Bamsey , D. Schubert, V. Vrakking, P. Zabel, C. Zeidler | German Aerospace Center (DLR)
G. Bonzano | AeroSekur
The development of plant cultivation technologies for safe food production in space is a research field which intends to increase the possibilities of human future long-term space missions.
EDEN ISS project (Evolution and Design Environmentally-closed Nutrition-Sources), which is funded by the European Union’s Horizon 2020 research and innovation program, is embedded in this context to provide a ground demonstration of a bio-regenerative life support system in an highly-isolated environment. In fact, during this project, a greenhouse will be built, tested and then placed in Antarctica, close to the German base “Neumayer Station III”, to collect experimental data on plant growth.
In detail this work shows the preliminary design phase of the air distribution system of this greenhouse. The optimization process of the air distribution system has followed this main aim: ensure the proper climate conditions for plant growth. Thus this means homogeneous temperature, relative humidity and velocity in the growth chamber. To achieve this goal CFD analyses are performed, checking global and local aspects.
This part of the project is developed in close collaboration with the German Aerospace Center (DLR), as EDEN ISS project coordinator, and AeroSekur, as responsible for the air management system.
New life requirements demands additional structure analysis of aged underwater vehicles
The MU90 torpedo is a high performance underwater vehicle whose structure is mainly dimensioned on buckling stresses.
Its success as well as its high acquisition cost makes customers require a prolongation of the operational life up to more than 40 years. The life prolongation is subjected to the assessment of the residual performances of the aged torpedoes.
Normal life affects the torpedo structure creating defects (scratches, abrasions, corrosions, …) that appear to be on all torpedoes in the same areas. These defects can reduce the structure performance.
The assessment of the residual capability of the torpedo structure has been achieved applying a methodology based on the verification and measurement of the effects of normal life on the torpedo shell, creation and validation of a FEM detailed ideal torpedo model, application of shell defects on the FEM model and measurement of the residual margin on structure performances.
Cubesat battery safety: Simulation of blasting phenomena in vacuum
Gabriele Bombaci, Aviospace
The present activity is focused on a safety assessment performed on CubeSat satellites, in the frame of an ESA-funded study. The simulation of blast waves is maintaining and maybe increasing its role in fluid dynamics, due to the many important applications primarily in the aerospace, defense and the oil&gas sectors. A Multi-Material Arbitrary Lagrange Eulerian (MM-ALE) solver is generally used, together with FSI (Fluid-Structure Interaction) algorithms. The structures are modeled as Lagrangian, and FSI is used for coupling with the MMALE domains. This computational approach is able to predict accurately the relevant aspects of the blast-structure interaction problem, including the blast wave propagation in the medium for pressurized loading cases and the response of the structure to loads induced by the blast.
Here, this methodology is applied to evaluate the effects of the thermal runaway phenomena originating inside a battery, to be subjected to external vacuum (zero pressure). The study is finalized mainly to verify the interaction between the blast of battery and the structure of cubesat, and assess the derived space debris production.
A finite element model of the ignition is built to simulate wave and pressure development, battery structural failure and solid / fluid parts ejection from the assembly. The goal is to evaluate permanent deformations and / or the fracturing pattern of the assembly and each part. LS-Dyna is the software used to model the phenomenon.
The approach can be applied fruitfully to assess the accomplishment of the structural design of the device, which can be subjected to dangerous environment conditions leading to an explosive thermal runaway, so that a suitable containing structure can be easily integrated, if necessary.
A conservative pressure mapping method based on Radial Basis Functions and Fuzzy Subsets
Marco Evangelos Biancolini, University of Tor Vergata
Ubaldo Cella, University of Tor Vergata
Francesco Giorgetti, University of Tor Vergata
Corrado Groth, University of Tor Vergata
A common issue of loose coupling of multi-physics simulations arises from the necessity to analyse the same structure relying on different meshes, each one suited for a different field of physics. Output data from a simulation must be transferred as input to another model to run a new analysis. It is strongly desirable for such information transfer to be conservative in terms of load balance.
A novel method for pressure mapping between dissimilar meshes is presented. Transfer procedure consists of two steps: pressure interpolation by means of Radial Basis Functions and Fuzzy Subsets correction. The first is a pointwise interpolation using a series of basis functions. The second phase applies to the outcome of the first one to restore balance between the two models by introducing a smooth correction field. Practical test cases from the aeronautical field are presented to validate the proposed method.
CETMA - Engineering, Design & Materials Technologies Centre
A numerical procedure for the prediction of draping process combining Matlab, LS-DYNA and Hyperworks
Annalisa Cassinelli, CETMA - Engineering, Design & Materials Technologies Centre
Danilo Bardaro, D’Appolonia
Antonio Caruso, Leonardo Helicopters
This paper describes a numerical tool for the prediction of draping process with the aim to increase the production and quality of composite parts. The drapabilty of a dry textile fabric into a mould is analyzed and predicted by explicit simulation. The developed tool provides a considerable simplification of the pre-processing, in particular, the f.e. model of the fabric is generated automatically. Starting from the contour line of the fabric (i.e. fabric.dxf) the customized Matlab subroutine allows to obtain the preliminary discretized f.e. model (i.e. fabric.k). The creation of the final input file is obtained with a second customized script in Hypermesh. The materials properties and meshing of the mould are assigned by the script on the basis of a pre-defined database; only the positioning of parts is decided manually.
The f.e. input file is ready for the simulations of draping process with LS-DYNA. Finally, the results can be analyzed easily by means of the developed tool that allows to plot the drapabilty response on fabric. An analytical model is proposed for relating the fabric parameter (E, ε, τ) to the locking angle in order to predict the arise of wrinkling.
Virtual Integrated Aircraft modeling methodology to manage increasing complexity of aircraft system
One of the main challenges of modern aircraft’s design deals with their increasing complexity. Aircraft manufacturers are striving to find means to accurately assess the interactions among systems and sub-systems since the beginning of their design, with the goal to produce better integrated products and reduce their time-to-market. To support these needs, methodologies and processes based on Model Based System Engineering, Modeling and Simulations, Verification and Validation procedure are more and more used. The virtual integration of aircraft systems is the outcome of the modeling process, starting with the creation of models and their assembly. As such, it depends on how this process is managed in the context of the extended enterprise. In order to answer to these needs a set of methodologies called Virtual Integrated Aircraft (VIA) is proposed and described in this paper. As a result of VIA methodologies, the modeling process is harmonized, and the know-how is capitalized.
This full presentation is not available
University of Repubblica di San Marino
Model helicopter configuration and optimisation using OpenFOAM®-based CFD solver technology in a HPC-based Cloud
Ulrich Heck, DHCAE Tools
Tamas Kiss, University of Westminster, England
Gabor Terstyanszky, University of Westminster, England
Nicola Fantini, CloudBroker GmbH, Switzerland
Andreas Oldenburg, CloudSME UG, Germany
The employment of CAE processes for the development and optimisation of high quality products has become widespread. Depending on the optimisation strategy, a large number of simulations must be performed to cover wide parameter ranges. For SMEs, it is often unfeasible to provide the required capacities for complex flow simulations. A solution would be the usage of open source technology in a HPC cloud.
The aim of CloudSME project ( www.cloudsme.eu ), funded by EU Commission, is the creation of HPC-based approaches to the rapid and effective deployment of CAE software in the cloud (HPC-as-a-service) in order to enable in particular SMEs companies to make use of both at affordable conditions (pay-on-demand basis). In order to achieve this goal, 29 project partners have been working on the implementation of different use cases (MSaaS). The software developer DHCAE Tools provides access from within their modelling environment CastNet to open-source solver technology (OpenFOAM for CFD, CalculiX of structural analysis) in the cloudSME HPC environment, which has been used for the simulation and the technical design of model helicopter rotors and their blades.
Leakage Behavior Analysis of Honeycomb Labyrinth Seals through Compared CFD and 1D Analytical Approaches
Andrea Rapisarda, Politecnico di Torino
Elena Campagnoli, Politecnico di Torino, Italy
The present work focuses on non-rotating honeycomb labyrinth seals, devices utilized to improve the efficiency by reducing the leakage flow, in modern Low Pressure Turbines (LPT) on aircraft engines. This research provides an effective comparison among different designs, pointing out how the most influencing geometrical parameters affect the labyrinth seal leakage flow behavior.
The first step consists in the validation of a numerical model, based on the literature data, by using the CFD approach. Then, a geometrical sensitivity is carried out, where the effects of combined variations of the seal clearance, the fin tip thickness and the honeycomb cell diameter are evaluated. The CFD analysis provides the detailed flow pattern and leakage flow information. These results are utilized to develop a 1D analytical model, allowing the prediction of the labyrinth seal leakage behavior simply referring on the geometrical data and consequently reducing the computational time and costs.