Dynamic stationary response of reinforced plates by the boundary element method

A direct version of the boundary element method (BEM) is developed to model the stationary dynamic response of reinforced plate structures, such as reinforced panels in buildings, automobiles, and airplanes. The dynamic stationary fundamental solutions of thin plates and plane stress state are used to transform the governing partial differential equations into boundary integral equations (BIEs). Two sets of uncoupled BIEs are formulated, respectively, for the in-plane state ( membrane) and for the out-of-plane state ( bending). These uncoupled systems are joined to formamacro-element, in which membrane and bending effects are present. The association of these macro-elements is able to simulate thin-walled structures, including reinforced plate structures. In the present formulation, the BIE is discretized by continuous and/or discontinuous linear elements. Four displacement integral equations are written for every boundary node. Modal data, that is, natural frequencies and the corresponding mode shapes of reinforced plates, are obtained from information contained in the frequency response functions (FRFs). A specific example is presented to illustrate the versatility of the proposed methodology. Different configurations of the reinforcements are used to simulate simply supported and clamped boundary conditions for the plate structures. The procedure is validated by comparison with results determined by the finite element method (FEM).

Determination of Copper, Iron, Nickel and Zinc in fuel kerosene by FAAS after adsorption and pre-concentration on 2-aminothiazole-modified silica gel

Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)

Riscos nucleares e outros riscos: avaliação e aceitabilidade

The risks of accidents, illness and early death are part of life on Earth, which touches all living creatures, including Mankind. Because of modern mass communication media, the emotional impact of current risks are greater than in the past. Many unnecessary risk can and should be avoided, and with respect to other they can be drastically reduced. In addition to this, some risks should be confronted in order to avoid greater ones. In any risk analysis, eventual benefits should be taken into consideration, the risks surrounding other activities and other factors. Some risks examples and their implications are presented and discussed, in general. Nuclear energy is specifically treated, but it also refers and comments that which surrounds other human activities (airplanes, automobiles, smog, gasoline, DDT, and coal energy). As in the history of aviation, nuclear industry has a history of greater successes than failures. Nonetheless, in both cases, serious accidents deserve deep thought, including the increment of security norms. The current fear of some people to nuclear energy is compared to the unfounded fear at the advent of gasoline last century. Risks, naturally, should not be exagerated, but they cannot be discarded. The main intention of the author is to discuss the complexity of the problem, and to see that risks are evaluated and accepted. In relation to nuclear energy, the author only mentions his point of view, defended in other publications, that it involves very high risks.

Riscos nucleares e outros riscos: Avaliação e aceitabilidade

The risks of accidents, illness and early death are part of life on Earth, which touches all living creatures, including Mankind. Because of modern mass communication media, the emotional impact of current risks are greater than in the past. Many unnecessary risks can and should be avoided, and with respect to others, they can be drastically reduced. In addition to this, some risks should be confronted in order to avoid greater ones. In any risk analysis, eventual benefits should be taken into consideration, the risks surrounding other activities, and other factors. Some risks examples and their implications are presented and discussed, in general Nuclear energy is specifically treated, but it also refers and comments that which surrounds other human activities (airplanes, automobiles, smog, gasoline, DDT, and coal energy). As in the history of aviation, nuclear industry has a history of greater successes than failures Nonetheless, in both cases, serious accidents deserve deep thought, including the increment of security norms. The current fear of some people to nuclear energy is compared to the unfounded fear at the advent of gasoline last century Risks, naturally, should not be exagerated, but they cannot be discarded. The main intention of the author is to discuss the complexity of the problem, and to see that risks are evaluated and accepted. In relation to nuclear energy, the author only mentions his point of view, defended in other publications, that it involves very high risks.

Semiautomatic dental recognition using a graph-based segmentation algorithm and teeth shapes features

Dental recognition is very important for forensic human identification, mainly regarding the mass disasters, which have frequently happened due to tsunamis, airplanes crashes, etc. Algorithms for automatic, precise, and robust teeth segmentation from radiograph images are crucial for dental recognition. In this work we propose the use of a graph-based algorithm to extract the teeth contours from panoramic dental radiographs that are used as dental features. In order to assess our proposal, we have carried out experiments using a database of 1126 tooth images, obtained from 40 panoramic dental radiograph images from 20 individuals. The results of the graph-based algorithm was qualitatively assessed by a human expert who reported excellent scores. For dental recognition we propose the use of the teeth shapes as biometric features, by the means of BAS (Bean Angle Statistics) and Shape Context descriptors. The BAS descriptors showed, on the same database, a better performance (EER 14%) than the Shape Context (EER 20%). © 2012 IEEE.

Efeito do condicionamento ambiental em compósitos soldados de PPS/fibras contínuas

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Controle da variação do arqueamento de um aerofólio utilizando atuadores de memória de forma

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

A influência do shot peening e das anodizações crômica, sulfúrica e dura sobre a resistência à fadiga da liga AL7050-T7451 de uso aeronaútico

Pós-graduação em Engenharia Mecânica - FEG

Estudo de cargas térmicas de uma aeronave e dimensionamento de um sistema de ar condicionado

This work deals with the thermal load study of a fictitious aircraft as well as scaling, in terms of the airflow and temperature of the air conditioning system, for heating and cooling of the its internal environment, aiming the thermal comfort of occupants. The first part is presented the techniques and methods utilized for modeling different heat exchanges that occur in the aircraft and then allowed to calculate the total heat load and the airflow and temperature necessary to comply with the requirements of the thermal comfort. Techniques to determine the basic parameters, as convection coefficient and global coefficient of heat exchange, are also presented. The work aims to develop a program, using a computational tool, to automate the calculations so that facilitate this study. It also allows to be used for other airplanes just changing parameters and the control variables related to the specific project. Finally the program performs calculations for a fictitious airplane, to analyze its functionality and the influence of parameters involved in the temperature controls. The program allowed analyzing the sensitivity of portions of the thermal load and the corresponding parameters of influence, as well as the scaling of the air conditioning in terms of airflow and temperature. It was considered, despite the simplifications, a good approximation to the actual values and then can be used in development of the other airplanes

Modelo para definição do kit de horas de montagem de aviões

This work was done a study to develop a model for definition of hours assembling planes, that were able to meet both the most complete plane, i.e. with the highest number of mounts but also that do not generate an idleness on the line when a plane less complex passing on the Assembly line. The proposed model has great advantages over the current model that the company has been using, as for example: leftover hand-to-hand for assembling airplanes only 10% than the current model raises and an expense to pay the human resource/time of only 6.7% compared with the current model at the company

Divergência genética entre árvores matrizes de Ceiba speciosa St. Hil. para características de frutos e sementes

Pós-graduação em Agronomia (Genética e Melhoramento de Plantas) - FCAV

A new damage model for composite laminates

Aircraft composite structures must have high stiffness and strength with low weight, which can guarantee the increase of the pay-load for airplanes without losing airworthiness. However, the mechanical behavior of composite laminates is very complex due the inherent anisotropy and heterogeneity. Many researchers have developed different failure progressive analyses and damage models in order to predict the complex failure mechanisms. This work presents a damage model and progressive failure analysis that requires simple experimental tests and that achieves good accuracy. Firstly, the paper explains damage initiation and propagation criteria and a procedure to identify the material parameters. In the second stage, the model was implemented as a UMAT (User Material Subroutine), which is linked to finite element software, ABAQUS (TM), in order to predict the composite structures behavior. Afterwards, some case studies, mainly off-axis coupons under tensile or compression loads, with different types of stacking sequence were analyzed using the proposed material model. Finally, the computational results were compared to the experimental results, verifying the capability of the damage model in order to predict the composite structure behavior. (C) 2011 Elsevier Ltd. All rights reserved.

Metodi di ottimizzazione morfologica nel progetto preliminare di propulsori aeronautici avanzati

The aim of this Doctoral Thesis is to develop a genetic algorithm based optimization methods to find the best conceptual design architecture of an aero-piston-engine, for given design specifications. Nowadays, the conceptual design of turbine airplanes starts with the aircraft specifications, then the most suited turbofan or turbo propeller for the specific application is chosen. In the aeronautical piston engines field, which has been dormant for several decades, as interest shifted towards turboaircraft, new materials with increased performance and properties have opened new possibilities for development. Moreover, the engine’s modularity given by the cylinder unit, makes it possible to design a specific engine for a given application. In many real engineering problems the amount of design variables may be very high, characterized by several non-linearities needed to describe the behaviour of the phenomena. In this case the objective function has many local extremes, but the designer is usually interested in the global one. The stochastic and the evolutionary optimization techniques, such as the genetic algorithms method, may offer reliable solutions to the design problems, within acceptable computational time. The optimization algorithm developed here can be employed in the first phase of the preliminary project of an aeronautical piston engine design. It’s a mono-objective genetic algorithm, which, starting from the given design specifications, finds the engine propulsive system configuration which possesses minimum mass while satisfying the geometrical, structural and performance constraints. The algorithm reads the project specifications as input data, namely the maximum values of crankshaft and propeller shaft speed and the maximal pressure value in the combustion chamber. The design variables bounds, that describe the solution domain from the geometrical point of view, are introduced too. In the Matlab® Optimization environment the objective function to be minimized is defined as the sum of the masses of the engine propulsive components. Each individual that is generated by the genetic algorithm is the assembly of the flywheel, the vibration damper and so many pistons, connecting rods, cranks, as the number of the cylinders. The fitness is evaluated for each individual of the population, then the rules of the genetic operators are applied, such as reproduction, mutation, selection, crossover. In the reproduction step the elitist method is applied, in order to save the fittest individuals from a contingent mutation and recombination disruption, making it undamaged survive until the next generation. Finally, as the best individual is found, the optimal dimensions values of the components are saved to an Excel® file, in order to build a CAD-automatic-3D-model for each component of the propulsive system, having a direct pre-visualization of the final product, still in the engine’s preliminary project design phase. With the purpose of showing the performance of the algorithm and validating this optimization method, an actual engine is taken, as a case study: it’s the 1900 JTD Fiat Avio, 4 cylinders, 4T, Diesel. Many verifications are made on the mechanical components of the engine, in order to test their feasibility and to decide their survival through generations. A system of inequalities is used to describe the non-linear relations between the design variables, and is used for components checking for static and dynamic loads configurations. The design variables geometrical boundaries are taken from actual engines data and similar design cases. Among the many simulations run for algorithm testing, twelve of them have been chosen as representative of the distribution of the individuals. Then, as an example, for each simulation, the corresponding 3D models of the crankshaft and the connecting rod, have been automatically built. In spite of morphological differences among the component the mass is almost the same. The results show a significant mass reduction (almost 20% for the crankshaft) in comparison to the original configuration, and an acceptable robustness of the method have been shown. The algorithm here developed is shown to be a valid method for an aeronautical-piston-engine preliminary project design optimization. In particular the procedure is able to analyze quite a wide range of design solutions, rejecting the ones that cannot fulfill the feasibility design specifications. This optimization algorithm could increase the aeronautical-piston-engine development, speeding up the production rate and joining modern computation performances and technological awareness to the long lasting traditional design experiences.

Flugzeuggestützte Messungen des atmosphärischen Aerosols

Flugzeuggestützte Messungen des atmosphärischen Aerosols: Saharastaub, stratosphärisches Hintergrundaerosol und nichtsichtbare Wolken in den Tropen Im Rahmen der vorliegenden Arbeit wurden flugzeuggestütze Messungen des atmosphärischen Aerosols durchgeführt. Das hierfür eingesetzten Meßinstrument (FSSP-300) mißt die Intensität des von einzelnen Aerosolpartikeln in Vorwärtsrichtung gestreuten Lichts. Der Meßbereich umfaßt Partikeldurchmesser von ca. 0,4 µm bis 20 µm. Das FSSP-300 wurde auf mehreren Flugzeugen eingesetzt, u. a. auch erstmals auf dem russischen Höhenforschungsflugzeug Geophysika. Bei der Meßkampagen ACE-2 wurden im Juli 1997 von Teneriffa aus zwei Schichten windgetragenen Sahara-Staubes beobachtet. Die tiefere Schicht reichte bis in 1500 m Höhe, die höhere Schicht bis in 6000 m bei einer Schichtdicke von über 3000 m. In einer Analyse der Wetterlage und von Rückwärtstrajektorien wird der Ursprung des Staubes dargestellt. Die mit dem FSSP-300 gemessenen Größenverteilungen werden durch Messungen anderer Partikel-Meßinstrumente ergänzt und mit Literaturdaten verglichen. Im Rahmen der Untersuchung des stratosphärischen Aerosols wurden Messungen aus zwei Perioden ohne vulkanischen Einfluß und aus der Zeit nach dem Ausbruch des Vulkans Pinatubo verglichen. Die beiden Perioden reinen Hintergrundaerosols lagen mit über fünf Jahren eine vergleichbare Zeitspanne nach großen Vulkanausbrüchen. Die Analyse der Aerosolmessungen umfaßt den zeitlichen Verlauf der Gesamtkonzentration als auch den Vergleich von Größenverteilungen aus den verschiedenen Perioden. Bei den Flügen über dem Indischen Ozean während der Meßkampagne APE-THESEO auf den Seychellen wurden verschiedene Schichten von Cirren im Bereich des Ausläufers eines Cumulonimbus und direkt an der Tropopause beobachtet. Letztere und auch einige Bereiche der ersteren waren nichtsichtbar, d. h. hatten eine optische Dicke von weniger als 0,03 im sichtbaren Licht. Die Partikelmessungen werden auch im Kontext der Ergebnisse anderer Meßinstrumente und einer meteorologischen Analyse der Wettersituation betrachtet. Die gemessenen Größenverteilungen sind eine wichtige Ergänzung der wenigen früheren Veröffentlichungen zu diesem Thema.

Analysis of Thematic Classified Aerial Images Trough Multispectral and LIDAR Data

The application of thematic maps obtained through the classification of remote images needs the obtained products with an optimal accuracy. The registered images from the airplanes display a very satisfactory spatial resolution, but the classical methods of thematic classification not always give better results than when the registered data from satellite are used. In order to improve these results of classification, in this work, the LIDAR sensor data from first return (Light Detection And Ranging) registered simultaneously with the spectral sensor data from airborne are jointly used. The final results of the thematic classification of the scene object of study have been obtained, quantified and discussed with and without LIDAR data, after applying different methods: Maximum Likehood Classification, Support Vector Machine with four different functions kernel and Isodata clustering algorithm (ML, SVM-L, SVM-P, SVM-RBF, SVM-S, Isodata). The best results are obtained for SVM with Sigmoide kernel. These allow the correlation with others different physical parameters with great interest like Manning hydraulic coefficient, for their incorporation in a GIS and their application in hydraulic modeling.