Um sistema de apoio a decisão utilizado no planejamento e controle de produção de uma empresa aeronaútica: Reinaldo de Almeida. -

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Monitoramento do processo de densificação de compósitos termoestruturais de carbono reforçado com fibras de carbono por tomografia computadorizada e resistividade elétrica

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Estudo das intempéries nas propriedades mecânicas e viscoelásticas de compósitos PPS/Fibras de carbono e EPOXI/Fibras de carbono de uso aeronaútico

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Otimização e caracterização microestrutural de cerâmicas de carbeto de silício obtidas com material nacional para uso em blindagem balística

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Estudo de cerâmicas de SiC e Al2O3 tratadas por expansor de plasma de nitrogênio

Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)

Influência na vida em fadiga da espessura das camadas de níquel e cromo duro em aço ABNT 4340

Pós-graduação em Engenharia Mecânica - FEG

Fatores de risco em cadeia de suprimentos do setor aeroespacial: aspectos qualitativos e quantitativos

The lack of risk management can generate disruption in the supply chain, and there is little literature related to the aerospace industry. This article aims at identifying the risk factors for supply chain of the main Brazilian aircraft manufacturer. Nine risk factors specific to aircraft manufacturers were identified: Environmental, Natural and Political, Supply Chain, Business Strategy, Product Management, Indicators, Organization, Productivity, and Quality and Information System. These factors were quantitatively evaluated with respect to their criticality using the Analytic Hierarchy Process (AHP). The Quality and Productivity factors were considered the most relevant in this study, which can be classified as a single case study. The necessary data were obtained through interviews with professionals from different areas of the studied enterprise.

Imagens hiperespectrais no monitoramento da nutrição em citros

Pós-graduação em Agronomia (Energia na Agricultura) - FCA

Análise estrutural de Tie-Rod pelo método dos elementos finitos e através de cálculos analíticos

Currently one of the great concerns of the aeronautical industry is in relation to the security and integrity of the aircraft and its equipments / components when under critical flight maneuvers such as during landing / takeoff and emergency maneuvers. The engineers, technicians and scientists are constantly developing new techniques and theories to reduce the design time and testing, ir order to minimize costs. More and more the Finite Element Method is used in the structural analysis of a project as well as theories based on experimental results. This work aimed to estimate the critical load to failure for tensile, compression and buckling of the Tie-Rod, a fixture aircraft widely used on commercial aircrafts. The analysis was performed by finite element method with the assistance of software and by analytical calculations. The results showed that the Finite Element Method provides relative accuracy and convenience in the calculations, indicating critical load values slightly lower than those found analytically for tension and compression. For buckling, the Finite Element Method indicates a critical load very similar to that found analytically following empirical theories, while Euler's theory results in a slightly higher value. The highest risk is to fail by buckling, but the geometric irregularity of Tie-Rod pieces makes difficult the calculations, therefore a practical test must be done before validation of the results

Estudo da estabilidade dinâmica e controle da aeronave AF-X da equipe AeroFEG

The present work aims to study the stability and control of the aircraft AF-X of AeroFEG team for AeroDesign to contribute with it in developing its theoretical project report for the competition and present the shortcomings of stability that it might measures for the practical test. In the first moment, it was presented forces and motion of the aircraft, so to define the equations of motion. After the equations of motion were calculated, the transfer functions were found and the aircraft response was analyzed under longitudinal stability and lateral-directional. We obtained responses from the aircraft and through the method of Root Locus the gains required to improve responses and reduce the overshoot, finally some changes and improvements for increased stability have been addressed. The study covered all the motions and control surfaces of the aircraft, showing the characteristics and behavior of the front disruptions, as well as opportunities for gains and improvementsThe present work aims to study the stability and control of the aircraft AF-X of AeroFEG team for AeroDesign to contribute with it in developing its theoretical project report for the competition and present the shortcomings of stability that it might measures for the practical test. In the first moment, it was presented forces and motion of the aircraft, so to define the equations of motion. After the equations of motion were calculated, the transfer functions were found and the aircraft response was analyzed under longitudinal stability and lateral-directional. We obtained responses from the aircraft and through the method of Root Locus the gains required to improve responses and reduce the overshoot, finally some changes and improvements for increased stability have been addressed. The study covered all the motions and control surfaces of the aircraft, showing the characteristics and behavior of the front disruptions, as well as opportunities for gains and improvements

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

Vitrocerâmicas para blindagens balísticas

The use of ceramic materials in ballistic armor is considerable. Such materials can be very harder and lighter than metallic materials commonly used and it presents advantages to replace metallic materials when necessary toughness can be achieved. However, as SiC and Al2O3 ceramic, traditionally used for shielding, still have high manufacturing cost or low density do not have enough to shield applications such as aircraft. An alternative is the glass-ceramics, ceramics obtained by controlled crystallization of glasses, whose properties can be adjusted by choosing the chemical composition of glass, heat treatment of crystallization and special treatments such as ion exchange on the surface, resulting in increased mechanical strength . The objective of this project is to study the kinetics of crystallization of a glass composition based on cordierite (2MgO.2Al2O3.5SiO2), low density and high hardness, for the manufacture of glass-ceramics for ballistic tests. Shown in this report are results of heat treatment of crystallization and characterization by thermal analysis (DSC) glass obtained previously, indicating uneven distribution of crystals, and drying, weighing, mixing of raw materials and a new fusion of glass, the same composition

Caracterização microestrutural de uma estrutura tubular aeronáutica submetida a sucessivos reparos de solda TIG

This work examines the possible effects of successive repair procedures on the microstructure of welded steel SAE 4130 by TIG welding process. Discussions and results were made about the metallographic analysis , non-metallic inclusions and microhardness tests , which were conducted on samples taken from the cradle engine component after the end of its life , a model airplane T-27 Tucano , made by EMBRAER and belonging were performed FAB . The choice of such component is due to the fact that this is critical to flight safety since it provides support for the aircraft engine . Thus regions of the weld metal , base metal and heat affected , with samples of the original weld bead , free of weld bead and also with four rework procedures for TIG welding zone were analyzed . It was found that after the fourth rework there is an increase in the amount of martensite , which may weaken the material with respect to resistance to fatigue. It was also found that the regions of the heat affected zone and weld metal have higher microhardness values when compared to those found in the base metal due to favoring the formation of ferritic and tempered martensite microstructures . Moreover, a welding process promotes a region with less non-metallic inclusions than metal base , which also explains the difference in the results obtained

Implementação de um tuboexpansor na refinaria do Planalto Paulista – REPLAN com objetivo do aproveitamento da energia contida nos gases residuais do FCC – Fluid Catalytic Cracking na geração de energia elétrica

The steel type AISI 4130 (ultra-high strength steel) is an alloy of low carbon and its main alloying elements are chromium and molybdenum, which improves the toughness of the weld metal. It has numerous applications, especially where the need for high mechanical strength. It is widely used in equipment used by the aviation industry, such as cradle-tomotor, and this is the motivation for this study. Cots are of fundamental importance, because the engine supports and maintains balance in the fixed landing gear. This equipment is subjected to intense loading cycles, whose fractures caused by fatigue are constantly observed. Will be determined the effects caused by re-welding the structure of aeronautical equipment, and will also study the microstructure of the metal without welding. The studies will be done on materials used in aircraft, which was given to study. The results provide knowledge of microstructure to evaluate any type of fracture that maybe caused by fatigue. Fatigue is a major cause of aircraft accidents and incidents occurred, which makes the study of the microstructure of the metal, weld and re-solder the knowledge essential to the life of the material. The prevention and control of the process of fatigue in aircraft are critical, since the components are subjected to greater responsibility cyclic loading

Analise mecânica e microestrutural em estruturas tubulares aeronáuticas soldadas de aço ABNT 4130

Airplane Motor Cradles have a complex geometry, since they require different conbinations between different tubes and TIG welded in several angles. In T-25 aircraft and Universal T-27 Tucano (EMBRAER / FAB), besides having to bear the engine balance, these components maintain fixed the nose landing gear in another extremity. They are considered critical to flight safety, and for this reason, the aviation standards are extremely rigid in their production, imposing a zero index” of defects on the final weld metal quality. These structures may be containing an historical of welding repairs, whose effects on their structural integrity are not computed. In this work we analyzed the standardised AISI 4130 steel and the raw steel of tubes to the Airplane Motor Cradles. First of all, microscopy and microanalysis of the base steel, then we analyzed the effects of the TIG weld. Tensile testing was conducted to measure the difference between the mechanical properties of standardised steel and without this treatment