The aim of this work is to evaluate the mechanical strength of a co-polymer of 2-hydroxyethylmethacrylate (HEMA) and methylmethacrylate (MMA), so that it can be applied as an interfacial layer between bone cement and steel implants to improve their performance and life. Finite element (FE) analysis techniques are used to assess the behavior of the interface layer under static and dynamic loading conditions. The material property of the co-polymer is a function of its composition and water saturation. The factors affecting the strength of the bone-implant interface are many. Implant interfacial fracture can lead to decreased stability. Fatigue life is a very important process in failure. The results obtained from static and dynamic analyses show that increasing the percentage of HEMA improves the strength of the interface by reducing the stiffness of the implant, absorbing more energy and by reducing the interfacial stress peaks and making the stress distribution more nearly uniform.

Made available in DSpace on 2014-06-12T17:41:16Z (GMT). No. of bitstreams: 2 arquivo7950_1.pdf: 7976216 bytes, checksum: f3253e3ea18bf74d50c49bd3c0818e5f (MD5) license.txt: 1748 bytes, checksum: 8a4605be74aa9ea9d79846c1fba20a33 (MD5) Previous issue date: 2007 / A segurança operacional da malha de dutos de transporte de hidrocarbonetos é uma grande preocupação de todas as companhias de petróleo, devido aos imensos danos econômi-cos, sociais e em termos da imagem da companhia que um acidente de grande porte com um duto pode causar. Esta malha deve ser monitorada continuamente e problemas encontrados devem ser avaliados de forma confiável, a fim de analisar o comprometimento da integridade estrutural do duto e permitir que reparos necessários sejam realizados com segurança, antes que estes defeitos causem um acidente. No caso de defeitos causados por corrosão, a análise computacional com o Método dos Elementos Finitos (MEF) tem se mostrado uma das ferra-mentas mais eficientes para a avaliação correta da integridade estrutural de dutos com defei-tos. Estas ferramentas permitem considerar diretamente os fenômenos físicos envolvidos no processo de falha do duto resultando assim em resultados mais precisos que os encontrados por meio de modelos semi-empíricos e bem mais rápidos e econômicos que os obtidos através de experimentos em laboratório. A análise via o MEF, no entanto, requer uma grande especialização e um treinamento específico que não são característicos de todos os engenheiros de tubulações. O processo para a criação de bons modelos computacionais para um defeito, que inclui a modelagem fiel da geometria deste defeito e a geração de uma malha apropriada, demanda uma interação manual constante do engenheiro, é demorado e muito repetitivo, e por estas razões muito propenso a erros. Normalmente, este procedimento é repetido desde o início para cada novo problema analisado, em um patente desperdício de recursos humanos qualificados. A principal proposta deste trabalho foi desenvolver um conjunto de ferramentas com-putacionais que produzem automaticamente modelos de dutos com defeitos, prontos para se-rem analisados em programas comerciais que implementam o MEF, a partir de alguns parâ-metros que localizem e forneçam as dimensões principais do defeito ou de uma série de de-feitos. Estas ferramentas são baseadas no programa comercial de pré e pós-processamento MSC.PATRAN e foram produzidas por meio da linguagem de programação PCL (Patran Command Language). O programa de geração automática de modelos (denominado programa PIPEFLAW) tem interface gráfica simplificada e personalizada, de forma que um engenheiro, com noções básicas de simulação computacional com elementos finitos, possa gerar rapida-mente modelos que resultem em simulações precisas e confiáveis. A realização das análises não-lineares foi feita por meio de um script implementado na linguagem de programação PYTHON a partir do qual toda a análise é gerenciada através da execução automática de tarefas pré-determinadas. Assim, a cada iteração da análise, o sol-ver ANSYS é acionado pelo script e em seguida, os resultados gerados durante aquela iteração são lidos e interpretados pelo script possibilitando que os critérios de convergência e incremento de carga, pré-definidos pelo usuário, sejam aplicados automaticamente, diferen-temente do procedimento usual quando se ativa os critérios de convergência e de incremento de carga determinados pelo solver . Por fim, são apresentados alguns exemplos de modelos de dutos gerados automatica-mente pelo programa PIPEFLAW. Os resultados de análises numéricas, realizadas utilizando as ferramentas desenvolvidas neste trabalho, são comparados com resultados empíricos, nu-méricos e experimentais disponíveis na literatura com o objetivo de validar as ferramentas aqui apresentadas

Diplomová práce je zaměřena na optimální modelování nýtového spoje pro tři různé konfigurace pomocí metody konečných prvků v programu MSC. Nastran/Patran. Na základě prezentovaných výsledků je možné virtuálně simulovat chování nýtových spojů při zatížení, za účelem správného návrhu před provedením statických pevnostních zkoušek. Použitím těchto MKP simulací v procesu certifikace výrobku lze významně redukovat časovou i finanční náročnost pevnostních zkoušek. Při lepším porozumění chování konstrukce lze také lépe predikovat reálnou únosnost nýtových spojů.

The AHRLAC aircraft is a high performance light aircraft that is developed and manufactured in South Africa by Aerosud ITC in partnership with Paramount. This aircraft is the first of its kind to originate from South Africa. The aircraft has a twin boom, tandem pilot seating configuration, with a Pratt and Whitney turbine-propeller engine in a pusher configuration. The main structure of the aircraft is a conventional metallic structure, while the fairings and some secondary structures are composite. This study will focus on the design and development of the composite ventral fin of the first prototype aircraft, the experimental demonstrator model (XDM). It is crucial to ensure that the ventral fin can function safely within the design requirements of the aircraft under the loads which the fin is likely to encounter. Preceding the design process, a critical overview of composite materials used in aircraft applications is provided. This will include the materials, manufacturing methods, analysis and similar work done in this field of study. The literature will be used in the study for decision-making and validation of proven concepts and methodologies. The first part of this study entailed choosing a suitable composite material and manufacturing method for this specific application. The manufacturing method and materials used had to suit the aircraft prototype application. The limitations of using composite materials were researched as to recognize bad practice and limit design flaws on the ventral fin. Once the material and manufacturing methods were chosen, ventral fin concepts were evaluated using computer aided finite element analysis (FEA) with mass, stiffness and strength being the main parameters of concern. The load cases used in this evaluation were given by the lead structural engineer and aerodynamicist. The calculations of these loads are not covered in detail in this study. The FEA input material properties used, were determined by material testing by the relevant test methods. The ventral fin concept started as the minimal design with the lowest mass. The deflections, composite failure and fastener failure were then evaluated against the required values. The concept was modified by adding stiffening elements, such as ribs and spars, until satisfactory results were obtained. In this way a minimal mass component is designed and verified that it can adequately perform its designed tasks under the expected load conditions. Each part used in the ventral fin assembly was not individually optimized for mass, but rather the assembly as a whole. The final concept was modelled using the computer aided design software, CATIA. This model used in combination with a ply book made it possible to manufacture the ventral fin in a repeatable manner. A test ventral fin was manufactured using the selected materials and manufacturing methods to validate the design methodology. In the next step the selected load cases were used in static testing to validate the FEM through comparison. The result of the study is a composite ventral fin of which the mass, stiffness and strength are suitable to perform its function safely on the first prototype AHRLAC aircraft. The study concludes on the process followed from material selection to FEA and detail design, in order for this same method to be used on other AHRLAC XDM composite parts. / M (Mechanical Engineering), North-West University, Potchefstroom Campus, 2015

The AHRLAC aircraft is a high performance light aircraft that is developed and manufactured in South Africa by Aerosud ITC in partnership with Paramount. This aircraft is the first of its kind to originate from South Africa. The aircraft has a twin boom, tandem pilot seating configuration, with a Pratt and Whitney turbine-propeller engine in a pusher configuration. The main structure of the aircraft is a conventional metallic structure, while the fairings and some secondary structures are composite. This study will focus on the design and development of the composite ventral fin of the first prototype aircraft, the experimental demonstrator model (XDM). It is crucial to ensure that the ventral fin can function safely within the design requirements of the aircraft under the loads which the fin is likely to encounter. Preceding the design process, a critical overview of composite materials used in aircraft applications is provided. This will include the materials, manufacturing methods, analysis and similar work done in this field of study. The literature will be used in the study for decision-making and validation of proven concepts and methodologies. The first part of this study entailed choosing a suitable composite material and manufacturing method for this specific application. The manufacturing method and materials used had to suit the aircraft prototype application. The limitations of using composite materials were researched as to recognize bad practice and limit design flaws on the ventral fin. Once the material and manufacturing methods were chosen, ventral fin concepts were evaluated using computer aided finite element analysis (FEA) with mass, stiffness and strength being the main parameters of concern. The load cases used in this evaluation were given by the lead structural engineer and aerodynamicist. The calculations of these loads are not covered in detail in this study. The FEA input material properties used, were determined by material testing by the relevant test methods. The ventral fin concept started as the minimal design with the lowest mass. The deflections, composite failure and fastener failure were then evaluated against the required values. The concept was modified by adding stiffening elements, such as ribs and spars, until satisfactory results were obtained. In this way a minimal mass component is designed and verified that it can adequately perform its designed tasks under the expected load conditions. Each part used in the ventral fin assembly was not individually optimized for mass, but rather the assembly as a whole. The final concept was modelled using the computer aided design software, CATIA. This model used in combination with a ply book made it possible to manufacture the ventral fin in a repeatable manner. A test ventral fin was manufactured using the selected materials and manufacturing methods to validate the design methodology. In the next step the selected load cases were used in static testing to validate the FEM through comparison. The result of the study is a composite ventral fin of which the mass, stiffness and strength are suitable to perform its function safely on the first prototype AHRLAC aircraft. The study concludes on the process followed from material selection to FEA and detail design, in order for this same method to be used on other AHRLAC XDM composite parts. / M (Mechanical Engineering), North-West University, Potchefstroom Campus, 2015

Made available in DSpace on 2014-06-12T17:37:42Z (GMT). No. of bitstreams: 2 arquivo3801_1.pdf: 5181378 bytes, checksum: dc67c4f39bc6a91e46c8fca687d06ce1 (MD5) license.txt: 1748 bytes, checksum: 8a4605be74aa9ea9d79846c1fba20a33 (MD5) Previous issue date: 2008 / Conselho Nacional de Desenvolvimento Científico e Tecnológico / Os dutos para transporte de petróleo e gás são um dos meios mais seguros e que menos agridem ao meio-ambiente, além de possuírem uma alta eficiência e produtividade. Mesmo tendo uma capacidade excepcional, eles são uma grande fonte de preocupação das companhias petrolíferas e estão sujeitos a diversos tipos de defeitos, dentre os quais o que mais se destaca são os defeitos causados por corrosão. Então, para que uma malha dutoviária opere com segurança, faz se necessário monitorar continuamente ela, para que defeitos encontrados sejam analisados de maneira rápida e confiável, verificando-se assim a integridade estrutural da região afetada. Neste contexto, a análise computacional pelo Método de Elementos Finitos (MEF) tem-se mostrado uma poderosa e eficiente ferramenta na avaliação estrutural de dutos com defeitos causados por corrosão, pois os resultados obtidos pelo método são mais rápidos e econômicos do que os conseguidos pelo método experimental, e bem mais precisos do que os obtidos pelos métodos analíticos. Ampliar com segurança a vida útil dos dutos transformou- se para os engenheiros uma tarefa fundamental e muito importante. Este trabalho teve como proposta, o desenvolvimento de um programa que automatizasse a geração de modelos computacionais identificados de defeitos utilizando malhas estruturadas e não estruturadas (malhas mistas) no mesmo modelo, através da implementação de funções escritas em linguagem de programação PCL (Patran Commando Language) e adicionadas ao programa PIPEFLAW (Cabral, 2007) desenvolvido pelo grupo PADMEC. Também foram construídos modelos computacionais de dutos com defeitos de corrosão com geometria irregular. Para a criação dos modelos foi empregado o programa comercial de pré e pósprocessamento MSC.PATRAN. Depois de concluídos, todos os modelos foram avaliados estruturalmente através da realização de análises não-lineares. Para esta etapa utilizou-se o programa comercial de simulação numérica o solver ANSYS. Por fim, são apresentados alguns exemplos de modelos de dutos gerados automaticamente, que utilizam malha mista, pelo programa PIPEFLAW. Os resultados dessas análises numéricas realizadas são comparados com resultados empíricos, numéricos e experimentais quando disponíveis na literatura. Também são apresentados alguns exemplos de modelos de dutos com defeitos de corrosão com geometria irregular construídos, e os resultados das análises numéricas realizadas nestes modelos para o estudo de suas capacidades estruturais

The acoustic environment generated during launch is the most demanding structural load case for large, lightweight satellite reflector antennas. The reflector is exposed to extremely high sound pressure levels originating from the structural excitation of the rocket engines and exterior air flow turbulence. This thesis aims to predict the structural responses in the reflector due to the acoustic pressure load with a model based on Finite Element Modelling (FEM). The FE-model is validated against a previously performed Boundary Element Method (BEM) analysis. An approach called Split Loading together with a combination of BEM and FEM will be utilized to handle the surrounding air mass and the applied sound pressures. The idea of Split Loading is to divide the structure into several patches and apply a unit pressure load to each patch separately. In the last step the unit pressure is scaled and correlated by a power spectral density calculated from the acoustic pressures. Split Loading will be implemented in software packages MSC.NASTRAN/PATRAN. The model developed in this thesis handles both the added mass of the surrounding air and the sound pressure applied to the reflector. The model can qualitatively well reproduce the results of the BEM-analysis and the test data. However, the model tends to overestimate responses at low frequencies and underestimate them at high frequencies. The end results is that the model becomes too conservative at low frequencies to be used without further development.

Tato práce zkoumá možností řešení kritické síly vzpěrné stability laminátových kompozitních válcových skořepin jak analytickým tak MKP přístupem. Analytické řešení je prezentováno detailně a je zpracován Matlab program pro jeho výpočet. MKP řešení je prováděno ve dvou řešičích softwaru MSC.Nastran, jsou zjišťována vhodná nastavení těchto řešičů a jejich chování. Všechny způsoby řešení jsou na závěr porovnány a je navrženo několik závěrů.

Indiana University-Purdue University Indianapolis (IUPUI) / In a multifidelity structural design process, depending on the required analysis, different levels of structural models are needed. Within the aerospace design, analysis and optimization community, there is an increasing demand for automatic generation of parametric feature tree (build recipe) attributed multidisciplinary models. Currently, this is mainly done by creating separate models for different disciplines such as mid-surface model for aeroelasticity, outer-mold line for aerodynamics and CFD, and built-up element model for structural analysis. Since all of these models are built independently, any changes in design parameters require updates on all the models which is inefficient, time-consuming and prone to deficiencies. In this research, Engineering Sketch Pad (ESP) is used to create attribution and maintain consistency between structural models with different fidelity levels. It provides the user with the ability to interact with a configuration by building and/or modifying the design parameters and feature tree that define the configuration. ESP is based an open-source constructive solid modeler, named OpenCSM, which is built upon the OpenCASCADE geometry kernel and the EGADS geometry generation system. The use of OpenCSM as part of the AFRL’s CAPS project on Computational Aircraft Prototype Syntheses for automatic commercial and fighter jet models is demonstrated. The rapid generation of parametric aircraft structural models proposed and developed in this work will benefit the aerospace industry with coming up with efficient, fast and robust multidisciplinary design standardization of aircraft structures. Metallic aircraft wings are usually not optimized to their fullest potential due to shortage of development time. With roughly \$1000 worth of potential fuel savings per pound of weight reduction over the operational life of an aircraft, airlines are trying to minimize the weight of aircraft structures. A stiffness based strategy is used to map the nodal data of the lower-order fidelity structural models onto the higher-order ones. A simple multi-fidelity analysis process for a parametric wing is used to demonstrate the advantage of the approach. The loads on the wing are applied from a stick model as is done in the industry. C program is created to connect the parametric design software ESP, analysis software Nastran, load file and design configuration file in CSV format. This problem gets compounded when it comes to optimization of composite wings. In this study, a multi-level optimization strategy to optimize the weight of a composite transport aircraft wing is proposed. The part is assumed to initially have some arbitrary number of composite super plies. Super plies are a concept consisting of a set of plies all arranged in the same direction. The thickness and orientation angles of the super plies are optimized. Then, each ply undergoes topometry optimization to obtain the areas of each super ply taking the least load so that it could be cut and removed. Each of the super plies are then optimized for the thickness and orientation angles of the sub plies. The work presented on this paper is part of a project done for Air Force Research Laboratory (AFRL) connecting the parametric geometry modeler (ESP) with the finite element solver (Nastran).

This master thesis focuses on modelling and simulation of impact tests of composite panels. Simulations and analysis were made by using Finite Element Method in software MSC Patran and Dytran. The first part of the thesis deals with describing the properties of composite panels during impact testing and other cases of impacts on composite structures. Next part deals with the used models and results from Dytran. These results are compared with experimental data from real low-velocity impact tests. Part of the thesis is devoted to impact on panels with the stacking sequences which is supposed to be used for design of air duct for airplane Aero L-39NG.