H υποβάθμιση της δομικής ακεραιότητας των αεροπορικών κατασκευών με το χρόνο και η αποτίμηση της αποτελεί ένα σημαντικό τεχνολογικό πρόβλημα της αεροναυπηγικής. Το πρόβλημα αυτό σε συνδυασμό με το ότι εξακολουθούν να χρησιμοποιούνται αεροσκάφη, τα οποία έχουν ξεπεράσει τον αρχικά σχεδιασμένο χρόνο της επιχειρησιακής τους λειτουργίας, οδήγησε τη διεθνή επιστημονική κοινότητα και την αεροπορική βιομηχανία να ασχοληθεί με το πρόβλημα του “γηράσκοντος” αεροσκάφους (aging aircraft). Το πρόβλημα της γήρανσης της δομής ενός αεροσκάφους οφείλεται κυρίως στην εμφάνιση ευρείας έκτασης βλάβης κόπωσης (wide spread fatigue damage) σε διάφορες περιοχές της κατασκευής, η οποία αυξάνει την πιθανότητα εμφάνισης καταστροφικών αστοχιών. Οι ηλωτές συνδέσεις των ελασμάτων που συνθέτουν την άτρακτο ή τις πτέρυγες ενός αεροσκάφους αποτελούν περιοχές συγκέντρωσης τάσεων και εστίες διάβρωσης με συνέπεια την εμφάνιση και εξέλιξη μικρών ρωγμών σε πολλαπλά σημεία της δομής. Η κατάσταση της ύπαρξης πολλών αλληλεπιδρουσών ρωγμών στο ίδιο δομικό στοιχείο ονομάζεται πολλαπλή βλάβη (Multiple Site Damage – MSD) και οδηγεί σε σημαντική μείωση της εναπομένουσας αντοχής του δομικού στοιχείου και σε υποβάθμιση της δομικής του ακεραιότητας. Η μελέτη του προβλήματος της πολλαπλής βλάβης και η αντιμετώπισή του αποτελεί σημαντικό πεδίο έρευνας, καθώς περιλαμβάνει πλήθος επιμέρους φαινομένων, τα οποία αλληλεπιδρούν μεταξύ τους. Τέτοια φαινόμενα είναι η έναρξη, η διάδοση και η συνένωση πολλαπλών ρωγμών, η τελική αστοχία δομικού στοιχείου σε συνθήκες πολλαπλής βλάβης, καθώς και η επίδραση περιβαλλοντικών παραγόντων όπως η διάβρωση στη συμπεριφορά των υλικών. Σκοπός της παρούσας εργασίας είναι η ανάπτυξη μιας ολοκληρωμένης μεθοδολογίας για την εκτίμηση της εμφάνισης και εξέλιξης της πολλαπλής βλάβης κόπωσης σε αεροπορικά δομικά στοιχεία, έτσι ώστε να είναι εφικτή η εκτίμηση της δομικής τους ακεραιότητας σε οποιαδήποτε στιγμή της διάρκειας λειτουργίας τους. Τα τεχνολογικά προβλήματα, που αντιμετωπίζονται στην παρούσα εργασία με ανάπτυξη πρωτότυπων μεθοδολογιών, περιλαμβάνουν: • Ανάλυση τάσεων σε πολλαπλά ρηγματωμένες κατασκευές και υπολογισμό συντελεστών έντασης τάσεων στις ρωγμές • Πρόβλεψη έναρξης και διάδοσης ρωγμών • Πρόβλεψη συνένωσης ρωγμών και εναπομένουσας αντοχής Για την ανάλυση τάσεων και τον υπολογισμό των συντελεστών έντασης τάσεων σε πολλαπλά ρηγματωμένα δομικά στοιχεία με ή χωρίς ενισχύσεις (stiffeners) αναπτύσσονται στη βάση της τεχνικής της υπο-μοντελοποίησης της μεθόδου των πεπερασμένων στοιχείων (ΠΣ) κατάλληλα υπερ-στοιχεία (super-elements) για τη μοντελοποίηση των κρίσιμων τμημάτων της κατασκευής. Η μεθοδολογία υπερ-στοιχείων επιλέγεται στην παρούσα εργασία, με σκοπό τη σημαντική μείωση του υπολογιστικού κόστους σε σχέση με τις κλασικές μεθόδους των πεπερασμένων στοιχείων, έτσι ώστε να καταστεί πρακτικά δυνατή η επίλυση του πολύπλοκου αυτού προβλήματος. Το πρόβλημα της δημιουργίας νέων ρωγμών λόγω κόπωσης σε κάποιο δομικό στοιχείο παρουσιάζει έντονα πιθανοθεωρητικό χαρακτήρα. Για την αντιμετώπισή του αναπτύσσεται μεθοδολογία σύμφωνα με την οποία η πιθανότητα να εμφανιστεί μια ρωγμή σε κάποιο σημείο μετά από ορισμένο αριθμό κύκλων φόρτισης εξαρτάται τόσο από την τάση που αναπτύσσεται στο σημείο αυτό όσο και από την πιθανότητα ύπαρξης τοπικών ατελειών του υλικού στο υπό εξέταση σημείο. Για την εφαρμογή της μεθοδολογίας χρησιμοποιούνται στατιστικά δεδομένα που προέρχονται από πειράματα κόπωσης απλών δοκιμίων. Για την εκτίμηση της εναπομένουσας αντοχής ενός πολλαπλά ρηγματωμένου δομικού στοιχείου αναπτύσσεται ένα ενεργειακό κριτήριο συνένωσης ρωγμών. Το κριτήριο βασίζεται της μεταβολής της ενέργειας παραμόρφωσης που λαμβάνει χώρα κατά τη διάρκεια της αστοχίας του υλικού που συνδέει δύο παρακείμενες ρωγμές. Τέλος, τα μοντέλα έναρξης, διάδοσης και συνένωσης ρωγμών συνδυάζονται σε μια ολοκληρωμένη μεθοδολογία, η οποία μπορεί να χρησιμοποιηθεί για την πρόβλεψη της εξέλιξης της πολλαπλής βλάβης κόπωσης. Η αποτελεσματικότητα της μεθόδου επαληθεύεται με τη βοήθεια πειραμάτων κόπωσης πολλαπλά ρηγματωμένων δοκιμίων. / Structural integrity degradation of aeronautical structures due to fatigue, as well as its assessment, represents a major problem of aeronautics. This problem, combined to the fact that numerous aircrafts that have already exceeded their initial design operational life are still in service, led the international scientific community and the aeronautical industry to the in-depth study of aging aircraft. The main problem of an aging aircraft structure is widespread fatigue damage at various areas of the structure, that increase the probability of catastrophic failures. Riveted joints of fuselage or wing panels are areas of high stress concentration and corrosion, therefore, sites susceptible to multiple cracks development. The state of multiple interacting cracks existence at the same structural element is called Multiple Site Damage (MSD) and leads to residual significant strength reduction and structural integrity degradation of the structure. Study and handling of multiple site damage problem is an important research field, as it involves a number of different interacting phenomena, such as crack initiation, propagation and link-up and final structural failure under MSD conditions, as well as the effect of environmental factors like corrosion on the material behaviour. The aim of the present work is the development of an integrated methodology for the prediction of MSD evolution at aeronautical structural elements, in order to make feasible the assessment of their structural integrity throughout their service life. The technological issues that are faced in the frame of the present work by the development of innovative methodologies are: • Stress analysis and stress intensity factors calculation of structures under MSD condition. • Crack initiation and propagation prediction. • Prediction of crack link-up and residual strength. For the stress analysis and stress intensity factor calculation of un-stiffened of stiffened structural elements suitable super-elements are developed for the simulation of crucial structural elements. The super-element methodology is based on finite element sub-structuring technique and, in the present work, is chosen in order to obtain a significant reduction of computation cost with compared to the classical finite element method, so that handling of such complex problems becomes feasible. Fatigue crack initiation at a structural element is a problem exhibiting a strongly stochastic character. A crack initiation prediction methodology is developed according to which the probability of crack initiation at a site of the structure depends on the local stress state combined to a stochastic (random) variation of the fatigue strength at every site susceptible to crack initiation. For the methodology application statistical data from simple fatigue tests are used. For the crack link-up and the residual strength estimation of a multiple cracked structural element an energy-based link-up criterion is developed. The proposed criterion is based on the strain energy variation during the failure of the ligament of two adjacent cracks. Finally, the initiation, propagation and link-up models are combined and implemented in an integrated methodology that can be used for the assessment of multiple site damage evolution. The effectiveness of the methodology is validated using suitable fatigue tests of multiple-site damaged panels.

Η παρούσα διπλωματική εργασία εκπονήθηκε στο τμήμα Ηλεκτρολόγων Μηχανικών και Τεχνολογίας υπολογιστών του πανεπιστημίου Πατρών και το θέμα της αφορά τη μελέτη σφαλμάτων στο δρομέα τριφασικής σύγχρονης μηχανής έκτυπων πόλων με τη δημιουργία δισδιάστατου μοντέλου πεπερασμένων στοιχείων. Σκοπός της διπλωματικής εργασίας είναι η ανάλυση της λειτουργίας τριφασικού σύγχρονου κινητήρα έκτυπων πόλων κατά την ασύγχρονη εκκίνηση του σε τρείς περιπτώσεις, με σφάλμα σε μία μπάρα ενός έκτυπου πόλου, στο δακτύλιο βραχυκύκλωσης και χωρίς κανένα σφάλμα και σύγκριση των αποτελεσμάτων. Για την σχεδίαση του μοντέλου του τριφασικού κινητήρα χρησιμοποιήθηκαν τα κατασκευαστικά στοιχεία μιας πραγματικής τριφασικής μηχανής πού προορίζεται για λειτουργία σε υδροηλεκτρικό σταθμό παραγωγής ενέργειας με τη δυνατότητα λειτουργίας σαν αντλία. Για την κατασκευή και εξομοίωση του μοντέλου στις δύο διαστάσεις χρησιμοποιήθηκε το λογισμικό Opera-2d, το οποίο χρησιμοποιεί την μέθοδο των πεπερασμένων στοιχείων, μια αριθμητική μέθοδο για να προσομοιώσει τη φυσική λειτουργία των ηλεκτρικών μηχανών. Για την επιτυχία του μοντέλου χρειάστηκαν αρκετές μετρήσεις και υπολογισμοί από τα δεδομένα που είχαμε τα οποία δεν παραθέτονται. Με την περάτωση του μοντέλου εξομοιώθηκαν διαφορετικές λειτουργίες στη μόνιμη κατάσταση για εξακρίβωση της ακρίβειας του μοντέλου που κατασκευάσαμε. Η διπλωματική εργασία χωρίζεται σε πέντε κεφάλαια, όπου αρχικά στο πρώτο κεφάλαιο γίνεται μια γενική περιγραφή των βασικών εννοιών της ηλεκτρικής ενέργειας και των βασικών αρχών που διέπουν την κατασκευή και λειτουργία των σύγχρονων μηχανών και γενικότερα των τριφασικών σύγχρονων μηχανών έκτυπων πόλων. Στο κεφάλαιο 2 εξηγείται πιο αναλυτικά η λειτουργία του τριφασικού σύγχρονου κινητήρα και οι μέθοδοι της εκκίνησης του με έμφαση στην ασύγχρονη εκκίνηση. Επίσης παρουσιάζονται μερικά δεδομένα γενικά γύρω από τους υδροηλεκτρικούς σταθμούς και τον τρόπο λειτουργίας τους. Στη συνέχεια στο κεφάλαιο 3 δίνονται επιγραμματικά τα κυρίως βήματα που ακολουθήσαμε κατά την σχεδίαση του μοντέλου πεπερασμένων στοιχείων μαζί με τα σχέδια των τμημάτων του κινητήρα και τα κυριότερα παράθυρα ελέγχου του λογισμικού Opera-2d. Στο κεφάλαιο 4 δίνονται τα βήματα και τα παράθυρα ελέγχου για τις παραμέτρους της ανάλυσης και παρουσιάζονται τα αποτελέσματα των εξομοιώσεων που για τις τρείς περιπτώσεις τους υγιούς μοντέλου, του μοντέλου με σπασμένη μπάρα και το μοντέλο με σφάλμα στο δακτύλιο βραχυκύκλωσης. Στο τέλος του κεφαλαίου 4 εξάγονται τα συμπεράσματα μας για την ασύγχρονη εκκίνηση του σύγχρονου κινητήρα και πως αυτή επηρεάζεται από τα σφάλματα σε μία μπάρα βραχυκύκλωσης και στο δακτύλιο βραχυκύκλωσης. / This thesis was produced in the department of Electrical Engineering and Computer Science at the University of Patras and involves the study of rotor errors in a three phase synchronous motor with salient poles with the help of finite element analysis. The purpose of this thesis is the monitoring of a three-phase synchronous motor with salient poles during asynchronous starting, with one broken bar, broken ring and in a healthy state for comparing the results. For the design of the motor we used the machine data of a real motor which is used in a pumped storage hydroelectric generator. For the creation of the model in two dimensions we used the software Opera-2d, which uses the finite element method to simulate the operation of electric machines. For the success of the design, a number of measurements and calculations was taken from the machine data which are not included in the thesis. Also, after the completion of the model, we run simulations in steady state to verify that the model was running according to designer parameters. The thesis is divided in five chapters. In the first chapter there is a general description of the basic knowledge of electric energy and the principles regarding the construction and operation of synchronous machines and in particular three-phase synchronous machines with salient poles. In chapter 2 there is a more detailed description of the operating characteristics of a three-phased synchronous motor and the starting methods, with emphasis at asynchronous starting. Additionally, there is some information regarding hydro-generator stations. Chapter 3 shows the main steps followed during the design stage of the model and it includes images of the main parts of the motor and the control windows of the software Opera-2d. Chapter 4 starts by showing the main steps and control windows for the analysis parameters and this is followed by the results of the simulations for the three cases: healthy motor, with broken bar and with broken ring. Finally the conclusions for the asynchronous starting of a synchronous motor and how it is affected by a broken bar and a broken ring at the rotor, are presented at the end of chapter 4.

Made available in DSpace on 2014-06-11T19:28:57Z (GMT). No. of bitstreams: 0 Previous issue date: 2006-12-12Bitstream added on 2014-06-13T20:37:55Z : No. of bitstreams: 1 gomes_ea_me_araca.pdf: 1098815 bytes, checksum: 1bafd8a36608b27cf45144d22d87c56d (MD5) / Odonto Mega / Objetivo: avaliar o deslocamento e distribuição interna de tensões do sistema coroa/implante/parafuso de retenção e tecido ósseo adjacente, em função de diferentes níveis de desadaptação angular unilateral, por meio do MEF-2D. Materiais e método: foram confeccionados 4 modelos matemáticos, representativos de coroa metálica conectada a implante por meio de parafuso deretenção, inseridos em tecido ósseo, determinando os 4 grupos estudados: Grupo 1 (controle), coroa completamente adaptada ao implante; Grupo 2, 3 e 4, coroa com desadaptações angulares unilaterais de 50æm, 100æm e 200æm, respectivamente. A partir do programa de elementos finitos Ansys, os modelos receberam carga de 133N, com angulação de 30o e deslocamento de 2mm do longo eixo do implante em lado oposto a desadaptação, sendo analisados os mapas de tensões e deslocamento. Resultados: com o aumento das desadaptações angulares, os mapas de tensões mostraram aumento gradativo das tensões na coroa (1056 N/mm2 a 2326N/mm2) e no parafuso de retenção (909.91 N/mm2 a 987.02N/mm2) e uniformidade na distribuição de tensões no implante e tecido ósseo medular. Quanto ao deslocamento, verificou-se inclinação do conjunto de 0.3101mm (controle) a 0.3179mm no grupo 4, em função do carregamento e das desadaptações. Conclusão: a redução do contato unilateral entre a coroa e o implante levou ao deslocamento de todo conjunto e alteração na distribuição e magnitude das tensões ao longo do sistema, principalmente na região da coroa e parafuso de retenção, sendo que, de modo geral, as desadaptações angulares unilaterais de 100æm e 200æm mostraram maiores valores de tensões em relação ao controle. / Objectives: the aim of this study was to evaluate the displacement and stress inner distribution of the prostheses/implant/abutment screw set and surrounding bone, with prostheses presenting different levels of angular misfit unilateral through FEA-2D. Materials and methods: four mathematic models were made, representing metal prostheses in connection of the implant through abutment screw, inside bone tissue, determining 4 groups: Group 1 (control) prostheses fit on the implant; Groups 2, 3 and 4, prostheses with angular misfit unilateral of 50æm, 100æm and 200æm, respectively. It was applied a load of 133N with 30o angulation and off-axis at 2mm of long axis of the implant in opposite direction of misfit on the models, through finite element program Ansys. Results: with upper of angular misfit, the stress maps showed gradual increased of prostheses stress (1056N/mm2 at 2326N/mm2) and uniform stress distribution in the implant and trabecular bone. About the displacement, observed inclination of the set of 0.3101mm (control) at 0.3179mm in the group 4 due to loading and misfit. Conclusions: the lower of the unilateral contact between prostheses and implant proportionate the displacement of all set and the distribution and magnitude alterations of the stress of all the system, principally in the prostheses and abutment screw regions; as a general rule, the angular misfit unilateral of the 100æm and 200æm showed higher stress values in relation to the control.

Leakage and blockage of oil and gas pipeline systems, water pipelines, pipe-work of process plants and other pipe networks can cause serious environmental, health and economic problems. There are a number of non-destructive testing (NDT) methods for detecting these defects in pipeline systems such as radiographic, ultrasonic, magnetic particle inspection, pressure transient and acoustic wave methods. In this study, the acoustic wave method and a modal frequency technique, which based on a roving mass method, are used. The aim of the thesis is to employ acoustic wave propagation based methods in conjunction with stationary wavelet transform (SWT) to identify leakage and blockage in pipe systems. Moreover, the research is also aimed at using the difference of modal frequencies of fluid-filled pipes with and without defects and a roving mass, and consequently, to develop a roving mass-based defect detection method for pipelines. In the study, the acoustic finite-element analysis (AFEA) method is employed to simulate acoustic wave propagation in small and large air-filled water-filled straight pipe and pipe networks with leakage and blockage but without flow. Computational fluid dynamics (CFD) analysis was also employed to simulate acoustic wave propagation in air-and water-filled pipes with flow, leakage and blockage. In addition, AFEA was used to predict the modal frequencies of air- and water-filled pipes with leakage and blockage in the presence of a roving mass that was traversed along the axis of the pipes. Experimental testing was conducted to validate some of the numerical results. Two major experiments were performed. The first set of experiments consisted of the measurement of acoustic wave propagation in a straight air-filled pipe with leakage and blockage. The second set of experiments concerned the measurement of acoustic wave propagation in an air-filled pipe network comprising straight pipe, elbows and T-piece and flange. The AFEA and CFD analysis of fluid-filled pipe can be used to simulate the acoustic wave propagation and acoustic wave reflectometry of a fluid-filled pipe with leakage and blockage of different sizes down to a small leakage size of 1mm diameter and a blockage depth of 1.2mm in a pipe. Similarly, the AFEA method of a static fluid-filled pipe can be used to simulate acoustic wave modal frequency analysis of a fluid-filled pipe with leakage and blockage of different sizes down to a leakage of 1mm diameter and a blockage depth of 1.2mm. Moreover, the measured signal of acoustic wave propagation in an air-filled can be successfully decomposed and de-noised using the SWT method to identify and locate leakages of different sizes down to 5mm diameter, and small blockage depth of 1.2mm. Also, the SWT approximation coefficient, detail and de-noised detail coefficient curves of an air-filled pipe with leakage and blockage and a roving mass give leakage and blockage indications that can be used to identify, locate and estimate the size of leakage and blockage in a pipe.

abstract: Current trends in the Computer Aided Engineering (CAE) involve the integration of legacy mesh-based finite element software with newer solid-modeling kernels or full CAD systems in order to simplify laborious or highly specialized tasks in engineering analysis. In particular, mesh generation is becoming increasingly automated. In addition, emphasis is increasingly placed on full assembly (multi-part) models, which in turn necessitates an automated approach to contact analysis. This task is challenging due to increases in algebraic system size, as well as increases in the number of distorted elements - both of which necessitate manual intervention to maintain accuracy and conserve computer resources. In this investigation, it is demonstrated that the use of a mesh-free B-Spline finite element basis for structural contact problems results in significantly smaller algebraic systems than mesh-based approaches for similar grid spacings. The relative error in calculated contact pressure is evaluated for simple two dimensional smooth domains at discrete points within the contact zone and compared to the analytical Hertz solution, as well as traditional mesh-based finite element solutions for similar grid spacings. For smooth curved domains, the relative error in contact pressure is shown to be less than for bi-quadratic Serendipity elements. The finite element formulation draws on some recent innovations, in which the domain to be analyzed is integrated with the use of transformed Gauss points within the domain, and boundary conditions are applied via distance functions (R-functions). However, the basis is stabilized through a novel selective normalization procedure. In addition, a novel contact algorithm is presented in which the B-Spline support grid is re-used for contact detection. The algorithm is demonstrated for two simple 2-dimensional assemblies. Finally, a modified Penalty Method is demonstrated for connecting elements with incompatible bases. / Dissertation/Thesis / Ph.D. Mechanical Engineering 2010

Neste trabalho buscou-se consolidar aspectos referentes à otimização de problemas envolvidos na mecânica dos meios contínuos, envolvendo diferentes áreas do conhecimento, tais como: otimização matemática, diferenciação automática, análise estrutural, análise aerodinâmica, parametrização de curvas, superfícies e sólidos do tipo B-spline racionais não-uniformes (NURBS, acrônimo do inglês), análise IsoGeométrica (IGA, acrônimo do inglês) e análise por Elementos Finitos (FEA, acrônimo do inglês). Como objetivo final busca-se otimizar formas de cascas estruturais e formas de corpos aerodinâmicos imersos em escoamentos compressíveis. No que concerne à análise estrutural, esta é realizada via análise IsoGeométrica utilizando elementos sólidos para modelar cascas. Uma cinemática co-rotacional abrangente e precisa baseada na exata decomposição polar é desenvolvida, para lidar com problemas estáticos e dinâmicos altamente não lineares. Na análise estática foram implementados o método de Newton-Raphson e controle de deslocamentos generalizado, para problemas dinâmicos foram implementados o método -generalizado (G) e o método energia momento generalizado (GEMM+). A análise aerodinâmica é realizada via análise por Elementos Finitos para modelar escoamentos compressíveis viscosos e não viscosos em regimes transônicos e supersônicos. Um esquema característico baseado na separação da equação de momento (CBS, acrônimo do inglês) é utilizado para obter uma adequada integração temporal. No que concerne à otimização matemática, é utilizado um método baseado em gradientes, conhecido por programação quadrática sequencial (SQP, acrônimo do inglês), onde a avaliação as derivadas de Fréchet são levadas a cabo via diferenciação automática (AD, acrônimo do inglês). No que concerne aos resultados finais é realizada a otimização estrutural de forma de cascas modeladas como sólidos são apresentados, evidenciando um desempenho ótimo com respeito à energia de deformação interna. Os resultados de otimização aerodinâmica bidimensionais apresentam perfis aerodinâmicos ótimos com respeito à relação arrasto/sustentação para uma ampla gama de número de Mach, enquanto um resultado tridimensional é apresentado evidenciando a robustez e eficiência da implementação proposta. Pretendese estabelecer com este trabalho as bases para pesquisas em problemas de otimização aeroelástica. / Consolidation of the link among optimization problems in continuum mechanics, involving different fields, such as mathematical optimization, automatic differentiation, structural analysis, aerodynamic analysis, curves, surfaces and solids parameterization using Non Uniform Rational B-spline (NURBS), IsoGeometric Analysis (IGA), Finite Element Analysis (FEA) is looked for. Structural shape optimization of shell structures and aerodynamic shape optimization of immersed bodies in compressible flows are the main goals of this work. Concerning structural analysis, the so-called IsoGeometric analysis is employed. An accurate and comprehensive corotational kinematic based on the exact polar decomposition is developed in order to study highly nonlinear static and dynamic problems. Static analysis is carried out with Newton-Raphson and Generalized Displacement Control Method, while dynamic analysis is carried out with Generalized- (G) and Generalized Energy-Momentum Method (GEMM+). Aerodynamic analysis is carried out via Finite Element Analysis (FEA) in order to solve compressible flows in transonic and supersonic regimes. A Characteristic Based Split (CBS) method is employed to obtain an accurate time integration, which is based on the splitting of the momentum equation. Concerning mathematical optimization, the so-called Sequential Quadratic Programming (SQP) is employed, which is a gradient-based method, where the Fréchet derivatives are evaluated using Automatic Differentiation (AD). Final results consisting in structural optimization shown an optimal behaviour with respect to internal strain energy. While, results concerning aerodynamic bi-dimensional shape optimization exhibit a optimal behaviour with respect drag/lift ratio, for a large range of Mach number, and a simple result for tri-dimensional case is presented in order to show the efficiency and robustness of the implementation. Bases for future research in aeroelastic optimization problems are established in this work.

Bone drilling is an essential part of many orthopaedic surgical procedures, including those for internal fixation and for attaching prosthetics. Drilling into bone is a fundamental skill that can be both very simple, such as drilling through long bones, or very difficult, such as drilling through the vertebral pedicles where incorrectly drilled holes can result in nerve damage, vascular damage or fractured pedicles. Also large forces experienced during bone drilling may promote crack formation and can result in drill overrun, causing considerable damage to surrounding tissues. Therefore, it is important to understand the effect of bone material quality on the bone drilling forces to select favourable drilling conditions, and improve orthopaedic procedures.

Les pales d’hélicoptère sont des structures composites soumises à un chargement cyclique multiaxial, et leur criticité impose de porter une attention particulière à la tolérance aux dommages. Leur revêtement peut potentiellement présenter des criques suite à certains évènements (impact, défaut, foudre). Ces travaux se focalisent sur un matériau de revêtement donné (tissu de verre) et concernent l’étude de la propagation de coupure (crique) sous chargement cyclique. Les sollicitations de service ont amené à considérer la traction et le cisaillement plan. Une étude expérimentale a été menée afin d’étudier les modes d’endommagement du matériau et sa résistance à la propagation de coupure pour différentes sollicitations (en traction et en cisaillement) et pour les drapages les plus courants. Elle a permis de dégager les mécanismes d’endommagement mis en jeu, et a fourni un ensemble important de propriétés matériau et de données quantitatives de vitesse de propagation. Elle a par ailleurs guidé vers une modélisation par éléments finis adaptée à l’architecture du matériau, et la manière dont il se dégrade en fatigue. Ce modèle repose sur un maillage à l’échelle de la mèche, et la prédiction de la propagation est obtenue par l’utilisation d’une courbe de fatigue S-N. La simulation a été évaluée par comparaison des faciès de rupture, des vitesses de propagation et de l’étendue des zones d’endommagement avec les essais réalisés sur éprouvettes. / Helicopter blades consist of composite structures which have to sustain multi-axial cyclic loading. Because of their criticality, damage tolerance has to be considered carefully. Their skin is subjected to environmental events like impact, flaw, lightning which can cause through-thethickness cracks. The present work focuses on one given skin material (woven glass fabric) and concerns the study of the through-the-thickness crack growth under cyclic loading. In-flight loading lead to consider tension and shear. An experimental study has been carried out to study damage in the material and its crackgrowth resistance under different loadings (tension and shear) and for usual stacking sequences. It highlighted damage mechanisms and provided an important set of material data and crack growth speeds. Besides, this led to a finite element approach adapted to the woven fabric architecture, anddamage feature under fatigue loading. This modeling is based on a bundle scale mesh, a semidiscrete damage modeling and an S-N curve to predict fiber failure. Numerical simulations of crack growth tests were carried out, and results were compared with experiments in terms of crack direction, crack growth speed, and size of damaged area.

Neste trabalho buscou-se consolidar aspectos referentes à otimização de problemas envolvidos na mecânica dos meios contínuos, envolvendo diferentes áreas do conhecimento, tais como: otimização matemática, diferenciação automática, análise estrutural, análise aerodinâmica, parametrização de curvas, superfícies e sólidos do tipo B-spline racionais não-uniformes (NURBS, acrônimo do inglês), análise IsoGeométrica (IGA, acrônimo do inglês) e análise por Elementos Finitos (FEA, acrônimo do inglês). Como objetivo final busca-se otimizar formas de cascas estruturais e formas de corpos aerodinâmicos imersos em escoamentos compressíveis. No que concerne à análise estrutural, esta é realizada via análise IsoGeométrica utilizando elementos sólidos para modelar cascas. Uma cinemática co-rotacional abrangente e precisa baseada na exata decomposição polar é desenvolvida, para lidar com problemas estáticos e dinâmicos altamente não lineares. Na análise estática foram implementados o método de Newton-Raphson e controle de deslocamentos generalizado, para problemas dinâmicos foram implementados o método -generalizado (G) e o método energia momento generalizado (GEMM+). A análise aerodinâmica é realizada via análise por Elementos Finitos para modelar escoamentos compressíveis viscosos e não viscosos em regimes transônicos e supersônicos. Um esquema característico baseado na separação da equação de momento (CBS, acrônimo do inglês) é utilizado para obter uma adequada integração temporal. No que concerne à otimização matemática, é utilizado um método baseado em gradientes, conhecido por programação quadrática sequencial (SQP, acrônimo do inglês), onde a avaliação as derivadas de Fréchet são levadas a cabo via diferenciação automática (AD, acrônimo do inglês). No que concerne aos resultados finais é realizada a otimização estrutural de forma de cascas modeladas como sólidos são apresentados, evidenciando um desempenho ótimo com respeito à energia de deformação interna. Os resultados de otimização aerodinâmica bidimensionais apresentam perfis aerodinâmicos ótimos com respeito à relação arrasto/sustentação para uma ampla gama de número de Mach, enquanto um resultado tridimensional é apresentado evidenciando a robustez e eficiência da implementação proposta. Pretendese estabelecer com este trabalho as bases para pesquisas em problemas de otimização aeroelástica. / Consolidation of the link among optimization problems in continuum mechanics, involving different fields, such as mathematical optimization, automatic differentiation, structural analysis, aerodynamic analysis, curves, surfaces and solids parameterization using Non Uniform Rational B-spline (NURBS), IsoGeometric Analysis (IGA), Finite Element Analysis (FEA) is looked for. Structural shape optimization of shell structures and aerodynamic shape optimization of immersed bodies in compressible flows are the main goals of this work. Concerning structural analysis, the so-called IsoGeometric analysis is employed. An accurate and comprehensive corotational kinematic based on the exact polar decomposition is developed in order to study highly nonlinear static and dynamic problems. Static analysis is carried out with Newton-Raphson and Generalized Displacement Control Method, while dynamic analysis is carried out with Generalized- (G) and Generalized Energy-Momentum Method (GEMM+). Aerodynamic analysis is carried out via Finite Element Analysis (FEA) in order to solve compressible flows in transonic and supersonic regimes. A Characteristic Based Split (CBS) method is employed to obtain an accurate time integration, which is based on the splitting of the momentum equation. Concerning mathematical optimization, the so-called Sequential Quadratic Programming (SQP) is employed, which is a gradient-based method, where the Fréchet derivatives are evaluated using Automatic Differentiation (AD). Final results consisting in structural optimization shown an optimal behaviour with respect to internal strain energy. While, results concerning aerodynamic bi-dimensional shape optimization exhibit a optimal behaviour with respect drag/lift ratio, for a large range of Mach number, and a simple result for tri-dimensional case is presented in order to show the efficiency and robustness of the implementation. Bases for future research in aeroelastic optimization problems are established in this work.

As lesões cervicais não cariosas foram, durante muito tempo, atribuídas à abrasão causada pela escovação dental, e/ou por processos erosivos. Teorias biomecânicas consideram a possibilidade de que concentrações de tensões na região cervical, causadas pela flexão de cúspides, poderiam contribuir, associadas a outros fatores clínicos, para o desenvolvimento dessas lesões chamadas de abfração O presente trabalho pretende através do método de elementos finitos, utilizando o programa ANSYS versão 8.1, analisar a distribuição de tensões na região cervical de modelos bidimensionais parametrizados dos primeiros prémolares superior e inferior quando estes são colocados em contatos cêntrico e excêntricos no plano frontal, sob uma carga de 1 N. Para simulação da diminuição da mobilidade do ligamento periodontal sob cargas de impacto, o valor real do seu módulo de elasticidade foi aumentado para o correspondente ao do osso esponjoso e ao do osso cortical. Os resultados permitiram concluir que, de uma maneira geral, nas posições excêntricas, os dentes se flexionam e tensões de tração ocorrem na região cervical oposta ao contato com valores compatíveis para formação das lesões. Na posição cêntrica, as tensões de tração se manifestam mais na região da fossa central de ambos os dentes e na cervical do pré-molar inferior. A simulação da diminuição da mobilidade dentaria sob cargas de impacto reduziu o valor das tensões de tração, em todas as regiões analisadas, na ordem de 33% para o pré-molar superior e 66% para o inferior, mas não alterou seu padrão de distribuição. / Non carious cervical lesions were often attributed to toothbrush abrasion and/or erosive process. Biomechanical theories consider that stress concentration in the cervical area, caused by cuspal flexure, may contribue, associated to other clinical factors for the development of the lesion called abfraction. The aim of this finite element study, using the ANSYS version 8.1, is to analyze the stress distribution in the cervical region of superior and inferior premolars bidimensional models. Contacts in centric and eccentric positions were reproduced under a 1 N load. To simulate tooth mobility reduction under impact loads, the elastic modulus of the periodontal ligament was increased to reach the corresponding ones of the alveolar and cortical bone. The results showed that, in eccentric positions, teeth bend and tensile stress are generated at the cervical region opposed to the contact side, justifying the possibility to initiation of the lesion. In centric position, tensile stress occurred on both teeth at the central fossae and at the buccal cervical area of the inferior premolar. The simulation of tooth mobility reduction under impact loads diminished the tensile stress value, at all of the analyzed positions, in a rate of 33% and 66% respectively to superior and inferior premolars.