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Till följ av de stora skadorna som riskeras vid frontalkollision mellan personbil och lastbil, utför Scania CV AB kraschtester för att bättre kunna utveckla komponenter med syfte att skydda passagerarna i personbilen. Den typ av test som denna studie bygger på utvärderar den s.k. FUP:en (engelska Front Underrun Protection). I dagsläget görs ett fullskaligt test, där en personbil avfyras in i en lastbil. Syftet med studien är att undersöka möjligheten att utveckla en förenklad test metod där endast de väsentliga komponenterna från lastbilen inkluderas, och en representativ struktur ersätter personbilen. Om möjligt kommer detta minska kostnaderna samt möjliggöra för större repeterbarhet. Tester och utvärderingar görs med hjälp av simulationer i LS-Dyna, ANSA & META, och designkoncept visualiseras i CAD-programmet CATIA V5. Resultat visar att det finns goda förutsättningar för att ersätta personbilen med en barriär av honeycomb struktur samt att lastbilen kan ersättas med en vagn där de väsentliga komponenterna fäst. Diskussioner kring simuleringarna och designen lyfter fram faktorer som visar på goda utvecklingsmöjligheter, men med betoning på det fortsatta arbetet som krävs. / Scania CV AB are developing components to prevent fatal damages during frontal collisions with passenger cars. Therefore, they need to test their assemblies and specifically FUP (Frontal Underrun Protection). Currently, a full-scale test is done in which a passenger car is launched into a truck. The purpose of this study is to examine and develop the possibility of having a simplified test procedure in which only the relevant components of the truck are included, and a representative structure replaces the car. If possible, this would reduce costs and allow for greater repeatability. Analysis and evaluations are done via finite element models using ANSA, LS-Dyna and META. The conceptual design is visualized using CATIA V5. Results show good indication that the passenger car can be replaced by a trolley with deformable barriers mounted on it and the truck can be replaced by a simplified structure with main FUP components mounted onto it. Discussions about the numerical models results and the conceptual design highlight factors that show promising possibilities, but with emphasis on the continued work that is required.

We study Schrödinger operators perturbed by non-compact (spatially extended) defects. We consider two models: a one-dimensional (1D) dimer structure with a global phase shift, and a two-dimensional (2D) honeycomb structure with a line-defect or "edge''. In both the 1D and 2D settings, the non-compact defects are modeled by adiabatic, domain wall modulations of the respective dimer and honeycomb structures. Our main results relate to the rigorous construction of states via bifurcations from continuous spectra. These bifurcations are controlled by asymptotic effective (homogenized) equations that underlie the protected or non-protected character of the states. In 1D, the states we construct are localized solutions. In 2D, they are "edge states'' - time-harmonic solutions which are propagating (plane-wave-like) parallel to a line-defect or "edge'' and are localized transverse to it. The states are described as protected if they persist in the presence of spatially localized (even strong) deformations of the global phase defect (in 1D) or edge (in 2D). The protected states bifurcate from "Dirac points'' (linear/conical spectral band-crossings) in the continuous spectra and are seeded by an effective Dirac equation. The (more conventional) non-protected states bifurcate from spectral band edges are seeded by an effective Schrödinger equation. Our 2D model captures many aspects of the phenomenon of topologically protected edge states observed in honeycomb structures such as graphene and "artificial graphene''. The protected states we construct in our 1D dimer model can be realized as highly robust TM- electromagnetic modes for a class of photonic waveguides with a phase-defect. We present a detailed computational study of an experimentally realizable photonic waveguide array structure.

This study was to investigate the effect on conversion, deactivation of long-term, selectivity of product, and kinetics in deep oxidation of toluene over copper catalyst. The copper catalyst is supported on honeycomb of ceramic monolith (400 cell/inch2). The operation parameters in heterogeneous reactor were performed as follows: 1000 ppm initial concentration of toluene, temperature of reaction in ranging from 200 ¢J to 400 ¢J, 15 % of oxygen concentration, and 4000 hr-1 of space velocity. In the selection of catalyst, we decided to use 20% Cu catalyst for its high conversion, high selectivity and low cost in oxidation of toluene. The conversion of toluene in catalytic reaction was increased with the increasing both of reaction temperature and influent concentration of oxygen, and decreased with the going up of initial concentration of toluene and of space velocity. In the catalyst stability of long-term test, Cu catalysts had a good stability after 7 days reaction in heterogeneous reactor. The tests such as BET, SEM and EA were also determined to verify the stability from surface of catalyst. The kinetics of heterogeneous reactor over Cu catalyst supported on ceramic honeycomb in oxidation of toluene was found that a pseudo-first order could be described by both Power-rate law and Mars-Van Krevelen model. The apparent reaction order and activated energy were obtained in this work.

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Thesis (M.S.)--University of Missouri-Columbia, 2007. / The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on April 9, 2009) Includes bibliographical references.

Dissertação (mestrado)—Universidade de Brasília, Faculdade de Tecnologia, Departamento de Engenharia Mecânica, 2017. / Submitted by Raquel Almeida (raquel.df13@gmail.com) on 2017-11-09T17:41:15Z No. of bitstreams: 1 2017_KleversonCarvalhodeSousa.pdf: 3285494 bytes, checksum: 0105d6bd92044b93ecc218a5708b051c (MD5) / Approved for entry into archive by Raquel Viana (raquelviana@bce.unb.br) on 2018-01-04T22:26:09Z (GMT) No. of bitstreams: 1 2017_KleversonCarvalhodeSousa.pdf: 3285494 bytes, checksum: 0105d6bd92044b93ecc218a5708b051c (MD5) / Made available in DSpace on 2018-01-04T22:26:09Z (GMT). No. of bitstreams: 1 2017_KleversonCarvalhodeSousa.pdf: 3285494 bytes, checksum: 0105d6bd92044b93ecc218a5708b051c (MD5) Previous issue date: 2018-01-04 / A hipótese de estruturas periódicas é muito usada em várias aplicações em engenharia, indo de plataformas de petróleo a projetos aeroespaciais. Tais estruturas podem ter seu comportamento vibroacústico interpretado através de suas propriedades de propagação de ondas, como uma alternativa à interpretação modal, fornecendo diferentes informações para análise e projeto. Este trabalho apresenta a modelagem e caracterização do comportamento dinâmico de um painel sandwiche honeycomb, de utilização aeroespacial, através do método de ondas e elementos finitos (Wave and Finite Elements - WFE). Um modelo de elementos finitos é proposto, assumindo-se propriedades homogeneizadas do núcleo honeycomb, e seus parâmetros são ajustados através de dados experimentais de um ensaio de análise modal, via vibrômetro laser doppler (LDV). A partir desse modelo, assumindo-se periodicidade em direções ortogonais, utiliza-se uma fatia da seção transversal do painel com apenas uma fração da quantidade de elementos necessária no modelo completo de elementos finitos. A partir do pós-processamento das matrizes de massa e rigidez, obtidas a partir de um pacote comercial, as curvas de dispersão são obtidas para frequências entre 1 Hz e 10 kHz, e os parâmetros de número de onda, velocidade de fase e modos de onda são analisados e seu comportamento físico é discutido. Os resultados experimentais obtidos são também discutidos a partir da análise de frequência espacial, via FFT2D, das formas de deflexão operacional, e ótima concordância é obtida. / The assumption of periodic structures is widely used in engineering applications, such as oil platforms and aerospace design. Such structures can have their vibroacustic behaviour interpreted by their wave characteristics, as an alternative to the model interpretation, providing extra information for analysis and design. This work presents the modelling and characterization of the dynamic behaviour of a honeycomb sandwich panel, for aerospace applications, through the wave and finite element (WFE) method. A full finite element model is proposed, assuming homogenized properties of the honeycomb core, and its parameters are fit by a modal analysis, using a laser doppler vibrometer (LDV). Then, assuming periodicity on orthogonal directions, a slice of the transversal section of the panel is used with only a fraction of the number of elements needed for the full finite element analysis. From the post-processing of the mass and stiffness matrices, obtained from a commercial software, the dispersion curves and obtained for frequencies from 1 Hz to 10 kHz. The wavenumbers, phase and group velocities are then analysed and their physical behaviour is discussed. The spacial frequency of the experimental results are also discussed, via FFT2D approach, from the operational deflection shapes, and good agreement is found.

Honeycomb-cored sandwich structures are widely used in transport for their high strength-to-mass ratio. Their inherent high stiffness and lightweight properties make them prone to high vibration cycles which can incur deleterious damage to transport vehicles. This PhD thesis investigates the performance of a novel passive damping treatment for honeycomb-cored sandwich structures, namely the Double Shear Lap-Joint (DSLJ) damper. It consists of a passive damping construct which constrains a viscoelastic polymer in shear, thus dissipating vibrational energy. A finite element model of such DSLJ damper inserted in the void of a hexagonal honeycomb cell is proposed and compared against a simplified analytical model. The damping efficiency of the DSLJ damper in sandwich beams and plates is benchmarked against that of the Constrained Layer Damper (CLD), a commonly used passive damping treatment. The DSLJ damper is capable of achieving a higher damping for a smaller additional mass in the host structure compared to the optimised CLD solutions found in the literature. The location and orientation of DSLJ inserts in honeycomb sandwich plates are then optimised with the objective of damping the first two modes using a simple parametric approach. This method is simple and quick but is not robust enough to account for mode veering occurring during the optimisation process. A more complex and computationally demanding evolutionary algorithm is subsequently adopted to identify optimal configurations of DSLJ in honeycomb sandwich plates. Some alterations to the original algorithm are successfully implemented for this optimisation problem in an effort to increase the convergence rate of the optimisation process. The optimised designs identified are manufactured and the modal tests carried out show an acceptable correlation in the trends identified by the numerical simulations, both in terms of damping per added mass and natural frequencies.

SAFRAN Aircelle produit des panneaux sandwiches constitués de peaux composites collées sur une âme nid d’abeille (« Nida ») en aluminium pour des applications de nacelle de moteur d’avion. Des décollements locaux peuvent exister à l’interface peau/Nida et réduire significativement la capacité structurale de ces sandwiches. L’objectif de cette thèse entre l’ISMANS et SAFRAN Aircelle réside dans la mise en place d’une approche de type « Virtual testing » pour réduire les coûts de validation et de vérification des sandwiches possédant des décollements.L’originalité de ces travaux vient du choix de la représentation des sandwiches à travers deux familles de modèles : les modèles « âme pleine » (modélisation volumique) prévus pour une utilisation en bureau d’études et les modèles « âme creuse » (modélisation physique des clinquants) permettant d’analyser finement les mécanismes de propagation des décollements peau/Nida. Une technique de sous-structuration a été mise en oeuvre avec succès et a permis de réduire significativement les temps de calcul du modèle « âme creuse ».La mécanique de l’endommagement, avec des éléments à zone cohésive, a été choisie pour déterminer numériquement le seuil de propagation des décollements, après une étude comparative avec la mécanique linéaire élastique de la rupture et une méthode de recalage essais. Pour alimenter les lois d’endommagement disponibles dans les codes industriels, une méthode expérimentale a été proposée. Des essais de type DCB sandwiches ont permis de remonter aux propriétés mécaniques de l’interface en mode d’ouverture et en mode mixte, avec un seul montage. Ces essais ont été recalés avec succès, notamment en mode I pur. / SAFRAN Aircelle manufactures sandwich structures made of composite skins bonded to aluminium honeycomb core for aircraft’s engines nacelles applications. Local disbonds may occur at the skins/core interface and lead to significant strength reduction under in-service loadings. The present work was done with ISMANS and SAFRAN Aircelle and deals with the introduction of a “Virtual Testing” approach in order to reduce substantiation and validation cost of sandwiches structures with embedded disbond.In this study we have two kinds of models at two scales to describe the sandwich behaviour: the “homogeneized” model, which provide an industrial tool for design offices and the “detailed” model, which provide a specific tool for accurate analysis of disbond growth initiation at skin/core interface. Due to the numerical cost of the second type of model, the superelement technique has been successfully used which permits to gain computational costs without altering the result quality.Damage mechanics, with cohesive zone elements, have been chosen to numerically determine the disbond growth threshold after a comparative study with linear fracture mechanics and a full experimental method. Inputs data for industrial code using cohesive zone elements have been studied through an experimental investigation. DCB type tests on reinforced sandwiches were perfomed in order to determine the energy release rate at the skin/core interface. Various mode-mixity and pure opening mode are available using the same testing tool. The latter has been successfully modelled.