Thesis (MSc)--University of Stellenbosch, 2007. / Bibliography. Also available via the Internet.

Este trabalho apresenta um estudo sobre métodos utilizados para realizar metamorfose entre imagens digitais. Segundo esses métodos é possível estabelecer uma imagem fonte, uma destino e, através de operações de mapeamento de texturas, realizar uma seqüência de imagens intermediárias. Essas imagens intermediárias apresentam-se como deformações sobre a imagem fonte ou como etapas de transição entre as imagens originais, efeito produzido pela inserção de um processo de fusão de imagens. O processo de deformação varia segundo o método empregado e influencia diretamente nos resultados por ele gerado. Assim, dois métodos com características diferentes para deformação de imagens foram escolhidos, dentre os encontrados, para um estudo mais aprofundado e são referenciados como o Método das Malhas e o Método dos Campos de Influência. Esses métodos são apresentados, seus funcionamentos discutidos e resultados gerados para se estabelecer uma análise entre os mesmos. A análise é efetuada segundo os aspectos de tempo de processamento, consumo de minoria e atribuição de correspondências entre as imagens, sendo que esta última característica leva em consideração o tempo total gasto para se estabelecer as correspondências necessárias entre a imagem fonte e a destino. Neste ponto também é estabelecido um quadro comparativo entre os métodos escolhidos, destacando-se vantagens e desvantagens. Os resultados da aplicação dos métodos analisados encontram-se distribuídos ao longo do texto sob a forma de imagens e tabelas, são utilizados para provar a eficiência desses métodos e foram gerados por um sistema de testes implementado. O sistema de testes desenvolvido possibilita a geração de imagens, segundo o método escolhido, informa os tempos utilizados no processamento e exibe essas imagens seqüencialmente sob a forma de uma animação. Por fim o trabalho apresenta conclusões sobre o estudo, salientando aspectos considerados relevantes quando do estudo e implementação dos métodos, e indica futuras extensões que podem ser efetuadas a fim de tornar o sistema de testes mais flexível e completo. / This work presents a study on methods used to make digital images metamorphosis. According to these methods it is possible to establish a source image, a destination image and also to generate a sequence of intermediate images through operations of texture mapping. These intermediate images appears as deformations of the source image or as transition steps between the original images which are produced by the insertion of a cross-dissolve process. The warping process varies according to the method which is used and it influences directly its results. Thus, two methods for image warping with different characteristics were chosen, among the available ones, for a more detailed study and are refered as the Mesh Method and as the Fields of Influence Method. These two methods are presented, their functioning is discussed and results are generated to allow comparative analyses. The analysis concerns aspects of processing time, memory allocation and correspondence establishment, which take into account the time waisted in order to establish the correspondences between the images. At this point it is also established a comparative table between the chosen methods highlighting advantages and disadvantages. The results of the application of the analysed methods are distributed throughout the text as images and tables, which are used to prove the efficiency of them and were generated by a test system implemented. The system developed provides the generation of images, according to the choosen method, informs the time waisted on processing and shows those images sequentially as an animation. Finally this work presents conclusions about the study and indicates future extensions that can be done in order to make the developed system more flexible and complete.

Este trabalho apresenta um estudo sobre métodos utilizados para realizar metamorfose entre imagens digitais. Segundo esses métodos é possível estabelecer uma imagem fonte, uma destino e, através de operações de mapeamento de texturas, realizar uma seqüência de imagens intermediárias. Essas imagens intermediárias apresentam-se como deformações sobre a imagem fonte ou como etapas de transição entre as imagens originais, efeito produzido pela inserção de um processo de fusão de imagens. O processo de deformação varia segundo o método empregado e influencia diretamente nos resultados por ele gerado. Assim, dois métodos com características diferentes para deformação de imagens foram escolhidos, dentre os encontrados, para um estudo mais aprofundado e são referenciados como o Método das Malhas e o Método dos Campos de Influência. Esses métodos são apresentados, seus funcionamentos discutidos e resultados gerados para se estabelecer uma análise entre os mesmos. A análise é efetuada segundo os aspectos de tempo de processamento, consumo de minoria e atribuição de correspondências entre as imagens, sendo que esta última característica leva em consideração o tempo total gasto para se estabelecer as correspondências necessárias entre a imagem fonte e a destino. Neste ponto também é estabelecido um quadro comparativo entre os métodos escolhidos, destacando-se vantagens e desvantagens. Os resultados da aplicação dos métodos analisados encontram-se distribuídos ao longo do texto sob a forma de imagens e tabelas, são utilizados para provar a eficiência desses métodos e foram gerados por um sistema de testes implementado. O sistema de testes desenvolvido possibilita a geração de imagens, segundo o método escolhido, informa os tempos utilizados no processamento e exibe essas imagens seqüencialmente sob a forma de uma animação. Por fim o trabalho apresenta conclusões sobre o estudo, salientando aspectos considerados relevantes quando do estudo e implementação dos métodos, e indica futuras extensões que podem ser efetuadas a fim de tornar o sistema de testes mais flexível e completo. / This work presents a study on methods used to make digital images metamorphosis. According to these methods it is possible to establish a source image, a destination image and also to generate a sequence of intermediate images through operations of texture mapping. These intermediate images appears as deformations of the source image or as transition steps between the original images which are produced by the insertion of a cross-dissolve process. The warping process varies according to the method which is used and it influences directly its results. Thus, two methods for image warping with different characteristics were chosen, among the available ones, for a more detailed study and are refered as the Mesh Method and as the Fields of Influence Method. These two methods are presented, their functioning is discussed and results are generated to allow comparative analyses. The analysis concerns aspects of processing time, memory allocation and correspondence establishment, which take into account the time waisted in order to establish the correspondences between the images. At this point it is also established a comparative table between the chosen methods highlighting advantages and disadvantages. The results of the application of the analysed methods are distributed throughout the text as images and tables, which are used to prove the efficiency of them and were generated by a test system implemented. The system developed provides the generation of images, according to the choosen method, informs the time waisted on processing and shows those images sequentially as an animation. Finally this work presents conclusions about the study and indicates future extensions that can be done in order to make the developed system more flexible and complete.

Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2010. / The Cape Peninsula University of Technology (CPUT) Advanced Manufacturing and Technology Laboratory (AMTL) developed an Unmanned Aerial Vehicle (UAV) Technology Demonstrator for the purpose of testing and maturing adaptronic devices. Extending the flight envelope of this unmanned aerial vehicle by increasing its range and endurance is the next step in its development. A seamless variable angle of incidence (sVAI) morphing wing is proposed to increase the lift with little coupling to drag during takeoff; and decrease the drag with little effect on lift during climb, thus increasing the total flight performance of the aircraft. CAD models of the conceptualized sVAI wing and a conventional (CON) wing, as used on the Technology Demonstrator, were modeled. Numerical analyses on these CAD models showed that the sVAI wing concept at a 4° twist decreased the ground roll distance and stall velocity by ±17% and ±31% respectively, as compared to the CON wing in standard takeoff configuration. This allowed for ± 11.7% less power required for takeoff allowing the aircraft to get to its operational altitude quicker, thus saving fuel and reducing energy losses; and increasing range and endurance. The results also showed that the sVAI wing concept could reduce the drag during climb by ± 14%, but the lift is also proportionately reduced thus having little improvement on the climb phase of flight performance. A prototype of the morphing wing was then conceptualized and designed, using a 3D CADmodeler, and then manufactured. The product development chain produced for this morphing wing included two rapid prototyping machines and reverse engineering technologies. The chain allowed for the rapid manufacturing of light weight and intricate parts. The manufactured wing is then incorporated into a test rig to compare the actual morphing ability of the prototype to the theoretical morphing ability of the CADmodel, and thus make flight performance predictions of the actual vehicle. 3D scans were taken of the prototype and then converted to 3D CADfiles. The geometrical and topographical deformation of the prototype was then compared to that of the CAD model showing an average difference of ±1.2% and ±3% at maximum positive and negative configurations, respectively. This allowed one to make the prediction that the sVAI wing will increase the performance of the Technology Demonstrator.

The classical continuum mechanics, which studies the mechanical behavior of structures based on partial differential equations, shows its deficiencies when it encounters a discontinuity. Peridynamics based on integral equations can simulate fracture but suffers from high computational costs. A hybrid local/nonlocal model combining the advantages of peridynamics with those of classical continuum mechanics can simulate fracture and reduce the computational cost. Under the framework of the hybrid local/nonlocal model, this research developed an approach and computational codes for fracture simulations. First, we developed the computational codes based on the hybrid model with a priori partition of the domain between local and nonlocal models to tackle engineering problems with relevant level of difficulty. Second, we developed a strength-induced approach to enhance the capability of the computational codes because the strength-induced approach can limit the peridynamic model to necessary computational steps at the time level and a relatively small zone at the space level during a simulation. The strength-induced approach also improved the hybrid models by enabling an automatic partition of the domain without manual involvement. At last, a strength-induced computational code was developed based on this research. This dissertation complemented and illustrated numerically some previous work of Cohmas laboratory, in which a new route was introduced toward simulating the whole process of material behaviors including elastic deformation, crack nucleation and propagation until structural failure.

The intent of this thesis is to outline the design, analysis, and characterization of an axially compressed piezocomposite actuator and, in particular, to determine the correlation and accuracy of two models used to predict deflection of an axially compressed piezocomposite bimorph. Restrictions in material properties lead to vehicle inefficiencies caused by the discontinuous geometry of deflected control surfaces in unmanned aircraft systems. This performance disadvantage in discrete control surfaces is caused in part by the sharp edges that are formed when the surface is pivoted. Flow continuity over the body of a vehicle is important in minimizing the effects of drag and, in turn, increasing aerodynamic performance. An efficient alternative to discrete control surface actuation is axially compressed piezocomposite actuation which could potentially improve the efficiency of the vehicle in all environments. Bimorph performance in angular deflection and displacement for the PA16N and MFC-M8528-P1 piezocomposites is analyzed using a Classical Laminate Plate Theory (CLPT) model and an Elastica model. Model accuracy is verified through experimental testing of a PA16N bimorph. CLPT model is shown to be accurate to within .05 mm and Elastica model is shown to be accurate to within .04 mm for axial forces below 30 N. Correlation between the mathematical models is confirmed. Experimental results for the PA16N show that a 30 N compression force applied to the bimorph can increase the maximum displacement by approximately 2.5 times the original displacement.

No description available.

The purpose of this research is to characterize the response of an airfoil with an oscillatory morphing, Macro-fiber composite (MFC) trailing edge. Correlation of the airfoil lift with the oscillatory input is presented. Modal analysis of the test airfoil and apparatus is used to determine the frequency response function. The effects of static MFC inputs on the FRF are presented and compared to the unactuated airfoil. The transfer function is then used to determine the lift component due to cambering and extract the inertial components from oscillating airfoil. Finally, empirical wind tunnel data is modeled and used to simulate the deflection of airfoil surfaces during dynamic testing conditions. This research serves to combine modal analysis, empirical modeling, and aerodynamic testing of MFC driven, oscillating lift to formulate a model of a dynamic, loaded morphing airfoil. / Master of Science

The HECS wing was developed by NASA Langley Research Center and has a nonplanar, hyper-elliptically swept leading and trailing edge as well as spanwise camber. For this wing, the leading and trailing edges are swept back according to a hyper-elliptical equation. The span of the wing is also defined with hyper-elliptical anhedral giving it nonplanar spanwise camber. A single-degree-of-freedom mechanism is developed to provide a means for the wing to continuously change shape from its nonplanar to planar configuration. The mechanism uses a repeating quaternary-binary link configuration to translate motion from one segment to the next. A synthesis of the mechanism is performed, such that with one input to the first segment of the chain, the other wing segments move into their desired positions. Linear aerodynamic theory is applied to the HECS wing configuration at certain morphed positions in order to predict the aerodynamic loads. This work performs a linear static analysis of the mechanism at different morphed positions. A finite element representation of the mechanism as a structure is developed. Using the predicted aerodynamic loads, a structural analysis is performed. The analysis investigates different materials and cross sections of the members to determine a need for redesign due to failure from buckling and bending stress. From the analysis of the mechanism, a design is finalized which lightens the structure as well as increases the strength. These results are beneficial for the next phase of model development of the mechanism. / Master of Science

Morphing aircraft combine both radical and subtle wing shape changes to improve vehicle performance relative to a rigid airframe. An aircraft wind tunnel model with considerable wing-shape freedom can serve as a tool in learning to model, control, and fully exploit the potential of such vehicles. This work describes the design, development, and initial analysis of a wind tunnel model that combines large and small wing shape variations for fundamental research in modeling and control of morphing air vehicles. The vehicle is designed for five primary purposes: quasi-steady aerodynamic modeling of an aircraft with large planform changes, optimization studies in achieving efficient flight configurations, transient aerodynamic modeling of high-rate planform changes, evaluating planform maneuvering as an control effector, and gimbaled flight control simulation of a morphing aircraft. The knowledge gained from the wind tunnel evaluations will be used to develop general stabilization and optimal control strategies that can be applied to other vehicles with large scale planform changes and morphing flight models. After a brief background on the development of the Morphing Aircraft Program, and previous research ventures, the first phase vehicle development is described. The vehicle function, subsystems, and control are all presented in addition to the results of first phase wind tunnel testing. Deficiencies in the phase one design motivated the phase two development which has led to the current vehicle model: MORPHEUS. The evolution towards the MORPHEUS configuration is presented in detail along with an elementary strength analysis. The new embedded control implementation to permit a rate controllable planform is included. A preliminary aerodynamic analysis is presented to contrast MORPHEUS against the phase one design and an industry morphing concept. In particular, it is shown how the redesigned model has enhanced performance characteristics and the additional degrees of freedom enable greater flexibility in optimizing a configuration, especially with respect to trim characteristics. An expansion of traditional analysis techniques is applied to derive a new optimal twist algorithm for the MORPHEUS model at each planform configuration. The analysis concludes with a hybrid continuous modeling method that combines first-order computational aerodynamic modeling with classic stability expressions and DATCOM enhancements. The elementary aerodynamic coefficients are computed over the range of possible planform configurations and combined with the optimal twist results for preliminary trim analysis. This work precedes phase two wind tunnel testing and transient modeling. Future work involves expansion into the five purposes detailed for the MORPHEUS model. / Master of Science