In Computer Graphics, in the context of shape modeling on a computer, a common characteristic of popular techniques is the possibility for the artist to operate on a shape by modifying directly the shape�s mathematical description. But with the constant increase of computing power, it has become increasingly realistic and effective to insert interfaces between the artist and the mathematics describing the shape. While in the future, shape descriptions are likely to be replaced with new ones, this should not affect the development of new and existing shape interfaces. Space deformation is a family of techniques that permits describing an interface independently from the description. Our thesis is that while space deformation techniques are used for solving a wide range of problems in Computer Graphics, they are missing a framework for the specific task of interactive shape modeling. We propose such a framework called sweepers, together with a set of related techniques for shape modeling. In sweepers, we define simultaneous-tools deformation, volume-preserving deformation, topology-changing deformation and animated deformation. Our swept-fluid technique introduces the idea that a deformation can be described as a fluid. In fact, the sweepers framework is not restrained to shape modeling and is also used to define a new fluid animation technique. Since the motion of a fluid can be considered locally as rigid, we define a formalism for handling conveniently rigid transformations. To display shapes, we propose a mesh update algorithm, a point-based shape description and a discrete implicit surface, and we have performed preliminary tests with inverse-raytracing. Finally, our technique called spherical-springs can be used to attach a texture to our shapes.

Fluid flows occurring in moving and/or deforming environments are influenced by the transient nature of their containment. In Computational Fluid Dynamics (CFD), simulating such flow fields requires effort to maintain the geometric integrity of the transient flow domain. Convective fluxes in such domains are evaluated with respect to the motion of the boundaries of the control volume. These simulations demand conservation of space in addition to the conservation of mass, momentum and energy as the solution continues in time. The Space Conservation Law in its continuous form can be inferred by using the rules of fundamental calculus. However, implementing it in a discrete form poses substantial challenges. During mesh motion, the surfaces enclosing the control volumes sweep through three-dimensional space. As per the Space Conservation Law, the change in the control volume has to match the sum of the swept volumes of all its faces exactly. The Space Conservation Law must be satisfied accurately and consistently in order to avoid the occurrence of non-physical masses and to prevent the violation of the continuity equation. In this work we have attempted to address the consistency issues surrounding the implementation of the Space Conservation Law in OpenFOAM. The existing method for calculation of swept volumes falls short in terms of consistency. Moreover, its capabilities are limited when it comes to complex three-dimensional mesh motions. The existing method of calculation treats swept volumes as net fluxes emanating from cell faces. We have implemented an alternate algorithm in which the swept volumes are treated as intermittent virtual cells whose volumes can be calculated in a unique and consistent manner. We will conclude by validating our approach for mesh motions of varying degrees of complexity.

Final publication is available at http://www.sciencedirect.com/science/article/pii/S0002939414000488 / 京都大学 / 0048 / 新制・課程博士 / 博士(医学) / 甲第19586号 / 医博第4093号 / 新制||医||1014(附属図書館) / 32622 / 京都大学大学院医学研究科医学専攻 / (主査)教授 大森 孝一, 教授 宮本 享, 教授 横出 正之 / 学位規則第4条第1項該当 / Doctor of Medical Science / Kyoto University / DFAM

京都大学 / 0048 / 新制・課程博士 / 博士(医学) / 甲第20271号 / 医博第4230号 / 新制||医||1021(附属図書館) / 京都大学大学院医学研究科医学専攻 / (主査)教授 木村 剛, 教授 富樫 かおり, 教授 高橋 淳 / 学位規則第4条第1項該当 / Doctor of Medical Science / Kyoto University / DFAM

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Low aspect ratio, highly-swept cranked arrow wing planforms are often proposed for high-speed civil transports. These wing planforms offer low supersonic drag without suffering greatly from low lift/drag ratios in low-speed flight. They can, however, suffer from pitch-up at modest angles of attack (as low as 5°) during low-speed flight due to leading edge vortex influence, flow separation and vortex breakdown. The work presented here describes an investigation conducted to study past research on the longitudinal aerodynamic characteristics of highly-swept cranked wing planforms, the development of a new method to estimate pitch-up of these configurations, and the applications of this new method to the analysis of tail designs for trim at high lift coefficients. The survey of past research placed emphasis on 1) understanding the problem of pitch-up, 2) ascertaining the effects of leading and trailing edge flaps, and 3) determining the benefits and shortfalls of tail, tailless, and canard configurations. The estimation method used a vortex lattice method to calculate the inviscid flow solution. Then, the results were adjusted to account for flow separation on the outboard wing section by imposing a limit on the equivalent 2-D sectional lift coefficient. The new method offered a means of making low cost estimates of the nonlinear pitching moment characteristics of slender, cranked arrow wing configurations with increased accuracy compared to conventional linear methods. Numerous comparisons with data are included. The new method was applied to analyze the trim requirement of slender wing designs generated by an aircraft configuration optimization and design program. The effects of trailing edge flaps and horizontal tail on the trimmed lift coefficient was demonstrated. Finally, recommendations were made to the application of this new method to multidisciplinary design optimization methods. / Master of Science

Thesis / Master of Science (MS)

No / Surface blending with tangential continuity is most widely applied in computer-aided design, manufacturing systems, and geometric modeling. In this paper, we propose a new blending method to effectively control the shape of blending surfaces, which can also satisfy the blending constraints of tangent continuity exactly. This new blending method is based on the concept of swept surfaces controlled by a vector-valued fourth order ordinary differential equation (ODE). It creates blending surfaces by sweeping a generator along two trimlines and making the generator exactly satisfy the tangential constraints at the trimlines. The shape of blending surfaces is controlled by manipulating the generator with the solution to a vector-valued fourth order ODE. This new blending methods have the following advantages: (1) exact satisfaction of C1C1 continuous blending boundary constraints, (2) effective shape control of blending surfaces, (3) high computing efficiency due to explicit mathematical representation of blending surfaces, and (4) ability to blend multiple (more than two) primary surfaces.

Many futuristic aircraft such as the Hybrid Wing Body have numerous control surfaces that can result in large hinge moments, high actuation power demands, and large actuator forces/moments. Also, there is no unique relationship between control inputs and the aircraft response. Distinct sets of control surface deflections may result in the same aircraft response, but with large differences in actuation power. An Artificial Neural Network and a Genetic Algorithm were used here for the control allocation optimization problem of a Hybrid Wing Body to minimize the Sum of Absolute Values of Hinge Moments for a 2.5-G pull-up maneuver. To test the versatility of the same optimization process for different aircraft configurations, the present work also investigates its application on the Forward Swept Wing aircraft. A method to improve the robustness of the process is also presented. Constraints on the load factor and longitudinal pitch rate were added to the optimization to preserve the trim constraints on the control deflections. Another method was developed using stability derivatives. This new method provided better results, and the computational time was reduced by two orders of magnitude. A hybrid scheme combining both methods was also developed to provide a real-time estimate of the optimum control deflection schedules to trim the airplane and minimize the actuation power for changing flight conditions (Mach number, altitude and load factor) in a pull-up maneuver. Finally, the stability derivatives method and the hybrid scheme were applied for an antisymmetric, steady roll maneuver. / Master of Science

Laser-based photo-thermal therapies can provide minimally-invasive treatment of cancers. Their effectiveness is limited by light penetration depth in tissue due to its highly scattering properties. The highly disordered refractive index distribution in tissue leads to multiple-scattering of incident light. It has been hypothesized that mechanical compression has a great potential to enhance the capabilities of laser therapy by inducing localized water transport, decreasing the refractive index mismatch, and decreasing the scattering coefficient of tissue. To better understand this process, we investigated the refractive index change of ex-vivo dog skin during mechanical compression using a swept-source optical coherence tomography (OCT) device built in our lab. The Lorentz-Lorenz rule of mixtures was applied to evaluate the water and protein weight fraction of tissue simultaneously. Results show that the refractive index of skin increased from 1.38 to 1.52 during compression and water content decreased about 60%-70% when the skin sample was compressed by 70%. In addition, we conducted compression experiments on human finger, palm, back of hand, and front of forearm in vivo. OCT images of these skin sites before and after compression by 1 minute were compared. Optical thickness of epidermis and light penetration depth in the dermis were measured. The extended Huygens-Fresnel model was applied to measure the scattering coefficient μs of skin specimens. μs of skin was measured to be about 10-17 mm-1 before compression and decreased 60%-80% after compression, which increases the averaged light intensity by 2-7 dB and almost doubles light penetration depth in dermis. It is quite significant in laser therapies especially for treating epithelia cancers which originate at 1-2 mm beneath the tissue surface. In the OCT imaging of skin dehydration experiment, we conclude that dehydration is an important mechanism of mechanical clearing. / Master of Science