Coronary arterial dynamics computation with medical-image-based time-dependent anatomical models and element-based zero-stress state estimates

Takizawa, Kenji; Torii, Ryo; Takagi, Hirokazu; Tezduyar, Tayfun E.; Xu, Xiao Yun

doi:10.1007/s00466-014-1049-6

Cited by 44 publications

(24 citation statements)

References 51 publications

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“…115,116 The imagebased arterial geometries used in patient-specific arterial FSI computations do not come from the zero-stress state (ZSS) of the artery. A number of methods 20,22,[121][122][123][124][125][126][127][128][129][130] have been proposed for estimating the ZSS required in the computations. Using IGA basis functions in space is now a key part of some of the newest ZSS estimation methods [128][129][130] and related shell analysis.…”

Section: St-igamentioning

confidence: 99%

Space–time Isogeometric flow analysis with built-in Reynolds-equation limit

Kuraishi

Takizawa

Tezduyar

2019

Math. Models Methods Appl. Sci.

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We present a space–time (ST) computational flow analysis method with built-in Reynolds-equation limit. The method enables solution of lubrication fluid dynamics problems with a computational cost comparable to that of the Reynolds-equation model for the comparable solution quality, but with the computational flexibility to go beyond the limitations of the Reynolds-equation model. The key components of the method are the ST Variational Multiscale (ST-VMS) method, ST Isogeometric Analysis (ST-IGA), and the ST Slip Interface (ST-SI) method. The VMS feature of the ST-VMS serves as a numerical stabilization method with a good track record, the moving-mesh feature of the ST framework enables high-resolution flow computation near the moving fluid–solid interfaces, and the higher-order accuracy of the ST framework strengthens both features. The ST-IGA enables more accurate representation of the solid-surface geometries and increased accuracy in the flow solution in general. With the ST-IGA, even with just one quadratic NURBS element across the gap of the lubrication fluid dynamics problem, we reach a solution quality comparable to that of the Reynolds-equation model. The ST-SI enables moving-mesh computation when the spinning solid surface is noncircular. The mesh covering the solid surface spins with it, retaining the high-resolution representation of the flow near the surface, and the SI between the spinning mesh and the rest of the mesh accurately connects the two sides of the solution. We present detailed 2D test computations to show how the method performs compared to the Reynolds-equation model, compared to finite element discretization, at different circumferential and normal mesh refinement levels, when there is an SI in the mesh, and when the no-slip boundary conditions are weakly-enforced.

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Section: St-igamentioning

confidence: 99%

Space–time Isogeometric flow analysis with built-in Reynolds-equation limit

Kuraishi

Takizawa

Tezduyar

2019

Math. Models Methods Appl. Sci.

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“…Examples, with the cited references reporting recent computations, are spacecraft aerodynamics [53], spacecraft parachutes [12,[54][55][56][57][58][59][60], cardiovascular fluid mechanics [4,[60][61][62][63][64][65][66][67], flapping-wing aerodynamics [4,60,64,[68][69][70], wind-turbine aerodynamics [60,64,71,72], and data compression [73].…”

Section: Introductionmentioning

confidence: 99%

Space–time computational analysis of MAV flapping-wing aerodynamics with wing clapping

2015

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Computational analysis of flapping-wing aerodynamics with wing clapping was one of the classes of computations targeted in introducing the space-time (ST) interface-tracking method with topology change (ST-TC). The ST-TC method is a new version of the deforming-spatialdomain/stabilized ST (DSD/SST) method, enhanced with a master-slave system that maintains the connectivity of the "parent" fluid mechanics mesh when there is contact between the moving interfaces. With that enhancement and because of its ST nature, the ST-TC method can deal with an actual contact between solid surfaces in flow problems with moving interfaces. It accomplishes that while still possessing the desirable features of interface-tracking (moving-mesh) methods, such as better resolution of the boundary layers. Earlier versions of the DSD/SST method, with effective mesh update, were already able to handle moving-interface problems when the solid surfaces are in near contact or create near TC. Flapping-wing aerodynamics of an actual locust, with the forewings and hindwings crossing each other very close and creating near TC, is an example of successfully computed problems. Flapping-wing aerodynamics of a micro aerial vehicle (MAV) with the wings of an actual locust is another example. Here we show how the ST-TC method enables 3D computational analysis of flapping-wing aerodynamics of an MAV with wing clapping. In the analysis,

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“…In the first 8 years of that period the ST computations were for FSI of abdominal aorta [30], carotid artery [30] and cerebral aneurysms [31][32][33][34][35][36][37]. In the last 7 years, the ST computations focused on even more challenging aspects of cardiovascular fluid mechanics and FSI, including comparative studies of cerebral aneurysms [38,39], stent treatment of cerebral aneurysms [40][41][42][43][44], heart valve flow computation [45][46][47][48][49][50], aorta flow analysis [50][51][52][53], and coronary arterial dynamics [54]. The computational challenges encountered were addressed by the advances in the core methods for moving boundaries and interfaces (MBI) and FSI (see, for example, [20,21,39,45,46,48,49,[55][56][57][58][59][60][61][62][63] and references therein) and in the special methods targeting cardiovascular MBI and FSI (see, for example,…”

Section: Introductionmentioning

confidence: 99%

“…Test computations with the method were also presented in [67] for straight-tube configurations with single and three layers, and for a curved-tube configuration with single layer. The method was used also in [54] in coronary arterial dynamics computations with medical-image-based time-dependent anatomical models.…”

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confidence: 99%

Medical-image-based aorta modeling with zero-stress-state estimation

2019

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Because the medical-image-based geometries used in patient-specific arterial fluid-structure interaction computations do not come from the zero-stress state (ZSS) of the artery, we need to estimate the ZSS required in the computations. The task becomes even more challenging for arteries with complex geometries, such as the aorta. In a method we introduced earlier the estimate is based on T-spline discretization of the arterial wall and is in the form of integration-point-based ZSS (IPBZSS). The T-spline discretization enables dealing with complex arterial geometries, such as an aorta model with branches, while retaining the desirable features of isogeometric discretization. With higher-order basis functions of the isogeometric discretization, we may be able to achieve a similar level of accuracy as with the linear basis functions, but using larger-size and fewer elements. In addition, the higher-order basis functions allow representation of more complex shapes within an element. The IPBZSS is a convenient representation of the ZSS because with isogeometric discretization, especially with T-spline discretization, specifying conditions at integration points is more straightforward than imposing conditions on control points. The method has two main components. 1. An iteration technique, which starts with a calculated ZSS initial guess, is used for computing the IPBZSS such that when a given pressure load is applied, the medical-image-based target shape is matched. 2. A design procedure, which is based on the Kirchhoff-Love shell model of the artery, is used for calculating the ZSS initial guess. Here we increase the scope and robustness of the method by introducing a new design procedure for the ZSS initial guess. The new design procedure has two features. (a) An IPB shell-like coordinate system, which increases the scope of the design to general parametrization in the computational space. (b) Analytical solution of the force equilibrium in the normal direction, based on the Kirchhoff-Love shell model, which places proper constraints on the design parameters. This increases the estimation accuracy, which in turn increases the robustness of the iterations and the convergence speed. To show how the new design procedure for the ZSS initial guess performs, we first present 3D test computations with a straight tube and a Y-shaped tube. Then we present a 3D computation where the target geometry is coming from medical image of a human aorta, and we include the branches in the model.

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Coronary arterial dynamics computation with medical-image-based time-dependent anatomical models and element-based zero-stress state estimates

Cited by 44 publications

References 51 publications

Space–time Isogeometric flow analysis with built-in Reynolds-equation limit

Space–time Isogeometric flow analysis with built-in Reynolds-equation limit

Space–time computational analysis of MAV flapping-wing aerodynamics with wing clapping

Medical-image-based aorta modeling with zero-stress-state estimation

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