FLUID STRUCTURE INTERACTION AND ADMITTANCE BOUNDARY CONDITIONS: SETUP OF AN ANALYTICAL EXAMPLE

2011 ◽  
Vol 19 (01) ◽  
pp. 63-74 ◽  
Author(s):  
STEFFEN MARBURG ◽  
ROBERT ANDERSSOHN

Often, acoustic simulation techniques suffer from errors of the computational model and its parameters. Quantification of the boundary condition is a crucial point for simulations. In particular, the boundary admittance is often unknown and hard to quantify. This article demonstrates how to reduce a fluid-structure interaction model to a pure fluid model with local or nonlocal admittance boundary conditions. Starting point is a BEM formulation for the fluid and a FEM formulation for the structure. An admittance matrix is derived from this formulation. Then, the multidimensional BEM–FEM formulation is adjusted to a one-dimensional example, a duct with structural elements at both ends. Two configurations are investigated, one with local admittance boundary conditions and one with nonlocal admittance boundary conditions which result in a diagonal and in a fully populated admittance matrix, respectively.

Author(s):  
Mohd Azrul Hisham Mohd Adib ◽  
Nur Hazreen Mohd Hasni

The objectives of this study are to observe the deformation of mitral leaflet in systole condition and compare the rigidity of heart valve leaflet during systole and diastole conditions. Two-dimensional model of the mitral valve leaflet with ventricle were created using fluid structure interaction model in computational simulations. The result shows rigidity of heart valve leaflet always opposite to degeneration and the simulated displacement models corresponded to normal deformation in physical heart valve in systole condition. Modeling simulation techniques are very useful in the study of degenerative heart valve and the findings would allow us to optimize feature and geometries to reduced deformation of heart valve failure.


Author(s):  
Mohammad Khairul Habib Pulok ◽  
Uttam K. Chakravarty

Abstract Rotary-wing aircrafts are the best-suited option in many cases for its vertical take-off and landing capacity, especially in any congested area, where a fixed-wing aircraft cannot perform. Rotor aerodynamic loading is the major reason behind helicopter vibration, therefore, determining the aerodynamic loadings are important. Coupling among aerodynamics and structural dynamics is involved in rotor blade design where the unsteady aerodynamic analysis is also imperative. In this study, a Bo 105 helicopter rotor blade is considered for computational aerodynamic analysis. A fluid-structure interaction model of the rotor blade with surrounding air is considered where the finite element model of the blade is coupled with the computational fluid dynamics model of the surrounding air. Aerodynamic coefficients, velocity profiles, and pressure profiles are analyzed from the fluid-structure interaction model. The resonance frequencies and mode shapes are also obtained by the computational method. A small-scale model of the rotor blade is manufactured, and experimental analysis of similar contemplation is conducted for the validation of the numerical results. Wind tunnel and vibration testing arrangements are used for the experimental validation of the aerodynamic and vibration characteristics by the small-scale rotor blade. The computational results show that the aerodynamic properties of the rotor blade vary with the change of angle of attack and natural frequency changes with mode number.


2018 ◽  
Vol 9 (4) ◽  
pp. 739-751 ◽  
Author(s):  
Anna Maria Tango ◽  
Jacob Salmonsmith ◽  
Andrea Ducci ◽  
Gaetano Burriesci

2018 ◽  
Vol 21 (16) ◽  
pp. 813-823 ◽  
Author(s):  
John T. Wilson ◽  
Lowell T. Edgar ◽  
Saurabh Prabhakar ◽  
Marc Horner ◽  
Raoul van Loon ◽  
...  

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