scholarly journals Simulation Analysis of Fluid-Structure Interaction of High Velocity Environment Influence on Aircraft Wing Materials under Different Mach Numbers

Sensors ◽  
2018 ◽  
Vol 18 (4) ◽  
pp. 1248
Author(s):  
Lijun Zhang ◽  
Changyan Sun
Keyword(s):  
High Velocity ◽  
Simulation Analysis ◽  
Fluid Structure Interaction ◽  
Aircraft Wing ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Mach Numbers ◽  
Environment Influence

A Parametric Modeling Approach for Prediction of Load Distribution due to Fluid Structure Interaction on Aircraft Structures

2019 ◽  
Author(s):  
Ahmet Barutcu ◽  
Recep M. Gorguluarslan
Keyword(s):  
Load Distribution ◽  
Fluid Structure Interaction ◽  
Parametric Modeling ◽  
Generation Process ◽  
Aircraft Wing ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Bézier Surface ◽  
Modeling Approach ◽  
Bezier Surface

Abstract The Fluid Structure Interaction (FSI) is a critical multi-physics phenomenon in the aerospace applications for computing loads. Including the FSI effects on the analysis requires high computational cost. A computationally efficient framework is presented in this study for predicting the FSI effects. The high-fidelity structural model is reduced on the elastic axis by using an efficient structural idealization technique. A parametric model generation process is developed by using Bezier surface control vertices (CVs) to estimate the changing load distribution under deformation. The aircraft wing outer surface is created by using Bezier surface modeling method for this purpose. The CVs of the surfaces are perturbed to predict the effect of the deformed shape on the load distribution. This method allows to predict the load distribution by using a few CVs instead of using all grid points. The Aerodynamic Influence Coefficients (AIC) matrix is generated based on the predicted loads based on this parametric modeling approach instead of conducting computationally expensive fluid flow analysis. The presented framework is implemented for an aircraft wing design to show its efficacy.

scholarly journals Development and experimental benchmarking of numeric fluid structure interaction models for research reactor fuel analysis

2015 ◽  
Author(s):  
◽  
John Charles Kennedy
Keyword(s):  
High Velocity ◽  
Plate Thickness ◽  
Fluid Structure Interaction ◽  
Quality Data ◽  
Flow Rates ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Manufacturing Tolerances ◽  
Enriched Uranium ◽  
Plate Deflection

As part of the Global Threat Reduction Initiative (GTRI) reactor conversion program, five U.S. High Performance Research Reactors (HPRRs) are currently studying a novel Low Enriched Uranium (LEU) foil based fuel to replace their current High Enriched Uranium (HEU) dispersion fuel. The proposed fuel uses a monolithic U-10Mo foil meat clad in aluminum, whereas the current HEU fuel meat is comprised of Uranium dispersed in an aluminum matrix, before being clad in aluminum. Along with a change in the physical structure of the fuel, the fuel plate thickness has been significantly decreased. Given that these fuel plates are subject to high velocity coolant flow, these changes in the plate design have led to a need to characterize the structural response of the plates in presence of high velocity flow. The proposed method for completing this analysis is to use novel fluid-structure interaction (FSI) simulations. These simulations are carried out using commercial CFD and FEA solvers Star-CCM+ and Abaqus, and iteratively coupling their solutions together at the interface between the plate and the fluid. Given the unique nature of these simulations, it is necessary to first benchmark and qualify the codes for this analysis. To generate benchmark quality data, a flow loop and test section have been constructed for studying plate deflection and channel pressure drop under a variety of fluid flow conditions. Similar experimental analysis which considered equally sized fluid channels has been studied by a number of individuals in the past. The work presented here differs however, by intentionally offsetting the plate and creating fluid channels of different thickness. This offset effectively simulates manufacturing tolerances of a real fuel assembly. A method for generating 'As-Built' numeric models of the experiment geometry is presented. These As-Built numeric models have been shown to dramatically improve matching between experiment and numeric solutions, particularly at low- to mid-range flow rates. At higher flow rates, the experiment exhibited a dynamic 'snap' behavior that could not be replicated numerically. Additional interrogation of the boundary conditions revealed a possible explanation for this snap, however numeric methods do not yet exist for recreating this behavior. In earlier works which considered equally sized channels, plate deflection was not examined in detail and was found to be largely unpredictable and reliant upon the manufacturing tolerances of the experiment. In the numeric and experimental work presented here, plate deflection behavior at low to mid-range flow rates is qualitatively consistent with theoretical expectations.

scholarly journals Study on Amplitude and Flatness Characteristics of Elastic Thin Strip under Fluid–Structure Interaction Vibration Excited by Unsteady Airflow

Metals ◽  
2019 ◽  
Vol 9 (5) ◽  
pp. 496
Author(s):  
Hongbo Li ◽  
Guomin Han ◽  
Jingbo Yang ◽  
Nong Li ◽  
Jie Zhang
Keyword(s):  
Simulation Analysis ◽  
Fluid Structure Interaction ◽  
Amplitude Distribution ◽  
Thin Strip ◽  
Analysis Model ◽  
Actual Measurement ◽  
Fluid Structure ◽  
Aerodynamic Loads ◽  
Structure Interaction ◽  
Rolling Strip

Based on unsteady airflow excitation and elastic thin strip vibration theory, a SI-FLAT flatness meter was taken as the research object, and an amplitude–residual stress simulation analysis model of the cold rolling strip under aerodynamic loads was established by using ANSYS Workbench. First, the influences of fluid–structure interaction on the strip amplitude distribution and the flatness calculation deviation were analyzed. It was found that the analysis with fluid–structure interaction matched the actual measurement of the flatness meter better. Then, the influences of different aerodynamic loads and tensions on the strip midpoint amplitude and the flatness calculation deviation were analyzed. It was found that when alternating aerodynamic loads increased, the strip amplitude increased in the form of a quadratic polynomial. However, when the tensions decreased, the strip amplitude decreased exponentially. The strip dimensions also influenced the amplitude of vibration: The wider and thinner the strip, the larger the amplitude. Finally, the influences of different flatness defects on the strip amplitude distribution and the flatness calculation deviation were analyzed. The deviation was serious on the strip edge, and the fluctuation characteristics of the deviation were opposite to those of the initial flatness defects.

Fluid-Structure Interaction and Co-Simulation: Analysis of a Beam-Supported Sphere for VIV Application

2014 ◽  
Author(s):  
Raffaele Ardito ◽  
Federico Perotti ◽  
Simone Mandelli ◽  
Davide Novarina ◽  
Stefano Malavasi
Keyword(s):  
Simulation Analysis ◽  
Fluid Structure Interaction ◽  
Time Integration ◽  
Free Surface Flow ◽  
Surface Flow ◽  
Simulation Technique ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Recent Developments ◽  
Software Modularity

The recent developments in numerical tools and computing resources seem to provide a suitable environment to perform numerical analyses of Fluid-Structure Interaction problems. The Co-Simulation technique, in particular, develops the idea of coupling a CFD software with a structural one in order to simulate complex FSI phenomena with a partitioned approach, stressing the concept of software modularity. In this way, it is possible to adopt software tools at the cutting edge of technology. Nonetheless, several difficulties may arise in the choice of the partitioning scheme and of the algorithmic details for the step-by-step time integration. This paper deals with the application of the Co-Simulation technique to a benchmark case experimentally investigated in previous works: the vortex-induced vibrations (VIV) of a beam supported sphere (that is, a sphere fixed to the end of a slender cantilever beam) in a free surface flow. This problem is challenging although apparently simple and it seems quite absent from literature so far. In this paper, the computational issues are thoroughly investigated and the model is validated by comparison with the experimental data. In this way, a robust framework is created in order to deal with VIV problems.

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