scholarly journals Progress toward using sensitivity derivatives in a high-fidelity aeroelastic analysis of a supersonic transport

1998 ◽  
Author(s):  
Anthony Giunta ◽  
Jaroslaw Sobieszczanski-Sobieski
Keyword(s):  
High Fidelity ◽  
Supersonic Transport ◽  
Sensitivity Derivatives ◽  
Aeroelastic Analysis

scholarly journals High-Fidelity Fin–Actuator System Modeling and Aeroelastic Analysis Considering Friction Effect

2021 ◽  
Vol 11 (7) ◽  
pp. 3057
Author(s):  
Jin Lu ◽  
Zhigang Wu ◽  
Chao Yang
Keyword(s):  
System Modeling ◽  
Past Research ◽  
High Fidelity ◽  
Aeroelastic Stability ◽  
Aeroelastic Analysis ◽  
Structural Nonlinearities ◽  
Flutter Boundary ◽  
Actuator System ◽  
Friction Models ◽  
Comparison Of The Results

Both the dynamic characteristics and structural nonlinearities of an actuator will affect the flutter boundary of a fin–actuator system. The actuator models used in past research are not universal, the accuracy is difficult to guarantee, and the consideration of nonlinearity is not adequate. Based on modularization, a high-fidelity modeling method for an actuator is proposed in this paper. This model considers both freeplay and friction, which is easy to expand. It can be directly used to analyze actuator characteristics and perform aeroelastic analysis of fin–actuator systems. Friction can improve the aeroelastic stability, but the mechanism of its influence on the aeroelastic characteristics of the system has not been reported. In this paper, the LuGre model, which can better reflect the friction characteristics, was integrated into the actuator. The influence of the initial condition, freeplay, and friction on the aeroelastic characteristics of the system was analyzed. The comparison of the results with the previous research shows that oversimplified friction models are not accurate enough to reflect the mechanism of friction’s influence. By changing the loads, material, and geometry of contact surfaces, flutter can be effectively suppressed, and the power loss caused by friction can be minimized.

scholarly journals High fidelity CFD-CSD aeroelastic analysis of slender bladed horizontal-axis wind turbine

2016 ◽  
Vol 753 ◽  
pp. 042009 ◽  
Author(s):  
M. Sayed ◽  
Th. Lutz ◽  
E. Krämer ◽  
Sh. Shayegan ◽  
A. Ghantasala ◽  
...  
Keyword(s):  
Wind Turbine ◽  
Horizontal Axis ◽  
High Fidelity ◽  
Horizontal Axis Wind Turbine ◽  
Aeroelastic Analysis

scholarly journals State consistence of data-driven reduced order models for parametric aeroelastic analysis

2021 ◽  
Vol 3 (2) ◽  
Author(s):  
William C. Krolick ◽  
Jung I. Shu ◽  
Yi Wang ◽  
Kapil Pant
Keyword(s):  
System Identification ◽  
Grid Point ◽  
The State ◽  
Data Driven ◽  
High Fidelity ◽  
Reduced Order Models ◽  
Reduced Order ◽  
Parametric Data ◽  
Aeroelastic Analysis ◽  
Grid Points

AbstractThis paper investigates the state consistence of parametric data-driven reduced order models (ROMs) in a state-space form obtained by various system identification methods, including autoregressive exogenous (ARX) and subspace identification (N4SID), for aeroelastic analysis in varying flight conditions. The target flight envelop is first partitioned into discrete grid points, on each of which an aerodynamic ROM is constructed using system identification to capture the dependence of the generalized aerodynamic force on the generalized displacement of structural modes. High-fidelity aeroelastic modal perturbation simulations are used to generate the ROM training and verification data. Aerodynamic ROMs not on the grid point are obtained by interpolating those at neighboring grid points. Through a thorough analysis of the model coefficients and pole migration, it is found that only the ARX-based aerodynamic ROM preserves the state consistence, and hence, allowing direct interpolation of system matrices at the non-grid point and rapid aerodynamic ROM database development in the entire flight parameter space. In contrast, N4SID-based ROM destroys the state consistence and yields physically meaningless results when ROMs are interpolated. The origin of the difference in the state consistence caused by both methods is also discussed. The interpolated ARX aerodynamic ROMs coupled with the structural ROM for parametric aeroelastic analysis exhibit excellent agreement with the high fidelity full order model (mostly <5% relative error) and salient computational efficiency.

scholarly journals Scalable Parallel Approach for High-Fidelity Steady-State Aeroelastic Analysis and Adjoint Derivative Computations

AIAA Journal ◽  
2014 ◽  
Vol 52 (5) ◽  
pp. 935-951 ◽  
Author(s):  
Gaetan K. W. Kenway ◽  
Graeme J. Kennedy ◽  
Joaquim R. R. A. Martins
Keyword(s):  
Steady State ◽  
High Fidelity ◽  
Aeroelastic Analysis

Implementation of a CFD-Based Aeroelastic Analysis Toolbox for Turbomachinery Applications

2014 ◽  
Author(s):  
G. Romanelli ◽  
L. Mangani ◽  
E. Casartelli
Keyword(s):  
Structural Model ◽  
Structural Integrity ◽  
State Of The Art ◽  
Fluid Dynamic ◽  
Test Problems ◽  
High Fidelity ◽  
Compressor Cascade ◽  
Aeroelastic Analysis ◽  
Non Linear ◽  
Fully Coupled

The understanding of aeroelastic phenomena is fundamental for the structural integrity of many applications in aerospace and mechanical engineering and even in some other disciplines (e.g. civil engineering) where flexible structures possibly undergo unsteady fluid-dynamic loads. Therefore the availability of accurate analysis tools for the study of the aeroelastic interaction between aerodynamic and elastic forces is an important asset for the design of modern, high performance turbomachinery. Together with the more and more powerful computing resources, current trends pursue the adoption of high-fidelity tools and state-of-the-art technology within the research fields of Computational Structural Dynamics (CSD) and Computational Fluid Dynamics (CFD). This choice is somehow obliged when dealing with highly non-linear aeroservoelastic phenomena. The approach typically used for turbomachinery aeroelastic analysis features the so-called “one-way coupling”, i.e. the loads predicted by the aerodynamic model are transferred to the structural model to evaluate relevant stresses and displacements. The objective of the present work is to illustrate the design and implementation of a platform for solving multidisciplinary non-linear Fluid-Structure Interaction (FSI) problems with a “two-way coupling” or fully coupled approach, that is linking together high-fidelity state-of-the-art CSD and CFD tools by means of a robust, flexible aeroelastic interface scheme. The credibility of the proposed aeroservoelastic analysis toolbox is assessed by tackling a set of aeronautical and turbomachinery-oriented benchmark test problems such as: the evaluation of the fully coupled non-linear aeroelastic trim of HIRENASD (HIgh REynolds Number AeroStructural Dynamics) wing and the identification of the aerodynamic damping coefficient of Standard Configuration 10, high subsonic/transonic, 2D/3D compressor cascade. The results are compared with reference experimental and numerical data available in literature.

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