scholarly journals Static aeroelastic analysis including geometric nonlinearities based on reduced order model

2017 ◽  
Vol 30 (2) ◽  
pp. 638-650 ◽  
Author(s):  
Changchuan Xie ◽  
Chao An ◽  
Yi Liu ◽  
Chao Yang
Keyword(s):  
Reduced Order Model ◽  
Order Model ◽  
Geometric Nonlinearities ◽  
Reduced Order ◽  
Aeroelastic Analysis

Aeroelastic Analysis of Blades Cascades Through Aerodynamic Reduced-Order Modeling

2011 ◽  
Author(s):  
Davide Finamore ◽  
Fred Nitzsche ◽  
Massimo Gennaretti
Keyword(s):  
Reduced Order Model ◽  
Aeroelastic Stability ◽  
Order Model ◽  
Control Laws ◽  
Reduced Order ◽  
Aerodynamic Model ◽  
Blade Cascade ◽  
Aeroelastic Analysis ◽  
Direct Use ◽  
High Computational Efficiency

An aerodynamic Reduced-Order Model (ROM) is introduced to describe the aeroelastic behavior of a blade cascade of a turbomachine. This is obtained coupling an aerodynamic model with a semi-rigid 2D model for the description of the structure dynamics. The advantages of using an aerodynamic reduced-order model concern the high computational efficiency compared to the direct use of a CFD code, and the applicability of control laws to reduce, for instance, blades vibrations. ROMs are identified from both an analytical aerodynamic model and a numerical CFD solver. The aeroelastic stability of a blade cascade is examined with the presence or not of mistuning.

The Study of Aeroelastic Reduced-Order Model Based on CFD/CSD Method and its Application

2014 ◽  
Vol 978 ◽  
pp. 131-134
Author(s):  
Rui Li ◽  
Chang Hong Tang
Keyword(s):  
Harmonic Balance ◽  
Unsteady Aerodynamics ◽  
Harmonic Balance Method ◽  
Reduced Order Model ◽  
Reduced Order Models ◽  
Order Model ◽  
Reduced Order ◽  
Advantages And Disadvantages ◽  
Aeroelastic Analysis ◽  
Proper Orthogonal

Unsteady aerodynamics research is the foundation of aeroelastic analysis. How to effectively improve the aeroelastic computational efficiency,it is the key of current research on aeroelasticity now.Reduced order models are proposed as a powerful tool to solve this problem. Analyzed the three reduced-order models for Volterra ,Proper Orthogonal Decomposition and Harmonic Balance method ,their advantages and disadvantages were pointed out. The direction of the reduced order model in the future was Proposed and some suggest was given out for its application.

A Reduced Order Model for the Aeroelastic Analysis of Flexible Wings

2013 ◽  
Vol 6 (2) ◽  
pp. 447-458 ◽  
Author(s):  
Enrico Cestino ◽  
Giacomo Frulla ◽  
Piergiovanni Marzocca
Keyword(s):  
Reduced Order Model ◽  
Order Model ◽  
Flexible Wings ◽  
Reduced Order ◽  
Aeroelastic Analysis

Reduced-Order-Model Approach for Aeroelastic Analysis Involving Aerodynamic and Structural Nonlinearities

AIAA Journal ◽  
2005 ◽  
Vol 43 (3) ◽  
pp. 560-571 ◽  
Author(s):  
Sorin Munteanu ◽  
John Rajadas ◽  
Changho Nam ◽  
Aditi Chattopadhyay
Keyword(s):  
Reduced Order Model ◽  
Order Model ◽  
Reduced Order ◽  
Aeroelastic Analysis ◽  
Structural Nonlinearities ◽  
Model Approach

scholarly journals A Hybrid Reduced-Order Model for the Aeroelastic Analysis of Flexible Subsonic Wings—A Parametric Assessment

Aerospace ◽  
2018 ◽  
Vol 5 (3) ◽  
pp. 76 ◽  
Author(s):  
Marco Berci ◽  
Rauno Cavallaro
Keyword(s):  
Structural Parameters ◽  
Equations Of Motion ◽  
Three Dimensional ◽  
Unsteady Aerodynamics ◽  
Reduced Order Model ◽  
Order Model ◽  
Flexible Wings ◽  
Reduced Order ◽  
Aeroelastic Analysis ◽  
Strip Theory

A hybrid reduced-order model for the aeroelastic analysis of flexible subsonic wings with arbitrary planform is presented within a generalised quasi-analytical formulation, where a slender beam is considered as the linear structural dynamics model. A modified strip theory is proposed for modelling the unsteady aerodynamics of the wing in incompressible flow, where thin aerofoil theory is corrected by a higher-fidelity model in order to account for three-dimensional effects on both distribution and deficiency of the sectional air load. Given a unit angle of attack, approximate expressions for the lift decay and build-up are then adopted within a linear framework, where the two effects are separately calculated and later combined. Finally, a modal approach is employed to write the generalised equations of motion in state-space form. Numerical results were obtained and critically discussed for the aeroelastic stability analysis of a uniform rectangular wing, with respect to the relevant aerodynamic and structural parameters. The proposed hybrid model provides sound theoretical insights and is well suited as an efficient parametric reduced-order aeroelastic tool for the preliminary multidisciplinary design and optimisation of flexible wings in the subsonic regime.

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