Bayesian calibration of hysteretic reduced order structural models for earthquake engineering applications

2020 ◽  
Vol 224 ◽  
pp. 111204
Author(s):  
Dimitrios Patsialis ◽  
Aikaterini P. Kyprioti ◽  
Alexandros A. Taflanidis
Keyword(s):  
Earthquake Engineering ◽  
Structural Models ◽  
Bayesian Calibration ◽  
Engineering Applications ◽  
Reduced Order

Theory and implementation of switch-based hybrid simulation technology for earthquake engineering applications

2017 ◽  
Vol 46 (14) ◽  
pp. 2603-2617 ◽  
Author(s):  
T.Y. Yang ◽  
Dorian P. Tung ◽  
Yuanjie Li ◽  
Jian Yuan Lin ◽  
Kang Li ◽  
...  
Keyword(s):  
Earthquake Engineering ◽  
Hybrid Simulation ◽  
Simulation Technology ◽  
Engineering Applications

Development of an aeroelastic model based on system identification using boundary elements method

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Rohollah Dehghani Firouz-Abadi ◽  
Mohammad Reza Borhan Panah
Keyword(s):  
Boundary Element Method ◽  
Boundary Element ◽  
Structural Models ◽  
Elastic Mode ◽  
Content Type ◽  
Reduced Order ◽  
Aerodynamic Model ◽  
Aeroelastic Model ◽  
Proposed Model ◽  
Element Method

Purpose The purpose of this paper is to analyze the stability of aeroelastic systems using a novel reduced order aeroelastic model. Design/methodology/approach The proposed aeroelastic model is a reduced-order model constructed based on the aerodynamic model identification using the generalized aerodynamic force response and the unsteady boundary element method in various excitation frequency values. Due to the low computational cost and acceptable accuracy of the boundary element method, this method is selected to determine the unsteady time response of the aerodynamic model. Regarding the structural model, the elastic mode shapes of the shell are used. Findings Three case studies are investigated by the proposed model. In the first place, a typical two-dimensional section is introduced as a means of verification by approximating the Theodorsen function. As the second test case, the flutter speed of Advisory Group for Aerospace Research and Development 445.6 wing with 45° sweep angle is determined and compared with the experimental test results in the literature. Finally, a complete aircraft is considered to demonstrate the capability of the proposed model in handling complex configurations. Originality/value The paper introduces an algorithm to construct an aeroelastic model applicable to any unsteady aerodynamic model including experimental models and modal structural models in the implicit and reduced order form. In other words, the main advantage of the proposed method, further to its simplicity and low computational effort, which can be used as a means of real-time aeroelastic simulation, is its ability to provide aerodynamic and structural models in implicit and reduced order forms.

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