A hybrid probabilistic framework for model validation with application to structural dynamics modeling

To investigate the structural dynamic characteristics of a folding wing effectively, a fast structural dynamic modeling approach is proposed. Firstly, the interface compatible relationship of the traditional fixed interface component modal synthesis method is modified, and the internal force of the interface is completely expressed in the structural dynamic equation, so that the influence of the connection stiffness on the wing structure dynamics can be considered. Then, on the basis of the fixed interface component modal synthesis method, the main mode of fixed-loaded interface is introduced to establish the mixed-loaded interface component modal synthesis method, which makes it feasible to accurately reflect the influence of elasticity and inertia of fuselage and outer wing on inner wing. The structural dynamics modeling method based on two different kinds of component modal synthesis method analyzed and deduced in detail. The application of component modal synthesis method in the fast structural dynamics modeling of folding wing is achieved. The whole program is compiled in MATLAB. At the same time, the dynamic characteristics of the folding wing with different folding angles, different connections and different connection positions is investigated. The results of the method proposed in this paper are compared with the results of the repeated finite model established in MSC.NASTRAN to verify the effectiveness from the aspects of natural frequency and vibration mode.

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Feature Extraction for Structural Dynamics Model Validation

10.2172/1235219 ◽

2016 ◽

Author(s):

Charles Farrar ◽

Mayuko Nishio ◽

Francois Hemez ◽

Chris Stull ◽

Gyuhae Park ◽

...

Keyword(s):

Feature Extraction ◽

Model Validation ◽

Structural Dynamics ◽

Dynamics Model

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Structural Dynamics Analysis of Rotating Blades Using Fully Intrinsic Equations, Part I: Formulation and Verification of Single-Load-Path Configurations

Journal of the American Helicopter Society ◽

10.4050/jahs.58.032003 ◽

2013 ◽

Vol 58 (3) ◽

pp. 1-9 ◽

Cited By ~ 1

Author(s):

Zahra Sotoudeh ◽

Dewey H. Hodges

Keyword(s):

Structural Dynamics ◽

Equations Of Motion ◽

Turbine Blades ◽

Rotor Blades ◽

Load Path ◽

Dynamics Modeling ◽

Governing Equations ◽

Wind Turbine Blades ◽

First Order ◽

Infinite Degree

As part of an ongoing investigation into potential advantages of so-called fully intrinsic formulations, this paper presents an application of the fully intrinsic equations of motion and kinematics for beams to rotor blades. A fully intrinsic formulation is devoid of displacement and rotation variables. Although the governing equations are geometrically exact, they are free of the attendant singularities and infinite-degree nonlinearities found in other types of formulations. These nonlinear, first-order partial differential equations are suitable for analyzing initially curved and twisted, anisotropic beams and thus are very attractive for analysis of both helicopter and wind turbine blades. This two-part paper is devoted to the structural dynamics modeling of rotor blades with a wide variety of boundary conditions—in particular hingeless and bearingless rotor configurations. In Part I, the theory and the formulation are presented, along with verification of single-load-path configurations. Part II is devoted to the verification of dual-load-path configurations.

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