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A Nonlinear Aeroelastic Dynamic Response Analysis Method Based on Structural Reduced-Order Model

A technology of reduced-order models and analysis methods, applied in special data processing applications, complex mathematical operations, geometric CAD, etc., can solve the problems of reduced applicability, inconvenient solution, and large amount of calculation of structural reduced-order models, so as to improve the application performance, reduced computing resource consumption, and low computational load

Active Publication Date: 2022-06-21
BEIHANG UNIV
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

For the complex wing model, the spanwise displacement orthogonal basis function is not easy to solve
At the same time, the test load used to build the reduced-order model is the aerodynamic load under a certain deformation, which requires a large amount of calculation and reduces the applicability of the generated structural reduced-order model

Method used

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  • A Nonlinear Aeroelastic Dynamic Response Analysis Method Based on Structural Reduced-Order Model
  • A Nonlinear Aeroelastic Dynamic Response Analysis Method Based on Structural Reduced-Order Model
  • A Nonlinear Aeroelastic Dynamic Response Analysis Method Based on Structural Reduced-Order Model

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Embodiment Construction

[0057] like figure 1 As shown, the nonlinear aeroelastic dynamic response analysis method based on the structural reduction model of the present invention comprises the following steps:

[0058] S1: Calculation initialization

[0059] Establish the finite element model of the wing model, divide the structural finite element mesh of the finite element model, and define the element properties (including the section size and normal direction of the beam element) and material properties of the structural finite element mesh, and set the calculation boundary conditions , that is, the clamp constraint is performed on the boundary point of the wing root that needs to be clamped;

[0060] S2: Calculate structural modes

[0061] The nonlinear structural reduced-order model is established based on the linear mode of the structure. Before the nonlinear structural reduced-order model is established, the linear modes in the vertical bending, torsion and horizontal bending directions of t...

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Abstract

The invention belongs to the field of structural dynamics and aeroelasticity analysis, and in particular relates to a nonlinear aeroelastic dynamic response analysis method based on a structural reduction model. This method adopts the method of regression analysis on the input test load and its corresponding structural deformation to solve the nonlinear stiffness coefficient of the given form, and uses the nonlinear stiffness coefficient to construct the dynamic equation of the large deformation structure. The test load is constructed by means of proportional coefficients, and the spanwise displacement of the wing is accurately restored by constructing the displacement residual basis function; finally, the geometric nonlinear aeroelastic gust response is constructed by combining the dynamic equation given by the structural reduction model and the unsteady surface vortex lattice method Solving process. The invention takes into account the solution accuracy, calculation efficiency and complex model applicability, and can be applied to the analysis and calculation of the geometric nonlinear aeroelastic gust response of aerospace vehicles.

Description

technical field [0001] The invention belongs to the field of structural dynamics and aeroelasticity analysis, in particular to a nonlinear aeroelastic dynamic response analysis method based on a structural reduced order model. Background technique [0002] Aeroelasticity, as a branch of applied mechanics, mainly studies the coupling between aerodynamic force, elastic force and inertial force. Under the action of aerodynamic force, the elastic structure will vibrate and deform, and the elastic movement of the structure will in turn lead to changes in the magnitude and distribution of the aerodynamic force. This interaction will bring about a variety of aeroelastic phenomena, including aeroelastic deformation, vibration vibration, gust response, etc. In the historical development process of powered flight, aeroelasticity has played an important role and is a key factor that must be considered to ensure the safety of aircraft and improve the flight performance of aircraft. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15G06F30/17G06F17/15G06F119/14
CPCG06F30/23G06F30/15G06F30/17G06F17/15G06F2119/14
Inventor 安朝谢长川杨澜杨超
Owner BEIHANG UNIV
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