Nonlinear aeroelasticity dynamic response analysis method based on structure reduced-order model

A technology of reduced-order model and analysis method, applied in special data processing applications, complex mathematical operations, instruments, etc., can solve the problems of reduced applicability of structural reduced-order models, inconvenient to solve, and large amount of calculation, so as to improve the applicability , The effect of reducing the consumption of computing resources and the amount of calculation is low

Active Publication Date: 2021-03-30
BEIHANG UNIV
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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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  • Nonlinear aeroelasticity dynamic response analysis method based on structure reduced-order model
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  • Nonlinear aeroelasticity dynamic response analysis method based on structure reduced-order model

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Embodiment Construction

[0057] Such as figure 1 As shown, the nonlinear aeroelastic dynamic response analysis method based on the structure reduction model of the present invention comprises the 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 of the structural finite element mesh (including the cross-sectional size and normal direction of the beam element) and material properties, and set the calculation boundary conditions , that is, fix the constraint on the boundary point of the wing root that needs to be fixed;

[0060] S2: Calculating 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 of the vertical bending, torsion and horizontal bending directions of the structure ar...

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Abstract

The invention belongs to the field of structural dynamics and aeroelastic mechanics analysis, and particularly relates to a nonlinear aeroelastic dynamic response analysis method based on a structuralreduced-order model. The method includes: solving a structural nonlinear stiffness coefficient in a given form by adopting a method for carrying out regression analysis on an input test load and corresponding structural deformation, constructing a large-deformation structural kinetic equation by utilizing the nonlinear stiffness coefficient, and on the basis, constructing the test load by utilizing a mode of multiplying a proportionality coefficient by a mode combination; accurately recovering the spanwise displacement of the wing by constructing a displacement residual basis function; and finally, constructing a geometric nonlinear aeroelastic gust response solving process in combination with a kinetic equation given by the structure reduced-order model and an unsteady curved surface vortex lattice method. The method gives consideration to the solving precision, the calculation efficiency and the applicability of a complex model, and can be applied to the analysis and calculation ofthe geometrical nonlinear aeroelastic gust response of aerospace aircrafts.

Description

technical field [0001] 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. Background technique [0002] As a branch of applied mechanics, aeroelasticity mainly studies the coupling between aerodynamic force, elastic force and inertial force. Under the action of aerodynamic force, the elastic structure vibrates and deforms, and the elastic movement of the structure will in turn cause the magnitude and distribution of aerodynamic force to change. This interaction will bring about a variety of aeroelastic phenomena, including aeroelastic deformation, chatter vibration, gust response, etc. In the historical development of powered flight, aeroelasticity has played an important role, and it is a key factor that must be considered to ensure the safety of aircraft and improve the flight performance of aircraft. [0003] Th...

Claims

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Application Information

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Patent Type & Authority Applications(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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