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Thermo-aeroelastic dynamic response analysis method for thin-walled structures

A thin-walled structure and analysis method technology, which is applied in design optimization/simulation, instrumentation, electrical and digital data processing, etc. Elastic dynamic response analysis, the effect of good adaptability

Active Publication Date: 2021-05-11
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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Problems solved by technology

The commonly used finite element analysis software MSC.Nastran in the aerospace field provides the calculation function of the linear aeroelastic response of the structure, but it cannot perform the analysis of the nonlinear aeroelastic dynamic response of the structure

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  • Thermo-aeroelastic dynamic response analysis method for thin-walled structures
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  • Thermo-aeroelastic dynamic response analysis method for thin-walled structures

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Embodiment Construction

[0035] The present invention will be described in detail below in conjunction with specific examples and accompanying drawings.

[0036] according to figure 1 As shown, a thin-walled structure thermoaeroelastic dynamic response analysis method, including the following steps:

[0037] Step 1. Establish a thin-walled finite element model according to the thin-walled structure and boundary conditions. The thin-walled structure is as follows figure 2 As shown, the thin-walled structure is discretized into space shell elements, such as image 3 As shown, for reinforced thin-walled structures, it is also necessary to discretize the reinforcement into space beam elements, such as Figure 4 shown.

[0038] For thin-walled structures, each node has seven degrees of freedom Δ C =[u v w w ,x w ,y w ,xy θ z ] T , including two in-plane displacements w m ={u,v} T and four bending displacements w b ={w,w ,x ,w ,y ,w ,xy ,θ z} T , unit such as Figure 5 Shown; the spati...

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Abstract

The present invention proposes a thin-walled structure thermal aeroelasticity dynamic response analysis method, according to the thin-walled structure and boundary conditions, the thin-walled structure is discretized into shell elements with seven degrees of freedom, and the ribs are discretized into beam elements with seven degrees of freedom. The thin-walled finite element model is used to obtain the structural finite element grid; the temperature field of the thin-walled structure is applied to the structural finite element grid, and the linear flutter analysis is performed on the finite element model to obtain the unsteady gas corresponding to each reduction frequency k Power matrix Q k , to fit the time-domain expression of the unsteady aerodynamic matrix; iteratively calculate the time-domain expression of the unsteady aerodynamic matrix, analyze the nonlinear transient response of the thin-walled structure, and obtain the nonlinear thermal Aeroelastic dynamic response. The method of the invention can solve the calculation problem of the nonlinear thermal aeroelastic dynamic response of the complex thin-walled structure.

Description

technical field [0001] The invention relates to thermal aeroelastic response analysis and belongs to the technical field of aircraft aeroelasticity. Background technique [0002] Large-scale thin-walled structures are widely used on supersonic and hypersonic vehicles, such as thermal protection structures, engine protection covers and large-scale wing skins, etc. Such thin-walled structures are prone to elastic force, inertial force, aerodynamic force and thermal stress The thermo-aeroelastic problems caused by mutual coupling between the four often lead to performance degradation or even structural damage of the aircraft. In addition, because the lateral deflection of the thin-walled structure causes in-plane stress in the mid-plane of the plate, the in-plane stress produces a hard-elastic effect in vibration, which is a typical structural geometric nonlinear problem. [0003] For the classical methods of panel flutter, such as Galerkin method, Rayleigh-Ritz method, harmon...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/28G06F119/14
CPCG06F30/23G06F2119/06
Inventor 苑凯华罗金玲操小龙田海涛
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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