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Thin-wall structure thermodynamic elastic dynamic response analysis method

A thin-walled structure and analysis method technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as analysis, aeroelastic dynamic response that cannot perform structural nonlinearity, and achieve good adaptability and realization Nonlinear thermoaeroelastic dynamic response analysis and simulation effect

Active Publication Date: 2019-08-23
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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  • Thin-wall structure thermodynamic elastic dynamic response analysis method
  • Thin-wall structure thermodynamic elastic dynamic response analysis method
  • Thin-wall structure thermodynamic elastic dynamic response analysis method

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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 invention provides a thin-wall structure thermodynamic elastic dynamic response analysis method, which comprises the following steps: according to a thin-wall structure and boundary conditions, dispersing the thin-wall structure into seven-degree-of-freedom shell units, dispersing ribs into seven-degree-of-freedom beam units, and establishing a thin-wall finite element model to obtain a structure finite element grid; applying a thin-wall structure temperature field to the structure finite element grid, performing linear flutter analysis on the finite element model to obtain an unsteady aerodynamic matrix Qk corresponding to each reduction frequency k, and fitting a time domain expression of the unsteady aerodynamic matrix; and carrying out iterative calculation on the obtained time domain expression of the unsteady aerodynamic matrix, and carrying out nonlinear transient response analysis on the thin wall to obtain the nonlinear thermodynamic elastic dynamic response of the thin wall structure. The method provided by the invention can solve the calculation problem of the nonlinear thermodynamic elastic dynamic response of a complex thin-wall 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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IPC IPC(8): G06F17/50
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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