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A high-angle flutter analysis method based on reduced-order modeling

A technology of flutter analysis and high angle of attack, applied in CAD numerical modeling, instrumentation, geometric CAD, etc., to save calculation time

Active Publication Date: 2022-08-05
BEIHANG UNIV
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Problems solved by technology

[0005] However, the current research on the unsteady aerodynamic reduced-order model is mainly aimed at a fixed flow state. If the current reduced-order method is used for flutter analysis, especially when it is used to find the matching solution of the flutter boundary, it is bound to need repeated iterations to determine Appropriate incoming and outgoing conditions to build reduced-order models

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  • A high-angle flutter analysis method based on reduced-order modeling
  • A high-angle flutter analysis method based on reduced-order modeling
  • A high-angle flutter analysis method based on reduced-order modeling

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Embodiment Construction

[0034] In order to facilitate the understanding and implementation of the present invention by those of ordinary skill in the art, the present invention will be further described in detail and in-depth below with reference to the accompanying drawings and the embodiments of the AGARD445.6 airfoil.

[0035] A reduced-order modeling process suitable for three-dimensional wing high-angle-of-attack flutter analysis proposed by the present invention is as follows: figure 1 shown; based on the unsteady aerodynamic reduced-order model to complete the three-dimensional wing large angle of attack flutter analysis process is as follows figure 2 shown. Specific steps are as follows:

[0036] In one embodiment according to the invention, for the AGARD445.6 airfoil, such as image 3 As shown, the initial angle of attack of 10 degrees is completed, and the atmospheric density is 1.11kg / m 3 , Flutter analysis of temperature 298K, pressure 95215Pa.

[0037] Step A: Carry out finite eleme...

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Abstract

The invention discloses a large angle of attack flutter analysis method based on reduced-order modeling. First complete the analysis of the modal characteristics of a given wing; then select a series of Mach numbers, solve the static aeroelastic deformation at the angle of attack and these Mach numbers, design training motion signals and predicted motion signals, and obtain training data samples Then, an unsteady aerodynamic reduced-order model is established to evaluate the training effect and generalization ability of the unsteady aerodynamic reduced-order model. Finally, the flutter analysis is completed using the obtained unsteady aerodynamic reduced-order model.

Description

technical field [0001] The invention relates to a high-angle-of-attack flutter analysis method based on reduced-order modeling, and belongs to the field of nonlinear aeroelasticity. Background technique [0002] The high maneuverability of modern fighter jets makes it necessary to fly at a high angle of attack; when the missile maneuvers, the rudder is in a high angle of attack state; when the aircraft encounters a gust of wind, its wings may enter a large angle of attack state; wind turbine blades , turbine blades and other mechanical components usually work at a certain angle of attack. However, the current research on aeroelasticity mainly focuses on the zero angle of attack state, and there are few studies on aeroelasticity with a non-zero angle of attack. [0003] The related research on aeroelasticity is mainly wind tunnel test and numerical simulation method. The wind tunnel test needs to prepare the corresponding site, wind tunnel and equipment, not only the time pe...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23G06F30/27B64F5/60G06F111/10G06F119/14
CPCG06F30/15G06F30/23G06F30/27B64F5/60G06F2111/10G06F2119/14Y02T90/00
Inventor 戴玉婷容浩然杨超
Owner BEIHANG UNIV
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