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Ground test unsteady aerodynamic loading method

A technology of unsteady aerodynamics and ground testing, which is applied in aerodynamic testing, testing of machine/structural components, measuring devices, etc., and can solve problems such as poor practicability

Inactive Publication Date: 2019-03-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0003] In order to overcome the shortcomings of poor practicability of the existing unsteady aerodynamic loading method, the present invention provides a ground test unsteady aerodynamic loading method

Method used

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  • Ground test unsteady aerodynamic loading method

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Embodiment Construction

[0062] refer to Figure 1-6 .

[0063] The simulation is carried out on the international standard aeroelastic calculation example AGARD 445.6. The AGARD 445.6 wing is an elastic model used to study flutter characteristics in the transonic wind tunnel of NASA Langley Research Center, and has become a standard aeroelastic example for studying nonlinear unsteady aerodynamic forces. The wing is 45°swept wing, the airfoil is NACA64A004, the root-to-tip ratio is 0.6576, and the display ratio is 1.65.

[0064] The specific steps of the ground test unsteady aerodynamic loading method of the present invention are as follows:

[0065] 1. To process the data of the measurement points of the test structure. In the process of establishing the unsteady aerodynamic reduction model, in order to facilitate unified processing, it is necessary to convert the deformation information collected from the measurement points of the test structure into the form of generalized displacement. According...

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Abstract

The invention discloses a ground test unsteady aerodynamic loading method, and is used for solving the technical problem that an existing unsteady aerodynamic loading method has poor practicability. The technical scheme is to firstly process test structure measurement point data, a constant volume conversion method is adopted to achieve the reduction from a distributed unsteady aerodynamic force to an excitation concentrated force, an unsteady aerodynamic reduction model established based on computational fluid dynamics, and the unsteady aerodynamic reduction model based on Volterra series istransformed into a state space form. Due to the constant volume conversion method, the reduction from the distributed unsteady aerodynamic force to the excitation concentrated force is achieved, and the method is suitable for two-dimensional and three-dimensional complex surfaces. The unsteady aerodynamic reduction model based on computational fluid dynamics is established based on a Volterra series theory. The calculation accuracy is high, the ability to characterize a nonlinear system is strong, a minimum feature realization algorithm of the system is used for converting a reduced-order model into a state space form, and the method provides convenience for engineering application and has good practicability.

Description

technical field [0001] The invention relates to an unsteady aerodynamic loading method, in particular to a ground test unsteady aerodynamic loading method. Background technique [0002] In order to obtain the structural performance of the aircraft, it is usually necessary to adopt the method of wind tunnel test, but the cost of wind tunnel test is relatively high, and for some special tests, the design of test model and the real simulation of flight conditions will become very complicated. Therefore, researchers at home and abroad try to use ground tests instead of conventional wind tunnel tests, which is called dry wind tunnel tests. The document "GVT-BASED GROUND FLUTTER TEST WITHOUT WIND TUNNEL, 52nd AIAA / ASME / ASCE / AHS / ASC Structures, Structural Dynamics and Materials Conference, AIAA Paper2011-1942, 2011" discloses a non The steady aerodynamic loading method, which uses the infinite plate spline interpolation method to realize unsteady aerodynamic reduction, uses engine...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 权恩欠徐敏李广宁闫循良安效民张忠郭静
Owner NORTHWESTERN POLYTECHNICAL UNIV
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