Dry wind tunnel aeroelastic test method

A technology of aeroelasticity and test methods, which is applied in the field of aerospace engineering, can solve the problems of not using signal feedback, small amplitude, and inability to realize large-amplitude vibration, and achieve the effect of strong followability and error reduction

Active Publication Date: 2017-05-03
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

[0004] (1) The applied load is usually a concentrated load, which cannot accurately simulate the aerodynamic force
[0005] (2) When loading with equipment such as a vibrator, the amplitude is small and it is impossible to achieve large-amplitude vibration
[0006] (3) It is impossible to simulate the torsion of the wing and the influence of structural deformation on the aerodynamic load, that is, to simulate the aeroelasticity
[0007] (4) The contact between the loading device and the test model will interfere with the accuracy of the test data
[0008] (5) Without signal feedback, quasi-steady aerodynamic force / unsteady aerodynamic force cannot be simulated

Method used

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  • Dry wind tunnel aeroelastic test method
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  • Dry wind tunnel aeroelastic test method

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Embodiment Construction

[0028] like figure 2 , image 3 As shown, the present invention includes displacement sensor or speed sensor or angle sensor 1, data line 2, switch 3, data collector 4, test model 5, computer 6, program-controlled power supply 7, loading wire 8, uniform magnetic field 9, data acquisition and Feedback system 10 and aerodynamic force generation system 11.

[0029] Firstly, the loading wire 8 is bound or pasted and fixed on the test model 5, and then the displacement sensor or the speed sensor or the rotation angle sensor 1 is associated with the test model through a measuring device that is not sensitive to a magnetic field such as a vibrometer or an optical fiber. The deformation data of the test model 5 is collected. The measurement range of the measuring equipment should be able to meet the requirements of the deformation range of the model. The higher the data sampling frequency, the better, and it should not be lower than 100Hz.

[0030] Then the test model 5 is placed ...

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Abstract

The invention provides an aeroelasticity testing method for a dry wind tunnel. According to the method, a closed aeroelasticity testing system is utilized to test a testing model. The method comprises the steps that firstly, the closed aeroelasticity testing system is formed by a data acquisition and feedback system and an aerodynamic force generation system through a computer; afterwards, the closed aeroelasticity testing system is utilized to test the testing model; accordingly, the purpose that a simulated aircraft responds under the action of unsteady aerodynamic force is achieved. As a circuit is formed through a signal acquisition / feedback system, the influence on load distribution by structural deformation, namely the aeroelasticity influence, can be effectively simulated. Moreover, as loading equipment does not make contact with a loading model, the errors caused in a traditional ground test can be reduced.

Description

technical field [0001] The invention relates to a dry wind tunnel test on the ground, in particular to an aeroelasticity test method in a dry wind tunnel, and belongs to the field of aerospace engineering. Background technique [0002] In order to measure the structural performance of aircraft, the test method of wind tunnel test is usually used, but the cost of wind tunnel test is high, and for some special tests, the design of test model and the real simulation of flight conditions become very complicated. Therefore, some domestic and foreign researchers try to use ground tests instead of wind tunnel tests. This type of test is called a dry wind tunnel test, and conventional dry wind tunnel tests use equipment such as vibrators for loading (such as figure 1 ). [0003] However, the existing ground test methods have the following deficiencies: [0004] (1) The applied load is usually a concentrated load, which cannot accurately simulate the aerodynamic force. [0005] (...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00G01M9/06
Inventor 刘子强侯英昱付志超吕计男朱剑陈占军
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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