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Device for forced vibration test of dynamic derivative in wind tunnel

A technology of forced vibration and dynamic derivative, applied in the direction of aerodynamic test, measuring device, machine/structural component testing, etc. Ideal, low load-carrying capacity, etc., to achieve the effect of small overall size, reduced balance diameter, and low assembly difficulty

Active Publication Date: 2017-06-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The normal load bearing capacity of the current forced vibration test device is not high, the installation and fixation of the torque output parts are not ideal, the test accuracy is insufficient, and it also lacks the ability to realize the superposition of the test angle of attack, sideslip angle and roll angle

Method used

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  • Device for forced vibration test of dynamic derivative in wind tunnel
  • Device for forced vibration test of dynamic derivative in wind tunnel
  • Device for forced vibration test of dynamic derivative in wind tunnel

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Experimental program
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Effect test

Embodiment

[0060] Most of the existing technologies can only rely on the wind tunnel machete to adjust the change of the angle of attack α for testing, the change of the test conditions is very limited, and the dependence on the wind tunnel machete is very high. The lower capacity will greatly affect the number of test conditions and the number of tests. The forced vibration test device can realize three different attitude angle changes of wind tunnel scimitar adjustment of attack angle α, sideslip angle mechanism to change sideslip angle β, and roll angle mechanism to give roll angle K, so it can cover most dynamic tests. The requirements of the working conditions can provide sufficient test data.

[0061] In addition, the angle of attack, sideslip angle and roll angle have approximately the following relationship under the forced vibration of small amplitude:

[0062] β=K*sinα

[0063] Combining the relational expressions of the three, the results of another attitude angle can be sol...

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Abstract

The invention discloses a device for forced vibration test of dynamic derivative in wind tunnel. The device comprises a dynamic balance, a supporting mechanism, a side-slip angle mechanism and a rolling angle mechanism. The dynamic balance is connected to the side-slip angle mechanism through the supporting mechanism. The rolling angle mechanism is connected to the side-slip angle mechanism, and a relative position and angle between the side-slip angle mechanism and the rolling angle mechanism are adjusted through the coordination between the side-slip angle mechanism and the rolling angle mechanism so as to meet the test requirements under the condition of different attack angles, side-slip angles and rolling angles. According to the device, an output torque of a servo motor can drive a transmission shaft to continuously perform rotational motion in a fixed-frequency or a sweep-frequency mode, and an eccentric cam cooperates with a groove of the dynamic balance to complete the motion form conversion and realize the harmonic forced vibration. The device has the advantages of reasonable and compact structure, large normal-direction bearing capacity and high precision, and has great application value in the field of aviation and aerospace.

Description

technical field [0001] The invention relates to a device for forced vibration testing of wind tunnel dynamic derivatives, belonging to the technical field of wind tunnel testing. Background technique [0002] When designing the flight control system and analyzing the dynamic quality of the aircraft, the aerodynamic forces and moments appear in the form of aerodynamic derivatives, namely static and dynamic stability derivatives. Due to the complex generation mechanism, the above parameters are usually obtained by forced vibration wind tunnel tests. [0003] The dynamic derivative wind tunnel test uses the model oscillation to simulate the rigid body motion mode of the aircraft to obtain the dynamic derivative. With the development of high-speed aircraft, missiles, rockets and re-entry vehicles, more and more attention has been paid to flight quality and dynamic stability, and dynamic derivative tests have become more and more important. Especially the test and measurement te...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 孙竣利陈农
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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