Airfoil high speed wind tunnel dynamic test device

A high-speed wind tunnel and dynamic test technology, which is applied in aerodynamic tests, measuring devices, and machine/structural component testing, etc., can solve the problems of difficult dual-motor synchronous motion control, complex measurement and control system, and high cost, and achieve synchronization The effect of less difficulty in motion control, simple scheme and low cost

Inactive Publication Date: 2019-04-16
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

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Problems solved by technology

[0004] At present, the airfoil wind tunnel test device, such as the patent CN103852235B, adopts a single-motor single-end drive test device. Compared with the single-end drive, the double-end drive can reduce the elastic deformation of the end after being loaded; and the existing ones are Dual-motor double-terminal drive equipment, the synchronous motion control of dual motors is more difficult, and the accompanying measurement and control system is complex and costly

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  • Airfoil high speed wind tunnel dynamic test device
  • Airfoil high speed wind tunnel dynamic test device
  • Airfoil high speed wind tunnel dynamic test device

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[0033] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0034] Any feature disclosed in this specification, unless specifically stated, can be replaced by other alternative features that are equivalent or have similar purposes. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0035] Such as Figure 1-3 As shown, an airfoil high-speed wind tunnel dynamic test device of the present embodiment includes a driving device 1; 6 and turn window bottom plate 9.

[0036] The driving device 1 includes a motor 101 and a reducer 102. The motor 101 has a power of 8.2KW and a speed of 3000rpm. The reducer is a T-type precision reducer, which divides the driving torque of the motor into two, and transmits the torque to the wing through the crank linkage mechanism. Two ends of the type ...

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Abstract

The invention discloses an airfoil high speed wind tunnel dynamic test device which comprises a driving device. The driving device is connected with a driving shaft. A crank-link mechanism, a driven shaft, a balance and a rotating window bottom plate are symmetrically arranged on both ends of the driving shaft. The crank-link mechanism comprises an amplitude adjusting rod, a connecting rod and a balanced angle of attack converter. The amplitude adjusting rod is connected with both ends of the driving shaft. The amplitude adjusting rod is connected with the balanced angle of attack converter through the connecting rod. One end of the driven shaft is connected with the balanced angle of attack converter, and the other end is connected with the balance. After the driving device controls the rotation of the driving shaft, the crank-link mechanism drives the driven shaft to perform pitching oscillation. According to the invention, the airfoil high speed wind tunnel dynamic test device usessingle-motor double-end driving; double-end driving can reduce the elastic deformation of a loaded end compared with single-end driving; and compared with double-motor double-end driving, the scheme of single-motor double-end driving is simpler.

Description

technical field [0001] The invention relates to an airfoil high-speed wind tunnel dynamic test device, which belongs to the technical field of wind tunnel test equipment. Background technique [0002] Helicopters are widely used in civil and military fields. The dynamic characteristics of the helicopter rotor are closely related to the dynamic characteristics of the airfoil used. The dynamic characteristics of the airfoil have an important effect on the aerodynamic load of the rotor, the handling characteristics, the life of the rotor moving parts, and even the performance of the helicopter. influences. Therefore, to provide a reliable design basis for rotor design, it is necessary to carry out in-depth and detailed research on the dynamic characteristics of the airfoil; in addition, the research on the dynamic characteristics of the airfoil can also provide a basis for the flutter characteristics of the aircraft wing, horizontal tail, vertical tail and control surface. Res...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 张卫国李国强康洪铭孔鹏顾艺赵亮亮孙俊峰谢琦
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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