High-speed wind tunnel large attack angle pitching dynamic stalling test device

A high-speed wind tunnel and dynamic stall technology, applied in aerodynamic tests, measuring devices, testing of machine/structural components, etc., can solve problems such as single-degree-of-freedom dynamic simulation tests

Inactive Publication Date: 2016-07-27
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
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  • Application Information

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Problems solved by technology

However, at home and abroad, the multi-degree-of-freedom dynamic simulation test has only been successfully realized in the low-speed wind tunnel. The condition that the aircraft model is equal to or

Method used

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  • High-speed wind tunnel large attack angle pitching dynamic stalling test device
  • High-speed wind tunnel large attack angle pitching dynamic stalling test device

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Embodiment Construction

[0017] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0018] Such as figure 1 , figure 2 As shown, the high-speed wind tunnel pitching dynamic stall test device of the present invention includes a motor drive mechanism, a flywheel and a synchronous transmission gear set, a connecting rod 12, a swing lug 15, a rotating window 16, a main drive wheel 17, and a rocker beam And the balance rod system, the motor drive mechanism drives the flywheel and the synchronous transmission gear set to drive the main drive wheel 17 to rotate, and the connecting rod 12 fixed on the main drive wheel 17 drives the reciprocating motion of the revolving window 16, and is fixedly connected to the revolving window 16 The swing lug 15 on the top is connected with the rocker arm beam and the balance rod system, and the rocker arm beam and the balance rod system drive the model 14 to perform pitching motion at a large angle of attack;

[0019]...

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Abstract

The present invention provides a high-speed wind tunnel high-angle-of-attack pitching dynamic stall test device. The device is driven by a motor, and the flywheel is driven to rotate through a belt drive wheel. The central axis of the flywheel drives a synchronous transmission gear set to transmit kinetic energy to the main drive. The four-link motion system consists of the main drive wheel, the connecting rod and the rotating window, which realizes the conversion of the flywheel rotation into the reciprocating oscillation of the rotating window, and then drives the fixed aircraft model to achieve pitching motion at a large angle of attack. The high-speed wind tunnel pitching dynamic stall test device with large angle of attack of the present invention overcomes the difficulties of strong vibration during operation of the existing high-speed wind tunnel, small space in the test section, low structural response frequency of the test section, and large environmental noise, etc., and can provide The dynamic aerodynamic test results of the aircraft model under the conditions of large angle of attack (up to 75°), large amplitude (‑15°~75°), and high frequency (0~6Hz) are used for aerodynamic optimization design, flight quality evaluation, and control rate design Provide key test basis.

Description

technical field [0001] The invention belongs to the technical field of high-speed wind tunnel tests, and in particular relates to a high-speed wind tunnel high-angle-of-attack pitch dynamic stall test device. Background technique [0002] High maneuverability and high agility are necessary technical and tactical indicators for modern high-performance fighters and advanced tactical missiles. For example, fourth-generation fighters require that they can achieve post-stall maneuvering flight within the range of the maximum controllable flight angle of attack a=60°, and It has good longitudinal / lateral control characteristics; while advanced tactical missiles have higher requirements for large angle of attack maneuverability, and must have the ability to launch at large off-axis angles, that is, to achieve an angle of attack of 60° in a very short time after launch separation The turning, flight process and attack target are also completed through fast maneuvering. [0003] Aer...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01M9/04
CPCG01M9/00G01M9/04
Inventor 李其畅伍开元黄存栋王涛赵忠良杨海泳刘维亮李玉平马上
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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