Trailing edge winglet-based helicopter rotor noise active control wind tunnel test method

A helicopter rotor and wind tunnel test technology, applied in the field of wind tunnel test, can solve the problems that the test research has not been carried out effectively, and achieve the effect of improving the test quality

Active Publication Date: 2021-11-19
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

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Problems solved by technology

[0005] The relevant research on helicopter rotor noise control technology is still in its infancy in our country, and the experimental research in this area has not yet been effectively carried out.

Method used

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  • Trailing edge winglet-based helicopter rotor noise active control wind tunnel test method
  • Trailing edge winglet-based helicopter rotor noise active control wind tunnel test method
  • Trailing edge winglet-based helicopter rotor noise active control wind tunnel test method

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Embodiment

[0053] In order to study the influence of active control technology on helicopter rotor noise, the present invention provides a helicopter rotor noise active control wind tunnel test method based on trailing edgelets based on the existing large-scale aeroacoustic wind tunnel and a helicopter rotor acoustic test platform, The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0054] The wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets is mainly implemented based on a large acoustic wind tunnel, a helicopter rotor acoustic test platform and a trailing edgelet active control rotor model, such as Figure 2~Figure 4 shown.

[0055] Aeroacoustics wind tunnel is a low-turbulence and low-noise recirculation wind tunnel with dual-purpose open / closed test section. The wind tunnel is equipped with tail support devices, acoustic measurement systems and other equipment, and mainly carri...

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Abstract

The invention discloses a trailing edge winglet-based helicopter rotor noise active control wind tunnel test method, belongs to the technical field of wind tunnel tests, and mainly depends on an aviation acoustic wind tunnel, a rotor model acoustic test platform and a trailing edge winglet-based rotor active control test model. Research on influence of active control of the trailing edge winglet on rotor noise is carried out. According to the test method, the test process of rotor noise active control based on the trailing edge winglet is firstly standardized, and wind tunnel test research can be efficiently and safely carried out with high quality. Then the problem of safe operation of the rotor wing model in the active control process of the trailing edge winglet is solved. And finally, a rotor control mode, a trailing edge winglet active control mode and a noise data acquisition, analysis and transmission method in the test process of the rotor model with trailing edge winglet active control are established, so that the influence of trailing edge winglet active control on the noise characteristics of the helicopter rotor can be conveniently and accurately evaluated.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets. Background technique [0002] With its unique hovering, low-altitude and low-speed flight and good maneuverability, helicopters have played an irreplaceable role in modern economic construction, human life and modern military operations. The rotor is not only the lifting surface and control surface of the helicopter, but also the main source of external noise of the helicopter. With the flight speed, paddle disk load, and maneuverability of modern helicopters getting higher and higher, and the scope of use becoming wider and wider, the adverse effects of helicopter noise, especially rotor noise, are becoming more and more prominent. [0003] According to noise characteristics, helicopter rotor noise can be divided into: thickness noise, load noise, high-speed pulse noise,...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/08B64F5/60
CPCG01M9/02G01M9/08B64F5/60
Inventor 唐敏王畅尹欣繁车兵辉黄明其田斌杜旭董凌华罗欢
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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