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Wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets

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

Active Publication Date: 2022-01-25
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

AI Technical Summary

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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  • Wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets
  • Wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets
  • Wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets

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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 wind tunnel test method for active control of helicopter rotor noise based on trailing edgelets, which belongs to the technical field of wind tunnel tests and mainly relies on aeroacoustic wind tunnels, a rotor model acoustic test platform and a trailing edgelet-based Rotor active control test model, to carry out research on the influence of trailing edgelet active control on rotor noise. This test method first standardizes the test process of active control of rotor noise based on the trailing edge winglet, and can carry out wind tunnel test research with high efficiency, high quality and safety. Then it solves the problem of safe operation of the rotor model during the active control of the trailing edgelet. Finally, a rotor control method, trailing edgelet active control method, noise data acquisition, analysis and transmission method during the rotor model test with trailing edgelet active control are established, which can conveniently and accurately evaluate the trailing edgelet The effect of active control on the noise characteristics of a helicopter rotor.

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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Patent Type & Authority Patents(China)
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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