An Experimental Device for Reducing Helicopter Rotor Thickness Noise
A helicopter rotor and experimental device technology, applied in the field of aerodynamic noise, can solve the problems of high facility requirements, complex control mechanism, and difficult implementation methods, and achieve the effect of reducing rotor thickness noise and reducing the difficulty of experiments
Active Publication Date: 2020-04-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
At present, there are few experiments on noise reduction of rotor thickness noise at home and abroad, and the active trailing edge flap (ACF) is mainly used for active control of noise, which has high requirements for facilities, difficult implementation methods, and complicated control mechanism.
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[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0023] The purpose of the present invention is to provide a kind of experimental device for reducing the thickness noise of helicopter rotor, to solve the problems in the above-mentioned prior art, so that the experiment of helicopter rotor thickness noise can be carried out in the acoustic wind tunnel, and reduce the difficulty of experiment implementation.
[0024] In order to make the above objects, features and advantages of the present invention more compr...
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The invention discloses an experimental device used for reducing helicopter rotor thickness noise. The device comprises a blade, a power device and a resistance exciter, wherein the power device and the resistance exciter are arranged in the blade and are in transmission connection, and the resistance exciter is provided with a resistance sheet which can be driven by the power device to extend outof the blade. The experimental device can be used for conducting a rotor thickness noise reduction experiment in an acoustic wind tunnel, the resistance sheet is driven by the power device to extendout of the blade, the windward area of the resistance exciter is changed, the noise of the resistance exciter is changed, so that additional noise is generated and used for reducing the rotor thickness noise, the experiment difficulty is reduced, and technical support is provided for reducing the helicopter rotor thickness noise.
Description
technical field [0001] The invention relates to the technical field of aerodynamic noise, in particular to an experimental device for reducing the thickness noise of a helicopter rotor. Background technique [0002] The rotor is an important part of the helicopter. During the flight of the helicopter, the rotor plays a dual role of generating lift and pulling force. Not only that, the rotor also plays a role similar to the aileron and elevator of an airplane. The rotor consists of a hub and several blades. The hub is mounted on the rotor shaft, and the blades shaped like slender wings are connected to the hub. One of the main vibration sources of a helicopter is the rotor, and the noise of the rotor is greater than that of the engine. In a sense, the noise of the helicopter rotor limits its further extensive application to a large extent. Rotor thickness noise is produced by the blades periodically displacing the air. It has the characteristics of low frequency and propaga...
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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 史勇杰董凌华周金龙贺祥徐国华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS