A bulge design method for suppressing high-speed impulse noise of helicopter rotor

A helicopter rotor and high-speed pulse technology, which is applied in design optimization/simulation, sustainable transportation, geometric CAD, etc., can solve problems such as bulging design methods that have not been studied by anyone, and achieve simple structure, shock wave weakening, and convenient technical implementation.

Active Publication Date: 2022-02-18
XIAMEN UNIV
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Problems solved by technology

At the same time, no one has studied the bulge design method for the suppression of high-speed impulse noise of the helicopter rotor.

Method used

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  • A bulge design method for suppressing high-speed impulse noise of helicopter rotor
  • A bulge design method for suppressing high-speed impulse noise of helicopter rotor
  • A bulge design method for suppressing high-speed impulse noise of helicopter rotor

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Embodiment Construction

[0029] The following examples will be further described with reference to the accompanying drawings.

[0030] The rotor model of the embodiment of the present invention is as figure 1 As shown, the embodiment of the present invention proposes a method of suppressing a rotor high-speed pulse noise in a rotor bladed pin design drum bag, and the specific embodiment includes the following steps:

[0031] 1) Determine the design point status of the rotor blade drum bag

[0032] The rotor high-speed pulse noise occurs on the hippower of the rotor, the forward paddle tip speed is a superposition of the rotor itself rotational speed and the helicopter front speed. The design point state of the rotor pip drum bag of the present invention is a reference, m = (v + ωr) / A0, where V is a helicopter speed, ω is a rotor rotation angle velocity of the helicopter. , R is the radius of rotor blades 2, and A0 is a sound speed. The design point status of the rotor blade drum bag is m = 0.9-1.05.

[...

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Abstract

A bulge design method for suppressing high-speed impulse noise of a helicopter rotor relates to the noise of a helicopter rotor. The method comprises the following steps: 1) determining the state of the design point of the rotor blade tip bulge; 2) determining the position of the forward tip shock wave of the rotor; 3) determining the position and parameters of the triangular conical shock wave; 4) discretely slicing the triangular conical shock wave , find the parameters on each kissing plane shock line; 5) solve the flow field parameters behind each kissing plane shock line according to the characteristic line theory, and determine the bump line in the kissing plane; 6) generate three-dimensional Drum profile. Using the kiss-cut theory and the characteristic line method to design the bulge on the tip of the rotor can not only weaken the shock wave, eliminate the "delocalization" phenomenon of the shock wave, but also suppress the high-speed pulse noise of the rotor. In addition, the proposed bulge design method has a simple structure, convenient technical implementation, and does not require an additional complicated control system. It is a potential high-speed impulsive noise suppression scheme for rotors.

Description

Technical field [0001] The present invention relates to helicopter rotor noise, and more particularly to a drum kit design method for suppressing helicopter rotor high speed pulse noise. Background technique [0002] Compared with fixed-wing aircraft, the helicopter has a wide range of advantages such as vertical, high mobility, and air hover, and has been widely used in military and civilian areas. However, the noise of the helicopter is very large, and for military helicopters, noise will greatly affect its stealth performance, which will affect the living ability of the helicopter. For civil helicopters, noise will affect passengers ride comfort. Therefore, noise problem is increasingly a problem of focus on helicopter design, and has important significance for helicopter noise reduction research. [0003] Rotor noise is the main source of helicopter noise, which can be divided into rotary noise and broadband noise, high-speed impulsive (HSI) noise, paddle-vortex intection, bv...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20G06F30/17
CPCY02T90/00
Inventor 陈荣钱程佳铭柳家齐林威尤延铖
Owner XIAMEN UNIV
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