Method for adjusting vibration in rotating surface of rotor hub of a helicopter

A helicopter rotor and vibration adjustment technology, which is applied to rotorcraft, motor vehicles, aircraft, etc., can solve outstanding problems and achieve high efficiency

Active Publication Date: 2020-02-14
HARBIN
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003]Because the lift of the helicopter comes from the rotor system, the rotating blades bring periodic vibration problems, so the problem of helicopters is more prominent than that of fixed-wing aircraft

Method used

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  • Method for adjusting vibration in rotating surface of rotor hub of a helicopter
  • Method for adjusting vibration in rotating surface of rotor hub of a helicopter
  • Method for adjusting vibration in rotating surface of rotor hub of a helicopter

Examples

Experimental program
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specific Embodiment

[0031] see figure 2 , taking the specific vibration adjustment method of the rotor hub with four blades as an example:

[0032] After testing, the initial vibration value of the rotor hub is 0.9ips, and the phase is 5:28 (clock notation), which is represented by the "T" point at figure 2 According to the figure, the rotation direction of the rotor of this type of aircraft is clockwise when viewed from above.

[0033] The damper of the propeller arm 4 that lags behind the vibration phase and is closest to the 90° phase difference from the vibration phase can be selected for adjustment; the adjustment method is: the dynamic stiffness increases, and the increase is eccentric force / average damper displacement;

[0034] Or select the damper of propeller arm 2 that is ahead of the vibration phase and has the closest 90° phase difference to the vibration phase for adjustment; the adjustment method is: the dynamic stiffness is reduced, and the reduction is eccentric force / average d...

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Abstract

The invention belongs to the technical field of helicopter dynamics, and relates to a method for adjusting vibration in a rotating surface of a rotor hub of a helicopter. The method comprises two parts, specially, the adjustment of a hub shimmy damper and the adjustment of a hub weight stack are carried out, when the vibration eccentric force in the rotating surface of the rotor hub reaches 60-100kg or the speed value of the vertical vibration in a cabin reaches 0.6-1 IPS, and the hub shimmy damper is adopted to adjust; when the vibration eccentric force in the rotating surface of the rotor hub is less than 60 kg or the speed value of the vertical vibration in the cabin is less than 0. 6g IPS, and the hub weight stack is adopted to adjust. According to the method, the defects of a currentsingle adjustment mode can be overcome, and the vibration environment of the helicopter is ensured to be kept at a comfortable level.

Description

technical field [0001] The invention belongs to the technical field of helicopter dynamics, and relates to a method for adjusting vibration in the rotation plane of a helicopter rotor hub. Background technique [0002] The helicopter rotor system is mainly composed of blades and hubs. The hub generally consists of a central piece and hub arms, the number of hub arms is the same as the number of blades. [0003] Since the helicopter lift comes from the rotor system, the rotating blades bring periodic vibration problems, so the problem of helicopters is more prominent than that of fixed-wing aircraft. In order to reduce the vibration load of the helicopter and at the same time provide a comfortable environment for the occupants, it is necessary to reduce the vibration of the rotating parts of the helicopter. [0004] The helicopter rotor system generates lift through high-speed rotation. The difference in the mass distribution of the rotor system parts will cause the imbalan...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/51
CPCB64C27/51Y02T90/00
Inventor 杨库李五洲刘政高世军李麟赵德杨于馨皓胡伟刘博奚宽阳李野
Owner HARBIN
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