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Layout for inter-blade shimmy damper of rotor wing of helicopter

A technology for helicopter rotors and sway dampers, which is applied in the directions of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of complex rotor and body systems, and achieve the effects of improving dynamic stability and modal damping.

Inactive Publication Date: 2012-10-03
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Blade flapping, shimmy, and pitch change are inherently coupled, and the rotor and airframe systems become more complicated due to the presence of interblade dampers

Method used

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  • Layout for inter-blade shimmy damper of rotor wing of helicopter
  • Layout for inter-blade shimmy damper of rotor wing of helicopter
  • Layout for inter-blade shimmy damper of rotor wing of helicopter

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Embodiment Construction

[0018] The layout of the damper between the rotor blades proposed by the present invention to improve the dynamic stability of the helicopter will be described in detail below in conjunction with the accompanying drawings.

[0019] Such as figure 1 It is a schematic diagram of the inter-blade damper 1 of the traditional helicopter rotor system, the number of blades of the helicopter rotor blade 2 is greater than or equal to 3, the rotor blade 2 is fixedly connected to the hub 3, and the inter-blade damper 1 is connected to two adjacent blades Between the rotor blades 2, the inter-blade damper 1 is mainly used to increase the damping of the rotor system and improve its dynamic stability. figure 2 Shown is a schematic diagram of the layout of the helicopter rotor in the prior art. The inter-blade damper 1 is connected between two adjacent rotor blades 2. Specifically, the inter-blade damper 1 is connected to the front Between the blade trailing edge 8 of a rotor blade 2 and th...

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PUM

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Abstract

The invention discloses a layout for an inter-blade shimmy damper of a rotor wing of a helicopter, belonging to the field of the dynamic design of helicopters. According to the layout, the inter-blade shimmy damper is connected between the front edge of a previous rotor blade and the rear edge of a next rotor blade; and an included angle between a mounting support arm of the inter-blade shimmy damper and a propeller hub plane is located between -180 DEG and -150 DEG. With the adoption of the layout, the shimmy regressive lag modal damping of the rotor wing of the helicopter is increased, and the steady load of the inter-blade shimmy damper is reduced, so that the dynamic stability of a rotor wing system can be improved.

Description

technical field [0001] The invention belongs to the field of helicopter dynamics design, and in particular relates to a method for layout design of a helicopter rotor blade damper. It can be used in articulated, hingeless and bearingless rotor blade interblade damper designs for helicopter rotor blades. Background technique [0002] Helicopter is a very complicated dynamical system, not only the coupling between the rotor and the body, but also the flapping, shimmy and variable pitch coupling inside the rotor blades. In some cases, due to the existence of coupling between each other, different degrees of freedom will interact with each other and cause dynamic instability. For example, ground resonance and air resonance are the result of the coupling between the rotor and the body, and have become an important issue in helicopter design. [0003] In order to avoid the occurrence of dynamic instability, damping must be introduced, so the damper is introduced in the design of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/51
Inventor 向锦武任毅如罗漳平郭俊贤张亚军黄明其
Owner BEIHANG UNIV
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