Layout method for shimmy damper

A layout method and shimmy reducer technology, applied in the direction of instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as large speed fluctuations, structural life of the transmission system, hidden dangers of helicopter flight safety, and collisions of transmission gears

Active Publication Date: 2015-10-28
CHINA HELICOPTER RES & DEV INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, due to the symmetrical layout, the shimmy absorber does not provide damping and stiffness to the collective shimmy of the rotor, so it is necessary to add a band-stop filter to the engine control software system to prevent the occurrence of torsional vibration instability.
Although the use of a band stop filter can prevent the engine control system from diverging during the control process of the rotor speed, but because there is almost no shim

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  • Layout method for shimmy damper
  • Layout method for shimmy damper
  • Layout method for shimmy damper

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Embodiment Construction

[0032] The layout method of the shock absorber involved in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0033] The layout method of the shimmy reducer of the present invention comprises the following steps:

[0034] (1) A layout method for asymmetric inter-blade shimmy dampers is proposed through conventional layout analysis;

[0035] (2) Establish the dynamic model of the asymmetric interblade shimmy damper;

[0036] (3) Obtain the damping factor of the shimmy stiffness, and design the parameters of the asymmetric interblade shimmy damper.

[0037] In this embodiment, specifically,

[0038] The first step: according to the characteristics of the installed rotor, establish a coordinate system describing the asymmetric interblade layout shimmy damper (between the Kth piece and the K+1th piece). Its structure can be simplified to this form, see figure 2 . Define the origin of the coordinate system as the c...

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Abstract

The present invention relates to a layout method for a shimmy damper and belongs to the field of helicopter kinetics physical design, comprising: performing dynamics modeling analysis on a layout scheme of the yaw damper; taking a hub center as the origin of a coordinate system and an extending direction of a blade K as X axis; establishing a coordinate system describing asymmetry in-blade layout of the blade K and a blade K+1 of the yaw damper; establishing a yaw damper-to-blade damping torque formula in the new scheme: a collected damping torque formula and a periodic damping torque formula; and according to a stiffness damping of yaw damper that needs to be satisfied, obtaining an optimal geometrical parameter. The present invention is applicable to blade yaw damper design of a machine under development or other helicopter models, is capable of meeting the requirements of eliminating both ground resonation and torsional vibration instability, and can improve the rotor yaw vibration damping and stiffness.

Description

technical field [0001] The invention belongs to the field of helicopter dynamic structure design, and in particular relates to a layout method of a novel helicopter damper and the design of parameters thereof. Background technique [0002] There are usually two layouts of the shimmy reducer, one is the independent layout, and the other is the symmetrical interleaf layout. [0003] For the independent layout, since the distance from the axis of the shimmy damper to the vertical hinge is limited by the space of the propeller hub, the damping and stiffness of the shimmy damper must be increased in order to achieve the required shimmy damping and stiffness. The dynamic load of the propeller hub, which is the deficiency of the independent layout of the shimmy reducer. However, the independent layout of the shimmy absorber can provide the same value of damping and stiffness for the rotor periodic and collective shimmy, and can meet the design requirements of eliminating ground re...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 凌爱民朱艳
Owner CHINA HELICOPTER RES & DEV INST
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