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Design method for preventing ground resonance of bearingless rotary-wing helicopter

A technology of rotor helicopter and design method, which is applied to ground installations, aircraft parts, transportation and packaging, etc., can solve the problems of no ground resonance research, no test verification and model development, etc., and achieves ground resonance prevention and good engineering application. performance, improve damping efficiency

Active Publication Date: 2015-07-22
CHINA HELICOPTER RES & DEV INST
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In the existing technology, the domestic research on the resonance of the hingeless rotor in the air was carried out in the 1980s. The configuration of the hub is simple, there is no multi-channel force transmission, no ground resonance research has been carried out, and no test verification and model development have been carried out.

Method used

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  • Design method for preventing ground resonance of bearingless rotary-wing helicopter
  • Design method for preventing ground resonance of bearingless rotary-wing helicopter
  • Design method for preventing ground resonance of bearingless rotary-wing helicopter

Examples

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Effect test

Embodiment 1

[0026] The hub configuration and the layout design of the damper to improve the damping of the damper. figure 1 It is a bearing-less rotor hub configuration and damper design layout. The inner end of the flexible beam is fixed to the hub of the propeller, and its vibration rigidity is very high. The vibration and swing rigidity of the middle part of the flexible beam are low. The outer end of the flexible beam is directly fixed to the outer end of the sleeve, and the outer end of the sleeve is also directly fixed to the blade . In the middle of the flexible beam, a rod is hinged with the flexible beam, one end of the damper is fixed on the outside of the sleeve, and the other end is connected with the rod to form the slewing direction stiffness damping of the damper in series with the sleeve. The deformation of the sleeve and the flexible beam at the outer end creates a displacement difference where the damper is installed, which is the deformation of the damper to provide sti...

Embodiment 2

[0038] Similar to Embodiment 1, the difference is that the hub design configuration to improve shimmy damping also includes, such as figure 2 The shown another design configuration of the hub for improving the shimmy damping can significantly improve the shimmy damping by laying a section of damping material in the chord direction of the flexible beam due to the large deformation of the minimum shimmy stiffness section of the flexible beam.

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Abstract

The invention relates to a design method for preventing ground resonance of a bearingless rotary-wing helicopter, in particular to a design method for improving damping efficiency of a yaw damper, and belongs to the helicopter dynamics design technique. The propeller hub structure for improving damping of the yaw damper and the layout design of the yaw damper are adopted for improving the damping efficiency of the yaw damper. The frequency and damping of a helicopter body on a skidding undercarriage are designed by increasing the difference between rigidity and damping. The yaw damper and aeroelasticity are analyzed and designed by designing parameter influence. The design method can be applied to preventing ground resonance of the bearingless rotary-wing helicopter, and has good engineering applicability, and the aim of preventing ground resonance can be achieved in the design stage.

Description

Technical field [0001] The invention belongs to helicopter dynamics design technology and relates to a design method for preventing ground resonance of a bearingless helicopter. Background technique [0002] The design measures of the classic articulated rotor helicopter to prevent ground resonance include two aspects: frequency and damping design. The frequency design requires the configuration of the rotor swing back frequency Ω-ω ζ And the natural frequency ω of the body on the landing gear Fi (i=1,2,...,6), so that Ω-ω ζ With ω Fi The rotor speed zone that is close to and equal is designed at the desired position; and the damping design requires that the rotor hub configuration, damper layout and damping characteristics, and landing gear system damping design eliminate ground resonance instability within the rated speed, and It has sufficient damping margin and at the same time provides sufficient damping to control the lower boundary speed of the unstable speed zone of grou...

Claims

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Application Information

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IPC IPC(8): B64F5/00
Inventor 凌爱民朱艳钱峰程起有
Owner CHINA HELICOPTER RES & DEV INST
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