A helicopter rotor system capable of active shimmy

A helicopter rotor and active pendulum technology, applied in the field of helicopter rotor system, can solve the problems of limited blade adaptability and inability to realize large-scale shimmy motion, reduce forward resistance and backward stall tendency, and reduce fatigue load , Improve the effect of flying speed

Inactive Publication Date: 2015-09-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This traditional shimmy mechanism is limited by damping and cannot achieve large-scale shimmy motion, which makes the blade's ability to adapt to various extreme flight conditions limited.

Method used

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  • A helicopter rotor system capable of active shimmy
  • A helicopter rotor system capable of active shimmy
  • A helicopter rotor system capable of active shimmy

Examples

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Embodiment Construction

[0020] Please refer to Figure 1 to Figure 3 As shown, the active shimmy helicopter rotor system of the present invention includes a shimmy control mechanism, a universal joint link mechanism, a two-degree-of-freedom plane parallel restraint mechanism and an automatic tilter.

[0021] Please refer to figure 1 As shown, the automatic tilter includes a fixed ring 2, which can tilt in any direction and can also perform vertical displacement movement. A moving ring 3 is arranged on the fixed ring 2, and four moving ring connecting rods arranged in the center are arranged on it. 7. The inner end of the moving ring connecting rod 7 is hinged with a variable pitch rod 6, and the pitch variable rod 6 is connected to the connecting rod of the blade 1 through a pitch variable control hinge 13.

[0022] The propeller hub 12 is arranged on the top of the main shaft 4, and the propeller hub 12 is hinged with a swing hinge connector 11 through the swing hinge 5, and the swing hinge connect...

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PUM

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Abstract

The invention discloses a helicopter rotor system capable of actively shimmying. The helicopter rotor system comprises a shimmying control mechanism, a universal joint connecting rod mechanism, a two-degree-of-freedom planar parallel constraint mechanism and an automatic inclinator, wherein the universal joint connecting rod mechanism transfers the rotation motion of a main shaft to a shimmying control table; the two-degree-of-freedom planar parallel constraint mechanism controls the plane position of the shimmying control table, so that the shimmying control table eccentrically rotates relative to the main shaft, and the aim of periodically controlling the shimmying amplitude of blades is achieved through a sliding block and a shimmying control connecting rod. By actively controlling the shimmying motion of the blades, the phase and amplitude of a shimmying motion period of the blades can be controlled. By virtue of the mechanism, the angular speed of advancing blades is greatly decreased, the angular speed of retreating blades is greatly increased, the advancing resistance and retreating stall of the blades in a high-speed flight state of a helicopter are effectively reduced, the fatigue load of the blades during alternation of advancing and retreating states is reduced, the helicopter rotor system actively adapts to various flight states of the helicopter, and the extreme flight speed is increased.

Description

Technical field: [0001] The invention relates to a helicopter rotor system that can actively vibrate, which belongs to the field of helicopter rotor structure design. Background technique: [0002] As we all know, when the helicopter is flying forward, the helicopter blades will experience two states of forward and backward in one rotation cycle. When the blade moves forward, the relative speed of the blade and the air is higher than the linear velocity caused by the rotation itself; conversely, when the blade moves backward, the relative speed of the blade and the air is lower than the linear velocity caused by the rotation itself , so that the lift generated on both sides of the rotor will be uneven. Therefore, in order to compensate for the uneven lift force on the left and right and reduce the fatigue of the blade, a flapping hinge is installed at the root of the blade to allow the blade to generate flapping motion adaptively during the forward and backward state altern...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/32B64C27/52
Inventor 李洪双夏爽马元卓王宇郭麦萍赵安龙
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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