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Damping device and plane rotator system comprising the same

A damping device and damper technology, applied in the field of damping devices, can solve the problems of high strength, technical complexity, excessive external temperature sensitivity, etc., and achieve the effects of preventing cavitation, low temperature sensitivity, and simple structure

Inactive Publication Date: 2009-09-09
HUTCHINSON SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main disadvantages of this solution, which is very simple to implement, are on the one hand the high stiffness of the device relative to low excitation amplitudes and on the other hand its excessive sensitivity to external temperatures
Although these devices work relatively well, they still have the disadvantage of introducing a certain degree of technical complexity, which additionally requires a lot of maintenance

Method used

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  • Damping device and plane rotator system comprising the same
  • Damping device and plane rotator system comprising the same

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Embodiment Construction

[0026] Such as figure 2 As shown, the damping device 101 according to the invention, specially designed to damp the traction mode of a helicopter blade, essentially comprises:

[0027] - a radially outer frame 102 intended to be coupled to a helicopter blade (not shown), for example via a first joint 103, and comprising a generally cylindrical portion 102a which is positioned at the center of the device 101 is extended at the first end 104 near the first joint 103 by a converging frusto-conical portion 102b;

[0028] - a radially inner tubular element 105 mounted coaxially to the frame 102 and intended to be coupled to a helicopter rotor (not shown), for example via a second joint 106;

[0029] - an elastomer damper 107 of annular cross-section fixedly mounted to the frame 102 and the inner element 105; and

[0030] - two hydraulic chambers, the working chamber 108 and the compensation chamber 109, which are respectively formed at the first end 104 of the device 101 and ins...

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Abstract

The present invention relates to a damping device specially used for forming a drag-mode damper for a helicopter blade, and is incorporated in an aircraft rotor system. The present invention also relates to a plane rotator system comprising the sam. This damping device comprises: an external frame intended to be coupled to a first rotating element, and a radially internal element mounted coaxially to the frame and intended to be coupled to a second rotating element; at least one elastomer damper of annular cross section mounted fixedly to the frame and to the internal element; and a working chamber bounded by the frame and by the damper and communicating with a compensation chamber bounded by a highly deformable flexible member mounted coaxially to the internal element. The working chamber is formed at a first end of the device and communicates with the compensation chamber via a porous structure surmounting an end opening of the flexible member, which member is mounted in the internal element.

Description

technical field [0001] The present invention relates to a damping device, in particular for forming a traction mode damper for a helicopter blade, and to a rotorcraft rotor system, such as a helicopter rotor, comprising such a device. The invention is applied in a general manner in dampers not only for the aerospace sector, but also for other industrial sectors involving angular oscillations around joints close to the rotor. Background technique [0002] In a known manner, the lift rotor of a helicopter has an articulated hub, which is provided for each blade with a joint called a drag hinge, which is located around an axis perpendicular to the plane in which the blades lie, and which is said The paddles provide a degree of freedom of angular oscillation in the plane of rotation of the rotor. Trying to provide each blade with an elastic return towards its mean angular position about the joint, thereby enabling adjustment of the natural frequency of the ensemble of each blad...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16F15/16F16F13/10B64C27/51
CPCF16F13/18F16F13/16B64C27/51F16F13/1463
Inventor 埃尔夫·里歇尔·德·福尔热让-皮埃尔·乔尔奇克
Owner HUTCHINSON SA
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