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Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor

A technology of rotating azimuth and blades, which is applied in the field of rotor rotors to achieve the effect of avoiding coupling

Active Publication Date: 2012-12-26
国家宇航研究所(奥尼拉)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The disadvantage of this type of turntable is that it includes many mechanical parts that require frequent maintenance and inspection

Method used

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  • Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor
  • Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor
  • Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor

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Embodiment Construction

[0070] exist figure 1 The rotor rotor RO of a helicopter shown schematically in , comprises: a hub M driven in rotation about its axis Z-Z by a main gearbox (not shown); connected to the hub M. Thus, the blade P can rotate about the axis Z-Z at the rotational frequency Ω of said hub M.

[0071] Such as figure 2 As shown, a blade P according to the invention comprises an aerodynamic part A and a fixed part B shorter than said part A.

[0072] The fixing part B, for example with a cruciform section, cooperates with the fixing means L to fix the blade P to the hub M.

[0073] The aerodynamic part A comprises a top surface 2 and a bottom surface 3 forming a leading edge 4 at the front and a trailing edge 5 at the rear.

[0074] Near the leading edge 4 (see also image 3 ), the bottom surface 3 is divided into a front longitudinal part A1 comprising said front edge 4 and a rear longitudinal part A2 comprising said trailing edge 5 by a longitudinal cut 6, the longitudinal cut ...

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Abstract

The present invention relates to a rotary wing paddle, a rotor comprising at least two of such paddles and a method to implement such the rotor. Each paddle (P) has a torsion frequency around its span being substantially equal to a rotation frequency ([Omega]) of the rotor; torsion means twist to the rotation frequency of the rotor (RO), in synchronization with said rotation; and comprising a material configured to dampen the torsion resonance, so as to avoid the resonance divergence.

Description

technical field [0001] The present invention relates to rotor rotors, more particularly rotor rotors for helicopters, and blades of such rotors. Background technique [0002] It is well known that the blades of a rotor rotor are controlled in collective pitch and cyclic pitch. [0003] The collective pitch allows the stable flight of the helicopter by positioning it so that the incidence of all the blades is equal to the axis of rotation of said rotor, and then blending with the drive axis of its mounts, said collective pitch resulting in a vertical And balance the total lift of the helicopter main body. [0004] Hitherto, cyclic pitch allows the total lift to be tilted relative to the vertical by positioning the angle of attack of each blade according to the azimuth, thereby moving the helicopter in question. [0005] For collective and cyclic pitch control, the rotor usually includes a mechanism called a cyclic plate, which is mounted on the frame of the rotor and includ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/46B64C27/51
CPCB64C27/473B64C27/72Y02T50/34B64C2027/7216Y02T50/30B64C27/46B64C27/32B64C27/54
Inventor H·梅西耶德罗什特L·比沙尼埃D·若利J·迪帕P·勒孔特
Owner 国家宇航研究所(奥尼拉)
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