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Equal load transmission mechanism and helicopter reducer

A technology of transmission mechanism and reducer, which is applied in the direction of transmission device, gear transmission device, aircraft, etc., and can solve the problems of poor load equalization effect of split torsion transmission mechanism and unable to realize power average distribution.

Active Publication Date: 2020-08-25
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a load equalizing transmission mechanism and a helicopter speed reducer to solve the technical problem that the existing split torque transmission mechanism has poor load equalizing effect and cannot realize power equal distribution

Method used

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  • Equal load transmission mechanism and helicopter reducer

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Embodiment Construction

[0022] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0023] figure 1 It is a structural schematic diagram of the load equalizing transmission mechanism of the preferred embodiment of the present invention.

[0024] Such as figure 1 As shown, the load equalizing transmission mechanism of this embodiment is used to split and transmit the output power of the engine to the parallel gears for confluence. The first output gear assembly and the second output gear assembly meshingly connected and the conjugate gear pair installed on the input gear structure 1 and meshingly connected with the first output gear assembly and the second output gear assembly; the conjugate gear pair includes the input The first sun gear shaft 2 and the second sun gear shaft 3 of the coaxial assembly of the gear structure 1 are installed on the...

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Abstract

The invention discloses a uniformly loaded transmission mechanism and a helicopter reducer. The uniformly loaded transmission mechanism comprises an input gear structure connected with the output shaft of an engine, a first output gear module and a second output gear module which are mounted inside a gearbox and connected in an engaged mode with a paralleling gear, and a conjugate gear pair mounted on the input gear structure and engaged with the first output gear module and the second output gear module; the conjugate gear pair comprises a first sun gear shaft, a second sun gear shaft and a planetary gear which are coaxially assembled; the input end of the first sun gear shaft and the input end of the second sun gear shaft are simultaneously engaged with the planetary gear; the planetarygear can self-adaptively adjust the angular position deviation between the first sun gear shaft and the second sun gear shaft to uniformly deliver the input power of the input gear structure to the first output gear module and the second output gear module.

Description

technical field [0001] The invention relates to the technical field of helicopter reducers, in particular to a load-sharing transmission mechanism for splitting and transmitting the output power of an engine to a parallel gear for confluence, and furthermore, to a helicopter reducer. Background technique [0002] The transmission type of the helicopter reducer is constantly improving. In the traditional helicopter reducer, the power of the engine is transmitted in a single way from input to output, and is decelerated step by step. axis. But this traditional configuration is only suitable for the main reducer of light and small tonnage helicopters. Once the transmission power increases, the size of the reducer will increase, the quality will increase, and the vibration and noise will also increase. [0003] In the prior art, by splitting the power in two ways and then transmitting it to the split torque transmission mechanism on the parallel gear, the meshing force on each ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16H1/28F16H1/36B64C27/12
CPCB64C27/12F16H1/2809F16H1/36
Inventor 张志龙蒋燕英
Owner AECC HUNAN AVIATION POWERPLANT RES INST