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Tilting mechanism and sealing mechanism

A technology of sealing mechanism and tilting mechanism, which is applied in the aviation field, can solve problems such as difficult sealing and inability to ensure the reliability of liquid lubricated sealing, and achieve the effect of reducing structure and simple structure

Active Publication Date: 2017-01-04
王泽民
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Provide a sealing mechanism: solve the problem that due to the coaxial line, the structural characteristics of the tilting mechanism, there are sealing difficulties, and the reliability of the liquid lubrication seal cannot be ensured

Method used

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  • Tilting mechanism and sealing mechanism
  • Tilting mechanism and sealing mechanism

Examples

Experimental program
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Effect test

Embodiment 1

[0025] A tilting mechanism and a sealing mechanism, comprising: an engine FJ and a rotor Y, the engine FJ is connected to a support 1, the support 1 is connected to a tilting arm 2, and the tilting arm 2 is connected to The connection of the support 1 is a gearbox C, and the gearbox C is connected to the sealing mechanism J.

Embodiment 2

[0027] A tilting mechanism and a sealing mechanism described in Embodiment 1, a horizontal shaft 8 is installed in the gearbox C, and a power transition bevel gear 5 and bearings 9, 10, 11 are installed on the horizontal shaft 8 , 12, the power bevel gear 5 below is connected to the power bevel gear 4, the power bevel gear 4 is connected to the engine power shaft 3, the power bevel gear 5 is connected to the power output bevel gear 6, and the The power output bevel gear 6 is connected to the power output shaft 7, the power output shaft 7 is connected to the tilt arm 2 through the bearings 13, 14, and the power output shaft 7 is connected to the rotor Y.

Embodiment 3

[0029] Embodiments 1 and 2, a tilting mechanism and a sealing mechanism, the engine power shaft 3 has a bearing gland G, and the front end of the bearing gland G is in a convex shape 15, and the There is an O-ring groove 17 on the convex shape 15 of the garden, and an O-ring 16 is set in the described sealing groove.

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Abstract

The invention provides a tilting mechanism and a sealing mechanism. A traditional tilt-rotor aircraft employs a structure mode of integral tilting of an engine and rotor wings, and the structure mode has disadvantages in practice in spite of the advantage of simple and direct structure; a conventional tilting mode which arranges an engine and a tilting structure in a parallel and non-coaxial manner can overcome the disadvantages of the mode of integral tilting of the engine and the rotor wings and overcome problems in sealing of the tilting structure, but the biaxial arrangement manner which allows the engine and the tilting structure to be separated also has disadvantages in practice since a transverse power transmission structure has to be additionally arranged. The invention provides a coaxial arrangement manner for an engine and a tilting structure to overcome defects caused by existence of the transverse power transmission structure in the non-coaxial arrangement manner. The invention also provides a sealing mechanism to overcome problems in sealing of the coaxially arranged tilting structure.

Description

[0001] Technical field: [0002] The invention relates to the aviation field, in particular to: a tilting mechanism and a sealing mechanism applied to the tilting mechanism. [0003] Background technique: [0004] At present, only the U.S. Osprey v-22 and subsequent models (V-280) can be used in the field of aviation. The vertical take-off and landing of the V-22 is achieved by pulling up the body from a horizontal state to a state of upward deflection of 90 degrees (greater than 90 degrees) through two engines installed at the ends of the double wings. Although the overall tilting of the engine and the rotor has the advantages of simple, direct and efficient structure, at the same time, due to the overall tilting of the engine and the rotor, there are: increased control difficulty, its deflection support structure, deflection control mechanism, and the volume of related structures, There are some practical shortcomings such as relatively high weight, vibration of the engine a...

Claims

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Application Information

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IPC IPC(8): B64C27/52B64D35/00F16H57/029
Inventor 王泽民
Owner 王泽民
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