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Composite propeller blade and blade root connecting structure

A technology of blade root connection and composite material, applied in propellers, aircraft parts, transportation and packaging, etc., can solve the problems of poor molding and assembly process, heavy weight, complex structure, etc., to achieve reliable connection, light weight, and improve economic benefits. Effect

Pending Publication Date: 2018-05-18
AVIC HUIYANG AVIATION PROPELLER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main disadvantages of this structure are complex structure, heavy weight, poor molding and assembly process

Method used

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  • Composite propeller blade and blade root connecting structure
  • Composite propeller blade and blade root connecting structure
  • Composite propeller blade and blade root connecting structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0017] Below in conjunction with accompanying drawing, the present invention is further described:

[0018] A connection structure of composite material and metal blade root, see image 3 . The connection structure is composed of metal blade root 1, carbon girder 2, blade root winding fiber 3, skin 4 and foam 5. The metal blade root 1 plays the role of connecting the metal hub and the composite material blade, the carbon girder 2 is spread on the surface of the metal blade root 1 to bear the load generated during the propeller operation, and the foam 5 is used as the sandwich core of the structure to withstand shearing Load, blade root winding fiber 3 fixes the carbon girder 2 on the metal blade root, and the skin 4 wraps all parts into a whole. The arc shape 6 of the metal blade root 1 and the blade root winding fiber 7 work together to fix the carbon girder 2; in order to prevent the composite material blade from rotating relative to the metal blade root during assembly, d...

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Abstract

The invention belongs to mechanical structure design, and relates to a composite propeller blade and blade root connecting structure. According to the composite propeller blade and blade root connecting structure, in order to realize reliable connection between carbon girders of composite main force-bearing parts and a metal blade root, first the carbon girders are laid on the metal blade root, and the carbon girders are composed of a plurality of layers of carbon fiber one-way cloth and satin cloth; and then carbon fiber is wound around the arc-shaped surface of the metal blade root, so thatthe carbon girders and the metal blade root are fixed together. When a propeller rotates, the centrifugal load and the pneumatic load brought by rotating are transmitted to the blade root, and the radian appearance of the metal blade root and the fiber are wound so that disengaging of the carbon girders can be prevented, and then damage to the composite propeller blade is avoided. The number of parts of the blade root connecting structure is reduced from original 12 to 5, and the composite propeller blade and blade root connecting structure is simple in structure, low in weight and good in manufacturability, the manufacturing cost is further greatly reduced, and the economic benefits are obviously increased.

Description

technical field [0001] The invention belongs to mechanical structure design and relates to a composite material paddle root connection structure. Background technique [0002] Propellers are mainly composed of metal hubs and composite material blades, see figure 1 . In order to ensure that the aircraft propeller can maintain maximum efficiency in all flight states such as take-off, climb, cruise, and landing, the propeller is generally designed as an automatic variable-pitch propeller, that is, when the flight state changes, the propeller will rotate around its own axis. sports. However, the hub does not have rotational motion in this direction, so it is necessary to add a bearing connection between the blade and the centering shaft of the hub. Since the composite material cannot meet the high-precision dimensions of the bearing fit, it is necessary to pre-embed the metal blade root at the root of the composite material blade. [0003] Therefore, in order to ensure that ...

Claims

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Application Information

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IPC IPC(8): B64C11/20B64C11/06
CPCB64C11/06B64C11/20
Inventor 陈丽智何九领李兵昝丙合刘婷
Owner AVIC HUIYANG AVIATION PROPELLER
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