A helicopter rigid rotor hub

A rotor hub and helicopter technology, applied to propellers, rotorcraft, motor vehicles, etc., can solve problems such as the deviation of the natural frequency of the rotor from the design value, change the dynamic characteristics, and reduce the overall stiffness of the rotor, so as to achieve small elastic deformation and improve flapping frequency and shimmy frequency, effect of guaranteed flapping stiffness and shimmy stiffness

Active Publication Date: 2022-03-18
NO 60 RES INST OF GENERAL STAFF DEPT PLA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the existence of the bearing clearance of the hingeless rotor hub, the blade will swing or shimmy in a small angle range around the structural clearance, which reduces the overall stiffness of the rotor, makes the natural frequency of the rotor deviate from the design value, changes the dynamic characteristics, and even causes dynamics problem

Method used

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  • A helicopter rigid rotor hub
  • A helicopter rigid rotor hub
  • A helicopter rigid rotor hub

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Embodiment Construction

[0020] The present invention will be further introduced below in conjunction with the accompanying drawings and specific embodiments.

[0021] combine Figure 1-Figure 4 , a helicopter rigid rotor hub of the present invention, comprising a center piece module 1, a pitch variable arm module 2, a blade mounting pin 3 and a blade 4;

[0022] The blade 4 is installed on the pitch-changing arm module 2 through the blade mounting pin 3 , and four pitch-changing arm modules 2 are evenly distributed around the center piece module 1 to form a whole hub.

[0023] combine figure 2 , the center piece module 1 is the center of the propeller hub, which plays the role of connecting the pitch-changing arm module 2 and the rotor shaft, and is composed of an upper splint 5, a center piece 6, a lower splint 7, tightening bolts 8 and large bolts 9. The central part 6 is fixed between the upper splint 5 and the lower splint 7 by tightening bolts 8; four cylindrical grooves 10 are evenly distrib...

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Abstract

A helicopter rigid rotor hub, a plurality of pitch-variable arm modules are arranged around the center piece module; blades are fixed on the pitch-variable arm modules; the pitch-variable arm modules include blade mounts, outer radial lamination elastic bearings, Laminated Elastomeric Bearing, Inner Radial Laminated Elastomeric Bearing; The blade is fixed on the blade mount; Outer Radial Laminated Elastomeric Bearing and Inner Radial Laminated Elastomeric Bearing The outer ring is fixed on the blade mounting seat, and the outer ring is fixed on the center piece module; the inner ring of the inner radially laminated elastic bearing is fixed on the blade mounting seat, and the outer ring is fixed on the center piece module; the thrust lamination elastic bearing The bearing is composed of axially stacked laminated elastic bearings, the inner side of the thrust laminated elastic bearing is fixed on the blade mount, and the outer side is fixed on the center piece module; the axes of the three elastic bearings are collinear. The propeller hub of the present invention has the characteristics of high service life, no lubrication, no wear, no maintenance and the like.

Description

technical field [0001] The invention belongs to the field of helicopter rotor design, in particular to a helicopter rigid rotor hub. Background technique [0002] Helicopters have vertical take-off and landing and hovering capabilities, and have low requirements for take-off and landing sites. They can take off and land on non-paved ground or on the top of high-rise buildings in cities. Due to their flexibility, helicopters are irreplaceable in the field of aircraft. effect. Compared with fixed-wing aircraft, helicopters with traditional conventional configurations have low flying speed and poor endurance. In order to increase the flight speed of helicopters, new helicopter configurations such as coaxial high-speed helicopters have emerged. Coaxial high-speed helicopters use two pairs of rotors that turn in opposite directions to provide lift and thrust propellers to provide thrust, which can effectively improve the speed performance of helicopters. The rotor of the coaxia...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/32B64C11/02B64C11/06
CPCB64C27/32B64C11/02B64C11/06
Inventor 刘士明仰杰杰孙宇应旭成邵松范汪明
Owner NO 60 RES INST OF GENERAL STAFF DEPT PLA
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