Rigid rotor hub of helicopter

A technology for rotor hubs and helicopters, applied in the directions of rotorcraft, propellers, 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 ensure swinging. Stiffness and sway stiffness, the effect of large radial stiffness

Active Publication Date: 2020-12-08
NO 60 RES INST OF GENERAL STAFF DEPT PLA
View PDF5 Cites 4 Cited by
  • Summary
  • 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 t

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Rigid rotor hub of helicopter
  • Rigid rotor hub of helicopter
  • Rigid rotor hub of helicopter

Examples

Experimental program
Comparison scheme
Effect test

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...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a rigid rotor hub of a helicopter. A plurality of variable-pitch arm modules are arranged around a center piece module; paddles are fixed on the variable-pitch arm module; eachvariable-pitch arm module comprises a paddle mounting base, an outer side radial laminated elastic bearing, a thrust laminated elastic bearing and an inner side radial laminated elastic bearing; thepaddles are fixed on the paddle mounting bases; the outer side radial laminated elastic bearings and the inner side radial laminated elastic bearings have the same structure; an inner ring of each outer side radial laminated elastic bearing is fixed on the corresponding paddle mounting base, and an outer ring of each outer side radial laminated elastic bearing is fixed on the center piece module;an inner ring of each inner side radial laminated elastic bearing is fixed on the corresponding paddle mounting base, and an outer ring of each inner side radial laminated elastic bearing is fixed with the center piece module; each thrust laminated elastic bearing is composed of laminated elastic layers stacked in the axial direction, the inner side of each thrust laminated elastic bearing is fixed to the corresponding paddle mounting base, and the outer side of each thrust laminated elastic bearing is fixed to the center piece module; and the axes of the three elastic bearings of each variable-pitch arm module are collinear. The rigid rotor hub has the advantages of being long in service life and free of lubrication and maintenance, having no abrasion, 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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
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
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap