Supercharge Your Innovation With Domain-Expert AI Agents!

Rotor wing propeller hub connecting piece fatigue test load debugging method

A fatigue test and rotor hub technology, which is applied in the field of fatigue test load debugging of helicopter rotor hub connectors, can solve the problems of inability to apply variable-pitch tie rod force, inability to apply damping force, and conservative service life.

Active Publication Date: 2017-06-06
CHINA HELICOPTER RES & DEV INST
View PDF3 Cites 11 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Background Art The fatigue test of the main propeller hub connector adopts the "resonance method" of mechanical vibration loading of the motor at the end of a cantilever beam hinged at one end. Centrifugal force, flapping moment and shimmy bending moment are taken into account. The damper force is measured through a force measuring rod with fixed constraints. The damping force cannot be applied as required, and the force of the variable-distance tie rod cannot be applied. The engineering method used in the life analysis ignores the The influence of the variable pitch tie rod force and the combination of various loads on the main propeller hub connector can only be given a conservative service life through the analysis of test results

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
  • Rotor wing propeller hub connecting piece fatigue test load debugging method
  • Rotor wing propeller hub connecting piece fatigue test load debugging method
  • Rotor wing propeller hub connecting piece fatigue test load debugging method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0019] The present invention will be described in further detail below.

[0020] Such as figure 1 , the load to be simulated in the fatigue test of the main propeller hub connector is the damper force F a , pull rod force F bdp , centrifugal force F c , Torque M X (produced by the force of the variable pitch rod), swinging moment M Y and wielding shear force F Z (generated by the swinging shear force actuator), shimmy bending moment M Z and shimmy shear force F Y (generated by the shimmy shear actuator), each load is loaded in phase coordination. Such as figure 2 , a vector composite diagram for bending moment debugging.

[0021] A method for debugging fatigue test loads of rotor main propeller hub connectors, characterized in that the steps of the method for debugging test loads are as follows:

[0022] (1) Configure and debug the parameters of the load channels of centrifugal force, variable pitch rod force, damper force, shimmy force, and swing force, so that the...

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 provides a rotor wing propeller hub connecting piece fatigue test load debugging method. The method is intended for rotor wing propeller hub connecting piece fatigue tests. According to the invention, the method realizes the application of respective loads of the propeller hub connecting piece, and simulates loaded conditions of the propeller hub connecting piece. According to the invention, the method herein can produce a more authentic and accurate result from the rotor wing propeller hub connecting piece fatigue test.

Description

technical field [0001] The invention belongs to the fatigue test technology of a rotor hub connector, and relates to a fatigue test load debugging method for a helicopter rotor hub connector. Background technique [0002] The main hub connector is a typical complex key component in the helicopter structure. The loads transmitted by the blades, including centrifugal force, flapping moment, and shimmy bending moment, are transmitted to the central part through the connector. The connector also balances the damper force and pitch rod force. In the fatigue test, it is very important to simulate the magnitude, direction and phase relationship of each load to obtain the real fatigue performance and weak parts, and to provide a basis for determining its service life. [0003] Background Art The fatigue test of the main propeller hub connector adopts the "resonance method" in which the motor is mechanically excited and loaded at the end of a cantilever beam hinged at one end. Cent...

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): G01M13/02
CPCG01M13/027
Inventor 李清蓉喻溅鉴包名朱浩煜
Owner CHINA HELICOPTER RES & DEV INST
Features
  • R&D
  • Intellectual Property
  • Life Sciences
  • Materials
  • Tech Scout
Why Patsnap Eureka
  • Unparalleled Data Quality
  • Higher Quality Content
  • 60% Fewer Hallucinations
Social media
Patsnap Eureka Blog
Learn More

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

© 2025 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com