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Competitive failure analysis method for wear degradation and functional degradation of aircraft lock mechanism components

A technology of competition failure and analysis method, which is applied in the field of reliability analysis of aircraft lock mechanism components, and can solve the problems of low reliability of analysis results.

Active Publication Date: 2020-08-18
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of low reliability of the analysis results by separately modeling component wear degradation and functional degradation in the failure analysis method of the existing aircraft lock mechanism, and provides an aircraft lock mechanism component wear Competitive Failure Analysis Method for Degradation and Functional Degradation

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  • Competitive failure analysis method for wear degradation and functional degradation of aircraft lock mechanism components
  • Competitive failure analysis method for wear degradation and functional degradation of aircraft lock mechanism components
  • Competitive failure analysis method for wear degradation and functional degradation of aircraft lock mechanism components

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specific Embodiment approach 1

[0022] Specific implementation mode one: the following combination figure 1 Describe this embodiment, the aircraft lock mechanism component wear degradation and functional degradation competition failure analysis method described in this embodiment, it comprises the following steps:

[0023] Step 1: According to the aircraft lock mechanism, define the functional energy, then determine the components that affect the realization of the functional energy, and determine all the wear and degradation sub-components in the components;

[0024] Step 2: use nonlinear drift Brownian motion to establish a degradation model for each wear degradation sub-component, and determine the random characteristics of each wear degradation sub-component at different time points;

[0025] Step 3: Introduce a proxy model to establish the transfer relationship between the random characteristics of each wear and degradation component and the functional energy of the lock mechanism, and then obtain the r...

specific Embodiment approach 2

[0028] Specific implementation mode two: the following combination Figure 1 to Figure 7 Illustrate this embodiment, and this embodiment will further explain Embodiment 1. In step 1, the aircraft lock mechanism is an aircraft door upper lock mechanism, and the aircraft door upper lock mechanism consists of rocker arm 1, rocker middle link 2, The lower link 3 of the rocker arm, the lock hook 4 and the lock ring 5 are composed, and the distance from the top end of the hook end of the lock hook 4 to the center of the lock ring 5 is defined as the kinetic energy, and one end of the link 2 in the rocker arm is connected with the center of the rocker arm 1 Point connection, determine that the hinge A through which the other end of the connecting rod 2 in the rocker arm is connected to the fixed part is a wear and degradation sub-component;

[0029] figure 2 and image 3 The working process of the lock mechanism is briefly indicated in the figure. The function of the upper lock me...

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Abstract

The invention discloses a method for analyzing failures of wear degradation and functional degradation of parts of an aircraft lock mechanism, belonging to the technical field of reliability analysis of parts of an aircraft lock mechanism. The invention aims to solve the problem of low reliability of analysis results due to the need to separately model wear degradation and function degradation of components in the existing failure analysis methods of aircraft lock mechanisms and then consider correlation. It uses nonlinear drift Brownian motion to model the wear degradation failure of components, and uses a proxy model to establish the functional transfer relationship between each wear degradation sub-component and functional energy, so as to find the degradation law of functional energy. The FGM copula function is used to establish the joint probability density function between the component wear degradation and functional degradation, and based on this, the competitive failure probability and the overall reliability of the lock mechanism under different failure modes are calculated. The invention is used for calculating the reliability of aircraft lock mechanism components.

Description

technical field [0001] The invention relates to an aircraft lock mechanism component wear degradation and function degradation competition failure analysis method, and belongs to the technical field of reliability analysis of aircraft lock mechanism components. Background technique [0002] The reliability level of the aircraft lock mechanism directly affects the working state of the specific mechanism of the aircraft, and then affects the flight safety of the entire aircraft. Due to wear, corrosion, aging and other reasons, engineering mechanisms usually have wear and tear of components during use. Even in a normal working environment, these causes of wear cannot be avoided. At the same time, the mechanism has its specific function at the beginning of the design. Whether the mechanism function can be completed directly determines whether the working state of the mechanism is normal, and the completion of the mechanism function is jointly determined by the mechanism componen...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F30/15G06F111/10G06F119/04
CPCG06F2119/04G06F30/15G06F2111/10G06F30/20
Inventor 刘敬一张玉刚宋笔锋喻天翔申林杰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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