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Aircraft cabin door uplock mechanism part wear degradation and functional degradation competition failure analysis method

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: 2020-10-27
NORTHWESTERN POLYTECHNICAL UNIV
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  • Claims
  • Application Information

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Problems solved by technology

[0006] 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

Method used

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  • Aircraft cabin door uplock mechanism part wear degradation and functional degradation competition failure analysis method
  • Aircraft cabin door uplock mechanism part wear degradation and functional degradation competition failure analysis method
  • Aircraft cabin door uplock mechanism part wear degradation and functional degradation competition failure analysis method

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specific Embodiment approach 1

[0023] 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:

[0024] 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;

[0025] 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;

[0026] 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

[0029] 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;

[0030] 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 an aircraft cabin door uplock mechanism part wear degradation and functional degradation competition failure analysis method, and belongs to the technical field of aircraft lock mechanism part reliability analysis. The invention aims at solving the problems that in an existing failure analysis method of an aircraft lock mechanism, part abrasion degradation and functional degradation need to be modeled respectively, then correlation is considered, and the reliability of an analysis result is low. According to the method, nonlinear drift Brownian movement is used for modeling part wear degradation failure, and an agent model is used for establishing a function transfer relationship between each wear degradation sub-component and a function quantity so as to search a degradation rule of the function quantity, wherein the FGM copula function is used for establishing a joint probability density function between the part wear degradation amount and the functional degradation amount, and calculating the competition failure probability under different failure modes and the overall reliability of the lock mechanism based on the joint probability density function. Themethod is used for calculating the reliability of the aircraft lock mechanism part.

Description

[0001] This application is a divisional application with application number: 201710421125.5, application date: June 7, 2017, and the title of the invention "Analysis Method for Competitive Failure of Aircraft Lock Mechanism Components Wear Degradation and Function Degradation". technical field [0002] The invention relates to a method for analyzing the competition failure of wear degradation and function degradation of an aircraft cabin door upper lock mechanism component, and belongs to the technical field of reliability analysis of aircraft lock mechanism components. Background technique [0003] 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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15G06F111/10G06F119/04
CPCG06F2119/04G06F30/15G06F2111/10G06F30/20
Inventor 张玉刚刘敬一宋笔锋喻天翔申林杰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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