A method for generating fault physical simulation profiles of multi-stage mission systems of avionics equipment

A technology for avionics equipment and system failure, applied in design optimization/simulation, electrical digital data processing, special data processing applications, etc.

Active Publication Date: 2018-10-19
BEIHANG UNIV
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Problems solved by technology

Through the novelty search and retrieval of existing technologies, avionics equipment multi-stage task system fault physical simulation profile generation method has not been proposed at home and abroad from the perspective of fault physics.

Method used

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  • A method for generating fault physical simulation profiles of multi-stage mission systems of avionics equipment
  • A method for generating fault physical simulation profiles of multi-stage mission systems of avionics equipment
  • A method for generating fault physical simulation profiles of multi-stage mission systems of avionics equipment

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Embodiment Construction

[0023] The present invention will be further described in detail below with reference to the drawings and embodiments.

[0024] The following takes an aircraft inertial navigation system as an example to illustrate its reliability profile generation process based on fault physics.

[0025] The invention provides a method for generating a reliability simulation profile of avionics based on fault physics, figure 1 A schematic diagram of the work flow of the present invention is shown. In this embodiment, the specific steps of the method are as follows:

[0026] Step 1: Determine the missions of the aircraft where the inertial navigation system is located at different stages.

[0027] The aircraft performs two missions a day, namely outbound and return. According to the working condition table of the flight task, each flight task is shown in Table 1, including the following processes: stop (that is, all equipment is turned off), idle on the ground, waiting for take-off on the ground, ta...

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Abstract

The invention provides a method for generating multistage task system fault physical simulation sections of avionic devices. The method comprises the following steps: 1, determining a plurality of task stages of an airplane of an avionic device in a flight mission period and the duration time of each task stage; 2, determining the environment temperature of the avionic device in the task stages so as to generate an environment temperature section; 3, determining the vibration of the avionic device in the task stages so as to generate a vibration section; 4, determining the humidity of the avionic device in the task stages so as to generate a humidity section; and 5, enabling the time points of the task stages of the temperature section, the vibration section and the humidity section to correspond to each other, so as to generate a fault physical comprehensive simulation section of the avionic device. According to the method, the weak links of the avionic devices can be determined in allusion to reliable simulation results, so as to provide basis for the design improvement of products.

Description

Technical field [0001] The invention provides a method for generating a reliability simulation profile of avionics, in particular to a method for generating a reliability simulation profile of a multi-stage mission system considering the life cycle of the avionics, and belongs to the field of reliability simulation of electronic equipment. Background technique [0002] Fault physics believes that the failure of electronic products is directly related to the external environment and load it bears. Different environments, load values, and even different environmental load changes may cause different types of failure mechanisms and failure times. The existing reliability simulation profile generation method refers to the generation method of the reliability qualification test profile of electronic equipment to obtain the environmental profile under typical tasks, and avionics often have to perform multiple different tasks during its life cycle, such as aircraft Flight can be divided...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 陈颖袁增辉汤宁李颖异
Owner BEIHANG UNIV
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