A reliability analysis method for aircraft fly-by-wire control system

A technology of control system and analysis method, applied in electrical digital data processing, instruments, geometric CAD, etc., can solve problems such as poor applicability, low model correctness, and low reliability evaluation efficiency.

Inactive Publication Date: 2020-02-14
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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Problems solved by technology

[0009] In order to overcome the shortcomings of low reliability evaluation efficiency, low model correctness and poor applicability in the prior art, the present invention proposes a reliability analysis method for aircraft fly-by-wire control system

Method used

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  • A reliability analysis method for aircraft fly-by-wire control system
  • A reliability analysis method for aircraft fly-by-wire control system
  • A reliability analysis method for aircraft fly-by-wire control system

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Embodiment approach

[0166] For the ignitable time-delay transition t i , calculate its delay time X i The implementation method is as follows:

[0167] i) Generate random numbers U~U(0,1) that obey the uniform distribution of [0,1];

[0168] ii) Order X i =-InU / λ i ,λ i is the delay transition t i parameters.

[0169] When generating random numbers U~U(0,1) that obey the uniform distribution of [0,1], both matlab and C programming software can generate random numbers that obey the uniform distribution of [0,1]. In this embodiment, C programming software is used for random number extraction. Since the method proposed by the present invention is based on random sampling, the random numbers obtained by each sampling may be different. In this embodiment, this step only uses a possible sampling result as an example to illustrate the method of the present invention, which is an explanation of the present invention rather than a limitation.

[0170] According to the description in step 1, the m...

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Abstract

Provided is a reliability analysis method for an aircraft fly-by-wire control system. On the theoretical basis of a dynamic random Petri network, the invention provides a system reliability modeling and reliability calculation method based on a schematic diagram for system functions. The method is used for converting the schematic diagram for system functions into the dynamic random Petri network with a highly uniform topological structure used for system reliability analyses. The Petri network is capable of effectively avoiding interference of subjective factors of modeling personnel and accurately calculating system reliability. Therefore, the reliability analysis method for the aircraft fly-by-wire control system is of great importance in improvement of reliability assessment of a complex engineering system.

Description

technical field [0001] The invention belongs to the field of engineering system reliability analysis, and in particular relates to a system reliability modeling and system reliability calculation method for converting the functional schematic diagram of an aircraft telex control system into a stochastic Petri net. Background technique [0002] Reliability is an important technical attribute of the effectiveness of complex engineering systems. High-level reliability analysis technology has important engineering and technical value and significance for identifying weak links in aircraft systems, improving design defects, reducing life cycle costs, and improving functional application efficiency. The core of the work in the field of reliability is faults. The occurrence of faults will not only seriously affect the function of the system itself, but also cause casualties and property losses. In recent years, with the continuous development of the integration of aircraft fly-by-...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/22G06F119/02
CPCG06F30/15
Inventor 王瑶孙秦
Owner NORTHWESTERN POLYTECHNICAL UNIV
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