Design method of aircraft trailing edge flap control system based on model conversion

A technology of trailing edge flaps and control systems, applied in design optimization/simulation, calculation, special data processing applications, etc., can solve problems such as low efficiency in safety and/or reliability design analysis, improve efficiency and achieve constraints , the effect of efficient correlation

Active Publication Date: 2019-01-22
CHINA AERO POLYTECH ESTAB
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Problems solved by technology

[0004] The purpose of this application is to propose a technical problem that solves the low efficiency of safety and / or reliability design analysis in the design of the aircraft trailing edge flap control system, thereby solving the technical problems mentioned in the above background technology

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  • Design method of aircraft trailing edge flap control system based on model conversion
  • Design method of aircraft trailing edge flap control system based on model conversion
  • Design method of aircraft trailing edge flap control system based on model conversion

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Embodiment Construction

[0045] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It can be understood that the specific implementation cases described here are only used to explain related inventions, rather than to limit the invention. It should also be noted that, for the convenience of description, only the parts related to the related invention are shown in the drawings.

[0046] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0047] figure 1 A flow chart of the design method of the aircraft trailing edge flap control system of the present application is shown. This application does not limit this. The specific implementation process of this process is introduced in detail below.

[0048]...

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Abstract

The invention provides a design method of an aircraft trailing edge flap control system based on model conversion. The design method includes: A block definition diagram and an internal block diagramof the aircraft trailing edge flap control system are generated in SysML software to establish a SysML model of the aircraft trailing edge flap control system, the SysML model of aircraft trailing edge flap control system is exported as XMI file in SysML software, after the XMI file is parsed in RelLab software, the AltaRica model of the aircraft trailing edge flap control system is generated based on the conversion rules between the XMI file elements and the AltaRica model elements, based on the AltaRica model of aircraft trailing-edge flap control system, the safety and reliability of aircraft trailing-edge flap control system are analyzed, and the list of key equipment and failure probability of critical failure state are obtained. The system architecture design of the aircraft trailingedge flap control system is carried out synchronously with the system reliability and safety design, and the linkage is coordinated to effectively improve the efficiency of the safety and/or reliability design and analysis activities.

Description

technical field [0001] The application relates to the technical field of aircraft design, in particular to a design method of an aircraft trailing edge flap control system based on model conversion. Background technique [0002] At present, problems such as the lack of integration and linkage with the system architecture such as the design process of the aircraft trailing edge flap control system, the inability to form effective constraints on the system architecture design, the early reliability of the system development, or insufficient safety design control and process evaluation have become constraints. Critical issues for system reliability / security efforts. [0003] Moreover, the existing aircraft trailing edge flap control system design method cannot realize the efficient correlation of system architecture elements to FMEA (failure mode and effect analysis and FTA fault tree), and the effective traceability of system reliability / safety analysis, resulting in Ineffici...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 薛和平王如平周一舟刘晨艳王陶占自涛
Owner CHINA AERO POLYTECH ESTAB
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