Logic conversion control method for control system

A control system and logic conversion technology, applied in general control systems, control/regulation systems, instruments, etc., can solve the problems of system analysis, software design and the complexity of the testing process, and achieve the goal of simplifying the difficulty of system analysis and improving execution efficiency. Effect

Inactive Publication Date: 2016-10-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The object of the present invention is to provide a kind of logic conversion control method of control system, to solve the problem of the complexity of system analysis, software design and testing process at least to the present logic conversion control method

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  • Logic conversion control method for control system
  • Logic conversion control method for control system
  • Logic conversion control method for control system

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Embodiment Construction

[0015] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft on-board system control, in particular to a logic conversion control method of the control system, to at least solve the problem of the complexity of the system analysis, software design and testing process caused by the current logic conversion control method. A logic conversion control method for a control system, comprising the following steps: analyzing multiple control states and transition conditions between the multiple control states in the control system to obtain a state transition diagram; digitally abstracting the multiple control states and transition conditions and coding to obtain the state transition table; use two-dimensional array to model the state transition table to obtain the corresponding data model; in the data model, directly locate the target state through the array subscript to realize the mutual conversion between multiple control states . The logic conversion control method of the control system of the present invention enables the analysis of the whole system to be carried out on the same level all the time, without being affected by the scale and complexity of the problem, and can greatly simplify the difficulty of system analysis.

Description

technical field [0001] The invention relates to the field of aircraft on-board system control, in particular to a logic conversion control method of the control system. Background technique [0002] The software design and simulation modeling of the complex logic conversion relationship of aircraft airborne systems (such as flight control systems, avionics systems, electromechanical systems, etc.) are often encountered problems in engineering applications. Traditional program design is realized by multi-branch conditional transfer algorithm, and the program complexity increases with the complexity of the problem. Therefore, the ability to solve logic control is severely limited by the scale and complexity of the problem. In this way, the complexity of system analysis, software design and testing process is increased, the efficiency of software execution is reduced, and software maintenance, modification and function expansion are also difficult. Contents of the invention ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 李育李欣刘佳
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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