Optimization method for formalized modeling

A formal modeling and optimization method technology, applied in software testing/debugging, etc., can solve problems such as the ineffective application of common libraries, and achieve the effects of performance optimization, sufficient verification, and low time overhead

Inactive Publication Date: 2015-11-25
FLIGHT AUTOMATIC CONTROL RES INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0006] The purpose of the present invention is to introduce a design technology based on the bridge between formal modeling and general library, which solves the problem that the general library cannot be effectively applied in the formal modeling method by building an adaptive adaptation layer

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  • Optimization method for formalized modeling
  • Optimization method for formalized modeling
  • Optimization method for formalized modeling

Examples

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Embodiment

[0022] Taking the fault recovery module in the flight control system software as an example, a formal modeling optimization method is introduced in conjunction with the accompanying drawings. The overall flow chart is shown in figure 1 ,Specific steps are as follows:

[0023] The first step is to analyze the system requirements for fault recovery. In the fault recovery of the flight control system, the grading of recoverable faults and the defined recoverable fault items should be cautious and limited. When the recoverable signal fails once, the lights should be turned on to prompt the pilot to perform the recovery operation, and then the pilot decides whether to recover, and the pilot implements the recovery control;

[0024] The second step is to analyze the architecture of the fault recovery, perform functional analysis and formal modeling analysis on the fault recovery through the state machine (SSM) in the SCADE environment, and use the KCG in the SCADE tool to complete t...

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Abstract

The present invention relates to an optimization method for formalized modeling. In a critical and real-time flight control system that has strict requirements on time, single use of a formalized modeling design method causes time cost brought by partial intermediate redundant codes generated in a modeling process and requirements of a hard real-time task system cannot be met. According to the scheme adopted by the present invention, by introducing a formalized modeling tool and a bridging technological method of a general library, an architecture design of a system is completed by means of a formalized modeling method at an early period and calculation analysis is performed on performances, such as time cost, of each module in the system; and for the module that has relatively large time cost or not good performance, an existing general library is bridged by using a self-adaptive adaptation layer, so that cooperative work of the formalized modeling method and the general library is implemented, and performance optimization is performed on formalized modeling.

Description

technical field [0001] The invention belongs to the field of flight control system software design. Background technique [0002] In the field of flight control system software design and development, the main design and development include manual coding development methods and formal modeling design methods. [0003] The traditional flight control system software development mainly completes the software design through manual coding. Through the development and iteration of multiple models, some mature general libraries can be generated. These general libraries have been verified by multiple models and have the characteristics of compact and efficient code. . However, if the system requirements change, manual coding is not convenient for the maintenance of requirements changes, and at the same time, it lacks the support of graphical simulation and verification tools in the later stage. [0004] With the development of key technologies of the flight control system, formal ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F11/36
Inventor 刘海亮屈华敏杨东红阎振鑫
Owner FLIGHT AUTOMATIC CONTROL RES INST
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