System fault comprehensive declare processing method

A technology for system faults and processing methods, applied in general control systems, control/regulation systems, testing/monitoring control systems, etc., can solve the problems of low software design reuse, increase the workload of testing and verification, and reduce complexity. , Improve the testability and the effect of strong reusability

Active Publication Date: 2015-06-10
FLIGHT AUTOMATIC CONTROL RES INST
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Problems solved by technology

The traditional system fault synthesis method provides a corresponding fault synthesis algorithm for the failure mode of each component of each subsystem. The software code changes with the change of requirements, and the reusability of software design i

Method used

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  • System fault comprehensive declare processing method

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Embodiment

[0020] The following is a detailed introduction to the method for selecting the problem of comprehensive declaration of pitch rate gyro faults in combination with the accompanying drawings. The overall flow chart is as follows figure 1 As shown, the specific steps are as follows:

[0021] 1. Formulate a system fault reporting principle table: if the pitch rate gyro has 0, 1, 2, 3, and 4 faults, the corresponding system status is 0, 1, 2, 3, and 3 respectively;

[0022] 2. Determine the array dimension of the fault declaration structure: the maximum number of faults of all components is 4, so the array dimension includes 5 for the non-fault mode;

[0023] 3. Fill the address of the fault counter of the pitch rate gyro into the first column of the state matrix;

[0024] 4. Fill the system state corresponding to the fault of the pitch rate gyro into the second column {0, 1, 2, 3, 3} of the state matrix, where the first element 0 represents the corresponding declared state when t...

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Abstract

The invention relates to a system fault comprehensive declare processing method, in particular to a fault comprehensive declare processing method of a redundancy fly-by-wire flight control system. The redundancy fly-by-wire flight control system is composed of subsystems of a flight control computer, a servo actuator, a sensor, a control display, a built-in self detector and the like; in order to improve redundancy management information comprehensive capability of the subsystems, default information characteristic quantity of the subsystems are extracted and are composited by using a state matrix mode, fault levels are determined according to fault modes and number of faults, the system faults are comprehensively declared, and the fault modes and the fault levels are indicated through different modes and equipment, so that pilots can timely know flying state and security status of airplanes. The faults are comprehensively declared by the state matrix mode, the information of the faults is concentrated in one form document, the comprehensive declare information is acquired by searching the file, and accuracy in requirement description and execution efficiency of software are improved.

Description

technical field [0001] The invention belongs to the field of fault processing methods for fly-by-wire flight control systems, and relates to a comprehensive declaration processing method for system faults. Background technique [0002] With the widespread application of fly-by-wire flight control systems, the composition of the system is becoming more and more complex, and the synthesis and reporting of system fault status are also becoming more and more complicated. Synthesis and reporting of system failure status, for the flight control system composed of flight control computer, servo actuator, sensor, control display, internal self-test and other subsystems, the software integrates the redundancy management results of each subsystem, and according to the reasonableness of the system The principle of reporting, indicating or prompting the pilots of the fault category and fault level through different methods and equipment. The traditional system fault synthesis method pr...

Claims

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Application Information

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IPC IPC(8): G05B23/02
CPCG05B23/0272
Inventor 杨锦清徐艳玲许敏宛琳冯博徐建军朱立平
Owner FLIGHT AUTOMATIC CONTROL RES INST
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