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Redundancy measurement architecture and redundancy measurement method based on cross-correlation method

A redundancy management and redundancy technology, applied in the direction of instruments, computer control, simulators, etc., can solve the problems of difficult joint debugging, long test period, difficult simulation and synchronization accuracy failure, etc., to reduce redundancy and ensure normal use. Effect

Active Publication Date: 2020-03-13
四川泛华航空仪表电器有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although redundancy technology is an important means to improve system reliability, there are generally problems such as difficulty in joint debugging, long test cycle, and difficulty in simulating faults related to synchronization accuracy in the testing of redundant flight control computer software.

Method used

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  • Redundancy measurement architecture and redundancy measurement method based on cross-correlation method
  • Redundancy measurement architecture and redundancy measurement method based on cross-correlation method
  • Redundancy measurement architecture and redundancy measurement method based on cross-correlation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] This embodiment provides a redundancy measurement framework based on the cross-comparison method, such as figure 1 shown, including:

[0038] Two independent CPU (measurement and processing) modules with the same performance and the ability to independently measure and calculate the fuel volume of aircraft fuel tanks, and two power supply modules that independently supply power to the CPU (measurement and processing) modules.

[0039] Two CPU modules (measurement and processing): CPU_A module, CPU_B module;

[0040] Two power modules: power module A, power module B;

[0041] The power supply module A is connected to the CPU_A module and supplies power to the CPU_A module alone; the power supply module B is connected to the CPU_B module and supplies power to the CPU_B module alone.

[0042] The CPU_A module, the CPU_B module, the power module A, and the power module B will not affect each other, so as to ensure that the control computer has a dual-redundant hardware co...

Embodiment 2

[0050] In this embodiment, a redundancy measurement framework based on a cross-comparison method is used in an aircraft fuel quantity measurement computer.

[0051] A kind of redundancy measurement architecture based on the cross-comparison method in this embodiment is composed of two independent CPU modules and two power supply modules that independently supply power to the two CPU modules;

[0052] The two CPU modules are independent of each other, have the same performance, and both have the ability to independently measure and calculate the fuel volume of the aircraft fuel tank, and the two CPU modules are recorded as: CPU_A module and CPU_B module; there is no difference between the CPU_A module and CPU_B module. will influence each other to ensure that the control computer has a dual-redundant hardware configuration;

[0053] The two power supply modules are recorded as: power supply module A and power supply module B; the power supply module A is connected to the CPU_A ...

Embodiment 3

[0056] This embodiment provides a redundancy management method based on a cross-comparison method, and sets a redundancy management strategy based on a redundancy measurement framework;

[0057] The redundancy management strategies include dual redundancy signal monitoring and voting strategies, fault detection and diagnosis strategies, system reconstruction and recovery strategies, and synchronization management strategies;

[0058] The dual-redundancy signal monitoring and voting strategy specifically refers to: first determine the basic monitoring and voting principles, formulate a dual-redundancy signal monitoring and voting method according to the basic monitoring and voting principles, and finally the voting results are output by the main measurement and processing module;

[0059] The fault detection and diagnosis strategy specifically refers to: using the fault detection mechanism of the bus request / response handshake to detect faults; the detected content includes: sel...

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Abstract

The invention discloses a redundancy measurement architecture based on a cross-correlation method. The redundancy measurement architecture comprises two independent CPU modules, namely, a CPU_A moduleand a CPU_B module, which have the same performance and both have independent capabilities of measuring and calculating the oil quantity of an aircraft oil tank, and two power supply modules, namely,a power supply module A and a power supply module B, which are used for independently supplying power to the CPU modules. The CPU_A module and the CPU_B module do not influence each other, so that acontrol computer is ensured to have dual-redundancy hardware configuration. Each CPU module is internally provided with a DSP unit and an FPGA unit which are in communication connection, and each DSPunit is integrally provided with an SPI bus interface. According to the invention, sudden faults can be effectively handled, and normal use of a fuel oil measuring computer in a fault state is ensured.

Description

technical field [0001] The invention belongs to the technical field of aircraft control computers, and in particular relates to a redundancy measurement framework and a redundancy management method based on a cross-comparison method. Background technique [0002] The aircraft control computer is mainly responsible for measuring and reporting the fuel volume of the aircraft fuel tank. It has the typical characteristics of harsh operating environment, high precision and stability requirements, and high reliability requirements. [0003] At present, domestic aircraft control computers mostly adopt a single-redundancy measurement architecture design, which lacks an effective response mechanism and processing means for sudden failures. Redundancy is a technology that can improve the safety and reliability of aircraft. After its introduction, it can monitor the faults of the aircraft's control computer and fuel measurement system. When a fault occurs somewhere, the aircraft's cont...

Claims

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Application Information

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IPC IPC(8): G05B19/042
CPCG05B19/0421G05B2219/24182
Inventor 黎顺杰杨光明樊伟
Owner 四川泛华航空仪表电器有限公司
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