Triple-redundancy 1553B bus dynamic switching method

A triple-redundancy and triple-machine redundancy technology is applied in bus networks, data exchange networks, and data exchange through path configuration. Effect of market share and low-cost investment

Active Publication Date: 2017-11-14
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Application Information

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Problems solved by technology

[0008] In the past, rockets mainly used non-bus interfaces and single-bus interfaces. This method is complex for fault identification, and inevitably has many system single points, and has certain application limitations.

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  • Triple-redundancy 1553B bus dynamic switching method
  • Triple-redundancy 1553B bus dynamic switching method
  • Triple-redundancy 1553B bus dynamic switching method

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Embodiment Construction

[0038] The method steps of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0039] The invention provides a method for dynamically switching three redundant 1553B buses, the method comprising the following steps:

[0040]Step 1: set up a three-machine redundant bus network computer system architecture; wherein, the three-machine redundant bus network computer system architecture includes a first redundant module 10, a second redundant module 11 and a third redundant module 12; the first redundant module The redundancy module 10 includes a first CPU processor 1, a first logic processing and control module 2, and a first bus chip 3, and the second redundancy module 11 includes a second CPU processor 4, a second logic processing and control module 5, and a first bus chip 3. Two bus chips 6, the third redundant module 12 includes the third CPU processor 7, the third logic processing and control module ...

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Abstract

The invention provides a triple-redundancy 1553B bus dynamic switching method, which includes the following steps: S1, a triple-modular redundancy bus network computer system architecture is built; S2, a redundancy bus configuration method is designed, a bus A for communication is a main bus by default, a first redundancy module is a on-duty module by default when the computer system is powered on, a first bus chip is configured in a BC mode, and a second bus chip and a third bus chip are configured in an MT mode; S3, a bus fault diagnosis method is designed for triple-modular bus real-time fault identification; and S4, a triple-redundancy bus mode composed of a BC mode and two MT modes is reestablished according to the on-duty module switching principle. A spacecraft computer requiring high real-time performance and reliability can determine a triple-redundancy bus fault by using the serial timing characteristic and the information monitoring function of buses. The method is easy to implement, runs reliably, is not affected by the external environment, is quick, and can be easily used in engineering.

Description

technical field [0001] The invention relates to a launch vehicle control system, in particular to a low-cost, high-reliability bus dynamic fault diagnosis and switching method in a launch vehicle control system, which is suitable for remote measurement information collection, measurement stand-alone information collection, and attitude-orbit control command communication, ensuring first-degree failure The status provides real-time and continuous information channels. Background technique [0002] Due to the unique advantages of real-time performance and reliability of the 1553B bus, various types of upper stages, quick-response liquid small rockets, solid small vehicles, air-launched small vehicles, and heavy-duty launch vehicles for manned lunar exploration will be used in the future. Has a wide range of applications. [0003] With the development of my country's space applications, scientific exploration, and manned spaceflight, and the deepening of international commerci...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H04L12/24H04L12/26H04L12/40
CPCH04L12/40176H04L12/40189H04L41/06H04L43/50
Inventor 程亮周如好余薛浩梁家诚杨孔进杜建峰陈川
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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