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A Redundancy Voting Control Method Based on Dual Bus

A control method and dual-bus technology, applied in the direction of program control, computer control, general control system, etc., can solve problems such as difficulty in taking into account reliability and economy, achieve both reliability and economy, solve hardware single point failure, The effect of good versatility and scalability

Active Publication Date: 2020-04-21
SHANGHAI AEROSPACE COMP TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, when the existing spacecraft control unit fails with a single point of failure, it is often difficult to balance reliability and economy.

Method used

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  • A Redundancy Voting Control Method Based on Dual Bus
  • A Redundancy Voting Control Method Based on Dual Bus
  • A Redundancy Voting Control Method Based on Dual Bus

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Embodiment Construction

[0029] The applicable spacecraft control unit system of the present invention needs the following conditions:

[0030] 1. Bus communication interaction conditions

[0031] Since the present invention is carried out based on a dual-bus communication mode, the spacecraft control unit must have a way to receive the bus message sent on the bus, whether it is directly receiving the bus message sent by the corresponding BC controller from the MIL-STD-1553B bus , or a bus message forwarded from other control units through the CAN bus. The general spacecraft control unit can receive control commands from the MIL-STD-1553B bus of the control system or the internal CAN bus according to its overall architecture design.

[0032] 2. Hardware redundancy conditions

[0033] The spacecraft control unit supports the expansion of heartbeat signal and CAN bus access on the original mature system platform. At the same time, through the hardware redundancy combination of the improved control uni...

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Abstract

The invention discloses a redundancy decision control method based on double buses, and the method comprises the following steps that S1, one of the spacecraft control units A, B and C is taken as anRT terminal, receives a bus message sent by an MIL-STD-1553B bus transmission after the data is verified to be valid, and transmits a bus message to the other two control units via a CAN bus; S2, oneof the spacecraft control units A, B, and C receives the bus messages sent by the other two control units, and verifies the validity of command data; S3: one of the spacecraft control units A, B and Cperforms the two-out-of-three output of the received MIL-STD-1553B bus message and the bus message forwarded by the other two control units through combining with a heartbeat signal captured by the control unit, so as to cope with known one-degree and two-degree faults. The method uses two mature bus technologies of MIL-STD-1553B and CAN to effectively ensure real-time and highly reliable transmission of bus messages, effectively solves single-point faults of hardware, improves the reliability and security of the system, gives consideration to the balance reliability and economic performance,and has good versatility and scalability.

Description

technical field [0001] The invention relates to spacecraft control unit software, in particular to a dual bus-based redundant voting control method belonging to the spacecraft control unit software triple redundancy voting control technology. Background technique [0002] With the development of my country's new-generation carrier field, the requirements for the safety and reliability of the rocket system are getting higher and higher. The control system directly determines the success or failure of the rocket launch mission, and the reliability and safety design requirements are getting higher and higher. Conventional It is difficult to meet the target requirements of increasing the reliability of launch vehicles in active service by 1% with advanced reliability design methods and measures. [0003] The system reliability analysis and design of the spacecraft control unit is carried out based on the reliability of the flight mission as the first principle of configuration. I...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/042
CPCG05B19/0421
Inventor 徐建萍胡浩周振宇施雯陆灵君
Owner SHANGHAI AEROSPACE COMP TECH INST
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