Autonomous error correction management method for CAN bus of spacecraft

Abstract

The invention discloses an autonomous error correction management method for a CAN bus of a spacecraft. The CAN bus is composed of a master node and N slave nodes. The method comprises the steps: performing autonomous recovery management on bus errors by the master node, performing autonomous recovery management on the bus errors by the slave nodes, and performing autonomous recovery management on bus network errors by the master node, wherein the autonomous recovery management on the bus errors by the master node refers to that the main node regularly detects all channel buses and autonomously corrects errors of the channel buses which do not meet the standard; the autonomous recovery management on the bus errors by the slave nodes refers to that the slave nodes detect the own channel bus and performs autonomous error correction on the channel bus which finds the errors; and the autonomous recovery management on the bus errors by the master node refers to that the master node sends an instruction to start fault processing diagnosis when the proportion of the slave nodes which are monitored by the master node in the communication period T5 and have continuous communication abnormity is higher than a standard proportion.

Description

technical field [0001] The present invention relates to the field of electronic technology, and more specifically, relates to an autonomous error correction management method of a space vehicle CAN bus. Background technique [0002] Space vehicles are generally composed of multiple subsystems, mainly composed of integrated information processing system, measurement and control and data transmission subsystem, power supply and distribution subsystem, attitude control subsystem, propulsion subsystem, structure and mechanism subsystem, thermal control subsystem and load system. Each subsystem has a lot of equipment. Taking the attitude and orbit control subsystem as an example, it includes sensors, actuators and controllers. [0003] Therefore, the design of spaceborne information network is usually more complicated. General interfaces for data and command communication between equipment may include 422 interface, 485 interface, CAN interface, LVDS interface, 1553B interface,...

AI Technical Summary

Problems solved by technology

[0005] However, because the source of the development of the CAN bus interface is the automobile industry, its own quality level and other status are not satisfactory for the use of space vehicles.

Images