Satellite-borne computer communication reliability and fault-tolerant design method based on CAN bus
A technology of on-board computer and CAN bus, which is applied in the direction of bus network, data exchange through path configuration, digital transmission system, etc., can solve the problems of reducing bus reliability, bus communication network congestion, affecting equipment communication, etc., to improve reliability Effects on Sexual Processing
Pending Publication Date: 2022-01-25
北京轩宇空间科技有限公司
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Problems solved by technology
Since multiple data frames often occupy the bus intensively, it will cause problems such as bus communication network congestion and data redundancy, which will affect the communication between devices and reduce the reliability of the bus. There is also the problem of frame loss in multi-frame data transmission, which is difficult to meet Requirements for high reliability, high availability and autonomous fault tolerance proposed by large military products such as aviation and aerospace
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[0029] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0030] The communication link of the on-board computer based on the CAN bus generally adopts a dual-redundant bus network structure, including two buses, A and B, and the hardware circuits of the A and B buses adopt a physical isolation design. The central computer is the CAN master node, and the onboard computer is the CAN slave node. Its network structure is as follows: figure 1 shown.
[0031] When the space-borne computer based on the CAN bus fails due to the radiation of the space environment, resulting in a non-instantaneous failure of one CAN communication, the system needs to be able to sense the failure on the one hand and report the failure to the central computer; on the other hand, it also needs to autonomously Dispatch to another CAN bus link for con...
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The invention discloses a satellite-borne computer communication reliability and fault-tolerant design method based on a CAN bus. The method comprises fault detection and autonomous fault processing and repairing. The fault detection comprises the following steps: when a fault occurs, a spaceborne computer identifies the type of a fault, sets a corresponding fault identification bit, forms single-machine fault information and updates the single-machine fault information to a CAN telemetering response data packet in the current period; a center machine senses the fault state of the satellite-borne computer of a slave node according to the received CAN telemetering response data packet, and fault detection is achieved; autonomous fault processing and repairing comprises an automatic switching mode and a forced switching mode, the automatic switching mode is to automatically switch a CAN A bus / a CAN B bus according to a preset time length, and the steps are repeated; and in the forced switching mode, the center machine issues a CAN forced switching instruction data packet through the CAN A bus and the CAN B bus, so that the spaceborne computer is switched to the corresponding bus. According to the design method provided by the invention, autonomous fault processing and repairing of CAN bus faults can be realized, and the reliability of an electronic system in a radiation environment is improved.
Description
technical field [0001] The invention relates to the technical field of on-orbit data transmission reliability of aerospace products, in particular to a communication reliability and fault-tolerant design method for an on-board computer based on a CAN bus. Background technique [0002] Aerospace spaceborne computers must not only meet high performance, but also must ensure the accuracy and reliability of data processing, transmission and control. Spaceborne computers are often exposed to various electromagnetic radiation environments. These radiation environments are full of various high-energy particles. The impact of high-energy particles on electronic devices in work will cause radiation effects. One of the main reasons for system failure. The single event flip effect is a kind of space radiation effect, which directly acts on the interior of aerospace electronic components, causing logical bit flip errors in logic circuits, which can cause errors in memory data and regis...
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IPC IPC(8): H04L12/40H04L41/0663
CPCH04L12/40H04L12/40176H04L12/40189H04L41/0663H04L2012/40215
Inventor 王红霞曹靓王提义刘鸿瑾张绍林李宾王小波赫丛奎
Owner 北京轩宇空间科技有限公司