A dual-mode redundant satellite-borne computer system

A space-borne computer, dual-mode redundancy technology, applied in the field of computer systems, can solve the problems of system-level redundancy, low cost, small space, etc., and achieve the effect of ensuring reliable transmission

Inactive Publication Date: 2019-06-21
四川中天策略科技有限公司
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  • Description
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  • Application Information

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Problems solved by technology

However, commercial devices are far inferior to aerospace-grade devices in terms of reliability and box-resistant performance; CubeSat’s small space, low cost, and COTS-based devices make it impossible for all components of CubeSat to achieve system-level redundancy like traditional large satellites.

Method used

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  • A dual-mode redundant satellite-borne computer system
  • A dual-mode redundant satellite-borne computer system

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Embodiment Construction

[0011] In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention.

[0012] The technical solutions of the embodiments of the present invention will be described below with reference to the accompanying drawings.

[0013] like figure 1 As shown, the present invention provides a dual-mode redundant on-board computer system, including: independent I / O module, minimum system A, detection unit, minimum system B, computer power supply module, system bus, CAN module, SRAM, FLASH, whole star CAN network; there are multiple independent I / O modules, one of which is connected to the minimum system B as a...

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Abstract

The invention relates to a dual-mode redundancy satellite-borne computer system which comprises an independent I / O module, a minimum system A, a detection unit, a minimum system B, a computer power supply module, a system bus, a CAN module, an SRAM, a FLASH and a whole satellite CAN network. One of the independent I / O modules is used as an input end to be connected with the minimum system B; the minimum system B is connected with the detection unit; the detection unit is connected with the minimum system A; the minimum system A is connected with the other independent I / O module serving as an output end; the computer power supply module is respectively connected with the minimum system A, the detection unit and the minimum system and supplies power to the minimum system A, the detection unit and the minimum system; the bus module of the satellite-borne computer is subjected to redundancy design in a simple system redundancy mode, a bus node detection switching mechanism and a transmission layer protocol are designed, and reliable transmission of data and reliability of connection between subsystems are guaranteed.

Description

technical field [0001] The invention relates to the technical field of computer systems, in particular to a dual-mode redundant on-board computer system. Background technique [0002] With the rapid development of electronic technology in recent years, commercial devices are gradually replacing traditional devices in some aspects of large spacecraft design due to their advantages of low cost, low power consumption, high performance, and high integration. However, commercial devices are far inferior to aerospace-grade devices in terms of reliability and box-resistant performance. CubeSat’s small space, low cost, and COTS-based devices make it impossible for all components of CubeSat to achieve system-level redundancy like traditional large satellites. Contents of the invention [0003] The purpose of the present invention is achieved through the following technical solutions. [0004] A dual-mode redundant on-board computer system, comprising: an independent I / O module, a ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F11/16
Inventor 安祝英
Owner 四川中天策略科技有限公司
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