A satellite-borne integrated electronic system

Abstract

The invention discloses a satellite-borne integrated electronic system, comprising: a backplane, wherein the backplane is provided with an interconnected electric interface and a communication interface between other modules; A power module for converting a primary power source of the spacecraft into a secondary power source required by an integrated electronic interior, wherein the power module is connected with the backplane through a connector to provide a secondary power source and an internal low-speed bus; a Satellite service computer module which realizes the scheduling and management of the integrated electronic system tasks, is connected with the backplane through a connector, realizes the internal low-speed bus connection, transmits various instruction data to other modules in the system through the internal low-speed bus, and receives various information data of other modules; and a high-speed bus switch module, wherein a high-speed bus is directly connected between the satellite service computer module and the high-speed bus switch module to transmit large flow data of the integrated electronic system to the high-speed bus switch module.

Description

technical field [0001] The present invention relates to the field of aerospace, in particular, the present invention relates to a spaceborne integrated electronic system based on high and low speed hybrid bus Background technique [0002] Generally speaking, a traditional spacecraft is divided into several subsystems according to their functions, and each subsystem is designed independently, such as propulsion and attitude control, thermal control, data transmission, measurement and control, etc. The star computer is only responsible for remote control, telemetry, program control and For tasks such as time management, the communication interfaces between the star computer and other systems are different, resulting in complex interface relationships between systems, weak general capabilities, long design and development cycles, and high R&D costs. [0003] At present, the integrated electronic system for spacecraft has basically realized the transformation from subsystem to m...

AI Technical Summary

Problems solved by technology

[0004] a) At present, non-bus interfaces such as SPI, UART, and 422 are mainly used to realize communication between modules, which are used for the transmission of instructions and related data, and mixed transmission of data and instructions, resulting in low real-time performance of instruction reception and execution; data cannot be realized efficient transmission

[0005] b) The interfaces between modules and systems are different, resulting in poor versatility of modules and systems, low design and R&D efficiency, and high development costs

[0006] Therefore, there is a need in the art for an integrated electronic system architecture, through which technical problems such as modules and systems in the prior art are at least partially solved.

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