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Management and control system for medium and high-orbit satellite payloads

A payload, management and control system technology, applied in the aerospace field, can solve problems such as hardware methods that are not mentioned, and achieve the effects of strong SEU/SET protection function, high radiation resistance index, and high reliability

Inactive Publication Date: 2016-05-04
NO 32 RES INST OF CHINA ELECTRONICS TECH GRP
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Problems solved by technology

This method only describes the fault-tolerant method of the spaceborne computer from the software point of view, and does not mention the hardware method

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  • Management and control system for medium and high-orbit satellite payloads
  • Management and control system for medium and high-orbit satellite payloads

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Embodiment Construction

[0021] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0022] The management and control system for medium and high orbit satellite payloads provided by the present invention provides a highly reliable and long-life management and control solution for medium and high orbit satellite payloads. Through aerospace-grade components and cold backup design for the whole machine, it realizes highly reliable management and control of satellite payloads, and supports program reconstruction, communication (1553B, RS232), data storage and other functions. It aims...

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Abstract

The invention provides a management and control system for medium and high-orbit satellite payloads. The system comprises a hardware part and a software part, wherein the hardware part includes a CPU as well as an FPGA module, a communication module, a bus isolation driving module and a data memory which are connected with the CPU, and the software part includes guide software, system program software and FPGA software, wherein the guide software and the system program software operate on the CPU and are mainly responsible for system hardware initialization, electrified self checking and data processing, and the FPGA software operates on the FPGA module and is mainly responsible for system decoding control, command control, reset control and data memory collocation control. The management and control system of the invention are applied to commonly-used application of the satellite payloads, such as program reconstruction, communication management and data storage, and can load a variety of programs for loading satellites and make loading systems complete different functions in different conditions. The management and control system has the advantages of high reliability, long service life and anti-radiation performance.

Description

technical field [0001] The invention belongs to the field of aerospace and space, and relates to a method for managing and controlling payloads of medium and high orbit satellites, in particular to program reconstruction and communication management for payloads of medium and high orbit satellites. Background technique [0002] Chinese patent CN103744754A (published on April 23, 2014) discloses a radiation-resistant hardened parallel planetary computer system and its application method. The method is realized by three DSP chips and four FPGA chips. The system is composed of a system control unit and three identical subsystems. The system control unit is realized on an FPGA, and each subsystem is composed of a DSP and an FPGA, and is connected with the system control unit. The system adopts the structure of "2 parallel + 1 backup". Two DSPs process the spaceborne tasks in parallel, and the other DSP is used as a backup. When the DSP working in parallel has an unrecoverable f...

Claims

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Application Information

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IPC IPC(8): G05B19/042
CPCG05B19/0423G05B2219/25341
Inventor 刘启蒙许红梅丁慧敏
Owner NO 32 RES INST OF CHINA ELECTRONICS TECH GRP
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