Effective load control and processing system facing satellite

Abstract

The present invention provides an effective load control and processing system facing a satellite. The system comprises: a power supply module configured convert a 28V primary source to a positive 5V power supply for the usage of other function modules and realizing the cold-hot switching according to an external instruction, a first control module and a second control module configured to be responsible for the control realization of the effective load control and processing system facing a satellite, a main processing module configured to perform integration processing of digital signals and cold-hot backups, and a first preprocessing module, a second preprocessing module and a third preprocessing module which are configured to perform preprocessing of the intermediate-frequency signals and perform hot backups. The effective load control and processing system facing the satellite has high reliability and radiation hardening index and has high anti-single event effect capacity and the single event effect protection function, supports the real-time operation system and common communication interfaces and control interfaces of a plurality of loads, and has the functions of control, communication, remote measurement, redundancy backup and application software, etc.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to a satellite payload control and processing system. Background technique [0002] The Chinese invention patent with the patent publication number CN103744754A (publication date is April 23, 2014) discloses a radiation-resistant hardened parallel planetary computer system and its usage method. The method is realized by three DSP (Digital Signal Processing) chips and four FPGA (Field Programmable Gate Array) 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 "two parallel plus one 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 fault, the backup DSP replaces t...

AI Technical Summary

Problems solved by technology

The disadvantage of this method is mainly that there is a single point

The invention implements radiation hardened and parallel planetary computer systems such as figure 2 As shown, the system control unit is a single point, which reduces the reliability of the entire system

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