Information transmission method of spacecraft

Abstract

The invention discloses an information transmission method of a spacecraft. The information transmission method comprises the following steps that: when a numerical control computer works normally, the numerical control computer receives telemeasuring data acquired by a remote unit and telemeasuring data provided by the control computer per se, the numerical control computer also receives telemeasuring data of a loading task processing unit, carries out telemeasuring formatting on all the received telemeasuring data to generate whole spacecraft telemeasuring data and outputs the whole spacecraft telemeasuring data to the remote unit A, and the remote unit A finishes information source encryption of the whole spacecraft telemeasuring data and outputs the encrypted information sources to a measurement and control responder; and when the numerical control computer works abnormally, the remote unit A directly outputs the acquired telemeasuring data and the telemeasuring data generated by the remote unit A per se to the measurement and control responder for downloading all the telemeasuring data. The information transmission method disclosed by the invention realizes backup of a key telemeasuring information transmission path of the spacecraft, thereby ensuring continuous monitoring of the ground on working states of key equipment of the spacecraft and improving the information transmission reliability.

Description

technical field [0001] The invention relates to a method for transmitting information in a spacecraft, belonging to the technical field of spacecraft information. Background technique [0002] At present, there are three main types of spacecraft information architecture: decentralized, centralized, and a combination of decentralized and centralized. In the decentralized system, each subsystem of the spacecraft completes the information management in their respective subsystems relatively independently. In this system, the interface relationship between the subsystems is simple, but there are disadvantages that the information between the subsystems cannot be shared and the information utilization rate is low; In the centralized system, a system management unit is used to complete the information management of the subsystems of the entire spacecraft. In this system, the information processing is highly centralized. If the system management unit fails, the entire spacecraft sy...

AI Technical Summary

Problems solved by technology

In the decentralized system, each subsystem of the spacecraft completes the information management in their respective subsystems relatively independently. In this system, the interface relationship between the subsystems is simple, but there are disadvantages that the information between the subsystems cannot be shared and the information utilization rate is low; In the centralized system, a system management unit is used to complete the information management of the subsystems of the entire spacecraft. In this system, the information processing is highly centralized. If the system management unit fails, the entire spacecraft system will be paralyzed, and the risk is high; the combination of decentralization and centralization In the system, each sub-system completes the information management within its own sub-system, and a digital tube computer is used to complete the information management at the spacecraft system level. How to realize the reliable transmission, efficient fusion and full utilization of various information in the spacecraft is the core of the system design and the key to ensure the reliable operation of the spacecraft in orbit

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