Distributed information system for moon detection

Abstract

The invention provides a distributed information system for moon detection. System division and realization are according to the overall function planning and layout of moon detection; equipment in different areas of a spacecraft is controlled by different single information processing machines respectively. Single information processing machines at all areas collect measurement information of measurement units at areas in charge; according to a given control strategy, corresponding execution mechanisms are controlled independently to make corresponding control motion. When information of all areas needs to be combined for controlling, a main single information processing machine (1) serves as a main control single machine and all secondary single information processing machines (2,3,4) collect measurement information of measurement units in respective areas in charge; the information is transmitted to the main single information processing machine (1) by a bus; the main single information processing machine (1) combines the measurement information of measurement units at the area in charge and integrated measurement information of all secondary single information processing machines and sends the integrated control information to the execution mechanism in the area in charge or transmits the integrated control information to all secondary single information processing machines according to the given control strategy, so that corresponding execution mechanisms can be controlled to make corresponding combined control motion.

Description

technical field [0001] The invention relates to a distributed information system for lunar exploration. Background technique [0002] In the prior art, the spacecraft information processing system is mainly processed and controlled by a central controller. The central controller collects the telemetry information of each remote terminal through the bus, and after centralized summary processing, transmits the control information to each remote terminal through the bus, and each remote terminal passively controls the corresponding actuator. [0003] At present, a central controller is generally used to configure multiple remote terminals. This method is suitable when there are not many spacecraft equipment and the layout is relatively concentrated. However, if there are many spacecraft equipment and the layout is scattered and complex In this case, this method is not suitable. For example, a certain type of spacecraft is structurally divided into multiple parts, and there ar...

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Problems solved by technology

[0003] At present, a central controller is generally used to configure multiple remote terminals. This method is suitable when there are not many spacecraft equipment and the layout is relatively concentrated. However, if there are many spacecraft equipment and the layout is scattered and complex This method is inappropriate in the case

For example, a certain type of spacecraft is structurally divided into multiple parts, and there are many devices scattered in different areas. If centralized acquisition and control is adopted, it will be difficult to implement, with complex cable routing layout, severe signal attenuation, and uneven acquisition and control. Error-prone, and it is difficult to meet the requirements when the real-time requirements are high

This centralized acquisition and control method is not suitable for this multi-device combination aerospace field

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