Lightweight bus layout method for multi-satellite measurement and control platform system
A layout method and a lightweight technology, applied in the field of measurement and control, can solve problems such as the increase in the amount of data interaction and the number of interactions, the increase in the number of subsystems, and the improvement of the management of multi-satellite measurement and control platforms, so as to reduce the interaction channel and the number of interactions, reduce the Coupling degree and complexity, and the effect of improving intelligent management and control capabilities
Active Publication Date: 2021-11-30
SPACE STAR TECH CO LTD
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Problems solved by technology
However, with the increase of satellites, the amount and number of data interactions between subsystems continue to increase, and the management of existing technologies is becoming more and more difficult
At the same time, the increase in the number of subsystems also increases the difficulty of multi-satellite measurement and control platform management
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[0028] The technical solution of the present invention aims at the situation that the multi-satellite measurement and control management platform has a large number of subsystems, various types of data, and frequent interactions between subsystems. A lightweight bus is designed, and according to the characteristics and functions of the bus, it is divided into: Business data bus and control bus. The function of the service data bus is to link various subsystems in the platform system. The platform system is composed of multiple subsystems, all of which operate independently and are linked through the business data bus. Correspondingly, the control bus realizes the management and control of each subsystem in the system, and uniformly manages a large number of service processes, computing resources and execution modules in the system.
[0029] A number of embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.
[003...
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The invention discloses a lightweight bus arrangement method of a multi-satellite measurement and control management platform system, which includes: dividing the lightweight bus of the multi-satellite measurement and control management platform system into a business data bus and a control bus; The data bus is configured to link each subsystem in the multi-star measurement and control management platform system to realize data interaction between all subsystems that operate independently; Manage and control each subsystem of the multi-satellite measurement and control management platform system, wherein the management and control include performing unified management and control on the service process, computing resources and execution modules in the multi-satellite measurement and control management platform system. Utilizing the scheme of the invention greatly reduces the interaction channels and times of interaction between subsystems, and reduces the coupling degree and complexity between systems.
Description
technical field [0001] The present invention generally relates to the technical field of measurement and control. More specifically, the present invention relates to a lightweight bus layout method for a multi-satellite measurement and control platform system, which is used to optimize data interaction between subsystems of the multi-satellite measurement and control platform system and operation management of the subsystems. Background technique [0002] With the continuous development of space technology, the number of satellite launches has increased rapidly, which makes it more difficult for the satellite measurement and control management platform to manage satellites. At present, in order to solve this problem, each subsystem of the multi-satellite measurement and control management platform is modularized, and each functional module is managed in a process-based manner. However, with the increase of satellites, the amount and number of data interactions between subsy...
Claims
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IPC IPC(8): H04L12/40H04L29/06
CPCH04L12/40006H04L69/165H04L69/18
Inventor 李长德徐伟王燕姜伟刘永刚
Owner SPACE STAR TECH CO LTD