微小卫星综合电子系统及其关键技术研究
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摘要
本论文以“十一五”国防预先研究项目为背景,针对微小卫星对星上综合电子系统高可靠性、高性能和智能化的要求,论文研究了适合微小卫星平台的星上综合电子系统总体及其关键技术,研制了原理样机。
我国微小卫星近年来发展迅速,星上综合电子系统的研制水平也日益提高,但相对于国际先进的综合电子技术还有一定的差距。论文从集成度、处理性能、可靠性、快速响应性和智能化程度等方面对国内外现有卫星综合电子系统进行了分析,提出研究高可靠性、高度模块化以及具有高智能控制水平的微小卫星综合电子系统,确定了研究内容、总体目标和关键技术。
论文提出了基于动态互联网络的星载并行计算机的设计方案,提高了星载计算机的处理能力和可靠性。方案以桥接器作为纽带实现主从单机的互联,并在此基础上研究了基于双通道动态互联网络的总线拓扑结构,实现基于检查点技术的数据存储和故障诊断及恢复机制,使星载并行计算机系统的资源利用率、并行度和可靠性得到提高。
论文提出了基于即插即用技术的综合电子系统模块化设计方案,来满足微小卫星模块化设计和空间任务快速响应的需求。设计实现了综合电子即插即用平台和以分系统电子数据单为核心的即插即用分系统,并在此基础上完成应用于微小卫星的综合电子即插即用通信协议。
研究了微小卫星星务管理软件的智能控制方案。按照组织级、协调级和执行级三级递阶的控制模式设计了典型配置下的微小卫星智能星务管理软件平台,并针对星载并行计算机的并行处理的特点,研究了星务管理软件平台的并行化方案。
论文最后研制了微小卫星综合电子实验系统。系统由星载并行计算机和即插即用模块组成,基于该系统完成了综合电子基础性能测试、并行性能测试、故障诊断和恢复实验以及综合电子即插即用实验,对星上综合电子总体及关键技术进行了验证。
This thesis is based on the background of‘The Eleventh Five-Year Plan’National Defense Advanced Research Key Project. According to micro-satellite’s demand for an onboard integrated electronic system of high-reliability, high-performance and intelligence, the general and key techniques of the integrated electronic system are studied in this thesis. A prototype of a micro-satellite’s integrated electronic system is developed.
In recent years, with the development of micro-satellite in China, the development of integrated electronic system in micro-satellite is making a rapid progress. However, compared with the advanced international technology of integrated electronic system, there is still a certain gap. In this thesis, at the aspects of integration, processing capacity, reliability, rapid-response ability and intelligence, the existing domestic and abroad integrated electronic systems are compared and the necessity to research the micro-satellite’s integrated electronic system, which is of high reliability, highly modularity and high level of intelligent control, is analyzed. After that, the research content, the general objectives and key techniques of the study is proposed.
In order to enhance the processing capacity and reliability of the satellite-borne computer, a design of parallel computer based on dynamic interconnecting network is presented. In this design, the master computer and the slave computer are interconnected through a bridge. Based on that, the bus topological structure of dual-channel dynamic interconnecting network is studied. The checkpoint-based data storage technology and the fault diagnosis and recovery mechanism are accomplished. Therefore, the resource utilization, parallel degree and reliability of satellite-borne parallel computer system are improved.
To meet the micro-satellite’s need for modular design and fast-response to space mission, a modular design of integrated electronic system based on plug-and-play technology is presented in this paper. In this design, the research content and research objectives of the integrated electronic plug-and-play system are discussed. An integrated electronic plug-and-play platform and a plug-and-play subsystem with subsystem electronic data sheet at the core are accomplished. On this basis an integrated electronic plug-and-play communication protocol applied in micro-satellite is completed.
To meet micro-satellite’s need for intelligent control, the smart control program of micro-satellite’s satellite housekeeping management software is researched. Following the three-tier hierarchical control model, which are the organization level, the coordination level and the execution level, the housekeeping management smart software platform in micro-satellite of a typical configuration is designed. According to the parallel processing characteristics of satellite-borne parallel computer, the parallel program of satellite housekeeping management software platform is studied.
Finally, an experimental system of micro-satellite’s integrated electronic system is designed. On the basis of the experimental system, the test of parallel performance, fault diagnosis, recovery ability and plug-and-play experiment are performed, as well as basic performance. The general and key technologies of integrated electronic system are verified.
我国微小卫星近年来发展迅速,星上综合电子系统的研制水平也日益提高,但相对于国际先进的综合电子技术还有一定的差距。论文从集成度、处理性能、可靠性、快速响应性和智能化程度等方面对国内外现有卫星综合电子系统进行了分析,提出研究高可靠性、高度模块化以及具有高智能控制水平的微小卫星综合电子系统,确定了研究内容、总体目标和关键技术。
论文提出了基于动态互联网络的星载并行计算机的设计方案,提高了星载计算机的处理能力和可靠性。方案以桥接器作为纽带实现主从单机的互联,并在此基础上研究了基于双通道动态互联网络的总线拓扑结构,实现基于检查点技术的数据存储和故障诊断及恢复机制,使星载并行计算机系统的资源利用率、并行度和可靠性得到提高。
论文提出了基于即插即用技术的综合电子系统模块化设计方案,来满足微小卫星模块化设计和空间任务快速响应的需求。设计实现了综合电子即插即用平台和以分系统电子数据单为核心的即插即用分系统,并在此基础上完成应用于微小卫星的综合电子即插即用通信协议。
研究了微小卫星星务管理软件的智能控制方案。按照组织级、协调级和执行级三级递阶的控制模式设计了典型配置下的微小卫星智能星务管理软件平台,并针对星载并行计算机的并行处理的特点,研究了星务管理软件平台的并行化方案。
论文最后研制了微小卫星综合电子实验系统。系统由星载并行计算机和即插即用模块组成,基于该系统完成了综合电子基础性能测试、并行性能测试、故障诊断和恢复实验以及综合电子即插即用实验,对星上综合电子总体及关键技术进行了验证。
This thesis is based on the background of‘The Eleventh Five-Year Plan’National Defense Advanced Research Key Project. According to micro-satellite’s demand for an onboard integrated electronic system of high-reliability, high-performance and intelligence, the general and key techniques of the integrated electronic system are studied in this thesis. A prototype of a micro-satellite’s integrated electronic system is developed.
In recent years, with the development of micro-satellite in China, the development of integrated electronic system in micro-satellite is making a rapid progress. However, compared with the advanced international technology of integrated electronic system, there is still a certain gap. In this thesis, at the aspects of integration, processing capacity, reliability, rapid-response ability and intelligence, the existing domestic and abroad integrated electronic systems are compared and the necessity to research the micro-satellite’s integrated electronic system, which is of high reliability, highly modularity and high level of intelligent control, is analyzed. After that, the research content, the general objectives and key techniques of the study is proposed.
In order to enhance the processing capacity and reliability of the satellite-borne computer, a design of parallel computer based on dynamic interconnecting network is presented. In this design, the master computer and the slave computer are interconnected through a bridge. Based on that, the bus topological structure of dual-channel dynamic interconnecting network is studied. The checkpoint-based data storage technology and the fault diagnosis and recovery mechanism are accomplished. Therefore, the resource utilization, parallel degree and reliability of satellite-borne parallel computer system are improved.
To meet the micro-satellite’s need for modular design and fast-response to space mission, a modular design of integrated electronic system based on plug-and-play technology is presented in this paper. In this design, the research content and research objectives of the integrated electronic plug-and-play system are discussed. An integrated electronic plug-and-play platform and a plug-and-play subsystem with subsystem electronic data sheet at the core are accomplished. On this basis an integrated electronic plug-and-play communication protocol applied in micro-satellite is completed.
To meet micro-satellite’s need for intelligent control, the smart control program of micro-satellite’s satellite housekeeping management software is researched. Following the three-tier hierarchical control model, which are the organization level, the coordination level and the execution level, the housekeeping management smart software platform in micro-satellite of a typical configuration is designed. According to the parallel processing characteristics of satellite-borne parallel computer, the parallel program of satellite housekeeping management software platform is studied.
Finally, an experimental system of micro-satellite’s integrated electronic system is designed. On the basis of the experimental system, the test of parallel performance, fault diagnosis, recovery ability and plug-and-play experiment are performed, as well as basic performance. The general and key technologies of integrated electronic system are verified.
引文
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