摘要
基于冗余主从节点架构,设计了一种器载遥测参数采集系统,承担信息汇总功能的中心节点采用双机热备份,在出现故障时经自主判别和切换,可实现控制权快速切换,提高了系统的可靠性和重构性。采编单元的供电与信号采集模块采用一体化设计,降低了配套电缆网设计难度和重量。测试结果表明,该系统能有效地满足航天飞行器遥测参数隔离采集、传输和故障隔离的要求,实现遥测参数的高精度采集和传输,对于工程应用具有一定的参考意义。
A special data collection system for aircraft telemetry parameters was developed based on master⁃slave redundant nodes architecture.Dual hot standby redundant architecture was adopted in the central node,and control right can be switched rapidly when fault happens,the reliability and reconfiguration can be achieved.Power modules and signal collection modules of acquisition and coding unit were integrated,and then the complexity and weight of electric cables can be decreased.The experimental results indicate that the collection system can meet the demands of isolated acquisition and transmission and fault isolation.The data collection system has engineering application value for data acquisition and transmission with high reliability and accuracy.
作者
陈玉坤
梁君
荣刚
曾发
李恺
CHEN Yu-kun;LIANG Jun;RONG Gang;ZENG Fa;LI Kai(China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《宇航计测技术》
CSCD
2020年第6期51-56,63,共7页
Journal of Astronautic Metrology and Measurement
关键词
冗余
飞行器
遥测参数
数据采集
Redundance
Aircraft
Telemetry parameter
Data collection
