卫星主动段力学环境监测系统设计  

Design of mechanical environmental monitoring system for satellite powered-flight phase

作　　者：孙延博[1] 贾奥男 虞自飞 方厚招 顾桂华[1] SUN Yanbo;JIA Aonan;YU Zifei;FANG Houzhao;GU Guihua(Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]上海卫星工程研究所,上海201109

出　　处：《航天器环境工程》2024年第3期277-282,共6页Spacecraft Environment Engineering

基　　金：国家重点研发计划项目(编号:2019YFA0708904)。

摘　　要：为精确获取卫星发射主动段星箭界面的加速度与界面力,设计了卫星主动段力学环境监测系统。系统由振动监测单元、振动传感器及应变片组成,其中,振动监测单元设计有3种工作模式——主动段测量模式、在轨振动数据分析模式及振动数据传输模式,采用基于应变的星箭界面动态载荷识别技术,具备6路振动力学传感器数据采集和24路应变数据采集能力。地面试验验证表明,该系统的振动测量精度达到10%,应变测量与LMS(LabVIEW Measurement Studio)系统应变采集数据之间的误差最大不超过4%。实际搭载中获得的星上主动段力学环境测量结果可为优化卫星分析模型和完善卫星地面力学环境模拟试验条件提供参考依据,并为卫星的后续研发与应用提供重要的技术支持。To obtain the acceleration and force of satellite-rocket interface for satellite powered-flight phase accurately,a mechanical environmental monitoring system was designed.The system is composed of vibration monitoring unit,vibration sensors and strain gauges.The vibration monitoring unit was with three operating modes:powered-flight phase measurement mode,on-orbit vibration data analysis mode,and vibration data transmission mode.It adopts strain-based dynamic load identification technology on the satellite-rocket interface,enabling data acquisition from 6 channels of vibration mechanical sensors and 24 channels of strain data.The ground test shows that the vibration measurement accuracy of the system reaches 10%,and the maximum error between the strain measurement and the strain data collected by the LMS(LabVIEW Measurement Studio)system is less than 4%.The measurement results of the mechanical environment of the powered-flight phase on board may provide a reference for optimizing the satellite analysis model and improving the simulation conditions for the satellite ground mechanical environment,and provide important technical support for the subsequent development and application of satellites.

关 键 词：卫星主动段 星箭连接环 力学环境 力学传感器 振动测量 应变测量 

分 类 号：V417.7[航空宇航科学与技术—航空宇航推进理论与工程] V416.2