FY-4卫星微振动抑制技术研究
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摘要
根据装载干涉式大气垂直探测仪对微振动抑制的要求,对风云四号(FY-4)卫星的微振动抑制技术进行了研究。通过统计星上振源,规划整星级频谱,研究微振动传播机理,设计了振源隔离和载荷隔振的双级隔振系统。给出了动量轮的隔振设计,将动量轮的安装支架由刚性变为基于六角架(Hexapod)构型的非线性变刚度柔性支架,隔离动量轮传递至卫星平台的振动干扰,从源头控制振动。分析了发射段幅频特性和在轨段隔振性能,结果表明试验结果与理论分析一致。在此基础上,采用隔振组件和解锁组件并联使用方式,实现干涉式大气垂直探测仪的二次隔振设计,以进一步抑制卫星平台传递至探测仪的微振动干扰。地面微振动试验和在轨微振动实测结果表明:隔振系统能使卫星平台传递至载荷安装面的微振动量级控制在0.1×10-3g以下,满足指标要求。FY-4卫星微振动抑制技术可为其他卫星的微振动抑制提供参考。
According to the requirement of micro-vibration source isolation for interferometer detector,the micro-vibration suppression was studied for FY-4 meteorological satellite in this paper.The two level microvibration isolation system which composed of vibration source and sensitive payload isolation devices was designed by onboard vibration source statistics,the spectrum planning on the whole satellite level and the mechanism research of micro-vibration propagation.The vibration isolation was designed for reaction wheel.The vibration isolation device was designed based on the Hexapod configuration,the vibration from source hence be controlled as the vibration transferring into the satellite platform was weakened.The characteristics of amplitude-frequency in active phase and the performances of vibration isolation in orbit were analyzed.The results showed that the experiment results were well agreed with the simulation results.For the sensitive payload vibration isolation,the interferometer detector was isolated by isolators installed between the satellite top plate and the payload.The micro-vibration isolation experiments conducted both on ground and in orbit show that the two level vibration isolation system can effectively reduce the vibration transmitted into the payload and the vibration level is controlled at 0.1×10~(-3) gand below which satisfies the application requirement of FY-4 satellite.The micro-vibration isolation technology of FY-4 satellite has significance value and can also be used in other similar satellites.
According to the requirement of micro-vibration source isolation for interferometer detector,the micro-vibration suppression was studied for FY-4 meteorological satellite in this paper.The two level microvibration isolation system which composed of vibration source and sensitive payload isolation devices was designed by onboard vibration source statistics,the spectrum planning on the whole satellite level and the mechanism research of micro-vibration propagation.The vibration isolation was designed for reaction wheel.The vibration isolation device was designed based on the Hexapod configuration,the vibration from source hence be controlled as the vibration transferring into the satellite platform was weakened.The characteristics of amplitude-frequency in active phase and the performances of vibration isolation in orbit were analyzed.The results showed that the experiment results were well agreed with the simulation results.For the sensitive payload vibration isolation,the interferometer detector was isolated by isolators installed between the satellite top plate and the payload.The micro-vibration isolation experiments conducted both on ground and in orbit show that the two level vibration isolation system can effectively reduce the vibration transmitted into the payload and the vibration level is controlled at 0.1×10~(-3) gand below which satisfies the application requirement of FY-4 satellite.The micro-vibration isolation technology of FY-4 satellite has significance value and can also be used in other similar satellites.
引文
[1]董瑶海.航天器微振动——理论与实践[M].北京:中国宇航出版社,2015:1-3.
[2]BRONOWICKI A,MACDONALD R,GURSEL Y,et al.Dual-stage vibration isolation for Optical Interferometer Missions[J].Proc SPIE,Astronomical Telescopes&Instrumentation,2002,4852-68:753-763.
[3]DAVIS L P,WILSON J F,JEWELL R E,et al.Hubble Space Telescope reaction wheel assembly vibration isolation system[R].NASA N87-22702,1986.
[4]BRONOWICKI A.A layered vibration control strategy for space telescopes[C]//Smart Structures and Materials Conference 2003:Smart Structures and Integrated Systems.Bellingham:SPIE,2003:5056,487-496.
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[6]孟光.周徐斌.卫星微振动及控制技术进展[J].航空学报,2015,36(8):2609-2619.
[7]杨剑锋.空间光学载荷微振动关键技术研究[D].长春:中国科学院研究生院(长春光学精密机械与物理研究所),2016.
[8]刘兴天,郑京良,申军烽.隔振器安装位置对卫星载荷隔振性能的影响研究[J].上海航天,2016,33(6):67-71.
[9]谭天乐,朱春艳,朱东方,等.航天器微振动测试、隔离、抑制技术综述[J].上海航天,2014,31(6):36-45+51.
[10]庞世伟,潘腾,毛一岚,等.某型号卫星微振动试验研究及验证[J].航天器环境工程,2016,33(3):305-311.
[11]ZHOU W D,LI D X,Design and analysis of an intelligent vibration isolation platform for reaction/momentum wheel assemblies[J].Journal of Sound and Vibration,2012,331:2984-3005.
[12]HUANG X C,SUN J Y,HUA H X,et al.Modeling and optimization of octostrut vibration isolation platform by FRF-based substructuring method[J].ASCE Journal of Aerospace Engineering,2015,28:3.
[13]董瑶海.风云四号气象卫星及其应用展望[J].上海航天,2016,33(2):1-8.
[14]EYERMAN C E,SHEA J F.A systems engineering approach to disturbance minimization for spacecraft utilizing controlled structures technology[R].MIT SERC Report#2-90,Massachusetts Institute of Technology:MIT Space Engineering Research Center,1990.
[15]MELODY J W.Discrete-frequency and broadband reaction wheel disturbance models[R].Interoffice Memorandum 3411-95-200csi,La Canada Flintridge:Jet Propulsion Laboratory,1995.
[16]石新宇,周徐斌,申军烽,等.航天器电磁变频吸振器性能分析与测试[J].噪声与振动控制,2015,35(5):60-64.
[17]虞自飞,周徐斌,申军烽.卫星动量轮隔振与吸振联合减振系统设计[C]//中国空间科学学会2013年空间光学与机电技术研讨会.西安:中国空间科学学会,2013:241-246.
[18]申军烽,杜胜,周徐斌,等.高精度光学有效载荷微振动隔振系统设计与分析[C]//2011年全国机械动力学学术大会.杭州:中国振动工程学会机械动力学专业委员会,2011:124-129.
[19]申军烽,周徐斌,薛景赛,等.弹性元件刚度特性对隔振系统解耦度的影响分析[C]//中国宇航学会飞行器总体专业委员会第12届学术研讨会.延吉:中国宇航学会,2012:436-440.
[20]蒋国伟,周徐斌,申军烽,等.卫星微振动虚拟仿真技术研究及应用[J].计算机测量与控制,2011,19(9):2206-2209.
[2]BRONOWICKI A,MACDONALD R,GURSEL Y,et al.Dual-stage vibration isolation for Optical Interferometer Missions[J].Proc SPIE,Astronomical Telescopes&Instrumentation,2002,4852-68:753-763.
[3]DAVIS L P,WILSON J F,JEWELL R E,et al.Hubble Space Telescope reaction wheel assembly vibration isolation system[R].NASA N87-22702,1986.
[4]BRONOWICKI A.A layered vibration control strategy for space telescopes[C]//Smart Structures and Materials Conference 2003:Smart Structures and Integrated Systems.Bellingham:SPIE,2003:5056,487-496.
[5]BRONOWICKI A.Active vibration control of large optical space structures[J].Smart Materials and Structures,1999,8(6):740-752.
[6]孟光.周徐斌.卫星微振动及控制技术进展[J].航空学报,2015,36(8):2609-2619.
[7]杨剑锋.空间光学载荷微振动关键技术研究[D].长春:中国科学院研究生院(长春光学精密机械与物理研究所),2016.
[8]刘兴天,郑京良,申军烽.隔振器安装位置对卫星载荷隔振性能的影响研究[J].上海航天,2016,33(6):67-71.
[9]谭天乐,朱春艳,朱东方,等.航天器微振动测试、隔离、抑制技术综述[J].上海航天,2014,31(6):36-45+51.
[10]庞世伟,潘腾,毛一岚,等.某型号卫星微振动试验研究及验证[J].航天器环境工程,2016,33(3):305-311.
[11]ZHOU W D,LI D X,Design and analysis of an intelligent vibration isolation platform for reaction/momentum wheel assemblies[J].Journal of Sound and Vibration,2012,331:2984-3005.
[12]HUANG X C,SUN J Y,HUA H X,et al.Modeling and optimization of octostrut vibration isolation platform by FRF-based substructuring method[J].ASCE Journal of Aerospace Engineering,2015,28:3.
[13]董瑶海.风云四号气象卫星及其应用展望[J].上海航天,2016,33(2):1-8.
[14]EYERMAN C E,SHEA J F.A systems engineering approach to disturbance minimization for spacecraft utilizing controlled structures technology[R].MIT SERC Report#2-90,Massachusetts Institute of Technology:MIT Space Engineering Research Center,1990.
[15]MELODY J W.Discrete-frequency and broadband reaction wheel disturbance models[R].Interoffice Memorandum 3411-95-200csi,La Canada Flintridge:Jet Propulsion Laboratory,1995.
[16]石新宇,周徐斌,申军烽,等.航天器电磁变频吸振器性能分析与测试[J].噪声与振动控制,2015,35(5):60-64.
[17]虞自飞,周徐斌,申军烽.卫星动量轮隔振与吸振联合减振系统设计[C]//中国空间科学学会2013年空间光学与机电技术研讨会.西安:中国空间科学学会,2013:241-246.
[18]申军烽,杜胜,周徐斌,等.高精度光学有效载荷微振动隔振系统设计与分析[C]//2011年全国机械动力学学术大会.杭州:中国振动工程学会机械动力学专业委员会,2011:124-129.
[19]申军烽,周徐斌,薛景赛,等.弹性元件刚度特性对隔振系统解耦度的影响分析[C]//中国宇航学会飞行器总体专业委员会第12届学术研讨会.延吉:中国宇航学会,2012:436-440.
[20]蒋国伟,周徐斌,申军烽,等.卫星微振动虚拟仿真技术研究及应用[J].计算机测量与控制,2011,19(9):2206-2209.