小卫星姿态控制飞轮系统热设计
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摘要
为了满足小卫星姿态控制飞轮系统热设计的要求,对飞轮系统的热特性进行了分析和试验验证。根据飞轮运行工况,分别对飞轮系统机械损耗和电控损耗进行了理论计算,确定了系统主要热源点的分布情况。然后,依据系统拓扑结构,建立了整机的等效热网络模型;采用有限元法,分别对飞轮相关组件和整机在卫星连续侧摆工况下的热特性进行了分析。最后,研制了实验样机,并对样机进行了热真空试验。在经过8h卫星连续侧摆机动工况下的实验结果表明:当环境温度为45.0℃时,监测点最后平衡温度约为57.8℃,相对于有限元分析结果的53.2℃,误差为8.6%,表明热分析结果与试验结果吻合度较好,可为姿态控制飞轮系统的热设计提供重要参考。
To meet the thermal design requirements of an attitude control flywheel system for small satellites,the thermal performance of the flywheel system was analyzed and an experimental verification was carried out.According to the flywheel operating conditions,the electronically controlled loss and the mechanical loss of the flywheel system were calculated in theory to determine the distribution of the main heat source of the system.Then,an equivalent thermal network model was established based on the whole mechanical topology structure.The Finite Element Method(FEM)was applied to analysis of the thermal performance of the main components and the whole system under the swinging condition,respectively.Finally,aprototype was developed and the thermal vacuum test was carried out to validate the analysis results.The results show that the final equilibrium temperature of the monitoring point is about 57.8 ℃ under the swinging operating condition for 8hours with the ambient temperature 45.0 ℃.The error is 8.6%relative to the FEM result of 53.2 ℃,which indicates thatthe temperature values obtained in the analysis and the experiment are coincident with well and the thermal design meets the thermal requirements of the satellite systems.This analysis provides an important reference for the thermal design of attitude control flywheel systems.
To meet the thermal design requirements of an attitude control flywheel system for small satellites,the thermal performance of the flywheel system was analyzed and an experimental verification was carried out.According to the flywheel operating conditions,the electronically controlled loss and the mechanical loss of the flywheel system were calculated in theory to determine the distribution of the main heat source of the system.Then,an equivalent thermal network model was established based on the whole mechanical topology structure.The Finite Element Method(FEM)was applied to analysis of the thermal performance of the main components and the whole system under the swinging condition,respectively.Finally,aprototype was developed and the thermal vacuum test was carried out to validate the analysis results.The results show that the final equilibrium temperature of the monitoring point is about 57.8 ℃ under the swinging operating condition for 8hours with the ambient temperature 45.0 ℃.The error is 8.6%relative to the FEM result of 53.2 ℃,which indicates thatthe temperature values obtained in the analysis and the experiment are coincident with well and the thermal design meets the thermal requirements of the satellite systems.This analysis provides an important reference for the thermal design of attitude control flywheel systems.
引文
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[19]陈诚,杨利民,张晨阳,等.考虑运行条件的Elman网络丝杠驱动系统热误差建模[J].光学精密工程,2014,22(3):704-711.CHEN CH,YANG L M,ZHANG CH Y,et al..Modeling on thermal errors of ball screw driving system on Elman network considering operating conditions[J].Opt.Precision Eng.,2014,22(3):704-711.(in Chinese)
[2]林来兴.分布式小卫星系统的技术发展与应用前景[J].航天器工程,2010,19(1):60-66.LIN L X.Technological development and application prospects of distributed small satellite system[J].Spacecraft Engineering,2010,19(1):60-66.(in Chinese)
[3]张姝娜,房建成,韩邦成,等.磁悬浮飞轮转子组件温度场分析与研究[J].中国惯性技术学报,2007,15(1):67-71.ZHANG SH N,FANG J CH,HAN B CH,et al..Thermal analysis and research on magnetically suspended flywheel rotor[J].Journal of Chinese Inertial Technology,2007,15(1):67-71.(in Chinese)
[4]王春娥,房建成,汤继强,等.磁悬浮反作用飞轮热设计方法与实验研究[J].航空学报,2011,32(4):598-607.WANG CH E,FANG J CH,TANG J Q,et al..Thermal design method and experimental research of magnetically suspended reaction flywheel[J].Aeronautica et Astronautica Sinica,2011,32(4):598-607.(in Chinese)
[5]OKOU R,KHAN M A,BARENDSE P S,et al..Thermal model of electromechanical flywheel with brushless DC machine[C].2009 IEEE Electrical Power&Energy Conference,2009:1-5.
[6]HUYNH C,ZHENG L P,MULLEN P M.Thermal performance evaluation of a high-speed flywheel energy storage system[C].The 33rd Annual Conference of the IEEE Industrial Electronics Society,2007(58):163-168.
[7]王辉,武俊峰,李胤,等.小卫星用反作用飞轮系统设计[J].光学精密工程,2014,22(2):331-337.WANG H,WU J F,LI Y,et al..Design of the reaction flywheel system for small satellite[J].Opt.Precision Eng.,2014,22(2):331-337.(in Chinese)
[8]邓四二,李兴林,汪久根,等.角接触球轴承摩擦力矩波动性分析[J].机械工程学报,2011,47(23):104-112.DENG S E,LI X L,WANG J G,et al..Analysis on the friction torque fluctuation of angular contact ball bearings[J].Journal of Mechanical Engineering,2011,47(23):104-112.(in Chinese)
[9]KANATSU M,OHTA H.Running torque of ball bearings with polymer lubricant(running torque formulas of deep groove ball bearings under axial loads)[J].Journal of Tribology,2008,130(4):041507.
[10]邓四二,李兴林,汪久根,等.角接触球轴承摩擦力矩特性研究[J].机械工程学报,2011,47(5):114-120.DENG S E,LI X L,WANG J G,et al..Frictional torque characteristic of angular contact ball bearings[J].Journal of Tribology,2011,47(5):114-120.(in Chinese)
[11]朱爱华,朱成九,张卫华.滚动轴承摩擦力矩的计算分析[J].轴承,2008,(7):1-3.ZHU A H,ZHU CH J,ZHANG W H.Analysis on calculation of friction torque of rolling bearings[J].Bearing,2008,(7):1-3.(in Chinese)
[12]汤平华,漆亚梅,黄国辉,等.定子无铁心飞轮电机绕组涡流损耗分析[J].电工技术学报,2010,25(3):27-32.TANG P H,QI Y M,HUANG G H,et al..Eddy current loss analysis of ironless flywheel electric machine’s winding[J].Transactions of China Electrotechnical Society,2010,25(3):27-32.(in Chinese)
[13]陈茂盛,金光,安源,等.采用自适应PI控制的单框架控制力矩陀螺角动量飞轮系统设计[J].光学精密工程,2011,19(5):1075-1081.CHEN M SH,JIN G,AN Y,et al..Design of angular momentum wheel in SGCMG using adaptive compensation PI control[J].Opt.Precision Eng.,2011,19(5):1075-1081.(in Chinese)
[14]董恺琛,赵开春,赵鹏飞,等.微纳卫星姿控软件实时测试系统[J].光学精密工程,2013,21(8):2008-2015.DONG K CH,ZHAO K CH,ZHAO P F,et al..Real-time testing system for attitude control software of micro-nano satellite[J].Opt.Precision Eng.,2013,21(8):2008-2015.(in Chinese)
[15]陈立恒,吴清文,刘伟奇,等.空间摄像机热控系统设计[J].光学精密工程,2012,20(3):556-562.CHEN L H,WU Q W,LIU W Q,et al..Thermal design for space cameras[J].Opt.Precision Eng.,2012,20(3):556-562.(in Chinese)
[16]关奉伟,刘巨.空间光学遥感器大功率控制电箱的热设计[J].中国光学,2013,6(36):919-929.GUAN F W,LIU J.Thermal design of high power electronic control cabinet of space optical remote sensor[J].Chinese Optics,2013,6(36):919-929.(in Chinese)
[17]江帆,吴清文,刘巨,等.低轨道轻质星载一体化空间光学遥感器的热设计[J].中国光学,2013,6(2):237-243.JIANG F,WU Q W,LIU J,et al..Thermal design of lightweight spcace remote sensor integrated with satellite in low earth orbit[J].Chinese Optics,2013,6(2):237-243.(in Chinese)
[18]郭亮,吴清文,颜昌翔.空间光谱成像仪热设计参数的灵敏度[J].光学精密工程,2012,20(6):1208-1217.GUO L,WU Q W,YAN CH X.Sensitivity of thermal design parameters for spcace spectral imaging apparatus[J].Opt.Precision Eng.,2012,20(6):1208-1217.(in Chinese)
[19]陈诚,杨利民,张晨阳,等.考虑运行条件的Elman网络丝杠驱动系统热误差建模[J].光学精密工程,2014,22(3):704-711.CHEN CH,YANG L M,ZHANG CH Y,et al..Modeling on thermal errors of ball screw driving system on Elman network considering operating conditions[J].Opt.Precision Eng.,2014,22(3):704-711.(in Chinese)