基于温度模型的10N推力器点火异常发现方法
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摘要
为解决在轨卫星10N推力器点火异常无法及时发现的问题,根据10N推力器热平衡方程,考虑空间外热流、加热器加热、推进剂燃烧和向深冷空间热辐射等因素,应用10N推力器在轨实测温度数据,建立了精细化的10N推力器点火温度数学模型;进一步考虑测温热敏电阻测量误差,建立了10N推力器点火温度包络线模型;在此基础上提出了基于温度模型的10N推力器点火异常发现方法。该方法计算精度较高,绝对误差小于3℃,在10N推力器点火温度偏离正常趋势3～5℃后即可快速发现。以东方红3号平台某卫星为例进行了案例应用,所提方法计算得到的10N推力器点火温度理论值与实测值最大仅差2.72℃,证明所提方法预测精度较高,对于及时发现10N推力器点火异常、保证卫星轨道或者姿态控制的成功具有重要作用。
To solve a problem that ignition anomaly can't be detected in time,based on the thermal equilibrium equation,the space heat flow,heater heating,propellant combustion and thermal radiation to cryogenic space is considered to build accurate ignition temperature nodel for10 Nthruster by using on-orbit true temperature.Further considering the error of measuring thermistor,an envelope model for 10 Nthruster ignition temperature is established.Based on the above,a detection method for 10 Nthruster ignition anomaly of on-orbit satellites is proposed.The accuracy of the method is relatively high,and the absolute error is less than 3℃.It can be found quickly after 10 Nthruster ignition temperature deviating from the normal trend by 3～5℃.The method is applied to a DFH-3 satellite,and the maximum difference of 10 Nthruster ignition temperature between the theoretical values calculated by the proposed method and the measured values is only 2.72℃.It is proved that the prediction accuracy of the proposed method is high.It plays an important role in deteting 10 Nthruster ignition anomaly in time and ensures the success of satellite orbit or attitude control.
To solve a problem that ignition anomaly can't be detected in time,based on the thermal equilibrium equation,the space heat flow,heater heating,propellant combustion and thermal radiation to cryogenic space is considered to build accurate ignition temperature nodel for10 Nthruster by using on-orbit true temperature.Further considering the error of measuring thermistor,an envelope model for 10 Nthruster ignition temperature is established.Based on the above,a detection method for 10 Nthruster ignition anomaly of on-orbit satellites is proposed.The accuracy of the method is relatively high,and the absolute error is less than 3℃.It can be found quickly after 10 Nthruster ignition temperature deviating from the normal trend by 3～5℃.The method is applied to a DFH-3 satellite,and the maximum difference of 10 Nthruster ignition temperature between the theoretical values calculated by the proposed method and the measured values is only 2.72℃.It is proved that the prediction accuracy of the proposed method is high.It plays an important role in deteting 10 Nthruster ignition anomaly in time and ensures the success of satellite orbit or attitude control.
引文
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[4]Kenny B H,Kascak P E,Jansen R.et al.Control of a high speed flywheel system for energy storage in space applications[J].IEEE Transactions on Industry Applications,2005,41(4):1029-1038
[5]苏威,洪涛,徐川.红外地球敏感器修正的卫星姿态角动量反馈控制[J].西安交通大学学报,2014,48(4):115-118Su Wei,Hong Tao,Xu Chuan.Angular momentum feedback control of satellite attitude with infrared earth sensor correction[J].Journal of Xi’an Jiaotong University,2014,48(4):115-118(in Chinese)
[6]章仁为.卫星轨道姿态动力学与控制[M].北京:北京航空航天大学出版社,1998Zhang Renwei.Attitude dynamics and control of satellite[M].Beijing:Beijing University of Aeromutics and Astronautics Press,1998(in Chinese)
[7]王江,耿宏飞,刘炜葳,等.双组元25N发动机热辐射影响研究[J].上海航天,2016,33(2):73-77Wang Jiang,Geng Hongfei,Liu Weiwei,et al.Research on thermal radiation effect of 25N bi-propellant thrusters[J].Aerospace Shanghai,2016,33(2):73-77(in Chinese)
[8]陈阳春.25N双组元发动机热控研究[J].火箭推进,2015,41(2):38-41Chen Yangchun.Study on thermal control of 25Nbipropellant engine[J].Journal of Rocket Propulsion,2015,41(2):38-41(in Chinese)
[9]闵桂荣,郭舜.航天器热控制[M].北京:科学出版社,1998Min Guirong,Guo Shun.Spacecraft thermal control[M].Beijing:Science Press,1998(in Chinese)
[10]D G Gilmore.Spacecraft thermal control handbook[M].California:The Aerospace Press,2002
[11]田文华.卫星热控技术[M].北京:中国宇航出版社,1991Tian Wenhua.Satellite thermal control technology[M].Beijing:China Astronautics Press,1991(in Chinese)
[12]刘培.空间卫星目标红外辐射特性研究[D].西安:西安电子科技大学,2016Liu Pei.Study on infrared radiation characteristics of space satellite target[D].Xi’an:Xidian University,2016(in Chinese)