用于微推力测量的电磁恒力特性研究
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摘要
基于扭摆结构的微推力测量装置是空间微推力器微推力测量的常用方法,稳定、准确的标定力是标定微推力测量系统的关键。利用音圈电机能够产生较长行程恒定电磁力的特点,研究基于音圈电机的电磁力恒力特性。介绍了基于音圈电机的电磁力装置组成及在基于扭摆结构的微推力测量装置中的标定应用;仿真分析了音圈电机中的磁场分布情况,以及线圈电流、线圈与磁轭磁铁相对距离等控制因素下的电磁力变化特性;在此基础上,通过搭建微小电磁力恒力特性实验系统,采用高精度电子天平称重方式,获得了精确的电磁力变化特性;以电磁力误差小于等于5%作为判断标准,获得了音圈电机的稳定力输出行程,为应用于扭摆的微推力标定奠定基础。
Micro-thrust measurement device based on torsion pendulum structure is a common method for micro-thrust measurement of space micro-thruster. Aiming at the calibration problem in micro-thrust measurement, the electromagnetic force constant characteristic based on voice coil motor was studied. The composition and function of the voice coil motor and its calibration application in micro-thrust were introduced. The distribution of magnetic field in voice coil motor and the variation of electromagnetic force under the control factors of coil current, relative distance between coil and magnet were analyzed.An experimental system of constant force characteristics of micro-electromagnetic force was built. Based on the weighing method of high precision electronic balance, the precise electromagnetic force was obtained. With the criterion of electromagnetic force error less than 5%, the stable force output of voice coil motor was obtained, which will lay the foundation for the micro-thrust calibration of torsion pendulum.
Micro-thrust measurement device based on torsion pendulum structure is a common method for micro-thrust measurement of space micro-thruster. Aiming at the calibration problem in micro-thrust measurement, the electromagnetic force constant characteristic based on voice coil motor was studied. The composition and function of the voice coil motor and its calibration application in micro-thrust were introduced. The distribution of magnetic field in voice coil motor and the variation of electromagnetic force under the control factors of coil current, relative distance between coil and magnet were analyzed.An experimental system of constant force characteristics of micro-electromagnetic force was built. Based on the weighing method of high precision electronic balance, the precise electromagnetic force was obtained. With the criterion of electromagnetic force error less than 5%, the stable force output of voice coil motor was obtained, which will lay the foundation for the micro-thrust calibration of torsion pendulum.
引文
[1]Cao Xibin,Sun Zhaowei.Rapid Response Micro Satellite Design[M].Beijing:Science Press,2016.(in Chinese)
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[9]Hong Yanji,Zhou Weijing,Wang Guangyu.Methods of micro thr ust measurement and analysis of its key issues[J].Acta Aeronautica et Astronautica Sinica,2013,34(10):2287-2299.(in Chinese)
[10]Manuel Gamero-Casta觡o.A torsional balance for the characterization of microNewton thrusters[J].Review of Scientific Instruments,2003,74(10):4509-4514.
[11]Nathaniel P Selden,Andrew D Ketsdever.Comparison of force balance calibration techniques for the nano-Newton range[J].Review of Scientific Instruments,2003,73(12):5249-5254.
[12]Zhou Weijing,Hong Yanji,Chang Hao.A microNewton thrust stand for average thrust measurement of pulsed microthruster[J].Review of Scientific Instrument,2013,84:125115.
[13]He Zhen,Wu Jianjun,Zhang Daixian,et al.Precision electromagnetic calibration technique for micro-Newton thrust stands[J].Review of Scientific Instrument,2013,84:055107.
[14]Tang Haibin,Liu Chang,Xiang Min,et al.Full elastic microthrust measurement equipment[J].Journal of Propulsion Technology,2007,28(6):703-706.(in Chinese)
[2]Qiao Yi,Li Xiaoyu,Zhao Tian.Analysis on typical military application of small satellite[J].Foreign Electronic Measurement Technology,2017,36(3):47-50.(in Chinese)
[3]Igor Levchenko,Kateryna Bazaka,Yongjie Ding,et al.Space micropropulsion systems for Cubesats and small satellites:From proximate targets to furthermost frontiers[J].Applied Physics Reviews,2018,5:011104.
[4]Koizumi H,Komurasaki K,Arakawa Y.Development of thrust stand for low impulse measurement from microthrusters[J].Review of Scientific Instruments,2004,75(10):3185-3190.
[5]Brian C D′Souza,Andrew D Ketsdever.Investigation of timedependent forces on nano-Newton-Second impulse balance[J].Review of Scientific Instruments,2005,76:015105.
[6]Liu Xuhui,Yang Feihu,Wei Yanming,et al.Study of dynamic thrust measurement using torsional pendulum[J].Journal of Propulsion Technology,2017,38(4):925-931.(in Chinese)
[7]Zhou Weijing,Hong Yanji,Ye Jifei.Mechanical performance measurement method for laser micro-thruster working in multi-pulse mode[J].Infrared and Laser Engineering,2016,45(S2):S206002.(in Chinese)
[8]Jin Xing,Hong Yanji,Zhou Weijing,et al.A parameter calibration method for torsion pendulum using in micro thrust and impulse measurement[J].Journal of Propulsion Technology,2015,36(10):1554-1559.(in Chinese)
[9]Hong Yanji,Zhou Weijing,Wang Guangyu.Methods of micro thr ust measurement and analysis of its key issues[J].Acta Aeronautica et Astronautica Sinica,2013,34(10):2287-2299.(in Chinese)
[10]Manuel Gamero-Casta觡o.A torsional balance for the characterization of microNewton thrusters[J].Review of Scientific Instruments,2003,74(10):4509-4514.
[11]Nathaniel P Selden,Andrew D Ketsdever.Comparison of force balance calibration techniques for the nano-Newton range[J].Review of Scientific Instruments,2003,73(12):5249-5254.
[12]Zhou Weijing,Hong Yanji,Chang Hao.A microNewton thrust stand for average thrust measurement of pulsed microthruster[J].Review of Scientific Instrument,2013,84:125115.
[13]He Zhen,Wu Jianjun,Zhang Daixian,et al.Precision electromagnetic calibration technique for micro-Newton thrust stands[J].Review of Scientific Instrument,2013,84:055107.
[14]Tang Haibin,Liu Chang,Xiang Min,et al.Full elastic microthrust measurement equipment[J].Journal of Propulsion Technology,2007,28(6):703-706.(in Chinese)