基于双光束干涉原理的微小推力测量系统实验研究
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摘要
微小推力测量技术是微推进器研制的关键技术之一,是微小卫星技术发展的重要支撑。为了发展更高精度的测量系统,基于双光束干涉原理,提出了一种新的高精度光学微小推力测量方法,设计并搭建了一套测量微小推力的实验装置。进行了三次标定和测量实验,探索和总结出微推力测量的经验和方法,并对测量系统进行改进。实验结果表明,该测量系统使用方便,能获取实时推力曲线,最大测量误差1.86%,测量精度已达到现有推力架的测量精度,但没有达到双光束干涉原理的理论精度要求,在未来有较大的提升空间。
The micro-thrust measurement technology plays a key role in micro-thruster development,which is the essential technology of micro-satellite.To develop high-precision measurement system,a new high-precision optical micro-thrust measuring method based on the principle of double-beam interference was proposed,and a micro-thrust experimental device was founded as well.Through three different calibration and measurement tests,some experiences and methods of micro-thrust measurement were obtained and some measuring facilities were improved.The experimental result shows that the measurement system can acquire the real-time thrust curve and is convenient for operation.Its maximum measurement error is 1.86%.The mearuring accuracy is up to the precision of existing thrust-frame measuring equipment.However,the measuring precision is still below the theoretic precision of principle of double-beam interference.
The micro-thrust measurement technology plays a key role in micro-thruster development,which is the essential technology of micro-satellite.To develop high-precision measurement system,a new high-precision optical micro-thrust measuring method based on the principle of double-beam interference was proposed,and a micro-thrust experimental device was founded as well.Through three different calibration and measurement tests,some experiences and methods of micro-thrust measurement were obtained and some measuring facilities were improved.The experimental result shows that the measurement system can acquire the real-time thrust curve and is convenient for operation.Its maximum measurement error is 1.86%.The mearuring accuracy is up to the precision of existing thrust-frame measuring equipment.However,the measuring precision is still below the theoretic precision of principle of double-beam interference.
引文
[1]洪延姬,周伟静,王广宇.微推力测量方法及其关键问题分析[J].航空学报,2013,34(10):2287-2299.
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[13]王宇,尤政,王广宇,等.一种多脉冲微推力的测量方法[J].航空学报,2009,30(12):2257-2262.
[14]唐飞,叶雄英,周兆英.一种基于间接标靶法的微小推力测量技术[J]-微纳电子技术,2003(7):438-440.
[15]叶继飞,王广宇,洪延姬等.激光微推力测试平台自动聚焦处理方法[J].装备指挥技术学院学报,2008,19(4):99-102
[2]刘向阳,范宁军,李科杰.微型推进器推力测试的现状及发展趋势[J].测控技术,2004,23(5):18-20.
[3]杨乐,李殿东.脉冲等离子体推力器实验系统[J].真空,2008,45(4):41-44.
[4]那旭东,陈显河,党进锋,等.微波等离子推进器的调试与地面实验[J].应用科技,2011,38(7):49-51.
[5]宁中喜,范金葵.三丝扭摆微推力在线测量方法及不确定度分析[J].测控技术,2011,31(5):45-48.
[6]EMHOFF J W,SMON D H,LAND H B.Progress in thrust measurements from micro pulsed plasma discharges,AIAA2007-5299[R].USA:AIAA,2007.
[7]岑继文,徐进良.真空环境下微推力测量的研究[J].宇航学报,2008(2):621-625.
[8]岑继文,徐进良一种微推力测量的简化处理方法[J].航空学报,2008,29(2):297-303.
[9]栾希亭,张晰哲,韩先伟,等.FMMR微推进系统推力测量装置研究[J].固体火箭技术,2011,34(4):525-528.
[10]贺建武,邵明学,Ho J P,等.基于超导差分加速度测量原理的微推力测量方案[J].真空与低温,2012,19(4):208-213.
[11]YAN A H,APPEL B C,GEDRMAS B.Miliinewton thrust stand calibration using electrostatic fins,AIAA2009-212[R].USA:AIAA,2009.
[12]岑继文,徐进良.微推力与冲击力关系的实验研究[J].推进技术,2009,30(2):114-118.
[13]王宇,尤政,王广宇,等.一种多脉冲微推力的测量方法[J].航空学报,2009,30(12):2257-2262.
[14]唐飞,叶雄英,周兆英.一种基于间接标靶法的微小推力测量技术[J]-微纳电子技术,2003(7):438-440.
[15]叶继飞,王广宇,洪延姬等.激光微推力测试平台自动聚焦处理方法[J].装备指挥技术学院学报,2008,19(4):99-102