一种基于悬臂梁结构的动态推力测量方法
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摘要
为实现星载微推进器性能评价中的动态推力测量,基于悬臂梁动力学模型,建立了测量系统的传递函数,分析了系统的输入输出特性,根据悬臂梁响应速度快(振动频率高)、动态分量在较小时间区间内接近等幅振荡(阻尼比小)以及高阶振动可视为基频振动噪声的特性,提出了求解稳态位移的末端均值法。该方法通过消除位移响应中的动态分量,得到了误差带较大时的稳态位移时变值,实现了动态推力测量。依据系统稳态位移与推力为线性关系、线性系数为系统增益值这一特性,提出了参数标定方法。搭建了试验平台,标定得到系统响应时间为156ms,通过对比扭摆系统测量结果,悬臂梁测量得到的冲击力与实际推力相对误差为4.064%,结合冲击力本身的测量误差1.383%,最终得到推力测量误差为4.293%。
To realize dynamic thrust measurement in space-borne micro thrusters′performance assessment,the transfer function of the measurement system was determined based on cantilever′s dynamic model.System input and output characteristics were analyzed,and a terminal mean method for solving the steady-state displacement was put forward according to cantilever beams′characteristics that the response speed is high(vibration frequency is high),the dynamiccomponent is close to constant amplitude oscillation in a small time interval(damping ratio is small),and that the higher order vibration can be regarded as the noise for fundamental frequency vibration.By eliminating the dynamic components in the displacement response,the time variant value of the static displacement was obtained when the error band was large,and thus the dynamic thrust measurement was realized.According to the linear relationship between the thrust magnitude and the steady displacement under the action of step force with the linear coefficient as the system gain value,the parameter calibration method was put forward.An experimental platform was built with response time 156 ms by calibration.By comparison with measurement results of torsional balance system,the relative error 4.064% between the impact force on cantilever and the actual thrust was obtained,and the thrust measurement error 4.293% was finally obtained by combination with the measurement error 1.383% of impact force itself.
To realize dynamic thrust measurement in space-borne micro thrusters′performance assessment,the transfer function of the measurement system was determined based on cantilever′s dynamic model.System input and output characteristics were analyzed,and a terminal mean method for solving the steady-state displacement was put forward according to cantilever beams′characteristics that the response speed is high(vibration frequency is high),the dynamiccomponent is close to constant amplitude oscillation in a small time interval(damping ratio is small),and that the higher order vibration can be regarded as the noise for fundamental frequency vibration.By eliminating the dynamic components in the displacement response,the time variant value of the static displacement was obtained when the error band was large,and thus the dynamic thrust measurement was realized.According to the linear relationship between the thrust magnitude and the steady displacement under the action of step force with the linear coefficient as the system gain value,the parameter calibration method was put forward.An experimental platform was built with response time 156 ms by calibration.By comparison with measurement results of torsional balance system,the relative error 4.064% between the impact force on cantilever and the actual thrust was obtained,and the thrust measurement error 4.293% was finally obtained by combination with the measurement error 1.383% of impact force itself.
引文
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[19]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.WANG Y,YOU Z,WANG G Y,et al.Method of multipulse micro thrust measurement[J].Acta Aeronautica Et Astronautica Sinica,2009,30(12):2257-2262(in Chinese).
[2] PEREL J,YAHIKU A Y,MAHONEY J F,et al.Operational characteristics of colloid thrusters[J].Journal of Spacecraft&Rockets,2015,8(8):702-709.
[3] YU H C,LI H Y,WANG Y,et al.Brief review on pulse laser propulsion[J].Optics and Laser Technology,2018,100:57-74.
[4]王尚民,田立成,张家良,等.微脉冲等离子体推进器放电过程和性能初探[J].中国空间科学技术,2017,37(5):24-32.WANG S M,TIAN L C,ZHANG J L,et al.Elementary study on the discharge process and performance of micropulsed plasma thruster[J].Chinese Space Science and Technology,2017,37(5):24-32(in Chinese).
[5]曹帅,汤海滨,张尊,等.离子发动机羽流空间电位诊断[J].中国空间科学技术,2016,36(1):103-112.CAO S,TANG H B,ZHANG Z,et al.Space potential diagnostic study of ion thruster's plume[J].Chinese Space Science and Technology,2016,36(1):103-112(in Chinese).
[6]杨博,田苗,魏延明.皮纳卫星编队保持动力学分析[J].中国空间科学技术,2018,38(1):44-53.YANG B,TIAN M,WEI Y M.Kinetic analysis on nanopico satellite formation keeping[J].Chinese Space Science and Technology,2018,38(1):44-53(in Chinese).
[7]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.LIU X Y,FAN N J,LI K J,et al.The state-of-the-art and development tendencies of thrust measurement for micro-thrusters[J].Measurement&Control Technology,2004,23(5):18-20(in Chinese).
[8] DOU B X,ZHAO Y,YAO X,et al.Review of thrust measurement techniques for micro-thrusters[J].Journal of Measurement Science and Instrumentation,2013,4(2):103-110.
[9] WHITE H,MARCH P,LAWRENCE J,et al.Measurement of impulsive thrust from a closed radio-frequency cavity in vacuum[J].Journal of Propulsion&Power,2016,33(4):1-12.
[10]边星,邵明学,杨福全,等.双单摆式微推力测量系统的研究[J].真空与低温,2014(3):136-139.BIAN X,SHAO M X,YANG F Q,et al.Study of micro-thrust measurement using double pendulum[J].Vacuum&Cryogenics,2014(3):136-139(in Chinese).
[11] ORIEUX S,ROSSI C,ESTVe D.Thrust stand for ground tests of solid propellant microthrusters[J].Review of Scientific Instruments,2002,73(7):2694-2698.
[12] GRUBIIC'A N,GABRIEL S B.Development of an indirect counterbalanced pendulum optical-lever thrust balance for micro-to millinewton thrust measurement[J].Measurement Science&Technology,2010,21(10):105101.
[13] BOHRK H,AUWETERKURTZ M.Thrust measurement of the hybrid electric thruster TIHTUS by a baffle plate[J].Journal of Propulsion&Power,2012,25:729-736.
[14] CHAKRABORTY S,COURTNEY D G,SHEA H.A10 nN resolution thrust-stand for micro-propulsion devices[J].Review of Scientific Instruments,2015,86(11):279-285.
[15] WOLF E T.Porous emitter colloid thruster performance using optical techniques[D].Alabama:Air University,2013:17-18.
[16] WANG A L,WU H,TANG H B,et al.Development and testing of a new thrust stand for micro-thrust measurement in vacuum conditions[J].Vacuum,2013,91(3):35-40.
[17]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.CEN J W,XU J L.A simplification method for microthrust test[J].Acta Aeronautica Et Astronautica Sinica,2008,29(2):297-303(in Chinese).
[18]李家文,李道奎,周建平.冲击波作用下悬臂梁瞬态响应的传递函数方法[J].振动与冲击,2007,26(3):101-103.LI J W,LI D K,ZHOU J P.Transient response analysis of a cantilever beam under blast wave with distributed transfer function method[J].Journal of Vibration&Shock,2007,26(3):101-103(in Chinese).
[19]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.WANG Y,YOU Z,WANG G Y,et al.Method of multipulse micro thrust measurement[J].Acta Aeronautica Et Astronautica Sinica,2009,30(12):2257-2262(in Chinese).