一种基于动态补偿技术的微小稳态推力还原方法

doi:10.7527/S1000-6893.2018.21885

流体力学与飞行力学

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一种基于动态补偿技术的微小稳态推力还原方法

周伟静, 洪延姬, 叶继飞, 李南雷, 常浩

航天工程大学激光推进及其应用国家重点实验室,北京 101416

收稿日期:2017-11-22 修回日期:2018-03-23 出版日期:2018-07-15 发布日期:2018-03-23
通讯作者: 常浩 E-mail:changhao5976911@163.com
基金资助:
国家自然科学基金（11502301，11602304）

A reduction method for micro steady-state thrust based on dynamic compensation technique

ZHOU Weijing, HONG Yanji, YE Jifei, LI Nanlei, CHANG Hao

State key Laboratory of Laser Propulsion & Application, Space Engineering University, Beijing 101416, China

Received:2017-11-22 Revised:2018-03-23 Online:2018-07-15 Published:2018-03-23
Supported by:
National Natural Science Foundation of China (11502301, 11602304)

摘要/Abstract

摘要： 新型微推力器是未来微纳卫星的生力军，其设计、研制和应用都离不开推力性能测量的工程支撑。在设计和研究阶段，新型微推力器稳态力输出时间与机械式直接测量系统稳态调整时间之间存在匹配问题，无法利用测量系统的稳态响应直接还原推力大小。提出一种基于动态补偿技术的稳态推力还原方法，通过分析稳态力工作时间、稳态力大小与测量系统稳态响应之间的关系，提出了动态补偿器的设计原则和推力还原步骤，并进行了实验验证。研究结果表明：当稳态推力实际工作时间大于测量系统周期的0.25倍，且小于测量系统稳态调整时间时，可利用动态补偿器设计原则建立新的等效测量系统，使最终的输出达到稳态，并利用最终的稳态响应均值还原推力大小。

关键词: 测量, 微推力器, 推力, 水平扭摆, 动态补偿

Abstract: New micro thrusters are vital force of micro/nano satellites in the future. Thrust measurement is very important support in the design, development and application of micro thrusters. In the design stage, the steady-state force working time of the thruster is sometimes difficult to match the setting time of the mechanical and direct measurement system. Therefore, the steady-state force cannot be obtained by the steady-state response. A reduction method for micro steady-state thrust is proposed based on the dynamic compensation technique. The relation between the working time and value of the steady-state thrust and the steady-state response of the measurement is analyzed. The design principles of the compensation filter and the steady-state thrust reduction steps are provided. Experiments are carried out to verify the method. The results show that when the working time of the steady-state thrust is longer than 0.25 times of the natural period of the measurement system and shorter than the setting time of the measurement system, the final output of the equivalent measurement system using the compensation filter can reach a steady state, and the range of the steady-state thrust can be obtained through the final steady-state output.

Key words: measurement, micro thruster, thrust, horizontal torsional pendulum, dynamic compensation

中图分类号:

V439
TN249

周伟静, 洪延姬, 叶继飞, 李南雷, 常浩. 一种基于动态补偿技术的微小稳态推力还原方法[J]. 航空学报, 2018, 39(7): 121885-121885.

ZHOU Weijing, HONG Yanji, YE Jifei, LI Nanlei, CHANG Hao. A reduction method for micro steady-state thrust based on dynamic compensation technique[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(7): 121885-121885.

参考文献

[1] 姚保寅, 李辉, 许红英, 等. 基于微机电系统技术的微推进器发展简析[J]. 国际太空, 2016(3):23-26. YAO B Y, LI H, XU H Y, et al. Development of MEMS micro thruster[J]. Space International, 2016(3):23-26(in Chinese).
[2] 范林东, 杨博, 苗峻, 等. 基于SiC MEMS阵列的高精度微纳卫星编队保持[J]. 中国空间科学技术, 2016, 36(2):37-45. FAN L D, YANG B, MIAO J, et al. High precision micro-nano satellite formation keeping based on SiC MEMS micro thruster array[J]. Chinese Space Science and Technology, 2016, 36(2):37-45(in Chinese).
[3] 洪延姬, 王广宇, 窦志国. 激光烧蚀微推力器研究进展[J]. 航空学报, 2009, 30(9):1555-1564. HONG Y J, WANG G Y, DOU Z G. State of art of laser ablation microthruster[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(9):1555-1564(in Chinese).
[4] TAJMAR M, FIEDLER G. Direct thrust measurement of an EM drive and evaluation of possible side-effects:AIAA-2015-4083[R]. Reston, VA:AIAA, 2015.
[5] BRADY D A, WHITE H G, MARCH P, et al. Anomalous thrust production from an RF test device measured on a low-thrust torsion pendulum:AIAA-2014-4029[R]. Reston, VA:AIAA, 2014.
[6] 洪延姬, 周伟静, 王广宇. 微推力测量方法及关键问题分析[J]. 航空学报, 2013, 34(10):2287-2299. HONG Y J, ZHOU W J, WANG G Y. Methods of micro measurement and analysis of its key issues[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(10):2287-2299(in Chinese).
[7] POLK J E, PANCOTTI A, HAAG T, et al. Recommended practices in thrust measurements[C]//The 33rd International Electic Propulsion Conference. 2013:1-19.
[8] 汤海滨, 刘畅, 向民, 等. 微推力全弹性测量装置[J]. 推进技术, 2007, 28(6):703-706. TANG H B, LIU C, XIANG M, et al. Full elastic microthrust measurement equipment[J]. Journal of Propulsion Technology, 2007, 28(6):703-706(in Chinese).
[9] 杨元侠. 微牛顿量级推进器的推力性能研究[D]. 武汉:华中科技大学, 2012:17-18. YANG Y X. Researches on the thrust and impulse performances of micro-newton thrusters[D]. Wuhan:Huazhong University of Science and Technology, 2012:17-18(in Chinese).
[10] YANG Y X, TU L C, YANG S Q, et al. A torsion balance for impulse and thrust measurements of micro-Newton thrusters[J]. Review of Scientific Instrument, 2012, 83(1):015105.
[11] SONI J, ROY S. Design and characterization of a nano-Newton resolution thrust stand[J]. Review of Scientific Instruments, 2013, 84(9):095103.
[12] PHIPPS C, LUKE J, LIPPERT T, et al. Micropropulsion using a laser ablation jet[J]. Journal of Propulsion and Power, 2004, 20(6):1000-1011.
[13] 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.
[14] CIARALLI S, COLETTI M, GABRIEL S B. An impulsive thrust balance for applications of micro-pulsed plasma thrusters[J]. Measurement Science and Technology, 2013, 24(11):115003.
[15] 王广宇, 洪延姬. 微冲量测量的建模误差分析[J]. 推进技术, 2009, 30(4):509-512. WANG G Y, HONG Y J. Modeling error analysis of micro-impulse measurements[J]. Journal of Propulsion Technology, 2009, 30(4):509-512(in Chinese).
[16] JAMES E P, ANTHONY P, THOMAS H, et al. Recommended practice for thrust measurement in electric propulsion testing[J]. Journal of Propulsion and Power, 2017, 33(3):1-17.
[17] TAJMAR M, FIEDLER G. Direct thrust measurements of an EM drive and evaluation of possible side-effects:AIAA-2015-4083[R]. Reston, VA:AIAA, 2015.
[18] 王宇, 尤政, 洪延姬.一种实时测量微推力瞬时值的方法[J]. 推进技术, 2010, 31(3):2257-2262. WANG Y, YOU Z, HONG Y J. A method of real time measurement for transient microthrust[J]. Journal of Propulsion Technology, 2010, 31(3):2257-2262(in Chinese).
[19] 黄俊钦. 测试系统动力学及应用[M]. 北京:国防工业出版社, 2013:10, 51-90. HUANG J Q. Measurement system dynamics and it's application[M]. Beijing:National Defense Industry Press, 2013:10, 51-90(in Chinese).
[20] 洪延姬, 金星, 叶继飞, 等. 微推力和微冲量测量误差分析方法[M]. 北京:科学出版社, 2017:176. HONG Y J, JIN X, YE J F, et al. Analysis methods for micro-thrust and micro-impulse measurement errors[M]. Beijing:Science Press, 2017:176(in Chinese).
[21] 金星, 洪延姬, 周伟静, 等. 一种用于微小推力冲量测量的扭摆系统参数标定方法[J]. 推进技术, 2015, 36(10):1554-1559. JIN X, HONG Y J, ZHOU W J, 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).
[22] ZHOU W J, HONG Y J, CHANG H. A microNewton thrust stand for average thrust measurement of pulsed microthruster[J]. Review of Scientific Instruments, 2013, 84(12):407-434.

E-mail：hkxb@buaa.edu.cn

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一种基于动态补偿技术的微小稳态推力还原方法

A reduction method for micro steady-state thrust based on dynamic compensation technique

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