一种用于微小推力冲量测量的扭摆系统参数标定方法

推进技术 ›› 2015, Vol. 36 ›› Issue (10): 1554-1559.

一种用于微小推力冲量测量的扭摆系统参数标定方法

金星,洪延姬,周伟静,常浩

装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416,装备学院激光推进及其应用国家重点实验室，北京 101416

发布日期:2021-08-15
作者简介:金星(1962—), 男，博士，研究员，研究领域为激光与物质相互作用、激光航天应用。E-mail: jinxing@163.com 通讯作者:周伟静(1982—), 女，博士，助理研究员，研究领域为激光航天应用、激光与物质相互作用。
基金资助:
国家自然科学基金(11502301)。

A Parameter Calibration Method for Torsion Pendulum Using in Micro Thrust and Impulse Measurement

State Key Laboratory of Laser Propulsion and Application，Academy of Equipment，Beijing 101416，China,State Key Laboratory of Laser Propulsion and Application，Academy of Equipment，Beijing 101416，China,State Key Laboratory of Laser Propulsion and Application，Academy of Equipment，Beijing 101416，China and State Key Laboratory of Laser Propulsion and Application，Academy of Equipment，Beijing 101416，China

Published:2021-08-15

摘要/Abstract

摘要： 扭摆系统通常用来测量航天微推力器的微推力和微冲量。为了实现扭摆的系统参数精确标定，根据扭摆系统阶跃响应的特点，深入分析稳态扭转角和极值扭转角及其对应时间等特征点与系统参数的关系，提出了系统参数标定的比例回归法，所提出方法能够同时标定阻尼比、振动频率和扭转刚度系数等系统参数，计算分析简便，适合真空环境下的扭摆系统参数标定，有助于真空环境下航天微推力器的推力性能评价工作。实验表明:相对于传统数据处理方法，利用比例回归法估计的置信区间最大可缩小61%，可有效改善系数参数的标定结果。

关键词: 微推力；微冲量；参数估计；置信区间；阻尼比；振动频率；扭转刚度系数

Abstract: The torsion pendulum is usually used in micro thrust and impulse measurement for aerospace micro thruster. In order to realize the accurate calibration of the system parameters of the torsion pendulum，relationship between feature points of the step response and system parameters，such as the steady state torsion angle and the extreme torsion angle and their corresponding time，was analyzed based on the step response. And the Proportional Regression Method (PRM) was brought forward for the calibration for the pendulum parameters. The PRM can be used to obtain the damping ratio，the vibration frequency，torsion stiffness coefficient and so on at the same time. It is simpler and more convenient for the calibration in vacuum condition and performance evaluation of micro thruster. Compared with the traditional method，confidence interval based on the PRM can be reduced by 61%，and the PRM can improve the calibration results of the torsion pendulum.

Key words: Micro thrust；Micro impulse；Parameter estimation；Confidence intervals；Damping ratio； Vibration frequency；Torsion stiffness coefficient

金星,洪延姬,周伟静,常浩. 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 Xing,HONG Yan-ji,ZHOU Wei-jing,CHANG Hao. A Parameter Calibration Method for Torsion Pendulum Using in Micro Thrust and Impulse Measurement[J]. Journal of Propulsion Technology, 2015, 36(10): 1554-1559.

参考文献

[1] Juergen Mueller, John Ziemer, Richard Hofer, et al. A Survey of Micro-Thrust Propulsion Options for Microspacecraft and Formation Flying Missions[C]. USA: 5th Annual CubeSat Developers Workshop, 2008.
[2] Benson Scott W, Arrington Lynn A, Hoskins W Andrew, et al. Development of a PPT for the EO-1 Spacecraft[R]. AIAA 99-2276.
[3] Polzin K A, Sooby E.S, Kimberlin AC, et al. Performance of a Permanent-Magnet Cylindrical Hall-Effect Thruster[R]. AIAA 2009-4812.
[4] Paita L, Ceccanti F, Spurio M, et al. Alta’s FT-150 FEEP Microthruster: Development and Qualification Status[R]. IEPC 2009-186.
[5] Demmons Nathaniel, Hruby Vlad, Spence Douglas, et al. ST7-DRS Mission Colloid Thruster Development[R]. AIAA 2008-4823.
[6] Hruby Vlad, Spence Douglas, Demmons Nathaniel, et al. ST7-DRS Colloid Thruster System Development and Performance Summary[R]. AIAA 2008-4824.
[7] Ziemer John K, Randolph Thomas M, Franklin Garth W, et al. Delivery of Colloid Micro-Newton Thrusters for the Space Technology 7 Mission[R]. AIAA 2008-4826.
[8] Phipps C R. Micro Laser Plasma Thrusters for Small Satellites[R]. STTR 1999-F49620-98-C-0038.
[9] 洪延姬. 用于微小卫星姿轨控的激光烧蚀微推力器[J]. 装备学院学报, 2013, 24(6): 57-61.
[10] 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.
[11] Yuan-Xia Yang, Liang-Cheng Tu, Shan-Qing Yang, et al. A Torsion Balance for Impulse and Thrust Measurements of Micro-Newton Thrusters[J]. Review of Scientific Instrument, 2012, 83.
[12] Soni J, Roy S. Design and Characterization of a Nano-Newton Resolution Thrust Stand[J]. Review of Scientific Instruments, 2013, 85: 95-103.
[13] 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.
[14] 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.
[15] 洪延姬, 金星. 微推力和微冲量测量方法[M]. 北京:国防工业出版社, 2013.
[16] Lake C J, cavallaro L G, Spanjers G, et al. Resonant Operation of a Micro-Newton Thrust Stand[R]. AIAA 2002-3821.
[17] Manuel Gamero-Casta?o. A Torsional Balance for the Characterization of Micronewton Thrusters[J]. Review of Scientific Instruments, 2003, 74(10): 4509-4514.
[18] Haibin Tang, Chenbo Shi, Xin’ai Zhang, et al. Pulsed Thrust Measurements Using Electromagnetic Calibration Techniques[J]. Review of Scientific Instrument, 2011, 82.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2015-06-09；修订日期:2015-06-23。基金项目:国家自然科学基金(11502301)。作者简介:金星(1962—), 男,博士,研究员,研究领域为激光与物质相互作用、激光航天应用。E-mail: jinxing@163.com通讯作者:周伟静(1982—), 女,博士,助理研究员,研究领域为激光航天应用、激光与物质相互作用。 E-mail: viviazhouyy@163.com