Effect of Friction on Deployment Dynamics of Non-conductive Space Tether

doi:10.12382/bgxb.2022.0916

Abstract

Abstract:

The simulation results of the deployment dynamics of non-conductive space tether are inconsistent with the actual situation due to the lack of deployment friction data. To solve this problem, the deployment friction measurement experiments of non-conductive space tether are conducted based on a ground tether deployment platform, the effects of different materials, diameters, winding direction, and deployment velocity of tether on the deployment friction are studied, the main factors affecting the “ball effect” unstable phenomenon during the deployment process are clarified, and the quantitative relationship between the deployment friction and the deployment conditions is determine. By further study of tether deployment dynamics simulation, it is found that deployment friction has a significant influence on the tether deployment: for a 500m long tether, the difference between the deployment duration without considering deployment friction and the deployment duration with considering deployment friction is about 20% at an initial deployment velocity of 2m/s.

Key words: space tether, deployment friction, ground experiment, deployment velocity, dynamics simulation

CLC Number:

LIANG Fuwen, MIAO Long, TIAN Feng, SONG Jiahui, BAI Song, HE Zihao, WANG Ningfei. Effect of Friction on Deployment Dynamics of Non-conductive Space Tether[J]. Acta Armamentarii, 2024, 45(4): 1158-1167.

Figures/Tables 15

Fig.1 Schematic diagram of ground tether deployment experimental platform

Fig.2 Composition of ground tether deployment experimental platform

Fig.3 Force analysis on tether deployment friction

Fig.4 Ball effect in the process of tether deployment[27]

Fig.5 Different tether winding directions on tether spool

Fig.6 Deployment processes of tethers made of different materials

Fig.7 Changes of deployment friction of tethers with different diameters

Table 1 Friction result statistics of tethers with different diameters

系绳直径/mm	摩擦力平均值/N	摩擦力标准差/N
2	0.615	0.084
3	2.846	0.274
4	7.424	0.676

Fig.8 Change of deployment friction in different winding directions

Table 2 Statistics of friction results in different winding directions

缠绕方向	摩擦力平均值/N	摩擦力标准差/N
正向	0.674	0.108
反向	0.663	0.115

Fig.9 Change of deployment friction under typical deployment velocities

Fig.10 Change in the average value of deployment friction under different deployment velocities

Fig.11 Schematic diagram of tether deployment dynamics model

Fig.12 Effect of deployment friction on tether deployment

Fig.13 Change of tether deployment dynamicseffected by the inflection point in the deployment friction curve

References 30

[1]	余本嵩, 文浩, 金栋平, 等. 空间电动力绳系统理论及实验研究[J]. 力学进展, 2016, 46:226-266.
	YU B S, WEN H, JIN D P, et al. Theory and experiment of space electrodynamic tether systems[J]. Advances in Mechanics, 2016, 46:226-266. (in Chinese)
[2]	HUANG P F, ZHANG F, CHEN L, et al. A review of space tether in new applications[J]. Nonlinear Dynamics, 2018, 94:1-19.
[3]	PANG Z J, WEN H, RUI X T, et al. Nonlinear resonant analysis of space tethered satellite system in elliptical orbits[J]. Acta Astronautica, 2021, 182:264-273.
[4]	LI A J, TIAN H C, WANG C Q. Fixed-time terminal sliding mode control of spinning tether system for artificial gravity environment in high eccentricity orbit[J]. Acta Astronautica, 2020, 177:834-841.
[5]	LI G Q, ZHU Z H. Model predictive control for electrodynamic tether geometric profile in orbital maneuvering with finite element state estimator[J]. Nonlinear Dynamics, 2021, 106:473-489.
[6]	SUN X, ZHONG R. Tether attachment point stabilization of noncooperative debris captured by a tethered space system[J]. Acta Astronautica, 2020, 177:784-797.
[7]	BOMBARDELLI C, LORENZINI E C, QUADRELLI M B. Retargeting dynamics of a linear tethered interferometer[J]. Journal of Guidance, Control, and Dynamics, 2004, 27(6):1061-1067.
[8]	SANMARTIN J R, CHARRO M, PELAEZ J, et al. Floating bare tether as upper atmosphere probe[J]. Journal of Geophysical Research, 2006, 111(A11):1-15.
[9]	司骥跃, 庞兆君, 由锰, 等. 空间绳网结构设计及优化方法[J]. 兵工学报, 2021, 42(5):1065-1073. doi: 10.3969/j.issn.1000-1093.2021.05.019
	SI J Y, PANG Z J, YOU M, et al. Structural design and optimization of space tether-net[J]. Acta Armamentarii, 2021, 42(5):1065-1073. (in Chinese) doi: 10.3969/j.issn.1000-1093.2021.05.019
[10]	HUANG W C, HE D Z, LI Y B, et al. Nonlinear dynamic modeling of a tether-net system for space debris capture[J]. Nonlinear Dynamics, 2022,110:2297-2315.
[11]	郭甲, 庞兆君, 岳帅, 等. 空间绳系组合体的继电型控制离轨策略[J]. 航空学报, 2021, 42(12):324738. doi: 10.7527/S1000-6893.2020.24738
	GUO J, PANG Z J, YUE S, et al. De-orbit strategy using Bang-Bang control for space tethered-combination[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(12):324738. (in Chinese) doi: 10.7527/S1000-6893.2020.24738
[12]	胡永新, 黄攀峰, 刘习尧. 绳系系统在空间碎片清除中的应用[J]. 空间碎片研究, 2021, 21(3):1-8.
	HU Y X, HUANG P F, LIU X Y. Application of tethered system in space debris removal[J]. Space Debris Research, 2021, 21(3):1-8. (in Chinese)
[13]	SÁNCHEZ-ARRIAGA G, BORDERES-MOTTA G, CHIABÓ L. A code for the analysis ofmissions with electrodynamic tethers[J]. Acta Astronautica, 2022, 198:471-481.
[14]	娄宗勇. 电动力缆绳离轨时间特性研究[D]. 哈尔滨: 哈尔滨工业大学, 2007:4.
	LOU Z Y. Study on de-orbiting duration property of electro-dynamic tether[D]. Harbin: Harbin Institute of Technology, 2007:4. (in Chinese)
[15]	徐大富. 电动力绳系离轨系统的建模与动力学分析[D]. 哈尔滨: 哈尔滨工业大学, 2010:2-3.
	XU D F. Modeling and dynamic analysis of electrodynamic tether deorbiting system[D]. Harbin: Harbin Institute of Technology, 2010:2-3. (in Chinese)
[16]	WEN H, JIN D P, HU H Y. Advances in dynamics and control of tethered satellite systems[J]. Acta Mechanica Sinica, 2008, 24(3):229-241.
[17]	SAREGO G, OLIVIERI L, VALMORBIDA A, et al. Deployment requirements for deorbiting electrodynamic tether technology[J]. CEAS Space Journal, 2021, 13:567-581.
[18]	GATES S S, KOSS S M, ZEDD M F. Advanced tether experiment deployment failure[J]. Journal of Spacecraft and Rockets, 2001, 38(1):60-68.
[19]	OHKAWA Y, KAWAMOTO S, OKUMURA T, et al. Review of KITE-electrodynamic tether experiment on the H-II transfer vehicle[J]. Acta Astronautica, 2020, 177:750-758.
[20]	XU S D, WEN H, HUANG Z, et al. A fuzzy control scheme for deployment of space tethered system with tension constraint[J]. Aerospace Science and Technology, 2020, 106: 106143.
[21]	SALAZAR F J T, PRADO A F B A. Suppression of chaotic motion of tethered satellite systems using tether length control[J]. Journal of Guidance, Control, and Dynamics, 2022, 45(3):580-586.
[22]	GARCIA-GONZALEZ S, SANCHEZ-ARRIAGA G. Attitude determination and control for the deployment preparation phase of a space tether mission[J]. Acta Astronautica, 2022, 193:381-394.
[23]	VALMORBIDA A, OLIVIERI L, BRUNELLO A, et al. Validation of enabling technologies for deorbiting devices based on electrodynamic tethers[J]. Acta Astronautica, 2022, 198:707-719.
[24]	YAMADA T, FUJII H A, MIZUNO T, et al. Experimental study on deployment system of tape tether-on ground and space experiment[C]// Proceedings of AIAA Guidance, Navigation, and Control Conference. Portland, OR, US: AIAA, 2011:1-9.
[25]	IKI K, KAWAMOTO S, MORINO Y, et al. Experiments and numerical simulations of an electrodynamic tether deployment from a spool-type reel using thrusters[J]. Acta Astronautica, 2014, 94:318-327.
[26]	程守洙, 江之永. 普通物理学, 上册[M]. 第7版. 北京: 高等教育出版社, 2015:31.
	CHENG S Z, JIANG Z Y. General physics, volume 1[M]. 7th ed. Bejing: Higher Education Press, 2015:31. (in Chinese)
[27]	KRUIJFF M. Tethers in space: a propellantless propulsion in-orbit demonstration[D]. Delft, The Netherlands: Delft University of Technology, 2011:194.
[28]	DOBROWOLNY M, STONE N H. A technical overview of TSS-1: the first tethered-satellite system mission[J]. Il Nuovo Cimento C, 1994, 17:1-12.
[29]	LORENZINI E C, BORTOLAMI S B, RUPP C C, et al. Control and flight performance of tethered satellite small expendable deployment system-II[J]. Journal of Guidance Control Dynamics, 1996, 19(5):1148-1156.
[30]	WILLIAMS P, BLANKSBY C, TRIVAILO P. Tethered planetary capture: controlled maneuvers[J]. Acta Astronautica, 2003, 53:681-708.