高轨卫星平台在轨顽存技术体系

doi:10.12305/j.issn.1001-506X.2021.03.17

Abstract

Abstract:

As high value geostationary earth orbit (GEO) satellites are under a range of threats, it is helpful to improve the survivability of satellite bus by exploring the technology system of on-orbit strong survivability (TSO²S²). Focusing on this, the concept of TSO²S² is defined systematically. A protection system including warning and safety protection sub-system is built after the main threat sources are figured out. Firstly, 8 threats are divided into active type and passive type. The threat mechanisms are analyzed and the damage effects are evaluated using qualitative and quantitative methods. Secondly, an integrated space and terrestrial warning scheme is proposed and the equipment is designed which enabled 5 types of threats to be alarmed, including space debris, laser, et al. Finally, the protection technology and methods are summarized systematically, which can provide reference for the GEO satellite platform to improve the orbit safety.

Key words: satellite bus, damage effect, composite warning, security protection

CLC Number:

V476.5

Wenlong LI, Xianglong KONG, Wei MA, Lili YANG. Technology system of on-orbit strong survivability for GEO satellite bus[J]. Systems Engineering and Electronics, 2021, 43(3): 731-739.

Figures/Tables 13

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References 43

1	DOUGLAS V, HARALD W, LOU M. Lockheed Martin's A2100 spacecraft bus modernization[C]//Proc.of the 34th AIAA International Communications Satellite Systems Confe-rence, 2016: AIAA 2016-5724.
2	马晓兵, 魏强, 周江, 等. 高轨卫星平台被动防护体系及相关技术研究[J]. 航天电子对抗, 2018, 34 (4): 38- 40. doi: 10.3969/j.issn.1673-2421.2018.04.010
	MA X B , WEI Q , ZHOU J , et al. Passive defence system and correlated technology of GEO satellite platform[J]. Aerospace Electronic Warfare, 2018, 34 (4): 38- 40. doi: 10.3969/j.issn.1673-2421.2018.04.010
3	刘必鎏, 吴萌, 麻毅威, 等. 卫星面临的威胁及其防护[J]. 航天电子对抗, 2010, 26 (6): 25- 27. doi: 10.3969/j.issn.1673-2421.2010.06.009
	LIU B L , WU M , MA Y W , et al. Threats to the satellit and its protection[J]. Aerospace Electronic Warfare, 2010, 26 (6): 25- 27. doi: 10.3969/j.issn.1673-2421.2010.06.009
4	李发泉, 程学武, 杨勇, 等. 星载威胁激光探测告警的技术需求分析[J]. 红外与激光工程, 2008, 37 (S3): 331- 334.
	LI F Q , CHENG X W , YANG Y , et al. Technique requirement analysis of satellite borne threat laser detecting warning[J]. Infrared and Laser Engineering, 2008, 37 (S3): 331- 334.
5	闫军, 郑世贵, 韩增尧, 等. 天宫一号空间碎片防护设计与实践[J]. 中国科学:技术科学, 2014, 44 (3): 243- 250.
	YAN J , ZHENG S G , HAN Z Y , et al. Space debris protection design and application for Tiangong-1[J]. Scientia Sinica Techologica, 2014, 44 (3): 243- 250.
6	段敏.多弹丸高速撞击空间碎片防护结构的损伤与防护特性研究[D].哈尔滨: 哈尔滨工业大学, 2018.
	DUAN M. Research on damage characteristics of the space debris shield impacted by hypervelocity multiple projectiles[D]. Harbin: Harbin Institute of Technology, 2018.
7	WU Q, ZHANG Q M, GONG Z Z, et al. Shielding properties investigation of impact-initiated energetic materials under hypervelocity impact[C]//Proc.of the 7th European Conference on Space Debris, 2017.
8	CHERNIAEV A , TELICHEV I . Sacrificial bumpers with high-impedance ceramic coating for orbital debris shielding: a preliminary experimental and numerical study[J]. International Journal of Impact Engineering, 2018, 119, 45- 56. doi: 10.1016/j.ijimpeng.2018.05.004
9	KIM Y H , PARK Y , CHA J H , et al. Behavior of shear thickening fluid(STF) impregnated fabric composite rear wall under hypervelocity impact[J]. Composite Structures, 2018, 204, 52- 62. doi: 10.1016/j.compstruct.2018.07.064
10	KIM Y H , CHOI C , KUMAR S , et al. Behavior of dragon skin flexible metal bumper under hypervelocity impact[J]. International Journal of Impact Engineering, 2019, 125, 13- 26. doi: 10.1016/j.ijimpeng.2018.10.005
11	张旺勋, 侯洪涛, 王维平. 基于MATE的卫星导航系统安全防护设计[J]. 系统工程与电子技术, 2013, 35 (6): 1231- 1235. doi: 10.3969/j.issn.1001-506X.2013.06.17
	ZHANG W X , HOU H T , WANG W P . MATE based design for protection of GNSS[J]. Systems Engineering and Electronics, 2013, 35 (6): 1231- 1235. doi: 10.3969/j.issn.1001-506X.2013.06.17
12	DEBORAH H C . Cybersecurity threats to satellite communications: towards a typology of state actor responses[J]. Acta Astronautica, 2016, 128, 409- 415. doi: 10.1016/j.actaastro.2016.07.041
13	熊玉卿, 罗崇泰. 星载光学遥感仪器激光防护薄膜技术[J]. 红外与激光工程, 2007, 36 (6): 902- 905. doi: 10.3969/j.issn.1007-2276.2007.06.035
	XIONG Y Q , LUO C T . Laser protection thin film for satellite-borne remote sensing instrument[J]. Infrared and Laser Engineering, 2007, 36 (6): 902- 905. doi: 10.3969/j.issn.1007-2276.2007.06.035
14	常峥, 王咏梅, 田天, 等. 地球同步轨道卫星在轨异常与空间环境相关性分析[J]. 宇航学报, 2017, 38 (4): 435- 442.
	CHANG Z , WANG Y M , TIAN T , et al. Causal analysis between geosynchronous satellite anomalies and space environment[J]. Journal of Astronautics, 2017, 38 (4): 435- 442.
15	KOONS H C, MAZUR J E, SELESNICK R S, et al. The impact of the space environment on space system[R]. Segundo: Aerospace Corporation Technology Operations, 1999: 1-13.
16	张海涛, 张占月, 吴帅, 等. 地球静止轨道卫星碰撞碎片短期演化风险分析[J]. 上海航天, 2019, 36 (1): 67- 79.
	ZHANG H T , ZHANG Z Y , WU S , et al. Sort-term evolution risk of Geostationary satellites' collision[J]. Aerospace Shanghai, 2019, 36 (1): 67- 79.
17	沈金华, 贾浩. 电磁轨道炮及其应用[J]. 爆炸与冲击, 1984, 4 (2): 90- 96.
	SHEN J H , JIA H . Electromagnetic railgun and its applications[J]. Explosion and Shock Waves, 1984, 4 (2): 90- 96.
18	杨雨川, 谭吉春, 盛定仪, 等. 高功率微波武器对卫星的威胁及防范措施[J]. 航天电子对抗, 2007, 23 (5): 12- 15. doi: 10.3969/j.issn.1673-2421.2007.05.004
	YANG Y C , TAN J C , SHENG D Y , et al. Threaten of satellite by HPM weapon and its protective measures[J]. Aerospace Electronic Warfare, 2007, 23 (5): 12- 15. doi: 10.3969/j.issn.1673-2421.2007.05.004
19	梁斌, 徐文福, 李成, 等. 地球静止轨道在轨服务技术研究现状与发展趋势[J]. 宇航学报, 2010, 31 (1): 1- 13. doi: 10.3873/j.issn.1000-1328.2010.01.001
	LIANG B , XU W F , LI C , et al. The status and prospect of orbital servicing in the geostationary orbit[J]. Journal of Astronautics, 2010, 31 (1): 1- 13. doi: 10.3873/j.issn.1000-1328.2010.01.001
20	SATNEWS D. Northrop grumman's MEV-1 arrives on station to rescue intelsat 901[EB/OL].[2020-04-02].https://www.satnews.com/story.php?number=2019431572.
21	HIRZINGER G , LANDZETTEL K , BRUNNER B , et al. DLR's robotics technologies for on-orbit servicing[J]. Advanced Robotics, 2004, 18, 139- 174. doi: 10.1163/156855304322758006
22	DEBUS T J, DOUGHERTY S P. Overview and performance of the front end robotics enabling near-term demonstration (FREND)robotic arm[C]//Proc.of the AIAA Info-tech@ Aerospace Conference, 2009: AIAA 2009-1870.
23	BISCHOF B, ASTRIUM G. Roger-robotic geostationary orbit restorer[C]//Proc.of the 54th International Astronautical Congress, 2003.
24	REED J, BUSQUETS J, WHITE C. Grappling system for capturing heavy space debris[C]//Proc.of the 2nd European Workshop on Active Debris Removal, 2012.
25	ZHAI G , QIU Y , LIANG B , et al. System dynamics and feedforward control for tether-net space robot system[J]. International Journal of Advanced Robotic Systems, 2009, 6 (2): 137- 144.
26	PARNESS A, HEVERLY M, HILGEMANN E, et al. ON-OFF adhesive grippers for earth-orbit[C]//Proc.of the AIAA Space Conferences and Exposition, 2013: AIAA 2013-5533.
27	SHAN M H , GUO J , GILL E . Review and comparison of active space debris capturing and removal methods[J]. Progress in Aerospace Sciences, 2016, 80, 18- 32. doi: 10.1016/j.paerosci.2015.11.001
28	马俊, 黄攀峰, 孟中杰, 等. 自主机动空间绳网机器人设计与动力学建模[J]. 宇航学报, 2013, 34 (10): 1316- 1322. doi: 10.3873/j.issn.1000-1328.2013.10.004
	MA J , HUANG P F , MENG Z J , et al. Design and dynamics modeling of autonomous maneuvering tethered-net space robot system[J]. Journal of Astronautics, 2013, 34 (10): 1316- 1322. doi: 10.3873/j.issn.1000-1328.2013.10.004
29	WIGBER F . Automated rendezvous and docking of spacecraft[M]. New York: Cambridge University Press, 2003: 8- 15.
30	秦政.考虑空间碎片影响的航天器风险评估与设备布局设计[D].长沙: 国防科技大学, 2016.
	QIN Z. Risk assessment and equipment layout design for spacecraft considering space debris' influence[D]. Changsha: National University of Defense Technology, 2016.
31	王若璞.空间碎片环境模型研究[D].郑州: 信息工程大学, 2010.
	WANG R P. Research on space debris environment model[D]. Zhengzhou: Information Engineering University, 2010.
32	梁彦刚, 秦政. 空间碎片碰撞风险评估模型及其应用[J]. 国防科技大学学报, 2017, 39 (6): 19- 24.
	LIANG Y G , QIN Z . Space debris impact risk assessment model and its application[J]. Journal of National University of Defense Technology, 2017, 39 (6): 19- 24.
33	HYDE J, BJORKMAN M, CHRISTIANSEN E, et al. Micrometeoroid and orbital debris risk assessment with bumper 3[C]//Proc.of the European Conference of Space Debris, 2017.
34	MASUMI H, MARTIN S, FRANK S. Initial study on small debris impact risk assessment during orbit transfer to GEO for all-electric satellite[C]//Proc.of the European Conference on Space Debris, 2017.
35	管公顺.航天器空间碎片防护结构超高超声速撞击特性研究[D].哈尔滨: 哈尔滨工业大学, 2006.
	GUAN G S. Hypervelocity impact characteristic investigation of spacecraft space debris shield configuration[D]. Harbin: Harbin Institute of Technology, 2006.
36	KUMAR S K S , EDWIN A J M , KIM Y H , et al. Polybenzimidazole(PBI) film coating for improved hypervelocity impact energy absorption for space applications[J]. Composite Structure, 2018, 188, 72- 77. doi: 10.1016/j.compstruct.2017.12.052
37	CHRISTIANSEN E L , CREWS J L , WILLIAMSEN J E , et al. Enhanced meteoroid and orbital debris shielding[J]. International Journal of Impact Engineering, 1995, 17 (1): 217- 228.
38	MISHRA R , BEHERA B K , MILITKY J . Impact simulation of three-dimensional woven kevlar-epoxy composites[J]. Journal of Industrial Textiles, 2016, 45 (5): 978- 994. doi: 10.1177/1528083714550056
39	KHAN M B , HUSSAIN S , HUSSAIN S , et al. Enhancement of mechanical properties of kevlar-epoxy composite by improving the interface coupling[J]. Journal of Advanced Materials, 2010, 42 (3): 74- 87.
40	SON K J, FAHRENTHOLD E P. Hybrid particle-element simulation of composite material impact physics[C]//Proc.of the 18th International Conference on Composites Materials, 2011.
41	WHITE D M , TAYLOR E A , CLEGG R A . Numerical simulation and experimental characterization of direct hypervelocity impact on a spacecraft hybrid carbon fibre/Kevlar composite structure[J]. International Journal of Impact Engineering, 2003, 29 (1): 779- 790.
42	刘星.基于碳纳米粒子的非线性散射激光防护技术研究[D].南京: 南京航空航天大学, 2017.
	LIU X. Laser protection technology study based on nonlinear scattering of carbon nanoparticles[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017.
43	朱锦鹏, 马壮, 高红丽, 等. 基于等离子喷涂的反射型激光防护涂层研究[J]. 中国光学, 2017, 10 (5): 578- 588.
	ZHU J P , MA Z , GAO H L , et al. Reflective laser protective coating based on plasma spraying[J]. Chinese Optics, 2017, 10 (5): 578- 588.

卫星部件	损坏情况
包覆部件	热控表面的汽化热控表面光学特性的改变热控结构的变形和失效
结构部件	聚合物结构的汽化复合材料结构的分层铝合金结构的软化或熔化结构变形, 从而引起功能的降低
电气系统	电器绝缘材料的损伤或结构破坏焊点的熔化太阳能电池板和保护板的损伤
光学系统	光学涂层的剥离平面镜和透镜的损伤或畸形由于光学聚焦, 传感器的损伤

材料	能量密度阀值估算/(J/cm²)			30 s破坏功率密度阀值/(W/cm²)
材料	1.064 μm	1.315 μm	3.8 μm	1.064 μm	1.315 μm	3.8 μm
(c/e)T300	52	52	57	3.8	3.8	4
(c/e)M55J	54	54	60	4	4	4.2
玻璃钢	290	290	250	15.2	15.2	13.9
聚酰亚胺	4 110	4 110	2 350	136.9	136.9	78.2
砷化镓	220	290	1130	7.4	9.5	37.6
2 024铝合金	30 300	30 300	35 800	1 007.9	1 007.9	1163
Hg0.8Cd0.2Te	17.6	17.6	17.6	0.59	0.59	0.59
Si	70	70	6 150	2.3	2.3	204.7

敏感器材料	增益	1.064 μm	1.315 μm	3.8 μm
Hg0.8Cd0.2Te	10⁴	0.59E-4	0.59E-4	0.59E-4
Hg0.8Cd0.2Te	10⁶	0.59E-6	0.59E-6	0.59E-6
Si	10⁴	2.3E-4	2.3E-4	2.3E-4
Si	10⁶	2.3E-6	2.3E-6	2.3E-6

D/cm	P=100 MW			P=10 MW			P=1 MW
D/cm	1.064 μm	1.315 μm	3.8 μm	1.064 μm	1.315 μm	3.8 μm	1.064 μm	1.315 μm	3.8 μm
10	4.8E-4	4.2E-4	8.5E-5	4.8E-5	4.2E-5	8.5E-6	4.8E-6	4.2E-6	8.5E-7
50	0.012	0.01	0.002	1.2E-3	1E-3	2E-4	1.2E-4	1E-4	2E-5
100	0.047	0.042	8.5E-3	4.7E-3	4.2E-3	8.5E-4	4.7E-4	4.2E-4	8.5E-5
150	0.11	0.093	0.019	0.011	9.3E-3	1.9E-3	1.1E-3	9.3E-4	1.9E-4

敏感器材料	损伤情况	损伤阀值/(W/cm²)
微波混频器二极管	烧毁	10^-7
线形集成电路	干扰、烧毁	10^-6
小功率管、双极集成电路	干扰、烧毁	10^-5
CMOS逻辑、中功率管等	永久破坏	10^-4
大功率管、薄膜电阻等	受到破坏	10^-3

Technology system of on-orbit strong survivability for GEO satellite bus

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参数	作用距离/km
参数	1	10	50	100	200
目标处作用半径/m	12.2	24.4	61	1 220	2 440
功率密度/(W/cm²)	51	0.051	0.002	5.1E-4	1.27E-5

手段	机械臂	飞网/m	飞爪	绳系机器人	寄生粘附
距离	0	15	千米级	几十到几千米	0

威胁源		顽存手段
空间环境	单粒子事件	抗辐加固
	总剂量效应	单粒子锁定、翻转
	高能带电粒子	抗辐加固, 屏蔽
	空间碎片	告警、结构防护
主动威胁	激光	激光告警、激光防护
	微波	告警, 电磁防护
	撞击	告警, 结构防护, 机动
	操控	告警、轨道机动