AI Chat Paper
Note: Please note that the following content is generated by AMiner AI. SciOpen does not take any responsibility related to this content.
{{lang === 'zh_CN' ? '文章概述' : 'Summary'}}
{{lang === 'en_US' ? '中' : 'Eng'}}
Chat more with AI
Article Link
Collect
Show Outline
Outline
Show full outline
Hide outline
Outline
Show full outline
Hide outline
Review Article | Open Access

Research progress of space non-pyrotechnic low-shock connection and separation technology (SNLT): A review

Honghao YUEYifei YANGYifan LU( )Fei YANGJun WUQi RUANZongquan DENG
State Key Laboratory of Robotics and System, Harbin Institute of Technology, Harbin 150001, China

Peer review under responsibility of Editorial Committee of CJA.

Show Author Information

Abstract

Space missions have become diversified in recent years, where connection and separation devices play a crucial role as key components of various spacecraft. Traditional pyrotechnic devices have the advantages of large carrying capacity, rapid motion and functional reliability. However, their shortcomings such as great release shock, poor safety, unrepeatability and other prominent defects make them unsuitable for new generation spacecraft such as microsatellites to separate at low shock or lock repeatedly, etc. Therefore, it is necessary to develop space non-pyrotechnic low-shock connection and separation devices (SNLD) which are required for advanced aerospace missions. In this paper, the progress of the research on space non-pyrotechnic low-shock connection and separation technology (SNLT) is summarized and reviewed. Proceed from the principle of reducing shock for non-pyrotechnic devices, present studies are classified from the perspective of actuating technology and systematic designing methods. For non-pyrotechnic actuating techniques, according to different driving sources, the separation devices are classified into several main categories: electric, magnetic, gas and thermal actuating devices. The actuation principle and application prospect of separation techniques are introduced and the working process, dimension and mechanical properties of typical devices are compared and evaluated. For the systematic designing method, the common mechanism types of SNLDs are summarized according to the designing concept of reducing shock. Then connection configurations are classified according to the structural forms of connection devices, of which the principles, bearing capacities and general applications are discussed. This paper systematically summarizes the key problems, puts forward the future development trend of SNLT, and points out the breakthrough direction for related scholars.

References

1
Kroon M, Borst G, Grimminck M, et al. Articulated deployment system for antenna reflectors. Proceding of the 16th European Space Mechanisms and Tribology Symposium, 2015.
2
Wang YJ, Dong JH, Li W, et al. Locking and releasing system in space telescope. 7th International Symposium on Advanced Optical Manufacturing and Testing Technologies: Large Mirrors and Telescopes, 2014.
3

Li J, Yan S, Tan X. Dynamic-envelope analysis of clamp-band joint considering pyroshock of satellite separation. J Spacecr Rockets 2014;51(5):1390–400.

4

Moening CJ. Pyrotechnic shock flight failures. Institute of Environmental Sciences Pyrotechnic Shock Tutorial Program, 31st Annual Technical Meeting. Inst. Envir. Sc. 1985.

5
Bement LJ, Schimmel ML. A manual for pyrotechnic design, development and qualification. Hampton: National Aeronauticsand Space Administration Langley Research Center; 1995. p. 5-20.
6

Filippi E, Attouoman H, Conti C. Pyroshock simulation using the Alcatel ETCA test facility. Launch Vehicle Vibrations. First European Conference 1999.

7
Ni WT. Gravitational wave detection in space. In: Ni WT, editor. One Hundred Years of General Relativity: From Genesis and Empirical Foundations to Gravitational Waves. Cosmology and Quantum Gravity; 2017. p. 579–630.
8

Meguro A, Shintate K, Usui M, Tsujihata A. In-orbit deployment characteristics of large deployable antenna reflector onboard Engineering Test Satellite Ⅷ. Acta Astronaut 2009;65(9-10):1306–16.

9
Thompson SJ, Doel AP, Whalley M, et al. Large aperture telescope technology: a design for an active lightweight multisegmented fold-out space mirror. International Conference on Space Optics, ICSO 2010, 2017.
10

Hu X, Chen X, Zhao Y, Yao W. Optimization design of satellite separation systems based on Multi-Island Genetic Algorithm. Adv Sp Res 2014;53(5):870–6.

11

Sandau R, Brieß K, D’Errico M. Small satellites for global coverage: Potential and limits. ISPRS J Photogramm Remote Sens 2010;65(6):492–504.

12

Yang ZC, Luo RB, Liao H, et al. Overview of reusable locking technology in space. Spacecraft Recovery & Remote Sens 2019;40(4):10–21 [Chinese].

13
Lucy M, Hardy R, Kist E, et al. Report on alternative devices to pyrotechnics on spacecraft. 10th Annual AIAA/USU Conference on Small Satellites, 1996.
14
Buckley S, Fosness E, Gammill W. Deployment and release devices efforts at the Air Force Research Laboratory space vehicles directorate. Albuquerque: United states. AIAA International; 2001.
15

Bai ZF, Guo LL, Chen DS. Late-model non-pyrotechnic devices for separation of satellite-launching vehicle. Missiles and Space Vehicles 2009;1:31–7 [Chinese].

16

Yang BJ, Wang ZW, Gai YX. Research progress of non-pyrotechnic releasing devices on the spacecraft. Mach Des Manuf 2018;3:267–9 [Chinese].

17

Zhong ZY, Zhang HL, Zhou JP, et al. Review of non-pyrotechnic connection and separation technology of spacecraft. Manned Spaceflight 2019;25(1):128–42 [Chinese].

18

Cai FC, Meng XH. Non-pyrotechnic device for joining and separating. Spacecraft Recovery & Remote Sensing 2005;26(4):50–5 [Chinese].

19
Smith SH, Dowen D, Fossness E, et al. Development of shape memory alloy (SMA) actuated mechanisms for spacecraft release applications. 13th AIAA/USU Conference on Small Satellites, 1999.
20

Gao B. Shape memory alloys and their application to aerospace separation mechanisms. Spacecraft Recovery & Remote Sensing 2005;26(1):48–52 [Chinese].

21

Yang BJ, Xiao L, Gai YX. Research progress on non-pyrotechnic unlocking device of clamp-band separation for satellite and rocket. Mach Des Manuf 2018;84(Suppl.):178–80 [Chinese].

22

Cao NL, Dong DY, Li ZL. Non-pyrotechnic separation devices research based on shape memory alloy. Spacecraft Recovery & Remote Sensing 2014;35(5):9–18 [Chinese].

23

Binder J, McCarty M, Rasmussen C. Development of a pyrotechnic shock simulation apparatus for spacecraft applications. American Institute of Aeronautics and Astronautics 2012.

24
Kuo J, Goldstein S. Dynamic analysis of NASA Standard Initiator driven pin puller. 29th Joint Propulsion Conference and Exhibit; 1993 June 28-30; Monterey, United States. AIAA; 2012.
25
Chang K. Pyrotechnic devices, shock levels and their applications. 9th International Congress on Sound and Vibration Orlando; 2002 Jul 8-11; USA.
26

Caruso H. Revision highlights of the new MIL-STD-810F, test method standard for environmental engineering considerations and laboratory tests. J IEST 2001;44(3):30–4.

27
Little B. Electrically powered separation nuts. Proceedings of the 39th Aerospace Mechanisms Symposium; 2008 May 7-9; NASA Marshall Space Flight Center, United States. 2008.p. 185-90.
28
Wang ZW. The design of a satellite and launch vehicle separation device using redundant motors basing on two sectional segmented nut [dissertation]. Harbin: Harbin Institute of Technology; 2017 [Chinese].
29
Welsh J, Higgins J, Gilbert M, et al. Evaluation of electrically disbonding adhesive properties for use as separation systems. 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; 2003 Apr 7-10; Norfolk, United states. AIAA International; 2003.
30

Drossel W-G, Kunze H, Bucht A, Weisheit L, Pagel K. Smart3-smart materials for smart applications. Procedia CIRP 2015;36:211–6.

31

Wang XF. Research on unlocking separable structure based on piezoceramic. Mach Des Manuf 2018;7:236–9 [Chinese].

32
Cao NL, Dong DY, Chai FM, et al., inventors; Nan XP, assignee. Piezoelectric ceramic-driven spatial payload unlocking and separating mechanism. Chinese patent CN201310280399.9. 2013 Sep 18 [Chinese].
33

Zhang YW, Yang LP, Zhu YW, et al. An investigation of on-orbit release with inter-satellite electromagnetic force. Aerosp Sci Technol 2015;45:309–15.

34

Liao QS, Zhang XJ, Bao JQ. Design and implementation of cubesat and launch vehicle separation device. Missiles and Space Vehicles 2015;5:20–4 [Chinese].

35

Zhang Y, Yang L, Zhu Y, Huang H. Dynamics and nonlinear control of space electromagnetic docking. J Syst Eng Electron 2013;24(3):454–62.

36
Zhu HK, Zhang YW, Yang LP, et alStudy on the characteristics of a probe-drogue electromagnetic docking mechanism. Shanghai, China: Institute of Electrical and Electronics Engineers Inc.; 2020. p. 5512–5.
37
Valembois G, inventor; Conseil et Technique, assignee. Fixing device for the assembly and quick release of objects. United States patent US 8327511 B2. 2012 Dec 11.
38
Duforet O, Bonduelle B, Valembois G, et al. New concept of a resettable ultra low shock actuator (rulsa). 14th European Space Mechanisms & Tribology Symposium-ESMATS 2011; 2011 Sep 28-30; Constance, Germany. 2011.p. 297-304.
39
Ding LX, Tao WJ, Huang JJ, et al., inventors; Ma LJ, assignee. Non-pyrotechnic point separating device. Chinese patent CN201611176534.5. 2017 Apr 26 [Chinese].
40
Zhang X, Nan Y, Hu HB, et al., inventors; Zhu XG, assignee. Point type microsatellite separation unlocking device. Chinese patent CN201910441771.7. 2019 Aug 17 [Chinese].
41

Liu Q, Fang J, Han B. Novel electromagnetic repeated launch locking/unlocking device (RLLUD) based on self-locking for magnetic bearing flywheel. Sensors Actuators A Phys 2012;175:116–26.

42
Jiang H. The hold-on release device based on vortex coil spring winding self-locking principle [dissertation]. Harbin: Harbin Institute of Technology; 2016 [Chinese].
43
He ZL, Wu HL, Chen DS, et al., inventors. Solenoid-actuated non-pyrotechnic separation device based on volute spiral spring transmission assembly. Chinese patent CN201711231917.2. 2018 Jun 19 [Chinese].
44
Sang XJ. The Design and performance analysis for separation system of small satellite from rocket [dissertation]. Changsha: National University of Defense Technology; 2014 [Chinese].
45
Cui Y. Research on control of spacecraft in low-impact separation [dissertation]. Harbin: Harbin Institute of Technology; 2013 [Chinese].
46
Naresh C, Bose PSC, Rao CSP. Shape memory alloys: a state of art review. International Conference on Advances in Materials and Manufacturing Applications; 2016 Jul 14-16; Bangalore, India. IOP Publishing Ltd; 2016.
47

Mohd Jani J, Leary M, Subic A, Gibson MA. A review of shape memory alloy research, applications and opportunities. Mater Des 2014;56:1078–113.

48
Vázquez J, Bueno JI. Non explosive low shock reusable 20 kN hold-down release actuator. 9th European Space Mechanisms and Tribology Symposium; 2001 Sep 19-21; Liege, Belgium. European Space Agency; 2001. p. 131-5.
49
Christiansen S, Tibbitts S, Dowen D. Fast acting non-pyrotechnic 10kN separation nut. Proceedings of the 8th European Symposium; 1999; Toulouse, France. 1999.p. 323-8.
50
Jiang JM. Research on low shock and large load hold-down/release mechanism based on shape memory alloy [dissertation]. Harbin: Harbin Institute of Technology; 2012 [Chinese].
51
Wang YZ. Development and experiment of shape memory alloy rotary lock/release mechanism [dissertation]. Harbin: Harbin Institute of Technology; 2013 [Chinese].
52
Smith SH, Purdy B, Nygren B. Development of a new, no-shock separation mechanism for spacecraft release applications. The 31st Aerospace Mechanisms Symposium; 1997 May 14-16; Huntsville, United States; New York: NASA; 1997. p. 125-38.
53
Peng JS. Research on low shock trigger used on large load flywheel nut separation mechanism [dissertation]. Harbin: Harbin Institute of Technology; 2016 [Chinese].
54

Hu XN, Wu J, Peng JS, et al. Design and experimental research of a large load and low shock release device on shape memory alloy. Science Technology & Engineering 2016;16(30):319–23 [Chinese].

55

Yang F, Yue HH, Zhang YL, et al. Research on a low-impact unlocking trigger device of heavy load based on shape memory alloy fiber. Adv Mech Eng 2017;9(10):1–14.

56

Pan X, Zhang Y, Lu Y, Yang F, Yue H. A reusable SMA actuated non-explosive lock-release mechanism for space application. Int J Smart Nano Mater 2020;11(1):65–77.

57

Yoo YI, Jeong JW, Lim JH, Kim K-W, Hwang D-S, Lee JJ. Development of a non-explosive release actuator using shape memory alloy wire. Rev Sci Instrum 2013;84(1):015005. https://doi.org/10.1063/1.4776203.

58
Gardi R. Final improvements and tests on a SMA actuated, lightweight mechanism for microsatellite. 54th International Astronautical Congress of the International Astronautical Federation (IAF), the International Academy of Astronautics and the International Institute of Space Law; 2003 Sep 29-Oct 3; Bremen, Germany. International Astronautical Federation; 2003. p. 1821-7.
59
Zhang XY, Yan XJ, Yang QL. Design of a quick response SMA actuated segmented nut for space release applications. Sensors and Smart Structures Technologies for Civil, Mechanical, and Aerospace Systems 2010; 2010 March 8-11; San Diego, United states. Washington: SPIE; 2010.
60

Zhang XY, Yan XJ, Yang QL. Design and experimental validation of compact, quick-response shape memory alloy separation device. J Mech Des 2014;136(1):1–9.

61

Yan XJ, Huang DW, Zhang XY, et al. A one-stage, high-load capacity separation actuator using anti-friction rollers and redundant shape memory alloy wires. Rev Sci Instrum 2015;86(12):1–8.

62
Yan XJ, Zhang K, inventors; Liu XJ, Cheng JY, assignees. Minisized large-load SMA space synchronous unlocking mechanism. Chinese patent CN200610011626.8. 2006 Sep 6 [Chinese].
63
Yan XJ, Zhang K. Development of a small reusable space release device using SMA. Sensors and Smart Structures Technologies for Civil, Mechanical, and Aerospace Systems; 2007 Mar 19-22; San Diego, United states. Washington: SPIE; 2007.
64

Lee M-S, Jo J-U, Tak W-J, Kim B. Shape memory alloy (SMA) based non-explosive separation actuator (NEA) with a redundant function. Int J Precis Eng Manuf 2011;12(3):569–72.

65

Nava N, Collado M, Cabás R. REACT: Resettable hold down and release actuator for space applications. J Mater Eng Perform 2014;23(7):2704–11.

66

Zhang X, Yan X, Zhang S, Nie J. Development of a novel shape memory alloy-actuated resettable locking device for magnetic bearing reaction wheel. Rev Sci Instrum 2014;85(1):015006. https://doi.org/10.1063/1.4863340.

67

Qin XY, Yan XJ, Zhang XY, et al. Detailed design of an SMA-actuated self-locking device for rotary feed structure. Smart Mater Struct 2016;25(3):1–11.

68
Liu GF, Yan JH, Yang C, et al. SMA-based space release device for solar panels deployment. 11th IEEE International Conference on Mechatronics and Automation; 2014 Aug 3-6; Tianjin, China. IEEE Computer Society; 2014. p. 27-31.
69
Carpenter BF, Clark CR, Weems W. Shape memory actuated release devices. Proc. SPIE 2721, Smart Structures and Materials 1996: Industrial and Commercial Applications of Smart Structures Technologies; 1996 May 1; San Diego, United States. p. 420-6.
70

Tak W, Lee M, Kim B. Ultimate load and release time controllable non-explosive separation device using a shape memory alloy actuator. J Mech Sci Technol 2011;25(5):1141–7.

71
Mckinnis DN, inventor; The United State of America as representd by the Admiitrator of the National Aeronautics and Space Administration, assignee. Fastening apparatus having shape memory alloy actuator. United States patent US 5160233. 1992 Nov 3.
72
Busch JD, Bokaie MD. Implementation of heaters on thermally actuated spacecraft mechanisms. The 28th Aerospace Mechanisms Symposium; 1994 May 1; Lewis Research Center, United States. p. 379–94.
73
TiNiTM Frangibolt® Actuator[Internet]. 2021 May 1. Availablefrom: https://www.ebad.com/tini-frangibolt/.
74
Tuszynski A. Alternatives to pyrotechnics-nitinol release mechanisms. Proceedings of the 36th Aerospace Mechanisms Symposium; 2002 May 15-17; Cleveland, Ohio. New York: NASA. p. 137-40.
75
Gall K, Lake M, Harvey J, et al. Development of a shockless thermally actuated release nut using elastic memory composite material. 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; 2003 Apr 7-10; Norfolk, United states. American Inst. Aeronautics and Astronautics Inc.; 2003. p. 1623–33.
76
Tibbitts S. High output paraffin actuators : utilization in aerospace mechanism. Proceedings of the 22nd aerospace mechanisms symposium; 1988; Langley Research Center, United States. p. 13-28.
77

Zhang SJ, Wang LS, Nie C, et al. Development of a large load space-used paraffin actuator. Journal of Beijing University of Aeronautics and Astronautics 2017;43(5):1038–44 [Chinese].

78
Zhang XY, Yan XJ, Wang HL, et al., inventors. Fast reposition non-fired paraffin driver with SMA spring. Chinese patent CN201810629049.1. 2018 Nov 23 [Chinese].
79
Meng XH, inventor; Zeng YZ, assignee. Nano-satellite separating and unlocking device. Chinese patent CN201120389983.4. 2012 Jul 11 [Chinese].
80

Shang LB, Wang AP, Wang K, et al. Application of locking/unlocking device based on liquid metal in space deployable mechanism. Manned Spaceflight 2017;23(4):572–6 [Chinese].

81
Russell RA. Reconfigurable robot components based on liquid metal. 2008 Australasian Conference on Robotics and Automation; 2008 Dec 3-5; Canberra, Australia. Australian Robotics and Automation Association Inc.; 2008.
82
Yang WM, Jian RR, Dai KT, et al., inventors. Spacecraft unlocking and separating device. Chinese patent CN103615450A. 2014 Mar 05 [Chinese].
83

Wang L, Iida F. Physical connection and disconnection control based on hot melt adhesives. IEEE/ASME Trans Mechatronics 2013;18(4):1397–409.

84
Cremers J, Gooijer E, Kester G. Multipurpose holddown and release mechanism (MHRM). 8th European Space Mechanisms and Tribology Symposium; 1999 Sep 29-Oct 1; Toulouse, France. Paris: ESA; 1999.
85
Konink T, Kester G. Multipurpose holddown and release mechanism (MHRM). 13th European Space Mechanisms and Tribology Symposium; 2009 Sep 23-25; Vienna, Austria. Paris: ESA; 2009.
86
Stewart AC. A new and innovative use of the thermal knife and Kevlar cord components in a restraint and release system. 9th European Space Mechanisms and Tribology Symposium; 2001 Sep 19-21; Liege, Belgium. European Space Agency; 2001. p. 231–8.
87
Stewart AC, Hair JH. Intricacies of using Kevlar cord and thermal knives in a deployable release system: issues and solutions. Proceedings of the 36th Aerospace Mechanism Symposium; 2002 May 15-17; Cleveland, United States. Washington: NASA; 2002.
88
Bongers E, Koning J, Konink T. Robustness improvement of ARA Kevlar holddown restraint cables. 15th European Space Mechanisms & Tribology Symposium; 2013 Sep 25-27; Noordwijk, The Netherlands. 2013.
89
Augustijn J, Bongers E, Defence A. Engineering test results of nels hold down and release system. Proc. ‘ESMATS 2017’; 2017 Sep 20-22; Hatfield, UK. 2017.
90

Guo YZ, Guo HW, Li X, et al. A new type of multi-bar compaction and release device using flexible cable. Journal of Astronautics 2019;40(5):527–34 [Chinese].

91
Li B, Dong KJ, Wang XZ, et al., inventors; Fan XY, assignee. Large-bearing heat-cutter type press release device. Chinese patent CN106828979B. 2019 Jun 18 [Chinese].
92
Zhang F, Liu XW, Chen QF, et al., inventors. Heat knife type bolt device capable of achieving unlocking and releasing. Chinese patent CN201310228693.5. 2014 Dec 17 [Chinese].
93

Cao CM, Guan FL, Huang H, et al. Design and test of new thermal knife restraint and release device. Journal of Zhejiang University (Engineering Science) 2016;50(12):2350–6 [Chinese].

94

Choi J, Lee D, Hwang H-S, Kim B. Design, fabrication and test of qualification model of wire thermal cutting based non-explosive separation device for a small satellite. J Aerosp Eng 2015;229(4):612–20.

95
Zhao H, Guan F, Ma GC, et al., inventors; Jiang TT, assignee. Non-pyrotechnic fusing connection separation device. Chinese patent CN201911143937.3. 2020 Jan 21 [Chinese].
96

Xuan M, Zhang DW, Gu S, et al. Design of hold-down and release mechanism for solar panel of micro-satellite. Optics and Precision Engineering 2017;25(4):979–86 [Chinese].

97

Zhang XH, Yang Z, Qiu F. Structural design and analysis of hold-down and release mechanism for miniature spacecraft. Journal of Ordnance Equipment Engineering 2016;37(10):117–20, 46 [Chinese].

98
Ren WJ, Li XM, Wang C, inventors; Liu MX, assignee. Hot sword unlocking device. Chinese patent CN201720839676.9. 2018 Mar 30 [Chinese].
99
Tang XC, Ma Y, Luo JW, et al.,inventors; Luo ZW, assignee. Micro-small fuse cutter for aerospace. Chinese patent CN201811654244.6. 2019 Mar 26 [Chinese].
100
Cooper EA, Stephenson RC, inventors; G & H Technology, Inc., assignee. Fire fighting system. United States patent US 3924688. 1975 Dec 9.
101
Holt A, Wu JY, Dalton M, et al., inventors; G & H Technology, Inc., assignee. Spool assembly with integrated link-wire and electrical terminals for non-explosive actuators used in electromechanical structural separation devices. United States patent US 6747541. 2004 Jun 8.
102

Fu DB, Yu Y, Yu DJ, et al. Study on unlocking process and estimate model for joining and separating device using magnesium alloy band. Journal of Astronautics 2012;33(10):1384–90 [Chinese].

103
Huettl B, Willey CE. Design and development of miniature mechanisms for small spacecraft. 14th AIAA/USU Conference on Small Satellites, 2000.
104

Li JS, Liang X, Liu P, et al. System design and dynamic simulation analysis of release mechanism for a small-light folding wing. Aero Weaponry 2013;14(4):7–9 [Chinese].

105
Zhang X, Liu L, Zhou HQ, inventors; Zhang X, assignee. Micronano satellite unlocking and separating device and separating method thereof. Chinese patent CN201910258969.1. 2019 Jun 18 [Chinese].
106
Gai YX, Liang X, Wang R, et al., inventors; Song LG, assignee. Locking and releasing device for satellite and rocket separation. Chinese patent CN201710203183.0. 2017 Aug 18 [Chinese].
107

Han ML, Wang D, Tian Y, et al. The design and analysis of small satellite lock and release device. Mechanical Science and Technology for Aerospace Engineering 2020;39(9):1463–70 [Chinese].

108

Takeuchi S, Onoda J. Estimation of separation shock of the Marman clamp system by using a simple band-mass model. Trans Jpn Soc Aeronaut Space Sci 2002;45(147):53–60.

109
Dong XT, Jiang Y. Study on mechanical materials with overview of connection and separation devices. 2013 International Conference on Material Engineering, Chemistry and Environment; 2013 Aug 24-25; Wuhan China. Switzerland: Trans Tech Publications Ltd; 2013. p. 590-3.
110
Dowen D, Christiansen S, Arulf O. Development of a reusable,low-shock clamp band separation system for small spacecraft release applications. 9th European Space Mechanisms and Tribology Symposium; 2001 Sep 19-21; Liege, Belgium. Paris: European Space Agency; 2001. p. 191-2.
111
Peffer A, Denoyer K, Fosness E, et al. Development and transition of low-shock spacecraft release devices. 2000 IEEE Aerospace Conference; 2000 Mar 18-25; Big Sky, United States. Institute of Electrical and Electronics Engineers Computer Society; 2000. p. 277-84.
112

Crawford A, Johnson C, Gonzalez R, et al. Low shock payload separation system background report. Orbital ATK 2017.

113
Mark II Motorized Lightband [Internet]. 2021 May 1. Available from: https://www.planetarysystemscorp.com/product/mark-ii-motorized-lightband/.
114
Kelley K, Elson M, Andrews J. Deploying 87 satellites in one launch : design trades completed for the 2015 SHERPA flight hardware. 29th Annual AIAA/USU Conference on Small Satellites, 2015.
115
Haddler A, Seah C, Andrews J, et al. Spaceflight’s FORMOSAT-5/SHERPA mission how to set a world record for the number of satellites deployed in a single launch. 30th Annual AIAA/USU Conference on Small Satellites, 2016.
116
Walter H, inventor; Planetary Systems Corporation, assignee. Latching separation system. United States Patent US 7861976 B2. 2011 Jan 4.
117
Wang Y, Huang Y. Development and application prospects of modern small satellite technology. International Conference on Space Information Technology; 2009 Nov 26-27; Beijing, China. Washington: SPIE; 2010.
118
Chin A, Coelho R, Brooks L, et al. Standardization promotes flexibility: A review of cubesats’ success. 6th Responsive Space Conference; 2008 Apr 28-May 1; Los Angeles, United States. 2008.
119
Lee S, Toorian A, Clemens N, et al. Cal Poly Coordination of multiple cubesats on the DNEPR launch vehicle. 18th AIAA/USU Conference on Small Satellites; 2004 Aug; Logan, United States. 2004.
120
Chin A, Coelho R, Nugent R, et al. CubeSat: The pico-satellite standard for research and education. AIAA Space 2008 Conference and Exposition; 2008 Sep 9-11; San Diego, United States. American Institute of Aeronautics and Astronautics, Inc.;2008.
121
Toorian A, Blundell E, Puig SJ, et al. CubeSats as responsive satellites. 3rd Responsive Space Conference; 2005 Aug 30- Sep 1; Long Beach, United States. AIAA International; 2005.
122
Ali MR. Design and Implementation of ground support equipment for characterizing the performance of XPOD and CNAPS & thermal analysis of CNAPS pressure regulator valve [dissertation]. Toronto: University of Toronto; 2009.
123
Yang F, Yue HH, Wang G, et al. The design and analysis of picosatellite deployer with controllable release function. 2017 IEEE International Conference on Information and Automation; 2017 Jul 18-20; Macau, China. Institute of Electrical and Electronics Engineers Inc.; 2017. p. 548-53.
124

Zhou J, Liu YY, Liu GH, et al. QB50 Project and the development of CubeSat technology in China. Aerosp China 2019;19(2):30–9.

125

Yu XZ, Zhou J, Zhu PJ, et al. Star of AOXiang: An innovative 12U CubeSat to demonstrate polarized light navigation and microgravity measurement. Acta Astronaut 2018;147:97–106.

126
Zhang JL, Zhou J, Deng YS. CubeSat separation parameter optimization. 12th International Conference on Signal Processing and Communication Systems; 2018 Dec 17-19; Cairns, Australia. Institute of Electrical and Electronics Engineers Inc.; 2018.
127

Lu YF, Shao Q, Yue HH, et al. A review of the space environment effects on spacecraft in different orbits. IEEE Access 2019;7:93473–88.

128

Firstov GS, Van HJ, Koval YN. High-temperature shape memory alloys Some recent developments. Mater Sci Eng A 2004;378(1–2):2–10.

129

Gao B. Application of pyrotechnically actuated devices. Spacecraft Recovery & Remote Sensing 2004;25(1):55–9 [Chinese].

130

Bement LJ, Multhaup HA. Determining functional reliability of pyrotechnic mechanical devices. AIAA J 1999;37(3):357–63.

131
Dong HP, Zhang TF, Zhao X, et al. Review of reliability assessment methods for pyrotechnic devices. Proceedings of 2011 9th International Conference on Reliability, Maintainability and Safety; 2011. IEEE Computer Society; 2011. p. 46–9.
132
Naseh H, Mirshams M. A Bayesian networks approach to reliability analysis of a space vehicle separation sub-system. 6th International Conference on Recent Advances in Space Technologies; 2013 Jun 12-14; Istanbul, Turkey. IEEE Computer Society; 2013. p. 807-10.
133

Zhu YB, Rong JL, Song QQ, et al. Research on reliability evaluation method of aerospace pyrotechnic devices based on energy measurement. Appl Sci 2020;10(22):8200.

134

Cheng L, Yang YY, Mu HN, et al. Reliability evaluation method based on double beta prior distribution for the pyrotechnic device. J Shanghai Jiaotong Univ 2019;24(5):622–7.

135

Lee HN, Jang S. Reliability evaluation of a pin puller via monte carlo simulation. Int J Aeronaut Sp Sci 2015;16(4):537–47.

136
Labruyere G, Urmston P. Esa mechanisms requirements. Proc. Sixth European Space Mechanisms & Tribology Symposium; 1995 Oct 4-6; Zurich, Switzerland. 1995.
137
Gilmore A, Evernden B, Estes L, et al. Space shuttle orbiter structures & mechanisms. AIAA SPACE Conference and Exposition 2011; 2011 Sep 27-29; Long Beach, United States. 2011.
138
Olivieri L. Development and characterization of a standardized docking system for small spacecraft [dissertation]. Padova: Universit‘a degli Studi di Padova; 2015.
139
Hoff NR. Design and implementation of a relative state estimator for docking and formation control of modular autonomous spacecraft[dissertation]. Cambridge: Massachusetts Institute of Technology; 2007.
140

Akhras G. Smart materials and smart systems for the future. Can Mil J 2000;1(3):25–31.

141
Sherrit S. Smart material/actuator needs in extreme environments in spaceSmart Structures and Materials 2005 - Active Materials: Behavior and Mechanics. San Diego, United states. Washington: SPIE; 2005. p. 335–46.
142
Sater J, Crowe C. Smart air and space structure demonstrations: Status and technical issues. 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit; Reston, Virigina; 2000 Apr 3-6; Atlanta, USA. 2000. p. 176-90.
143

Basheer A. Advances in the smart materials applications in the aerospace industries. Aircr Eng Aerosp Technol 2020;92(7):1027–35.

144
Kortmann M, Zeis C, Meinert T, et al. Design and qualification of a multifunctional interface for modular satellite systems. 69th International Astronautical Congress; 2018 Oct 1-5; Bremen, Germany. 2018.
145

Xu WF, Han L, Wang X, et al. A wireless reconfigurable modular manipulator and its control system. Mechatronics 2021;73 102470.

146

Li WJ, Cheng DY, Liu XG, et al. On-orbit service (OOS) of spacecraft: A review of engineering developments. Prog Aerosp Sci 2019;108:32–120.

147
Wilson TB. Mechanical design of a trawl-resistant self-mooring autonomous underwater vehicle [dissertation]. Blacksburg: Virginia Tech; 2016.
148
Hayward DM, Duff A, Wagner C. F-35 weapons design integration. 18th AIAA Aviation Technology, Integration, and Operations Conference; 2018 Jun 25-29; Atlanta, United States. 2018.
Chinese Journal of Aeronautics
Pages 113-154
Cite this article:
YUE H, YANG Y, LU Y, et al. Research progress of space non-pyrotechnic low-shock connection and separation technology (SNLT): A review. Chinese Journal of Aeronautics, 2022, 35(11): 113-154. https://doi.org/10.1016/j.cja.2021.07.001

76

Views

9

Crossref

9

Web of Science

11

Scopus

2

CSCD

Altmetrics

Received: 27 May 2021
Revised: 23 June 2021
Accepted: 14 July 2021
Published: 24 July 2021
© 2021 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).

Return