[1] 于登云,杨建忠.航天器机构技术[M].北京:中国科学技术出版社,2011: 112.
[2] 蔡逢春,孟宪红.用于连接和分离的非火工装置[J].航天返回与遥感,2005,12(4): 50-55.
CAI Fengchun,MENG Xianhong. Nonpyrotechnic device for joining and separating [J]. Spacecraft Recovery and Remote Sensing, 2005, 12(4): 50-55.
[3] STEWART A C. A new and innovative use of the thermal knife and Kevlar cord components in a restraint and release system [J]. 2001, 480: 231-238.
[4] WASHER G, BROOKS T, SAULSBERRY R. Characterization of kevlar using raman spectroscopy [J]. Journal of Materials in Civil Engineering, 2009, 21(5): 226-234.
[5] CREMERS J, GOOIJER E, KESTER G. Multipurpose holddown and release mechanism (MHRM)[J]. European Space Agency-publications-esa sp, 1999, 438:329334.
[6] STEWART A C, HAIR J H. Intricacies of Using Kevlar Cord and Thermal Knives in a Deployable Release System: Issues and Solutions[C]. ∥Proceedings of the 36th Aerospace Mechanisms Symposium,2002: 243-256.
[7] 白志富,果琳丽,陈岱松.新型非火工星箭连接分离技术[J].导弹与航天运载技术,2009(1): 31-37
BAI Zhifu,GUO Linli,CHEN Daisong. Latemodel nonpyrotechnic devices for separation of satellitelaunching vehicle [J]. Missile and space vehcile,2009(1): 3137.
[8] KONINK T, KESTER G. Multipurpose holddown and release mechanism(MHRM) [C] ∥ The 13th European Space Mechanisams and Tribology Symposium. Vienna: ESTMAS, 2009.
[9] 姜水清,刘立平.热刀致动的压紧释放装置研制[J].航天器工程,2005,12(4): 31-34.
JIANG Shuiqing,LIU Liping. The thermal knife actuated pressing development and release device [J].Spacecraft Engineering,2005,12(4): 31-34.
[10] 李新立,姜水清,刘宾.热刀式压紧释放装置释放可靠性验证试验及评估方法[J].航天器工程,2012,4(2): 123-126.
LI Xinli, JIANG Shuiqing, LIU Bin. Reliability testevaluation method of thermal kniferestraint and release system [J]. Spacecraft Engineering, 2012, 4(2):123126.
[11] 胡明志.小卫星星箭分离系统设计、分析与优化研究[D].长沙:国防科技大学,2012: 24-25.
HU Mingzhi. Research on design, analysis, and op timization of separation systems for small satellites [D]. Changsha: National University of Defense Technology, 2012: 2425.
[12] 朱术华,关富玲.小型星载可展开结构的平面度测量[J].低温建筑技术,2015,6(6): 37-39.
ZHU Shuhua, GUAN Fuling. Flatness precision measurement of small spaceborne deployable planar mechanism [J]. Low temperature construction technology,2015,6(6): 37-39.
[13] 徐明忠.超高分子量聚乙烯纤维抗蠕变性能研究[D].北京.北京服装学院,2011: 24.
XU Mingzhong. The study on the creep resistance property of ultrahigh molecular weight polyethylenefiber [D]. Beijing: Beijing Institute of Fashion Technology, 2011: 24.
[14] 金日光,华幼卿.高分子物理[M].北京:化学工业出版社,2006: 180-182.
[15] 潘婉莲,刘兆峰,胡祖明.多级拉伸中超高相对分子质量聚乙烯纤维的结构与性能研究[J].合成纤维,2006,11(11): 68.
PAN Wanlian, LIU Zhaofeng, HU Zuming. Structure and properties of the multistage stretching inultrahigh molecular weight polyethylene fibers [J]. Synthetic Fiber,2006,11(11): 68.
[16] 朱术华.星载平台可展开结构的设计与试验[D].杭州:浙江大学,2015: 1-15.
ZHU Shuhua. Design and test of deployable plane structure for spaceborne platform [D]. Hangzhou:Zhejiang University, 2015: 1-15. |