|Table of Contents|

Influences of ascender unlock devices on takeoff stability

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2014年03期
Page:
375-
Research Field:
Publishing date:

Info

Title:
Influences of ascender unlock devices on takeoff stability
Author(s):
Hu Jianguo1Ma Dawei1Zhu Zhongling1Zhao Jie2Yang Fengbo1
1.School of Mechanical Engineering,NUST,Nanjing 210094,China; 2.Gansu Forestry Technological College,Tianshui 741020,China
Keywords:
aerospace engineeringplanetary explorationascendersunlock devicestakeoff stabilityrocket exhaustunlock ribbonsmaterialsmagnesium ribbonunlock time
PACS:
V423.6
DOI:
-
Abstract:
To study the unlocking processes of ascender unlock devices affected by rocket exhaust and their influences on takeoff stability,the structure and working principle are analyzed.The unlocking mechanisms of ascender unlock devices are theoretically studied and numerically calculated considering the material performance of unlock ribbons.The unlock time of ascenders is estimated,and the influences of different unlock time on the takeoff stability of ascenders are studied.The results show that magnesium ribbons don’t burn in the unlock processes of ascenders,and the main factor of magnesium ribbon fracture is the thermal and mechanical interaction,and the minimal influence on the takeoff stability of ascenders occurs when the unlock time is 0.3 s.

References:

[1]Cleveland M A.Low shock separation bolt[P].USA:US6925939 B2,2005-08-09.
[2]何春全,严楠,叶耀坤.导弹级间火工分离装置综述[J].航天返回与遥感,2009,30(3):70-77.
He Chunquan,Yan Nan,Ye Yaokun.Study of stage separation device for missile[J].Spacecraft Recovery & Remote Sensing,2009,30(3):70-77.
[3]高滨.火工驱动分离装置的应用[J].航天返回与遥感,2004,25(1):55-59.
Gao Bin.Application of pyrotechnically actuated devices[J].Spacecraft Recovery & Remote Sensing,2004,25(1):55-59.
[4]Peffer A,Fosness E,Hill S.Development and transition of lowshock spacecraft release devices for small satellites[A].14th Annual/USU Conference on Small Satellites[C].Logan,UT,USA:AIAA/Utah State University,2000.
[5]Toorian A,Blundell E,PuigSuari J,et al.CubeSats as responsive satellites[R].AIAA 2005-6826.
[6]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.Latemodel nonpyrotechnic devices for separation of satellitelaunching vehicle[J].Missiles and Space Vehicles,2009(1):31-37.
[7]傅德彬,于勇,于殿君,等.镁合金带连接分离装置解锁过程与预估模型[J].宇航学报,2012,33(10):1384-1390.
Fu Debin,Yu Yong,Yu Dianjun,et al.Study on unlocking process and estimate model for joining and separating device using magnesium alloy band[J].Journal of Astronautics,2012,33(10):1384-1390.
[8]姚昌仁,张波.火箭导弹发射装置设计[M].北京:北京理工大学出版社,1998.
[9]高凯,张志勇,邓科.某类导弹锁定机构解锁机理分析[J].导弹与航天运载技术,2012(2):39-42.
Gao Kai,Zhang Zhiyong,Deng Ke.Unlocking theory analysis of a missile locked mechanism[J].Missiles and Space Vehicles,2012(2):39-42.
[10]武晓松,陈军,王栋.固体火箭发动机气体动力学[M].北京:国防工业出版社,2005.
[11]赵镇南.传热学[M].2版.北京:高等教育出版社,2008.
[12]袁家军.卫星结构设计与分析[M].北京:中国宇航版社,2004.
[13]Heiken G H,Vaniman D T,French B M.Lunar sourcebook,a user’s guide to the moon[M].Cambridge,UK:Cambridge University Press,1991.
[14]欧阳自远.月球科学概论[M].北京:中国宇航出版社,2005.

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Last Update: 2014-06-30