[1]胡建国,马大为,朱忠领,等.上升器解锁装置对起飞稳定性的影响[J].南京理工大学学报(自然科学版),2014,38(03):375.
　Hu Jianguo,Ma Dawei,Zhu Zhongling,et al.Influences of ascender unlock devices on takeoff stability[J].Journal of Nanjing University of Science and Technology,2014,38(03):375.
点击复制

上升器解锁装置对起飞稳定性的影响
分享到：

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

卷:
38卷
期数:
2014年03期
页码:
375
栏目:
出版日期:
2014-06-30

文章信息/Info

Title:
Influences of ascender unlock devices on takeoff stability
作者:
胡建国1; 马大为1; 朱忠领1; 赵婕2; 杨风波1
1.南京理工大学 机械工程学院,江苏 南京 210094;2.甘肃林业职业技术学院,甘肃 天水 741020
Author(s):
Hu Jianguo1; Ma Dawei1; Zhu Zhongling1; Zhao Jie2; Yang Fengbo1
1.School of Mechanical Engineering,NUST,Nanjing 210094,China; 2.Gansu Forestry Technological College,Tianshui 741020,China
关键词:
航天工程; 星球探测; 上升器; 解锁装置; 起飞稳定性; 火箭排气; 锁紧带; 材料; 镁带; 解锁时间
Keywords:
aerospace engineering; planetary exploration; ascenders; unlock devices; takeoff stability; rocket exhaust; unlock ribbons; materials; magnesium ribbon; unlock time
分类号:
V423.6
摘要:
为研究上升器解锁装置在火箭排气作用下的解锁过程和对起飞稳定性的影响,分析了其结构及工作原理。结合锁紧带的材料性能,采用理论研究与数值计算相结合的方法,研究了上升器解锁装置的解锁机理。对上升器解锁时间进行了预估,并研究了不同解锁时间对上升器起飞稳定性的影响。结果表明:上升器解锁过程中,镁带不会燃烧;热、力共同作用是镁带断裂的主要因素;上升器解锁时间为0.3 s时对上升器起飞稳定性影响最小。
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.

参考文献/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.

备注/Memo

备注/Memo:
收稿日期:2013-11-29修回日期:2014-03-14
作者简介:胡建国(1986-),男,博士生,主要研究方向:航空航天科学与技术,Email:super-jianguo@163.com;通讯作者:马大为(1953-),男,教授,博士生导师,主要研究方向:兵器系统控制与仿真技术,E-mail:madawei@njust.edu.cn。
引文格式:胡建国,马大为,朱忠领,等.上升器解锁装置对起飞稳定性的影响[J].南京理工大学学报,2014,38(3):375-379.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2014-06-30