运载火箭分离与推冲机构综述

doi:10.3901/JME.260006

摘要/Abstract

摘要： 作为运载火箭多功能化体系的核心执行单元之一，分离与推冲机构的动作可靠性与分离精度直接影响航天发射任务的成败。随着各国航天任务复杂度与火箭运载能力的提升，分离与推冲机构在承载能力、响应速度及环境适应性等方面面临更为严苛的技术要求，系统梳理了国内外运载火箭分离与推冲机构的应用与发展现状，详细介绍了多类作动形式下各分离与推冲机构工作原理与特点，回顾了运载火箭分离与推冲机构的动态特性、冲击响应以及可靠性领域的发展，并介绍了部分典型机构的仿真分析技术，最后展望了运载火箭分离与推冲机构产品的发展趋势，旨在为新一代运载火箭分离推冲系统的创新设计与产品系统性发展提供参考。

关键词: 运载火箭, 解锁分离, 推冲机构, 仿真分析

Abstract: As one of the core executive unit of the multifunctional system of launch vehicles, the action reliability and separation accuracy of separation and thrust mechanisms directly affect the success or failure of space launch missions. With the increase of the complexity of space missions and the carrying capacity of rockets in various countries, separation and thrust mechanisms face more stringent technical requirements in terms of bearing capacity, response speed, and environmental adaptability. A review systematically combs through the application and development status of separation and thrust mechanisms for launch vehicles at home and abroad, introduces in detail the working principles and characteristics of various separation and thrust mechanisms from four aspects: pyrotechnic, spring, pneumatic, and other energy sources, reviews the development in the field of dynamic characteristics, impact response, and reliability of separation and thrust mechanisms for launch vehicles, and introduces the simulation analysis techniques of some typical mechanisms. Finally, it looks forward to the development trend of separation and thrust mechanism products for launch vehicles, aiming to provide references for the innovative design and systematic development of separation and thrust systems for new-generation launch vehicles.

Key words: launch vehicle, unlocking separation, thrust mechanism, simulation analysis

中图分类号:

郭晓霏, 李伟豪, 杨飞, 岳洪浩, 邓宗全. 运载火箭分离与推冲机构综述[J]. 机械工程学报, 2026, 62(1): 96-124.

GUO Xiaofei, LI Weihao, YANG Fei, YUE Honghao, DENG Zongquan. Review on the Separation and Thrust Mechanism of Launch Vehicles[J]. Journal of Mechanical Engineering, 2026, 62(1): 96-124.

参考文献

[1] 吴会强,张宏剑,张毅博.航天运载器机构技术发展及展望[J].中国航天,2023(10):9-17.WU Huiqiang,ZHANG Hongjian,ZHANG Yibo.Development and prospect of technology for mechanisms of launch vehicles[J].Aerospace China,2023(10):9-17.
[2] 王国辉,张宏剑,吴会强.运载火箭非火工分离机构技术发展与展望[J].宇航学报,2023,44(3):334-347.WANG Guohui,ZHANG Hongjian,WU Huiqiang.Development and outlook of non-pyrotechnic separation mechanism for launch vehicle[J].Journal of Astronautics,2023,44(3):334-347.
[3] 陈曦,张利艳,张艳艳,等.世界航天运载器大全[M].第2版.北京:中国宇航出版社,2007.CHEN Xi,ZHANG Liyan,ZHANG Yanyan,et al.The encyclopedia of world space launch vehicles[M].The 2nd Edition.Beijing:China Astronautics Publishing House,2007.
[4] RUDOLPH A,SLAYTON D K.Saturn V flight manual[Z].Alabama:Marshall Space Flight Center,1968.
[5] MCDONNELL Douglas Corporation.Delta II payload planners guide[M].California:The Boeing Company Space and Communications Group,1996.
[6] The Boeing Company.Delta IV payload planners guide[M].California:The Boeing Company Space and Communications Group,1999.
[7] The Boeing Company.Delta IV launch services user's guide[M].Colorado:United Launch Alliance,2013.
[8] FEROCITER G.New glenn payload user's guide[M].Washington:Blue Origin,2018.
[9] MUSK E.Falcon user's guide[M].Texas:Space Exploration Technologies Corp,2021.
[10] 吴晗玲,宋保永,苏晗,等.猎鹰9运载火箭结构分系统设计特点分析与研究[J].飞航导弹,2017(9):1-4.WU Hanling,SONG Baoyong,SU Han,et al.Analysis and research on the structural subsystem design characteristics of the Falcon 9 carrier rocket[J].Aerodynamic Missile Journal,2017(9):1-4.
[11] STARSEM.Soyuz user's manual[M].Paris:Starsem,2001.
[12] NESTEROV V E,MCKENNA F,BAKHVALOV Y O,et al.Proton launch system mission planner's guide[M].International Launch Services,2009.
[13] 张恒源.M系列[EB/OL].[2025-03-25].https://sat.huijiwiki.com/wiki/M%E7%B3%BB%E5%88%97.ZHANG Hengyuan.M launch vehicle series[EB/OL].[2025-03-25].https://sat.huijiwiki.com/wiki/M%E7%B 3%BB%E5%88%97.
[14] Ttjh.H-1,日本的一款火箭[EB/OL].[2025-03-25].https://sat.huijiwiki.com/wiki/H-1.Ttjh.H-1,a Japanese rocket[EB/OL].[2025-03-25].https://sat.huijiwiki.com/wiki/H-1.
[15] CEN Zheng,GAO Ruofei,SHEN Lei.LM-3A series launch vehicles user's manual[M].Beijing:China Academy of Launch Vehicle Technology,2011.
[16] 栾宇,李东,袁水林,等.长征五号运载火箭分离系统设计与验证技术研究[J].导弹与航天运载技术,2021(2):9-16.LUAN Yu,LI Dong,YUAN Shuilin,et al.Study on design and validation for separation system in development of LM-5 launch vehicle[J].Missiles and Space Vehicles,2021(2):9-16.
[17] 杨浩亮,王英诚,张延瑞,等.力箭一号分离系统设计与验证[J].载人航天,2024,30(1):81-88.YANG Haoliang,WANG Yingcheng,ZHANG Yanrui,et al.Design and verification of separation system of PR-1[J].Manned Spaceflight,2024,30(1):81-88.
[18] GREEVER B B.General description and design of the configuration of the Juno I and Juno II launching vehicles[J].IRE Transactions on Military Electronics,1960,MIL-4(2/3):70-77.
[19] WILKINS M,SOWERS G.Atlas V launch services user's guide[M].Colorado:United Launch Alliance,2010.
[20] HONEYCUTT J,BLEVINS D J.NASA's space launch system reference guide[M].Washington:National Aeronautics and Space Administration,2022.
[21] The Europen Space Agency.Ariane 5 fairing undergoes testing for shockless separation[EB/OL].[2025-03-25].https://www.esa.int/Enabling_Support/Space_Transportation/Ariane_5_fairing_undergoes_testing_for_shockless_separation
[22] CEN Zheng,GAO Ruofei,SHEN Lei.LM-3B user's manual[M].Beijign:China Academy of Launch Vehicle Technology,1999.
[23] FRICKW.Antares user's guide[M].Los Angeles:Northrop Grumman Space Systems Sector,2020.
[24] Minotaur I user's guide[M].Virginia:Orbital Sciences Corporation,2006.
[25] Minotaur IV user's guide[M].Virginia:Orbital Sciences Corporation,2006.
[26] BECK P.Electron payload user's guide v7.0[M].California:Rocket Lab USA,Inc,2022.
[27] LAGIER R.Ariane 6 user's manual[M].Guyana:Arianespace and Ariane group,2021.
[28] LAGIER R.Vega C user's manual[M].Guyana:Arianespace and Ariane group,2018.
[29] JAEA.Epsilon launch vehicle user's manual[M].Tokyo:Japan Aerospace Exploration Agency,2018.
[30] 李长纯.长征二号E火箭有效载荷整流罩分离技术[J].中国航天,1992(9):13-17.LI Changchun.The payload fairing separation technology of the Long March 2E rocket[J].Aerospace China,1992(9):13-17.
[31] 汪顺亮,董文源.长征四号卫星整流罩分离动力学研究[J].中国航天,1993(8):36-38.WANG Shunliang,DONG Wenyuan.Separation dynamic research of Long March 4's payload fairing[J].Aerospace China,1993(8):36-38.
[32] 张卫东,杨赧,杨帆.长征六号甲运载火箭及其技术特点[J].国际太空,2022(6):8-10.ZHANG Weidong,YANG Nan,YANG Fan.LM-6A carrier rocket and its technical characteristics[J].Space International,2022(6):8-10.
[33] ZHANG Wen,LIU Jiajia,LIU Wei,et al.Smart Dragon 3 launch vehicle system[J].Aerospace China,2022,23(4):3-10.
[34] GANNON M.Firefly alpha payload user guide[M].Cedar Park:Firefly Space Systems,2015.
[35] KOENIGSMANN H,SHOTWELL G E.The Falcon I launch vehicle[C]//57th International Astronautical Congress.Valencia,Spain:AIAA,2006:3341-3350.
[36] DREYER L.Latest developments on SpaceX's Falcon 1 and Falcon 9 launch vehicles and Dragon spacecraft[C]//2009 IEEE Aerospace Conference.Big Sky,MT,USA:IEEE,2009:1-15.
[37] 王辰,杨建民,崔照云,等.运载火箭落区控制的栅格舵机构技术实践[J].导弹与航天运载技术(中英文),2023(3):12-19.WANG Chen,YANG Jianmin,CUI Zhaoyun,et al.Research on application of grid fin mechanism on launch vehicle falling area control[J].Missiles and Space Vehicles (Chinese&English),2023(3):12-19.
[38] 星际荣耀航天科技集团.揭秘双曲线一号验证火箭上的栅格舵技术[EB/OL].[2025-10-10].https://zhuanlan.zhihu.com/p/45195079.Star Glory Aerospace Technology Group.Uncover the grid rudder technology on hyperbola-1 validation rocket[EB/OL].[2025-10-10].https://zhuanlan.zhihu.com/p/45195079.
[39] 张毅博,吴会强,张宏剑,等.太空探索技术公司运载火箭机构技术发展路线分析及启示[J].宇航学报,2025,46(3):631-640.ZHANG Yibo,WU Huiqiang,ZHANG Hongjian,et al.Analysis of the technological development path of SpaceX's launch vehicle mechanisms and its implications[J].Journal of Astronautics,2025,46(3):631-640.
[40] 石玉红,肖耘,徐卫秀.CZ-2F逃逸飞行器最大速度头模拟飞行试验技术[J].宇航学报,2004,25(5):484-487.SHI Yuhong,XIAO Geng,XU Weixiu.The technology of CZ-2F escape vehicle's maximum velocity head simulated flight test[J].Journal of Astronautics,2004,25(5):484-487.
[41] 杜涛,牟宇,杨建民,等.CZ-2C子级落区栅格舵的气动设计实践及发展展望[J].导弹与航天运载技术(中英文),2023(3):20-26.DU Tao,MOU Yu,YANG Jianmin,et al.Practices and prospects for aerodynamic design of CZ-2C first stage landing area control with grid fin project[J].Missiles and Space Vehicles (Chinese&English),2023(3):20-26.
[42] CHEN Xuewei,JIN Yihui.LM-4B Accomplished China's first grid fins reuse flight test[J].Aerospace China,2020,21(3):53-54.
[43] 牛枞,王宸,陈金宝,等.可重复使用运载火箭回收着陆装置研究进展[J].宇航学报,2025,46(5):825-837.NIU Cong,WANG Chen,CHEN Jinbao,et al.Review of the recovery system of reusable launch vehicle[J].Journal of Astronautics,2025,46(5):825-837.
[44] 张毅博,吴会强,张宏剑,等.太空探索技术公司运载火箭机构技术发展路线分析及启示[J].宇航学报,2025,46(3):631-640.ZHANG Yibo,WU Huiqiang,ZHANG Hongjian,et al,Analysis of the technological development path of SpaceX's launch vehicle mechanisms and its implications[J].Journal of Astronautics,2025,46(3):631-640.
[45] BARBOUR R T.Pyrotechnics in industry[M].New York:McGraw-Hill Book Company,1981.
[46] BRAUER K O.Handbook of pyrotechnics[M].Beijing:Chemical Publishing Company,1974.
[47] LUCY M H,HARDY R C,KIST E H,et al.Report on alternative devices to pyrotechnics on spacecraft[C]//Annual AIAA/USU Conference on Small Satellites,Logan,United States:NASA Technical Reports Server(NTRS),1996:1-19.
[48] BEMENT L J,SCHIMMEL M L.A manual for pyrotechnic design,development and qualification[R].Hampton,VA,United States:NASA Langley Research Center,1995.
[49] MOENING C J.Pyrotechnic shock flight failures[C]//Institute of Environmental Sciences Pyrotechnic Shock Tutorial Program,31st Annual Technical Meeting.Las Vegas,NV,USA:Citeseer,1985:4-5.
[50] 高滨.火工分离装置的性能研究[D].长沙:国防科学技术大学,2005.GAO Bin.Research on the pyrotechnically actuated separation devices[D].Changsha:National University of Defense Technology,2005.
[51] 夏冬星,杨安民,徐禄,等.一种双侧推负载整流罩分离作动筒输出特性研究[J].火工品,2020(3):9-12.XIA Dongxing,YANG Anmin,XU Lu,et al.Study on the output characteristics of the fairing separation actuator for double-side push-load[J].Initiators & Pyrotechnics,2020(3):9-12.
[52] 邢星星,张鹏,赵铮.火工分离器仿真与实验研究[J].兵器装备工程学报,2022,43(4):19-24.XING Xingxing,ZHANG Peng,ZHAO Zheng.Simulation and experimental study on pyrotechnic separator[J].Journal of Ordnance Equipment Engineering,2022,43(4):19-24.
[53] 朱维亮,张文峰.一种新型导弹级间分离机构研究[J].航天返回与遥感,2005,26(1):53-57.ZHU Weiliang,ZHANG Wenfeng.Research of a new stage separation mechanism for missiles[J].Spacecraft Recovery & Remote Sensing,2005,26(1):53-57.
[54] LEE Y J.Development of ball type separation bolt[C]//Proceedings of the Korean Society of Propulsion Engineers Conference.Korea:The Korean Society of Propulsion Engineers,2008:179-182.
[55] LEE Y J,KOO S H,JANG H B,et al.A study of separation mechanism in ball type separated bolt[J].Journal of the Korean Society of Propulsion Engineers,2011,15(2):62-7.
[56] NA M S,LEE Y W,PARK T H,et al.Apparatus for restraining and releasing missile using rigid sphere:US,Patent 6,286,409[P].2001-9-11.
[57] 叶耀坤,刘天雄,温玉全,等.航天火工连接分离机构设计技术研究[J].载人航天,2016,22(1):62-68.YE Yaokun,LIU Tianxiong,WEN Yuquan,et al.Study on design technology of space pyrotechnic connection and separation mechanism[J].Manned Spaceflight,2016,22(1):62-68.
[58] HWANG D H,HAN J H,LEE J,et al.A mathematical model for the separation behavior of a split type low-shock separation bolt[J].Acta Astronautica,2019,164:393-406.
[59] JEYAKUMAR D,BISWAS K K.Stage separation system design and dynamic analysis of isro launch vehicles[J].Journal of Aerospace Sciences and Technologies,2023:211-222.
[60] LI J,YAN S,TAN X.Dynamic-envelope analysis of clamp-band joint considering pyroshock of satellite separation[J].Journal of Spacecraft and Rockets,2014,51(5):1390-1400.
[61] 谢长雄.皮卫星星箭分离机构设计分析方法及关键技术研究[D].杭州:浙江大学,2014.XIE Changxiong.Research on design analysis method and key technology of separation mechanism of pico satellite star arrow[D].Hangzhou:Zhejiang University,2014.
[62] NARESH C,BOSE P S C,RAO C S P.Shape memory alloys:A state of art review[C]//IOP Conference Series.Bangalore,India:Materials Science and Engineering.IOP Publishing,2016:054-068.
[63] JANI J M,LEARY M,SUBIC A,et al.A review of shape memory alloy research,applications and opportunities[J].Materials & Design (1980-2015),2014,56:1078-1113.
[64] NORDT A A.The design of the sapphire separation system and launch vehicle interface[J].1995.
[65] BUSCH J D,BOKAIE M D.Implementation of heaters on thermally actuated spacecraft mechanisms[C]//NASA.Lewis Research Center,The 28th Aerospace Mechanisms Symposium.1994:379-393.
[66] 韩妙玲,王冬,田昀,等.微纳卫星联动式连接分离装置设计与分析[J].机械科学与技术,2020,39(9):1463-1470.HAN Miaoling,WANG Dong,TIAN Yun,et al.Design and analysis of lock and release device for small satellite[J].Mechanical Science and Technology for Aerospace Engineering,2020,39(9):1463-1470.
[67] 付佳丽.一种低冲击星箭分离机构:中国,202211627371.3[P].2023-02-28.FU Jiali.A low impact star arrow separation mechanism:China,202211627371.3[P].2023-02-28.
[68] 北京灵翼航宇科技有限公司.记忆金属星箭分离机构[EB/OL].[2025-03-25].http://www.le-aerospace.com/index/index/product_details/listid/11.html.Beijing Link-Easy Aerospace Technology Ltd.Memory metal star and arrow separation mechanism[EB/OL].[2025-03-25].http://www.le-aerospace.com/index/index/product_details/listid/11.html.
[69] YANG Haoliang,WANG Yuning,SUN Zhichao,et al.The development of memory alloy satellite-rocket separation device for commercial small satellites[J].Aerospace China,2022,23(1):55-60.
[70] 李腾飞,单悌磊,王瑞显,等.一种连杆式星箭分离机构:中国,202010357249.3[P].2020-09-04.LI Tengfei,SHAN Tilei,WANG Ruixian,et al.A linkage type star rocket separation mechanism:China,202010357249.3[P].2020-09-04.
[71] 北京微分航宇科技有限公司.星箭适配器.[EB/OL].[2025-03-25].https://www.weifenhangyu.com/product802924646277189632.Beijing differential Aerospace Technology Co.,Ltd.Star arrow adapter[EB/OL].[2025-03-25].https://www.weifenhangyu.com/product802924646277189632.
[72] LI Xuemei,SUN Beibei.Dynamic modeling and simulation analysis of non-explosive separation device[J].Journal of Physics:Conference Series,2022,2292(1):012010.
[73] LEE M S,JO J U,TAK W J,et al.Shape memory alloy (SMA) based non-explosive separation actuator (NEA) with a redundant function[J].International Journal of Precision Engineering and Manufacturing,2011,12(3):569-572.
[74] TAK W,LEE M,KIM B.Ultimate load and release time controllable non-explosive separation device using a shape memory alloy actuator[J].Journal of Mechanical Science and Technology,2011,25(5):1141-1147.
[75] 孟宪红,白曌宇,蔡桂喜.一种纳卫星分离解锁装置:中国,201120389983.4[P].2012-07-11.MENG Xianhong,BAI Zhaoyu,CAI Guixi.A nanosatellite separation unlock device:China,201120389983.4[P].2012-07-11.
[76] 杨卫民,鉴冉冉,戴坤添,等.一种航天器解锁分离装置:中国,201310634722.8[P].2014-03-05.YANG Weimin,JIAN Ranran,DAI Kuntian,et al.A spacecraft unlock separation device:China,201310634722.8[P].2014-03-05.
[77] 尚立斌,王安平,王珂,等.基于液态金属的锁紧/解锁装置在空间展开机构中的应用[J].载人航天,2017,23(4):572-576.SHANG Libin,WANG Anping,WANG Ke,et al.Application of locking/unlocking device based on liquid metal in space deployable mechanism[J].Manned Spaceflight,2017,23(4):572-576.
[78] NAKAYA K,KONOUE K,SAWADA H,et al.Tokyo tech cubeSat:CUTE-I-design & development of flight model and future plan[C]//21st International Communications Satellite Systems Conference and Exhibit.Yokohama,Japan:American Institute of Aeronautics and Astronautics,2003:2388-2398.
[79] 张峰,刘雪文,陈琪锋,等.一种可解锁与释放的热刀式螺栓装置:中国,201310228693.5[P].2014-12-17.ZHANG Feng,LIU Xuewen,CHEN Qifeng,et al.A hot knife bolting unit that can be unlocked and released:China,201310228693.5[P].2014-12-17.
[80] BECK P.Motorized lightband mkii[M].California:Rocket Lab,2022:16-23.
[81] BECK P.Canisterized satellite dispenser[M].California:Rocket Lab,2018.
[82] 王雪峰.压电陶瓷驱动的解锁分离机构研究[J].机械设计与制造,2018(7):236-239.WANG Xuefeng.Research on unlocking separable structure based on piezoceramic[J].Machinery Design & Manufacture,2018(7):236-239.
[83] HE Yunhan,WANG Zhaokui,ZHANG Yulin.The electromagnetic separation system for the small spherical satellite Q-SAT[J].Acta Astronautica,2021,184:180-192.
[84] 廖桥生,张祥金,包家倩.立方星星箭分离装置的设计实现[J].导弹与航天运载技术,2015(5):20-24.LIAO Qiaosheng,ZHANG Xiangjin,BAO Jiangqian.Design and implementation of cubesat and launch vehicle separation device[J].Missiles and Space Vehicles,2015(5):20-24.
[85] 张翔,刘磊,周晗琼.一种微纳卫星解锁分离装置及其分离方法:中国,201910258969.1[P].2019-06-18.ZHANG Xiang,LIU Lei,ZHOU Hanqiong.A micro nanosatellite unlock separation device and its separation method:China,201910258969.1[P].2019-06-18.
[86] BOGDANOV D.Carbonix user manual[M].Berlin:Exolaunch,2024.
[87] BOGDANOV D.Quadro user manual[M].Berilin:Exolaunch,2024.
[88] LIU Qiang,FANG Jiancheng,HAN Bangcheng.Novel electromagnetic repeated launch locking/unlocking device (RLLUD) based on self-locking for magnetic bearing flywheel[J].Sensors and Actuators A:Physical,2012,175:116-126.
[89] ZHAO Yong,YUE Honghao,YANG Fei,et al.A high thrust density voice coil actuator with a new structure of double magnetic circuits for cubesat deployers[J].IEEE Transactions on Industrial Electronics,2022,69(12):13305-13315.
[90] YUE Honghao,YANG Yifei,LU Yifan,et al.Research progress of space non-pyrotechnic low-shock connection and separation technology (SNLT):A review[J].Chinese Journal of Aeronautics,2022,35(11):113-154.
[91] 崔垚.航天器低冲击分离控制技术研究[D].哈尔滨:哈尔滨工业大学,2013.CUI Yao.Research on control of spacecraft in low-impact separation[D].Harbin:Harbin Institute of Technology,2013.
[92] 李辰,高浩鸿,闫冰,等.一种适用于多种载荷同时抛撒的自解锁推力抛撒装置:中国,202211352239.6[P].2023-03-07.LI Chen,GAO Haohong,YAN Bing,et al.A self-unlocking thrust dispenser suitable for simultaneous dispersal of multiple loads:China,202211352239.6[P].2023-03-07.
[93] 桑希军.小卫星星箭分离系统设计及性能分析[D].长沙:国防科学技术大学,2014.SANG Xijun.The design and performance analysis for separation system of small satellite from rocket[D].Changsha:National University of Defense Technology,2014.
[94] 秦春云,郭凤明,刘建,等.用于运载火箭中级间分离的气动分离系统:中国,202110782651.0[P].2021-11-05.QIN Chunyun,GUO Fengming,LIU Jian,et al.Aerodynamic separation system for stage separation of launch vehicles:China,202110782651.0[P].2021-11-05.
[95] 秦春云,郭凤明,钟友武,等.运载火箭及用于运载火箭子级分离及姿态控制的组合装置:中国,201920328022.9[P].2019-12-27.QIN Chunyun,GUO Fengming,ZHONG Youwu,et al.Launch vehicles and combined devices for separation and attitude control of launch vehicle sub stages:China,201920328022.9[P].2019-12-27.
[96] 于兵,陈岱松,王帅,等.一种兼具连接承载和分离推冲功能的重复使用运载火箭冷气分离系统:中国,201911158286.5[P].2020-04-14.YU Bing,CHEN Daisong,WANG Shuai,et al.A reusable launch vehicle cold air separation system with joint bearing and split thrust function:China,201911158286.5[P].2020-04-14.
[97] 石玉红,郭嘉,王辰,等.一种基于高压气体驱动的推冲分离导向机构:中国,202311578937.2[P].2024-02-20.SHI Yuhong,GUO Jia,WANG Chen,et al.A pusher thrust separation guidance mechanism based on high pressure gas actuation:China,202311578937.2[P].2024-02-20.
[98] CEBRIAN A S,HALTER B U,GERNGROSS T.RUAG's approach to develop a modular low shock separation and jettison system[C]//8th European Conference for Aeronautics and Space Sciences.Munich,Germany:EUCASS,2019:745-757.
[99] TERASHIMA K,KAMITA T,HORIE Y,et al.Development status of low-shock payload separation mechanism for H-IIA launch vehicle[C]//15th European Space Mechanisms and Tribology Symposium.Noordwijk,Netherlands:ESMATS,2013:718-731.
[100] 常志龙,张华,张伟程,等.一种防气压迅速下降的气动推冲装置及系统:中国,202410908615.8[P].2024-11-01.CHANG Zhilong,ZHANG Hua,ZHANG Weicheng,et al.A pneumatic pusher device and system to prevent rapid drop of air pressure:China,202410908615.8[P].2024-11-01.
[101] ONODA J,MORI D.The development of structure and mechanisms for Mu-3SII[J].The Journal of Space Technology and Science,1986,2(1):2_28-2_37.
[102] SMOOT L D.Prediction of interstage pressure in multistage solidpropellant systems[J].American Institute of Aeronautics and Astronautics Journal,1963,1(10):2361-2365.
[103] TONIOLO M,TARTABINI P,PAMADI B,et al.Constraint force equation methodology for modeling multibody stage separation dynamics[C]//46th AIAA Aerospace Sciences Meeting and Exhibit.Reno,Nevada:American Institute of Aeronautics and Astronautics,2008:219.
[104] TARTABINI P V,ROITHMAYR C M,TONIOLO M D,et al.Modeling multibody stage separation dynamics using constraint force equation methodology[J].Journal of Spacecraft and Rockets,2011,48(4):573-583.
[105] CUI Delin,YAN Shaoze,LI Junlan,et al.Dynamic analysis of satellite separation considering the flexibility of interface rings[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2015,229(10):1886-1902.
[106] CUI Delin,ZHAO Jieliang,YAN Shaoze,et al.Analysis of parameter sensitivity on dynamics of satellite separation[J].Acta Astronautica,2015,114:22-33.
[107] PAMADI B N,NEIRYNCK T A,HOTCHKO N J,et al.Simulation and analyses of stage separation two-stage reusable launch vehicles[J].Journal of Spacecraft and Rockets,2007,44(1):66-80.
[108] BURGER B S,ADDONA C,DIEDRICH B,et al.Space launch system liftoff and separation dynamics analysis tool chain[C]//AIAA Scitech 2021 Forum.VIRTUAL EVENT:American Institute of Aeronautics and Astronautics,2021:822-845.
[109] BLELLOCH Dr,ANTAL G.A residual flexibility approach to multibody dynamics[C]//34th Structures,Structural Dynamics and Materials Conference.La Jolla,CA,USA:American Institute of Aeronautics and Astronautics,1993:1543-1551.
[110] 朱春艳,臧旭,张锦,等.新一代火箭卫星整流罩的模态特性分析、试验与模型修正[J].动力学与控制学报,2017,15(6):544-549.ZHU Chunyan,ZANG Xu,ZHANG Jin,et al.Test,analysis and model updating of structural dynamics for satellite fairing of new generation space vehicle[J].Journal of Dynamics and Control,2017,15(6):544-549.
[111] 李哲,范学领,孙秦,等.大型整流罩分离动力学简化建模及仿真分析[J].固体火箭技术,2012,35(5):583-587.LI Zhe,FAN Xueling,SUN Qin,et al.Simplified finite element modeling method and separation dynamics of large scale fairing structure[J].Journal of Solid Rocket Technology,2012,35(5):583-587.
[112] 董寻虎,骆剑.大型柔性整流罩抛罩多体动力学仿真[J].上海航天,2005(5):28-33.DONG Xunhu,LUO Jian.Multibody dynamics simulation of large scale flexible fairing separation[J].Aerospace Shanghai,2005(5):28-33.
[113] RAO B N,JEYAKUMAR D,BISWAS K K,et al.Rigid body separation dynamics for space launch vehicles[J].The Aeronautical Journal,2006,110(1107):289-302.
[114] DALLE D J,ROGERS S E.Output-based adaptive meshing applied to space launch system booster separation analysis[C]//33rd AIAA Applied Aerodynamics Conference.Dallas,TX:American Institute of Aeronautics and Astronautics,2015:3152-3178.
[115] DALLE D J,ROGERS S E,LEE H C,et al.Inviscid and viscous CFD Analysis of booster separation for the space launch system vehicle[C]//54th AIAA Aerospace Sciences Meeting.San Diego,California,USA:American Institute of Aeronautics and Astronautics,2016:797-825.
[116] MEEROFF J G,DALLE D J,ROGERS S E,et al.Advances in space launch system booster separation computational fluid dynamics[J].Journal of Spacecraft and Rockets,2024,61(4):962-974.
[117] MOELYADI M A,BREITSAMTER C,LASCHKA B.Stage-separation aerodynamics of two-stage space transport systems part 2:Unsteady simulation[J].Journal of Spacecraft and Rockets,2008,45(6):1240-1250.
[118] KOCH J R,DUMLUPINAR E,HOUSMAN J A,et al.CFD analysis of space launch system solid rocket booster separation within the langley unitary plan wind tunnel[C]//AIAA AVIATION 2021 FORUM.VIRTUAL EVENT:American Institute of Aeronautics and Astronautics,2021:2966-3009.
[119] ZHANG Sijun,ZHAO Xiang.Computational studies of stage separation with an unstructured chimera grid method[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Cincinnati,OH:American Institute of Aeronautics and Astronautics,2007:5409-5420.
[120] LOCHAN R,ADIMURTHY V,KUMAR K.Separation dynamics of strap-on boosters in the atmosphere[J].Journal of Guidance,Control,and Dynamics,1997,20(4):633-639.
[121] 林三春,王欣,落龑寿,等.弹性整流罩低空分离仿真及影响因素分析[J].导弹与航天运载技术,2016(6):6-9.LIN Sanchun,WANG Xin,LUO Yanshou,et al.Elastic fairing separation simulation and influence factors analysis at low altitude[J].Missiles and Space Vehicles,2016(6):6-9.
[122] LONGREN D R.Stage separation dynamics of spin-stabilized rockets[J].Journal of Spacecraft and Rockets,1970,7(4):434-439.
[123] JEYAKUMAR D,RAO B N.Dynamics of satellite separation system[J].Journal of Sound and Vibration,2006,297(1-2):444-455.
[124] MIRZAEI M,NAJAFIE NIA B,SHADARAM A.Numerical simulation of stage separation manoeuvre with jet interaction[J].Aircraft Engineering and Aerospace Technology,2006,78(3):217-225.
[125] 刘昕,林敬周,张长丰.运载火箭级间分离气动特性数值模拟研究[C]//第14届中国系统仿真技术及其应用学术年会,2012:155-159.LIU Xin,LIN Jingzhou,ZHANG Changfeng.Direct numerical simulation on aerodynamic characteristics of rocket stage-separation flow[C]//Proceedings of 14th Chinese Conference on System Simulation Technology & Application,2012:155-159.
[126] 张海瑞,范晶晶,张为华.运载火箭芯级与助推级分离的数值模拟[J].国防科技大学学报,2014,36(2):7-12.ZHANG Hairui,FAN Jingjing,ZHANG Weihua.Numerical simulation of separation of central stage and booster stage for a carrier rocket[J].Journal of National University of Defense Technology,2014,36(2):7-12.
[127] WANG J C T.Coupled CFD and rigid body dynamics analysis for the launch vehicle stage separation[C]//33rd Joint Propulsion Conference and Exhibit.Seattle,WA,U.S.A.:American Institute of Aeronautics and Astronautics,1997:2944-2955.
[128] 程修妍,范博超,荣吉利,等.柔性整流罩地面展开试验仿真分析与飞行状态分离预测[J].兵工学报,2018,39(3):608-617.CHENG Xiuyan,FAN Bochao,RONG Jili,et al.Simulation and analysis on the ground separation test of a flexible fairing and its flying mode prediction[J].Acta Armamentarii,2018,39(3):608-617.
[129] 李易.固体运载火箭级间热分离仿真气体模型研究[J].宇航总体技术,2021,5(2):31-38.LI Yi.Gas modeling of a solid rocket motor for the simulation of hot stage separation[J],Astronautical Systems Engineering Technology,2021,5(2):31-38.
[130] LI Yi,EGGERS T,REIMANN B.A dynamics study for the hot stage separation of a multistage rocket with a coupled CFD flight mechanics approach[C]//18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference.Tours,France:American Institute of Aeronautics and Astronautics,2012:5820-5829.
[131] LI Yi,REIMANN B,EGGERS T.Coupled simulation of CFD-flight-mechanics with a two-species-gas-model for the hot rocket staging[J].Acta Astronautica,2016,128:44-61.
[132] CHOI S,KIM C,RHO O H,et al.Numerical analysis on separation dynamics of strap-on boosters in the atmosphere[J].Journal of Spacecraft and Rockets,2002,39(3):439-446.
[133] SU M W,MULLEN C R.Plume impingement force during tandem stage separation at high altitudes[J].Journal of Spacecraft and Rockets,1972,9(9):715-717.
[134] KUMAR P,SWAMINATHAN R,UNNIKRISHNAN C,et al.Modelling of jet impingement forces during hot stage-separation of a launch vehicle[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Cleveland,OH,U.S.A.:American Institute of Aeronautics and Astronautics,1998:3156-3168.
[135] ERAMYA A,CLINE J,BRAUNSTEIN M,et al.Transient modeling of high-altitude rocket-stage separation[J].Journal of Spacecraft and Rockets,2008,45(4):698-705.
[136] IWASA T,SHI Q,ANDO S,et al.Simplified SRS prediction method for pyroshock source of V-band clamp separation devices[C]//48th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference.Honolulu,Hawaii:American Institute of Aeronautics and Astronautics,2007:2020-2032.
[137] TAKEUCHI S,ONODA J.Estimation of separation shock of the marman clamp system by using a simple band-mass model[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2002,45(147):53-60.
[138] 武新峰,刘观日,雷勇军,等.基于LS-DYNA的包带式星箭连接装置分离过程和冲击响应分析[J].振动与冲击,2013,32(24):174-179.WU Xinfeng,LIU Guanri,LEI Yongjun,et al.Separation process and shock response analysis of clamp band systems based on LS-DYNA[J].Journal of Vibration and Shock,2013,32(24):174-179.
[139] 谭雪峰,阎绍泽.星箭分离面径向冲击预示的简化圆环分析方法[J].机械工程学报,2010,46(16):95-100.TAN Xuefeng,YAN Shaoze.Simplified analytical method of radial shock response of satellite-rocket separation interface[J].Journal of Mechanical Engineering,2010,46(16):95-100.
[140] 唐霄汉,李彬,李刚,等.基于动态本构模型的整流罩铰链系统自冲击分析[J].计算力学学报,2017,34(4):403-410.TANG Xiaohan,LI Bin,LI Gang,et al.Self-impact analysis of the fairing hinge system based on dynamic constitutive models[J].Chinese Journal of Computational Mechanics,2017,34(4):403-410.
[141] OH C S,SUN B C,PARK Y K,et al.Stage separation analysis of launch vehicle using monte carlo simulation[J].Journal of the Korean Society for Aeronautical & Space Sciences,2015,43(4):341-348.
[142] ROSHANIAN J,TALEBI M.Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle[J].Applied Mathematics and Mechanics,2008,29(11):1411-1426.
[143] SINGARAVELU J,JEYAKUMAR D,NAGESWARA RAO B.Taguchi's approach for reliability and safety assessments in the stage separation process of a multistage launch vehicle[J].Reliability Engineering & System Safety,2009,94(10):1526-1541.
[144] JEYAKUMAR D,BISWAS K K,NAGESWARA^RAO B.Stage separation dynamic analysis of upper stage of a multistage launch vehicle using retro rockets[J].Mathematical and Computer Modelling,2005,41(8-9):849-866.
[145] SHIEH T H,LIOU T M,LI M R,et al.Analysis on numerical results for stage separation with different exhaust holes[J].International Communications in Heat and Mass Transfer,2009,36(4):342-345.
[146] 高立华,张兵,权晓波,等.火箭级间热分离过程耦合数值模拟[J].清华大学学报(自然科学版),2011,51(4):462-466.GAO Lihua,ZHANG Bing,QUAN Xiaobo,et al.Coupled numerical simulation of the multi stage rocket stage separation[J].Journal of Tsinghua University (Science and Technology),2011,51(4):462-466.
[147] LOCHAN R,ADIMURTHY V,KUMAR K.Separation dynamics of heat shield fairings[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,1997,211(2):67-80.
[148] 王博哲,吴竞峰,桑希军,等.基于Adams的某整流罩分离影响因素仿真分析[J].弹箭与制导学报,2013,33(2):137-140.WANG Bozhe,WU Jingfeng,SANG Xijun,et al.Simulation and analysis of influence factors of fairing separation by ADMAS[J].Journal of Projectiles,Rockets,Missiles and Guidance,2013,33(2):137-140.
[149] 李刚,李彬,郝鹏,等.弹簧组件对大型弹性整流罩分离动力学的影响[J].固体火箭技术,2015,38(3):326-331.LI Gang,LI Bin,HAO Peng,et al.Effects of spring component on the separation dynamics of a large-scale elastic payload fairing[J].Journal of Solid Rocket Technology,2015,38(3):326-331.
[150] 于兵,相升海,闫利伟,等.火工分离推杆分离特性研究[J].兵器装备工程学报,2020,41(12):57-62.YU Bing,XIANG Shenghai,YAN Liwei,et al.Study on separation characteristics of pyrotechnic separation pushing rod[J].Journal of Ordnance Equipment Engineering,2020,41(12):57-62.
[151] 陈韬,郭龙飞,赵振,等.低冲分离装置引导阶段动力学建模与实验研究[J].宇航总体技术,2017, 1(3):44-53.CHEN Tao,GUO Longfei,ZHAO zhen,et al.Dynamical model and experimental study of low-shock separation device[J].Astronautical Systems Engineering Technology,2017,1(3):44-53.
[152] HWANG D H,LEE J,HAN J H,et al.Mathematical model for the separation behavior of low-shock separation bolts[J].Journal of Spacecraft and Rockets,2018,55(5):1208-1221.
[153] HU Xingzhi,CHEN Xiaoqian,TUO Zhouhui,et al.Dynamics and transient perturbation analysis of satellite separation systems[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2013,227(12):1968-1976.
[154] HU Xingzhi,CHEN Xiaoqian,ZHAO Yong,et al.Optimization design of satellite separation systems based on multi-ssland genetic algorithm[J].Advances in Space Research,2014,53(5):870-876.
[155] ZHAO Hongda,LIU Wei,DING Jifeng,et al.Numerical study on separation shock characteristics of pyrotechnic separation nuts[J].Acta Astronautica,2018,151:893-903.
[156] 张玉良.SMA驱动的空间高承载低冲击连接分离装置关键技术研究[D].哈尔滨:哈尔滨工业大学,2021.ZHANG Yuliang.Design and key characteristics of space high-load & low-impact non-pyrotechnic separation device[D].Harbin:Harbin Institute of Technology,2021.
[157] 张孟轲,关世玺,王讯,等.一种新型热刀式解锁分离机构分离安全性分析[J].机械设计与制造工程,2023,52(9):12-16.ZHANG Mengke,GUAN Shixi,WANG xun,et al.Separation safety analysis of a new hot knife type unlocking separation mechanism[J].Machine Design and Manufacturing Engineering,2023,52(9):12-16.
[158] 李勇,张策,申允德.大推程航天电连接器电磁分离机构的研究[J].电工技术学报,2015,30(5):128-134.LI Yong,ZHANG Ce,SHEN Yunde.The research on the electromagnetic separable mechanism for aerospace electric connector with large extending stroke[J].Transactions of China Electrotechnical Society,2015,30(5):128-134.
[159] 明爱珍,杨毅强,张延瑞,等.运载火箭非火工冷气推冲分离系统[J].中国航天,2022(11):20-24.MING Aizhen,YANG Yiqiang,ZHANG Yanrui,et al.Launch vehicle non pyrotechnic cold gas push-pull separation system[J].Aerospace China,2022(11):20-24.
[160] 黎忠,杜群贵.级间气动推冲分离系统动态建模与仿真[J].机床与液压,2024,52(18):129-135.LI Zhong,DU Qungui.Dynamic modeling and simulation of stages pneumatic thrust separation system[J].Machine Tool & Hydraulics,2024,52(18):129-135.