运载火箭机构动力学分析方法综述

doi:10.3901/JME.260003

摘要/Abstract

摘要： 近年来，运载火箭正向重型运载、可重复使用、多功能模块化、高可靠性、商业化发射等方向发展，对运载火箭上执行特定功能的各类机构提出更高要求，亟需发展更加精确的运载火箭机构动力学分析方法。为全面梳理运载火箭机构动力学分析方法的发展现状，从运载火箭机构动力学分析的特点出发，系统介绍运载火箭机构动力学分析中普遍使用的四类基础理论，详细介绍连接分离机构、着陆缓冲机构和气动控制机构三类运载火箭典型机构的动力学分析方法，最后对运载火箭机构动力学分析方法的未来研究工作进行展望。

关键词: 运载火箭, 机构, 动力学分析, 连接分离机构, 着陆缓冲机构, 气动控制机构

Abstract: In recent years, launch vehicles is progressing in a number of directions, including the capacity to carry heavy loads, the ability to be reused, multifunctional modularity, high reliability, and commercial launch. This trend imposes higher demands on various mechanisms performing specific functions within launch vehicles, necessitating the development of more precise launch vehicle mechanisms dynamics analysis methods. To comprehensively review the current state of launch vehicle mechanisms dynamics analysis methods, this research systematically introduces four fundamental theories widely used in this field, starting from the characteristics of launch vehicle mechanism dynamics analysis. It details the dynamics analysis methods for three typical launch vehicle mechanisms: connection and separation mechanism, the landing cushioning mechanism and the aerodynamic control mechanism. Finally, it gives an outlook on the future research directions for launch vehicle mechanisms dynamics analysis methods.

Key words: launch vehicle, mechanism, dynamical analysis, connection and separation mechanism, landing cushioning mechanism, aerodynamic control mechanism

中图分类号:

V421

林撼昕, 刘才山. 运载火箭机构动力学分析方法综述[J]. 机械工程学报, 2026, 62(1): 41-58.

LIN Hanxin, LIU Caishan. Review of Dynamical Analysis Methods for Launch Vehicle Mechanisms[J]. Journal of Mechanical Engineering, 2026, 62(1): 41-58.

参考文献

[1] 张卫东.运载火箭动力学与控制[M].北京:中国宇航出版社,2015.ZHANG Weidong.Launch vehicle dynamics and controls[M].Beijing:China Astronautic Publishing House,2015.
[2] 李东,李平岐.长征五号火箭技术突破与中国运载火箭未来发展[J].航空学报,2022,43(10):168-179.LI Dong,LI Pingqi.Technological breakthroughs of LM-5 and future developments of China's launch vehicle[J].Acta Aeronautica et Astronautica Sinica,2022,43(10):168-179.
[3] 李志洪,彭小波,谢红军,等.可重复使用商业运载火箭的发展与展望[J].中国航天,2022(7):27-33.LI Zhihong,PENG Xiaobo,XIE Hongjun,et al.Development and prospect of reusable commercial launch vehicles[J].Aerospace China,2022(7):27-33.
[4] 包为民.可重复使用运载火箭技术发展综述[J].航空学报,2023,44(23):629555.BAO Weimin.A review of reusable launch vehicle technology development[J].Acta Aeronautica ET Astronautica Sinica,2023,44(23):629555.
[5] 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.Space vehicle mechanism technology development and outlook[J].Aerospace China,2023(10):9-17.
[6] 张宏剑,于兵,吴会强,等.运载火箭机构技术发展研究[J].导弹与航天运载技术(中英文),2023(6):1-9.ZHANG Hongjian,YU Bing,WU Huiqiang,et al.Research on technology development of launch vehicle mechanism[J].Missiles and Space Vehicles,2023(6):1-9.
[7] 郭嘉,于兵,马红鹏,等.超重-星舰运输系统机构技术分析[J].导弹与航天运载技术(中英文),2024(3):29-37.GUO Jia,YU Bing,MA Hongpeng,et al.Analysis of super heavy-starship transport system mechanism[J].Missiles and Space Vehicles,2024(3):29-37.
[8] 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.
[9] 石玉红,张宏剑,季宝锋,等.运载火箭多体系统动力学发展及应用[J].导弹与航天运载技术,2017(5):13-16.SHI Yuhong,ZHANG Hongjian,JI Baofeng,et al.Development and application of multibody system dynamics in launch vehicle[J].Missiles and Space Vehicles,2017(5):13-16.
[10] SOMANATH S,KRISHNAN V,FRANCIS E.Dynamics simulation of pyro actuated "ball lock" separation system for micro-satellites to evaluate release shock[C]//9th European Space Mechanisms and Tribology Symposium,Noordwijk:ESA Publications Division,2001:199-206.
[11] LIN J,WANG X,LIU C.Modeling and experimental study on dynamics of a gas-driven split nut device[J].Multibody System Dynamics,2023,58(3):365-395.
[12] 孙加亮,田强,胡海岩.多柔体系统动力学建模与优化研究进展[J].力学学报,2019,51(6):1565-1586.SUN Jialiang,TIAN Qiang,HU Haiyan.Advances in dynamic modeling and optimization of flexible multibody systems[J].Chinese Journal of Theoretical and Applied Mechanics,2019,51(6):1565-1586.
[13] LI H,XU W,ZHAO Y,et al.Dynamics modeling and analysis of a vertical landing mechanism for reusable launch vehicle[J].Aerospace,2025,12(4):280.
[14] CIARLET P,LUNÉVILLE E.The finite element method:from theory to practice[M].New York:John Wiley & Sons,2023.
[15] 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.
[16] KHULIEF Y.Modeling of impact in multibody systems:An overview[J].Journal of Computational and Nonlinear Dynamics,2013,8(2):021012.
[17] 姚文莉,岳嵘.有争议的碰撞恢复系数研究进展[J].振动与冲击,2015,34(19):43-48.YAO Wenli,YUE Rong.Advance in controversial restitution coefficient study for impact problems[J].Journal of Vibration and Shock,2015,34(19):43-48.
[18] 王庚祥,马道林,刘洋,等.多体系统碰撞动力学中接触力模型的研究进展[J].力学学报,2022,54(12):3239-3266.WANG Gengxiang,MA Daolin,LIU Yang,et al.Research progress of contact force models in the collision mechanics of multibody system[J].Chinese Journal of Theoretical and Applied Mechanics,2022,54(12):3239-3266.
[19] WANG Y,YU H,XIE J,et al.The impact modeling and experimental verification of a launch vehicle with crushing-type landing gear[J].Actuators,2023,12(8):307.
[20] HERTZ H.Ueber die Berührung fester elastischer Körper[J].Journal Für Reine und Angewandte Mathematik,1882(92):156-171.HERTZ H.On the contact of elastic solids[J].Journal Für Reine und Angewandte Mathematik,1882(92):156-171.
[21] MACHADO M,MOREIRA P,FLORES P,et al.Compliant contact force models in multibody dynamics:Evolution of the hertz contact theory[J].Mechanism and Machine Theory,2012,53:99-121.
[22] HUNT K H,CROSSLEY F R E.Coefficient of restitution interpreted as damping in vibroimpact[J].Journal of Applied Mechanics,1975,42(2):440-445.
[23] FLORES P,AMBRÓSIO J,LANKARANI H M.Contact-impact events with friction in multibody dynamics:Back to basics[J].Mechanism and Machine Theory,2023,184:105305.
[24] 赵相禹.面向批产的高分辨立方星一体化设计及试验验证[D].北京:中国科学院大学,2023.ZHAO Xiangyu.Research on integrated design and test of high-resolution cubesat for batch production[D].Beijing:University of Chinese Academy of Sciences,2023.
[25] COULOMB C A.Théorie des machines simples en égard au frottement de leurs parties,et à la roideur de leurs cordages[M].Paris:Académie Royale des Sciences,1785.COULOMB C A.Theory of simple machines,having regard to the friction of their parts and the stiffness of their linkages[M].Paris:Académie Royale des Sciences,1785.
[26] STRIBECK R.Die wesentlichen eigenschaften der gleit-und rollenlager[J].Zeitschrift des Vereins Deutsc-her Ingenieure,1902,46(38-39):1342-1348,1432-1437.STRIBECK R.The key qualities of sliding and roller bearings[J].Zeitschrift des Vereins Deutsc-her Ingenieure,1902,46(38-39):1342-1348,1432-1437.
[27] THRELFALL D C.The inclusion of coulomb friction in mechanisms programs with particular reference to DRAM au programme DRAM[J].Mechanism and Machine Theory,1978,13(4):475-483.
[28] 李东旭.航天飞行器分离动力学[M].北京:科学出版社,2013.LI Dongxu.Spacecraft separation dynamics[M].Beijing:Science Press,2013.
[29] NIU L,TU H,DONG H,et al.Separation reliability analysis for the low-shock separation nut with mechanism motion failure mode[J].Aerospace,2022,9(3):156.
[30] SHI T,LIU C,ZHAO Z,et al.Rigid-flexible coupling dynamics of a threaded reusable low-shock spacecraft separation device[J].Nonlinear Dynamics,2025,113:4999-5021.
[31] 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.
[32] 王昊东,杨臻,武国梁.基于ADAMS的卫星对接机构球锁装置动力学分析[J].兵器装备工程学报,2019,40(10):45-49.WANG Haodong,YANG Zhen,WU Guoling.Dynamic analysis of ball locking device of satellite docking mechanism based on ADAMS[J].Journal of Ordnance Equipment Engineering,2019,40(10):45-49.
[33] 孙泽阳,刘宝龙,吴新跃.电驱钢球锁紧机构的试验研究及设计优化[J].导弹与航天运载技术,2017(3):84-86.SUN Zeyang,LIU Baolong,WU Xinyue.Experimental research and design optimization on electromotive steel-ball locking device[J].Missiles and Space Vehicles,2017(3):84-86.
[34] 张威,刘群,任法璞,等.某拔销器工作过程仿真分析及优化设计[J].航天返回与遥感,2021,42(3):62-71.ZHANG Wei,LIU Qun,REN Fapu,et al.Simulation analysis and optimization design of a pin puller[J].Spacecraft Recovery & Remote Sensing,2021,42(3):62-71.
[35] LI S,CHEN G,WANG D,et al.Rational design of pin puller and its closed bomb test-based equivalent testing[J].AIP Advances,2022,12:025124.
[36] WANG J,XIONG S,WEN Y,et al.Numerical simulation of actuation processes and decoupling pyroshock of a pressure cartridge-type pin puller[J].Journal of Low Frequency Noise,Vibration Active Control,2023,42(3):1363-1378.
[37] 李朋,尹娟妮,张佼龙,等.立方星SMA直线作动解锁机构的优化设计[J].西北工业大学学报,2023,41(3):510-517.LI Peng,YIN Juanni,ZHANG Jiaolong,et al.Optimal design of SMA linear actuation unlocking mechanism for CubeSat[J].Journal of Northwestern Polytechnical University,2023,41(3):510-517.
[38] 张婕,武鹏飞,王亚坤,等.国外星箭连接解锁装置技术与应用研究[J].航天器工程,2023,32(2):125-134.ZHANG Jie,WU Pengfei,WANG Yakun,et al.Technology and application research of foreign satellite-launching-vehicle connection and unlocking devices[J].Spacecraft Engineering,2023,32(2):125-134.
[39] KAYACıK E.The analytical and experimental investigation of force generation on V profile clamp[D].Istanbul:Istanbul Technical University,2015.
[40] LM-3A series launch vehicle user's manual[M].Beijing:China Academy of Launch Vehicle Technology,2011.
[41] 秦朝烨,褚福磊,阎绍泽.包带式星箭连接结构轴向刚度研究[J].宇航学报,2009,30(5):2080-2085.QIN Zhaoye,CHU Fulei,YAN Shaoze.Axial stiffness analysis of clamp band system[J].Journal of Astronautics,2009,30(5):2080-2085.
[42] 唐乾刚,孙世贤.包带式星箭紧锁预紧力分析[J].国防科技大学学报,1996(2):20-25.TANG Qiangang,SUN Shixian.An analysis of preforce in the locking device of the satellite and launching vehicle with wrapband[J].Journal of National University of Defense Technology,1996(2):20-25.
[43] QIN Z,YAN S,CHU F.Improved formulation for predicting the load capacity of marman clamps[J].Journal of Spacecraft and Rockets,2017,54(2):395-402.
[44] 郭欣.运载火箭刚性包带连接装置力学特性分析与优化[D].长沙:国防科技大学,2019.GUO Xin.Mechanical characteristics analysis and optimization of rigid clamp band connection device for launch vehicle[D].Changsha:National University of Defense Technology,2019.
[45] Marman clamp system design guidelines[M].Greenbelt:NASA Goddard Space Flight Center(GSFC),2000.
[46] ROME J,GOYAL V,MARTINO N.Techniques for finite element analysis of clamp band systems[C]//50th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference.New York:AIAA,2009:2353.
[47] DAVAR A,AZARAFZA R,MOUSAVI S S.Uncertainty analysis and reliability estimation of clamp band joints[J].Materials Science and Technology,2020,36(13):1487-1502.
[48] QIN Z,YAN S,CHU F.Dynamic analysis of clamp band joint system subjected to axial vibration[J].Journal of Sound and Vibration,2010,329(21):4486-4500.
[49] IWASA T,SHI Q,ANDO S,et al.Simplified SRS prediction method for pyroshock source of V-band cl-amp separation devices[C]//48th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Mate-rials Conference.New York:AIAA,2007:2020.
[50] 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.
[51] LI J L,YAN S Z,TAN X F.Modeling and simulation of clamp band dynamic envelope in a LV/SC separation system[J].Applied Mechanics and Materials,2012,141:359-363.
[52] 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.
[53] LONG X,ZHAO Z,YANG Z,et al.Measurement and analysis of single video camera-system in clamp-band unlocking test[C]//2nd International Conference on Artificial Intelligence and Computer Engineering (ICAICE),New York:IEEE,2021:745-748.
[54] LIDDLE J D,HOLT A P,JASON S J,et al.Space science with CubeSats and nanosatellites[J].Nature Astronomy,2020,4(11):1026-1030.
[55] BOMANI B M.CubeSat technology past and present:Current state-of-the-art survey[R].Cleveland:NASA Glenn Research Center,2021.
[56] 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 Jiaqian.Design and implementation of cubesat and launch vehicle separation device[J].Missiles and Space Vehicles,2015(5):20-24.
[57] KRISHNAPPA C,AROGBONLO A,D'SOUZA J M,et al.Design and development of a deployment system for small satellites (1U-4U)[J].IEEE Aerospace and Electronic Systems Magazine,2025,40(5):6-27.
[58] LIM Q,HELMICH J,LEMBECK M F,et al.Design and development of a dual-use satellite deployer[C]//38th Annual Small Satellite Conference,Logan:Utah State University,2024:SSC24-WP1-33.
[59] CHAU V M,VO H B.Structural dynamics analysis of 3-U CubeSat[J].Applied Mechanics and Materials,2019,894:164-170.
[60] ALHAMMADI A,AL-SHAIBAH M,ALMESMARI A,et al.Quasi-static and dynamic response of a 1U nano-satellite during launching[C]//8th European Conference for Aeronautics and Space Sciences (EUCASS),Bruxelles:EUCASS Association,2019:398.
[61] 张佼龙,周军.立方星星箭分离机构运动系统的设计与验证[J].光学精密工程,2017,25(4):387-395.ZHANG Jiaolong,ZHOU Jun.Design and verification of kinematic system in deploying mechanism for CubeSats[J].Optics and Precision Engineering,2017,25(4):387-395.
[62] XU Y,XUE G,LUO Y,et al.Design and verification of CubeSat deployer with the dual redundancy electromagnetic open door mechanism[C]//Journal of Physics:Conference Series,London:IOP Publishing,2024:2691.
[63] YUDINTSEV V.CubeSat separation dynamics[C]//II Latin American IAA CubeSat WorkShop,Paris:International Academy of Astronautics,2016.
[64] GUO J,ZHANG J,YUE C,et al.Modeling of the CubeSat deployment and initial separation angular velocity estimation[J].Aerospace Science and Technology,2019,95:105477.
[65] 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.
[66] MA H,ZHAO S,JIAO Z.Study of a hydro-pneumatic buffer with a variable damper for launch vehicle landing legs[C]//8th European Conference for Aeronautics and Space Sciences (EUCASS),Bruxelles:EUCASS Association,2019:183.
[67] 王佳南,丁沛,黄强.可重复使用火箭着陆回收机构的试验验证技术[J].中国航天,2023(10):25-33.WANG Jianan,DING Pei,HUANG Qiang.Experimental validation technology for reusable rocket landing and recovery mechanisms[J].Aerospace China,2023(10):25-33.
[68] 胡鹏翔,王檑,徐珊姝,等.垂直回收火箭可伸缩着陆腿展开的动力学仿真分析[J].宇航总体技术,2022,6(6):15-22.HU Pengxiang,WANG Lei,XU Shanshu,et al.Dynamic simulation and analysis of the deploying process of telescopic landing legs for vertically-recovered rockets[J].Astronautical Systems Engineering Technology,2022,6(6):15-22.
[69] RICKMERS P,DUMONT E,KRUMMEN S,et al.The CALLISTO and ReFEx flight experiments at DLR-Challenges and opportunities of a wholistic approach[J].Acta Astronautica,2024,225:417-433.
[70] WANG C,CHEN J,JIA S,et al.Parameterized design and dynamic analysis of a reusable launch vehicle landing system with semi-active control[J].Symmetry,2020,12(9):1572.
[71] HUANG M.Control strategy of launch vehicle and lander with adaptive landing gear for sloped landing[J].Acta Astronautica,2019,161:509-523.
[72] 王辰,袁文全,郭岳,等.重复使用火箭栅格舵传动机构动态特性实验研究[J].北京大学学报(自然科学版),2018,54(6):1137-1146.WANG Chen,YUAN Wenquan,GUO Yue,et al.Experimental study of kinetic characteristics for gid fin transmission mechanism of reusable launch vehicles[J].Acta Scientiarum Naturalium Universitatis Pekinensis,2018,54(6):1137-1146.
[73] 杨添元,李东光,张骢,等.一种修正引信栅格舵片的展开过程研究[J].弹箭与制导学报,2019,39(4):22-24.YANG Tianyuan,LI Dongguang,ZHANG Cong,et al.Research on theunfolding process of the grid fins of a trajectory correction fuze[J].Journal of Projectiles,Missiles and Guidance,2019,39(4):22-24.
[74] 林三春,阎军,潘旭,等.无阻尼杆式栅格翼展开动力学特性分析方法[J].导弹与航天运载技术,2018(5):16-20.LIN Sanchun,YAN Jun,PAN Xu,et al.Analysis method of unfolding dynamic characteristics of non-damping rod type grid fins[J].Missiles and Space Vehicles,2018(5):16-20.
[75] KRAMMER A,BLECHA L,LICHTENBERGER M.Fin actuation,thrust vector control and landing leg mechanisms design for the RETALT VTVL launcher[J].CEAS Space Journal,2022,14(3):577-591.
[76] CHARBONNIER D,VOS J,MARWEGE A,et al.Computational fluid dynamics investigations of aerodynamic control surfaces of a vertical landing configuration[J].CEAS Space Journal,2022,14(3):517-532.
[77] DINH V S,DINH C T,PHAM V S.Numerical study on aerodynamic characteristics of the grid fins with different grid patterns[J].Physics of Fluids,2023,35(12):3107-3121.
[78] 李永红,黄勇,陈建中,等.曲面形栅格翼气动特性研究[J].空气动力学学报,2016,34(4):536-540.LI Yonghong,HUANG Yong,CHEN Jianzhong,et al.Investigation of aerodynamic characteristics on circular-arc grid-fin configurations[J].Acta Aerodynamica Sinica,2016,34(4):536-540.
[79] 魏忠武,秦永明,杨学军,等.栅格翼大缩比模型超声速风洞试验方法研究[J].空气动力学学报,2017,35(3):392-398.WEI Zhongwu,QIN Yongming,YANG Xuejun,et al.Investigation of grid fins on large-scale model test in supersonic wind tunnel[J].Acta Aerodynamica Sinica,2017,35(3):392-398.
[80] LIU X.Fuel-optimal rocket landing with aerodynamic controls[J].Journal of Guidance,Control and Dynamics,2019,42(1):65-77.
[81] VILLAR J L H,ALDANA C,MONCADA W,et al.Sliding mode controller for re-entry dynamics of spacecraft reusable type Starship[C]//202410th International Conference on Control,Decision and Information Technologies (CoDIT),New York:IEEE,2024:706-711.
[82] 许晨舟,杜涛,韩忠华,等.机器学习数据融合方法在火箭子级栅格舵气动特性建模应用中的比较研究[J].实验流体力学,2022,36(3):79-92.XU Chenzhou,DU Tao,HAN Zhonghua,et al.Comparison of machine learning data fusion methods applied to aerodynamic modeling of rocket first stage with grid fins[J].Journal of Experiments in Fluid Mechanics,2022,36(3):79-92.