某远程多管火箭发射车发射动力学仿真
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摘要
随着世界军事技术的飞速发展,多管火箭武器系统被赋予了更多的作战使命,全新的作战任务要求发射车具有更高的射击精度和更好的机动性能。论文以某多管火箭武器系统发射车为研究对象,以发射动力学理论为基础,运用虚拟样机软件建立了发射车的多刚体动力学模型,研究了发射顺序、发射间隔,并取得了很好的效果。本文所做主要工作如下:
①以实体模型为基础,在充分理解发射系统结构原理的基础上,基于合理的简化和假设,运用多刚体动力学理论和虚拟样机技术建立了发射车的多刚体动力学模型。
②运用建立的多刚体虚拟样机模型进行了单发发射稳定性计算分析,通过仿真结果数据与工程算法数据及试验结果的对比验证动该虚拟样机模型正确性和仿真结果的有效性。
③根据系统的结构特点和“先上后下、左右交替”的射序编制原则,拟出了可能的典型发射顺序,并通过动力学仿真,对比分析了所编制射序工况下火箭弹的初始扰动,为确定合理的发射顺序提供了理论依据。
④研究该发射车整个模型的发射过程,根据贮运发射箱端口的振动衰减特性确定出合适的发射间隔,以减小后一发火箭弹发射时的起始扰动。
论文建立了发射车的动力学发射模型,通过动力学分析表明,射序越接近中心对称射击效果越好,不等间隔发射更有利于减小初始扰动,并有效地缩短发射时间,提高打击密度。所做的工作对发射车总体方案设计和武器系统设计有重要的参考意义。
With the rapid development of military technology in the world, the multiple launch rocket system (hereafter called MLRS for shot) is endowed with more new missions, and the bran-new campaign task requires higher firing accuracy and better maneuverability for rocket. On the basis of theory of firing dynamics, this article mainly make research on MLRS, establish multiple rigid body dynamics model of launch vehicle of MLRS by using virtual prototype software, research launch sequence and interval, and get approving purpose. The main research works in this article are as follows:
a. On the basis of entity model, with thorough understanding of structural principle of launching system and logical predigestion and hypothesis, to establish multiple rigid body dynamics model of MLRS by using theory of multiple rigid body dynamics and virtual prototype technology.
b. Make calculation and analysis of single firing stability with the established virtual prototype model, compare the simulating result data with the engineering arithmetic data and test result to verify the correctness of this virtual prototype and validity of simulating result.
c. To study out possible typical launching sequence according to the structural characteristics of system and the establishing principle of launching sequence of“lower tube comes after upper tube, left and right tube by turns”, and analyze initial disturbance of rocket under established launching sequence through dynamics simulating comparison so as to provide reasonable basis for determining reasonable launching sequence.
d. To research launching process of MLRS model, and determine proper firing interval as per vibrating and attenuating characteristics of port of storage-transport-launch box so as to reduce initiative of next rocket in firing.
This article establishes the dynamics launching model of launch vehicle, the dynamics analysis show that the more symmetrical and closer to center the launching sequence, the better the launching effect, and the more benefit to reduce initiative disturbance the inequi-interval launching. These work have helpful reference to overall conceptual design of MLRS.
①以实体模型为基础,在充分理解发射系统结构原理的基础上,基于合理的简化和假设,运用多刚体动力学理论和虚拟样机技术建立了发射车的多刚体动力学模型。
②运用建立的多刚体虚拟样机模型进行了单发发射稳定性计算分析,通过仿真结果数据与工程算法数据及试验结果的对比验证动该虚拟样机模型正确性和仿真结果的有效性。
③根据系统的结构特点和“先上后下、左右交替”的射序编制原则,拟出了可能的典型发射顺序,并通过动力学仿真,对比分析了所编制射序工况下火箭弹的初始扰动,为确定合理的发射顺序提供了理论依据。
④研究该发射车整个模型的发射过程,根据贮运发射箱端口的振动衰减特性确定出合适的发射间隔,以减小后一发火箭弹发射时的起始扰动。
论文建立了发射车的动力学发射模型,通过动力学分析表明,射序越接近中心对称射击效果越好,不等间隔发射更有利于减小初始扰动,并有效地缩短发射时间,提高打击密度。所做的工作对发射车总体方案设计和武器系统设计有重要的参考意义。
With the rapid development of military technology in the world, the multiple launch rocket system (hereafter called MLRS for shot) is endowed with more new missions, and the bran-new campaign task requires higher firing accuracy and better maneuverability for rocket. On the basis of theory of firing dynamics, this article mainly make research on MLRS, establish multiple rigid body dynamics model of launch vehicle of MLRS by using virtual prototype software, research launch sequence and interval, and get approving purpose. The main research works in this article are as follows:
a. On the basis of entity model, with thorough understanding of structural principle of launching system and logical predigestion and hypothesis, to establish multiple rigid body dynamics model of MLRS by using theory of multiple rigid body dynamics and virtual prototype technology.
b. Make calculation and analysis of single firing stability with the established virtual prototype model, compare the simulating result data with the engineering arithmetic data and test result to verify the correctness of this virtual prototype and validity of simulating result.
c. To study out possible typical launching sequence according to the structural characteristics of system and the establishing principle of launching sequence of“lower tube comes after upper tube, left and right tube by turns”, and analyze initial disturbance of rocket under established launching sequence through dynamics simulating comparison so as to provide reasonable basis for determining reasonable launching sequence.
d. To research launching process of MLRS model, and determine proper firing interval as per vibrating and attenuating characteristics of port of storage-transport-launch box so as to reduce initiative of next rocket in firing.
This article establishes the dynamics launching model of launch vehicle, the dynamics analysis show that the more symmetrical and closer to center the launching sequence, the better the launching effect, and the more benefit to reduce initiative disturbance the inequi-interval launching. These work have helpful reference to overall conceptual design of MLRS.
引文
[1]贾长治,王兴贵等.虚拟样机在装备仿真分析中的应用.机械设计与制造工程,2002,3
[2]姚昌仁.火箭导弹发射动力学.北京:北京理工大学出版社,1996
[3]贺北斗,林永明,曹厅荣.火箭发射装置设计[M].第1版].北京:国防工业出版社,1998
[4]姚昌仁,唐国梁等.火箭导弹发射动力学.北京:北京理工大学出版社,1996
[5]骆连珍.多管火箭动力学及软件开发.博士论文,南京理工大学,1999
[6]骆连珍,曹勇.发射装置振动对火箭弹起始扰动的影响[J] .弹箭与制导学报1998,No18:27～31
[7]孙华清.ADAMS用于插拔机构运动分析.美国MDI公司2001年年会论文集
[8]陆友林等.5450特种车转向杆系运动学与动力学分析计算.美国MDI公司2001年年会论文集
[9]刘民等.某型号运输车悬挂系统动力学仿真.美国MDI公司2001年年会论文集
[10]张胜山,王心谦等.多管火箭发射动力学仿真研究.导弹与航天运载技术,2001,No6:47～52
[11]徐振钦,乐贵高,马大为.机液耦合多管火箭发射系统动态仿真.系统仿真学报,2006,No.6:1562～1565
[12]冯勇,马大为,薛畅,陈兵.多管火箭武器系统刚柔多体动力学仿真研究.兵工学报,2006,27卷第3期:545～548
[13]章定国,张福祥.火箭发射系统得动力学控制.南京理工大学学报,2002,26卷第2期:139～143
[14]张胜山,郭卫东.多管火箭弹出管姿态仿真.导弹与航天运载技术,2003,No2:16～24
[15]王国平.远程多管火箭动力学及其应用研究.博士论文,南京理工大学,2004
[16]王国平,芮筱亭,陈卫东.多管火箭武器系统系统密集度仿真技术.系统仿真学报,2006,No. 5:963～966
[17]王国平,芮筱亭.弹管间歇对多管火箭密集度的影响.弹箭学报,2003,15卷第4期:27～32
[18]朱怀亮.大型旋转飞行器在非线性不对称支承下的发射特性分析.兵工学报,2001,22卷第2期:230～233
[19]王志军,陈国光.火箭弹起始扰动的仿真与试验研究.华北工学院测试技术学报,2001,15卷第3期:159～162
[20]张胜三,王心谦,郭卫东,王千.某多管火箭发射车动力学仿真研究.美国MDI公司2001年年会论文集
[21]裴胤,胡光宇,乐贵高,马大为.多管火箭武器系统系统动力学仿真研究.南京理工大学学报,2003,27卷第1期:40～43
[22]刘博文,廖嘉郁等.ADAMS在多管火箭发射系统动态分析上的应用.台湾中山科学研究院第二研究所学报
[23]陈笑全,徐美丽.多管火箭炮发射间隔仿真研究.弹箭与制导学报,2003,23卷第2期:48～50
[24]冯长根,温波,李才葆.自行火炮行进间发射动力学研究.兵工学报,2002,23卷第4期:457～461
[25]芮筱亭等.多管火箭发射动力学的发展与展望.中国兵工学会火箭导弹学会学术论文集,1986,2(1)
[26] Rietz A.Sufficiemcy of a finite exponent in SIMP(power law)method.Structural and Multidiscipline Optimization, 2001(21) :159-163
[27] Bendsoe M P, Sigmund O. Topology Optimization:theory, methods and applications. 2003. ISBN 3-540-42992-1 Springer-Verlag Berlin Heidelberg
[28] Stolpe M, Svanberg K. An alternative interpolation scheme for minmum compliance topology optimization. Structural and Multidiscipline Optimization, 2001(22):116-124 New York
[29] Allaire G, Belhachmi Z, &Jouve F. The homogenization method for topology and shape optimization.Single and multiple loads case, 1997,Rev, Europenne Im. Finis 5:649-67
[30] Lars Krog, et al. Application of topology, sizing and shape optimization methods to optimal design of aircraft components. Altair Engineering Ltd, 2002
[31] Cost T L Weeks G E. Free Flight Rocket Accuracy-Effect of Bending during Launch phase. AIAA-80-152
[32] Crosheck J E. Balloting phenomena in Rocket一Launcher Firings. AD 608262.
[33] Christensen D E,Richardson R L. A Multiple Rocket Launchers simulation一Report II. AD-A 041269
[34] Wempner G A, Lee S K. Analysis of Missile Launchers Part o Phase 1(Multi一degree of Freedom Models).AD 263892
[35] Dynamic Analysis of shipping container suspension system for the ASROC Launched Versionof the Harpoon missile RGM-84A-1. AD-A051422
[36] Simun R R, Peterson R S. Missile Transporter Vibration Analysis. The shock and Vibration Bulletin,1962 Bulletin 30 part III
[37] Artillery Research Missile Launcher Development Program. AD 771066
[38] Stippes M. Final Report Analysis of Missle Launchers. AD 291777
[39]金志明.高速推进内弹道学.国防工业出版社,2001
[40]郑建荣.ADAMS――虚拟样机技术入门与提高.机械工业出版社,2003,7
[41]李军,刑俊文,覃文浩.ADAMS实例教程.北京:北京理工大学出版社,2002
[42]王国强,张进平,马若丁.虚拟样机技术及其在ADAMS上的实践.西安:西北工业大学出版社,2002,3
[43]陈立平,张云清,任卫群等.机械系统动力学分析及ADAMS应用教程.北京:清华大学出版社,2005,1
[44]张蓉.某防空火箭炮发射动力学分析与结构轻量化研究.南京理工大学硕士论文,2008.5
[45]吴晨明.某多管火箭炮结构动态设计研究.南京理工大学硕士论文,2008.5
[46]陈效全,徐美丽.多管火箭炮发射时间间隔仿真研究[J].弹箭与制导学报2003,23卷第2期:48～50
[2]姚昌仁.火箭导弹发射动力学.北京:北京理工大学出版社,1996
[3]贺北斗,林永明,曹厅荣.火箭发射装置设计[M].第1版].北京:国防工业出版社,1998
[4]姚昌仁,唐国梁等.火箭导弹发射动力学.北京:北京理工大学出版社,1996
[5]骆连珍.多管火箭动力学及软件开发.博士论文,南京理工大学,1999
[6]骆连珍,曹勇.发射装置振动对火箭弹起始扰动的影响[J] .弹箭与制导学报1998,No18:27～31
[7]孙华清.ADAMS用于插拔机构运动分析.美国MDI公司2001年年会论文集
[8]陆友林等.5450特种车转向杆系运动学与动力学分析计算.美国MDI公司2001年年会论文集
[9]刘民等.某型号运输车悬挂系统动力学仿真.美国MDI公司2001年年会论文集
[10]张胜山,王心谦等.多管火箭发射动力学仿真研究.导弹与航天运载技术,2001,No6:47～52
[11]徐振钦,乐贵高,马大为.机液耦合多管火箭发射系统动态仿真.系统仿真学报,2006,No.6:1562～1565
[12]冯勇,马大为,薛畅,陈兵.多管火箭武器系统刚柔多体动力学仿真研究.兵工学报,2006,27卷第3期:545～548
[13]章定国,张福祥.火箭发射系统得动力学控制.南京理工大学学报,2002,26卷第2期:139～143
[14]张胜山,郭卫东.多管火箭弹出管姿态仿真.导弹与航天运载技术,2003,No2:16～24
[15]王国平.远程多管火箭动力学及其应用研究.博士论文,南京理工大学,2004
[16]王国平,芮筱亭,陈卫东.多管火箭武器系统系统密集度仿真技术.系统仿真学报,2006,No. 5:963～966
[17]王国平,芮筱亭.弹管间歇对多管火箭密集度的影响.弹箭学报,2003,15卷第4期:27～32
[18]朱怀亮.大型旋转飞行器在非线性不对称支承下的发射特性分析.兵工学报,2001,22卷第2期:230～233
[19]王志军,陈国光.火箭弹起始扰动的仿真与试验研究.华北工学院测试技术学报,2001,15卷第3期:159～162
[20]张胜三,王心谦,郭卫东,王千.某多管火箭发射车动力学仿真研究.美国MDI公司2001年年会论文集
[21]裴胤,胡光宇,乐贵高,马大为.多管火箭武器系统系统动力学仿真研究.南京理工大学学报,2003,27卷第1期:40～43
[22]刘博文,廖嘉郁等.ADAMS在多管火箭发射系统动态分析上的应用.台湾中山科学研究院第二研究所学报
[23]陈笑全,徐美丽.多管火箭炮发射间隔仿真研究.弹箭与制导学报,2003,23卷第2期:48～50
[24]冯长根,温波,李才葆.自行火炮行进间发射动力学研究.兵工学报,2002,23卷第4期:457～461
[25]芮筱亭等.多管火箭发射动力学的发展与展望.中国兵工学会火箭导弹学会学术论文集,1986,2(1)
[26] Rietz A.Sufficiemcy of a finite exponent in SIMP(power law)method.Structural and Multidiscipline Optimization, 2001(21) :159-163
[27] Bendsoe M P, Sigmund O. Topology Optimization:theory, methods and applications. 2003. ISBN 3-540-42992-1 Springer-Verlag Berlin Heidelberg
[28] Stolpe M, Svanberg K. An alternative interpolation scheme for minmum compliance topology optimization. Structural and Multidiscipline Optimization, 2001(22):116-124 New York
[29] Allaire G, Belhachmi Z, &Jouve F. The homogenization method for topology and shape optimization.Single and multiple loads case, 1997,Rev, Europenne Im. Finis 5:649-67
[30] Lars Krog, et al. Application of topology, sizing and shape optimization methods to optimal design of aircraft components. Altair Engineering Ltd, 2002
[31] Cost T L Weeks G E. Free Flight Rocket Accuracy-Effect of Bending during Launch phase. AIAA-80-152
[32] Crosheck J E. Balloting phenomena in Rocket一Launcher Firings. AD 608262.
[33] Christensen D E,Richardson R L. A Multiple Rocket Launchers simulation一Report II. AD-A 041269
[34] Wempner G A, Lee S K. Analysis of Missile Launchers Part o Phase 1(Multi一degree of Freedom Models).AD 263892
[35] Dynamic Analysis of shipping container suspension system for the ASROC Launched Versionof the Harpoon missile RGM-84A-1. AD-A051422
[36] Simun R R, Peterson R S. Missile Transporter Vibration Analysis. The shock and Vibration Bulletin,1962 Bulletin 30 part III
[37] Artillery Research Missile Launcher Development Program. AD 771066
[38] Stippes M. Final Report Analysis of Missle Launchers. AD 291777
[39]金志明.高速推进内弹道学.国防工业出版社,2001
[40]郑建荣.ADAMS――虚拟样机技术入门与提高.机械工业出版社,2003,7
[41]李军,刑俊文,覃文浩.ADAMS实例教程.北京:北京理工大学出版社,2002
[42]王国强,张进平,马若丁.虚拟样机技术及其在ADAMS上的实践.西安:西北工业大学出版社,2002,3
[43]陈立平,张云清,任卫群等.机械系统动力学分析及ADAMS应用教程.北京:清华大学出版社,2005,1
[44]张蓉.某防空火箭炮发射动力学分析与结构轻量化研究.南京理工大学硕士论文,2008.5
[45]吴晨明.某多管火箭炮结构动态设计研究.南京理工大学硕士论文,2008.5
[46]陈效全,徐美丽.多管火箭炮发射时间间隔仿真研究[J].弹箭与制导学报2003,23卷第2期:48～50