某多管火箭发射装置结构动力学仿真与动态特性优化研究
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摘要
本文结合结构动力学方法和非线性有限元理论,依据动力学分析的基本内容,运用ABAQUs有限元分析软件,对某多管火箭发射装置进行结构动力学仿真分析,以了解其固有特性,检查发射系统的可靠性(刚强度问题、炮口撞击问题等等)。在动力学仿真分析的基础上,采取不同的控制途径改善系统的动态特性,减少起始扰动,提高射击精度,实现多管火箭发射装置的动态设计与优化。
本文主要完成以下工作:①对多管火箭发射装置合理简化、建模,进行模态分析,了解其固有特性,发现结构薄弱环节,对可能引起共振的激励因素进行分析。模态分析对整个火箭发射装置的振动分析具有十分重要的意义,同时也为采取有效措施减少振动,提高火箭发射精度提供了很好的依据和帮助。②针对多管火箭发射装置三种不同的工作状态(瞄准、发射、行军),进行结构有限元分析,校核其动静态刚强度。此外,对发射过程中的炮口撞击问题进行校核。③根据不同定向器结构参数对起始扰动的影响规律,进行定向器结构参数分析,选取合理取值,改善多管火箭发射装置的动态特性,减少起始扰动,提高射击精度。④通过制定合理的发射间隔来改善多管火箭发射装置的动态特性。对多管火箭单击发射进行动态仿真分析,根据定向器管口的振动衰减情况确定合理的发射间隔,并通过对多管火箭连发特性的仿真研究、射击频率与火箭发射装置固有频率(发射过程中)之间的匹配性研究,验证所确定发射间隔的合理性。⑤突破常规初步设计定向器螺旋缠角中存在的诸多不足,从满足战术技术所要求的密集度指标出发,综合考虑影响散布的各扰动因素,基于起始扰动中间偏差对螺旋缠角进行优化设计。
According to the basic content of dynamical analysis, the thesis focus on the dynamic simulation of Multiple Rocket Launcher by ABAQUS with the theory of structure dynamics and nonlinear finite element analysis method, in order to realize the inherent characteristic and verify its reliability such as the stiffness and intensity, the collision between missile and muzzle and so on. On the basis of the dynamic simulation analysis, taking differrent control method improve the dynamic property of Multiple Rocket Launcher, so as to reduce initial disturbance , advance launch accuracy and carry out the structure dynamic design.
Main work in this thesis is as follows:①Reasonable simplified nonlinear finite element model of Multiple Rocket Launcher is built, its modal is studied in order to realize the inherent characteristic, find out the weak part of launcher and achieve the resonance analysis.The mode analysis lay the foundation for the oscillation analysis and taking efficient measure to reduce initial disturbance and rocket dispersion.②In response to three different working purpose of Multiple Rocket Launcher(the aiming state,the launching state,the march state), the stiffness and intensity of the structure is researched to verify its reliability. In addition, the collision between missile and muzzle is checked out.③According to effect of the different structure parameter of launching guider for the initial disturbance, resonable structure parameter value is obtained. In this way, the dynamic characteristic of Multiple Rocket Launcher and the launch accuracy is all improved.④Setting the rational firing interval make its dynamic feature better.By the study of the attenuation of guider nozzle oscillation, the rational launching interval is getted,which is also tested by the research of string firing and the matching relation between launching frequency and natural oscillation frequency(in launching).⑤Overcoming the disadvantages in the preliminary design of director rifling angle, with full consideration of the influence of variable disturbing factor for dispersion ,the reasonable value of rifling angle, which satisfy the tactical and technical density performance index ,will be acquired through the mean-square deviation of initial disturbance.
本文主要完成以下工作:①对多管火箭发射装置合理简化、建模,进行模态分析,了解其固有特性,发现结构薄弱环节,对可能引起共振的激励因素进行分析。模态分析对整个火箭发射装置的振动分析具有十分重要的意义,同时也为采取有效措施减少振动,提高火箭发射精度提供了很好的依据和帮助。②针对多管火箭发射装置三种不同的工作状态(瞄准、发射、行军),进行结构有限元分析,校核其动静态刚强度。此外,对发射过程中的炮口撞击问题进行校核。③根据不同定向器结构参数对起始扰动的影响规律,进行定向器结构参数分析,选取合理取值,改善多管火箭发射装置的动态特性,减少起始扰动,提高射击精度。④通过制定合理的发射间隔来改善多管火箭发射装置的动态特性。对多管火箭单击发射进行动态仿真分析,根据定向器管口的振动衰减情况确定合理的发射间隔,并通过对多管火箭连发特性的仿真研究、射击频率与火箭发射装置固有频率(发射过程中)之间的匹配性研究,验证所确定发射间隔的合理性。⑤突破常规初步设计定向器螺旋缠角中存在的诸多不足,从满足战术技术所要求的密集度指标出发,综合考虑影响散布的各扰动因素,基于起始扰动中间偏差对螺旋缠角进行优化设计。
According to the basic content of dynamical analysis, the thesis focus on the dynamic simulation of Multiple Rocket Launcher by ABAQUS with the theory of structure dynamics and nonlinear finite element analysis method, in order to realize the inherent characteristic and verify its reliability such as the stiffness and intensity, the collision between missile and muzzle and so on. On the basis of the dynamic simulation analysis, taking differrent control method improve the dynamic property of Multiple Rocket Launcher, so as to reduce initial disturbance , advance launch accuracy and carry out the structure dynamic design.
Main work in this thesis is as follows:①Reasonable simplified nonlinear finite element model of Multiple Rocket Launcher is built, its modal is studied in order to realize the inherent characteristic, find out the weak part of launcher and achieve the resonance analysis.The mode analysis lay the foundation for the oscillation analysis and taking efficient measure to reduce initial disturbance and rocket dispersion.②In response to three different working purpose of Multiple Rocket Launcher(the aiming state,the launching state,the march state), the stiffness and intensity of the structure is researched to verify its reliability. In addition, the collision between missile and muzzle is checked out.③According to effect of the different structure parameter of launching guider for the initial disturbance, resonable structure parameter value is obtained. In this way, the dynamic characteristic of Multiple Rocket Launcher and the launch accuracy is all improved.④Setting the rational firing interval make its dynamic feature better.By the study of the attenuation of guider nozzle oscillation, the rational launching interval is getted,which is also tested by the research of string firing and the matching relation between launching frequency and natural oscillation frequency(in launching).⑤Overcoming the disadvantages in the preliminary design of director rifling angle, with full consideration of the influence of variable disturbing factor for dispersion ,the reasonable value of rifling angle, which satisfy the tactical and technical density performance index ,will be acquired through the mean-square deviation of initial disturbance.
引文
[1]周长省鞠玉涛.火箭弹设计理论[M].北京理工大学出版社,2005
[2]孙菊芳荣王武.有限元法及其应用[M].北京航天航空出版社,1990
[3]Clough R W.The finite element method in plane stress analysis[R].Proc.2ndConf.Electronic Computation,ASCE,Pittsburg,1960
[4]经文王宏钰.结构有限元分析[M].科学出版社,2004
[5]姚昌仁 唐国梁 宋廷伦.火箭导弹发射动力学[M].北京理工大学出版社,1996
[6]包世华.结构动力学[M].武汉理工学出版社,2004
[7]102教研室.火箭导弹发射装置概论[M].华东工学院,1979
[8]季宗德周长省等.火箭弹设计理论[M].兵器工业出版社,1995
[9]宋传滨.火箭炮的发展及性能提高的途径[J].科技咨询导报,2007No.14.(2007)05(b)-0109-01
[10]郭暄.多管火箭炮的全球性发展[J].兵器大观,2007(12)
[11]董晓军.火箭炮的昨天、今天和明天[J].国防科技参考,2000(3)
[12]Stippes M.Final Report Analysis of Missle Launchers.AD 291777
[13]Stippes M.Approximate Formulas for pitch Velocity a Tip-off.AD 285042
[14]Artillery Research Missile Launcher Development Program.AD 771066
[15]芮筱亭 陆毓琪 王国平等.多管火箭发射动力学仿真与试验测试方法[M].国防工业出版社,20032003,23(2):48-50
[16]芮筱亭 陆毓琪 陈卫东等.多管火箭发射动力学研究[J].兵工学报,2004,25(5):556-561
[17]Cochran John E.Investigation of Factors Which Contribution to Mallaunch of Free rockets.AD-A024570,1976
[18]Cochran John E.Artillery Reseach Missile Launch Development Program.AD-771066,1977
[19]Cochran John E.Gunnels Richard T.Rocket Launchers as Passive Controls.AD-A112571,1984
[20]韩珺礼 徐明友 沈坚平等.多管火箭发射动力学普遍方程的研究[J].南京理工大学学报,1996,20(5):421-424
[21]芮筱亭.多体系统发射动力学[M].国防工业出版社,1995
[22]芮筱亭等.多体系统传递矩阵法在火炮动力学中的应用[J].力学与实践,1995,17(4):51-66
[23]芮筱亭邱凤昌.多体火炮系统的固有振动特性[J].兵工学报,1995,No.2:7-12
[24]芮筱亭 隋文海 邵允中.刚体的场传递矩阵及其在多体动力学中的应用[J]. 宇航学报,1993,No.4:82-87
[25]芮筱亭 陆毓琪.多体系统振动的传递矩阵法[J].宇航学报,1995,No.3:41-47
[26]王勖成 邵敏.有限元单元法基本原理和数值方法[M].清华大学出版社,1995
[27]曾攀.有限元分析及其应用[M].第1版.清华大学出版社,2004
[28]张洪武等.有限元分析与CAE技术基础[M].清华大学出版社,2004
[29]傅志方,华宏星.模态分析理论与应用[M].上海交通大学出版社,2000
[30]管迪华.模态分析技术[M].清华大学出版社,1995
[31]李兵尚 潘奠华.用有限元法进行多连装发射装置的模态分析[J].烟台大学学报,2006,19(2):148-151
[32]庄茁 张帆等.ABAQUS非线性有限元分析与实例[M].科学出版社,2005
[33]李波.某火箭武器特种集装箱式发射系统结构分析及动力学仿真[D],南京理工大学,2006
[34]李惠彬.振动理论与工程应用[M].北京理工大学出版社,2006
[35]姚昌仁.导弹发射装置设计[M].国防工业出版社,1981
[36]贺北斗林永明曹听荣.火箭发射装置设计[M].国防工业出版社,1988
[37]石亦平 周玉蓉.ABAQUS有限元分析实例详解[M].机械工业出版社,2006
[38]庄茁 张帆等.ABAQUS非线性有限元分析与实例[M].科学出版社,2005
[39]吴秉贤 严世泽 龚龙兴.火箭发射装置结构分析[M].国防工业出版社,1988
[40]张蓉.某防空火箭炮发射动力学分析与结构轻量化研究[D].南京理工大学,2006
[41]陈效全 徐美丽.多管火箭炮发射间隔仿真研究[J].弹道与制导学报,2003,23(2):48-50
[42]陈兵 马大为 乐贵高 赵岗.基于 BP 网络的防空火箭炮变间隔研究[J].系统仿真学报,2007,19(5):1148-1150
[43]陈兵 马大为 乐贵高.群射防空火箭炮射序优化[J].弹道学报,2006,18(4):25-28
[44]焦益群 谢友宝 姚昌仁.八自由度弹架系统建模研究[J].南昌航空工业学院学报.1996.10(2):58-64
[45]徐明友.火箭外弹道学[M].第一版.兵器工业出版社,1989
[46]邵大燮郭锡福.火箭外弹道学[M].华东工程学院,1982
[47]李文兵.基于流固耦合的舰炮身管动态特性分析[D],南京理工大学,2006
[2]孙菊芳荣王武.有限元法及其应用[M].北京航天航空出版社,1990
[3]Clough R W.The finite element method in plane stress analysis[R].Proc.2ndConf.Electronic Computation,ASCE,Pittsburg,1960
[4]经文王宏钰.结构有限元分析[M].科学出版社,2004
[5]姚昌仁 唐国梁 宋廷伦.火箭导弹发射动力学[M].北京理工大学出版社,1996
[6]包世华.结构动力学[M].武汉理工学出版社,2004
[7]102教研室.火箭导弹发射装置概论[M].华东工学院,1979
[8]季宗德周长省等.火箭弹设计理论[M].兵器工业出版社,1995
[9]宋传滨.火箭炮的发展及性能提高的途径[J].科技咨询导报,2007No.14.(2007)05(b)-0109-01
[10]郭暄.多管火箭炮的全球性发展[J].兵器大观,2007(12)
[11]董晓军.火箭炮的昨天、今天和明天[J].国防科技参考,2000(3)
[12]Stippes M.Final Report Analysis of Missle Launchers.AD 291777
[13]Stippes M.Approximate Formulas for pitch Velocity a Tip-off.AD 285042
[14]Artillery Research Missile Launcher Development Program.AD 771066
[15]芮筱亭 陆毓琪 王国平等.多管火箭发射动力学仿真与试验测试方法[M].国防工业出版社,20032003,23(2):48-50
[16]芮筱亭 陆毓琪 陈卫东等.多管火箭发射动力学研究[J].兵工学报,2004,25(5):556-561
[17]Cochran John E.Investigation of Factors Which Contribution to Mallaunch of Free rockets.AD-A024570,1976
[18]Cochran John E.Artillery Reseach Missile Launch Development Program.AD-771066,1977
[19]Cochran John E.Gunnels Richard T.Rocket Launchers as Passive Controls.AD-A112571,1984
[20]韩珺礼 徐明友 沈坚平等.多管火箭发射动力学普遍方程的研究[J].南京理工大学学报,1996,20(5):421-424
[21]芮筱亭.多体系统发射动力学[M].国防工业出版社,1995
[22]芮筱亭等.多体系统传递矩阵法在火炮动力学中的应用[J].力学与实践,1995,17(4):51-66
[23]芮筱亭邱凤昌.多体火炮系统的固有振动特性[J].兵工学报,1995,No.2:7-12
[24]芮筱亭 隋文海 邵允中.刚体的场传递矩阵及其在多体动力学中的应用[J]. 宇航学报,1993,No.4:82-87
[25]芮筱亭 陆毓琪.多体系统振动的传递矩阵法[J].宇航学报,1995,No.3:41-47
[26]王勖成 邵敏.有限元单元法基本原理和数值方法[M].清华大学出版社,1995
[27]曾攀.有限元分析及其应用[M].第1版.清华大学出版社,2004
[28]张洪武等.有限元分析与CAE技术基础[M].清华大学出版社,2004
[29]傅志方,华宏星.模态分析理论与应用[M].上海交通大学出版社,2000
[30]管迪华.模态分析技术[M].清华大学出版社,1995
[31]李兵尚 潘奠华.用有限元法进行多连装发射装置的模态分析[J].烟台大学学报,2006,19(2):148-151
[32]庄茁 张帆等.ABAQUS非线性有限元分析与实例[M].科学出版社,2005
[33]李波.某火箭武器特种集装箱式发射系统结构分析及动力学仿真[D],南京理工大学,2006
[34]李惠彬.振动理论与工程应用[M].北京理工大学出版社,2006
[35]姚昌仁.导弹发射装置设计[M].国防工业出版社,1981
[36]贺北斗林永明曹听荣.火箭发射装置设计[M].国防工业出版社,1988
[37]石亦平 周玉蓉.ABAQUS有限元分析实例详解[M].机械工业出版社,2006
[38]庄茁 张帆等.ABAQUS非线性有限元分析与实例[M].科学出版社,2005
[39]吴秉贤 严世泽 龚龙兴.火箭发射装置结构分析[M].国防工业出版社,1988
[40]张蓉.某防空火箭炮发射动力学分析与结构轻量化研究[D].南京理工大学,2006
[41]陈效全 徐美丽.多管火箭炮发射间隔仿真研究[J].弹道与制导学报,2003,23(2):48-50
[42]陈兵 马大为 乐贵高 赵岗.基于 BP 网络的防空火箭炮变间隔研究[J].系统仿真学报,2007,19(5):1148-1150
[43]陈兵 马大为 乐贵高.群射防空火箭炮射序优化[J].弹道学报,2006,18(4):25-28
[44]焦益群 谢友宝 姚昌仁.八自由度弹架系统建模研究[J].南昌航空工业学院学报.1996.10(2):58-64
[45]徐明友.火箭外弹道学[M].第一版.兵器工业出版社,1989
[46]邵大燮郭锡福.火箭外弹道学[M].华东工程学院,1982
[47]李文兵.基于流固耦合的舰炮身管动态特性分析[D],南京理工大学,2006