某型号火箭发射车动力学仿真分析与优化设计
摘要
提高火箭武器射击密集度和机动性,是现代战争的需求,也是今后火箭武器研发的发展趋势。动力学仿真是提高火箭武器射击密集度的一种重要技术途径,结构优化是提高火箭武器机动性的重要方法。本文对某火箭发射车发射过程进行了动力学仿真分析,对发射过程关键部件瞄准机的动力学情况进行了分析,应用有限元分析方法对瞄准机进行了有限元分析,对结构进行了优化研究。
本文以多体动力学和结构有限元理论和方法为核心,主要做了以下工作:
建立了某自行火箭发射车全炮三维实体模型,为建立该火箭发射车系统的动力学等效模型提供了必要条件,进行了发射动力学仿真,得到了贮运发射箱端口的振动线速度和线加速度曲线,获得了火箭弹运行速度变化趋势,为评价火箭武器系统密集度提供了数据。
用动力学仿真方法和经典力学理论方法分别计算了发射车稳定性,用经典力学理论方法对模型正确性进行了校验。
输出了该火箭发射车瞄准机在发射状态下的载荷,为有限元分析和结构优化提供了必需的数据。
建立了该火箭发射车瞄准机的有限元模型,分为24°和57°两种工况,对模型进行了有限元强度分析,得出了关键部位的变形和应力值,对其应力和变形分布有了具体的了解。
运用经典力学分析方法对瞄准机变形对射角变化影响情况进行了分析,结果表明瞄准机变形对射角的影响较小。
运用结构有限元理论和方法,对瞄准机的结构进行了优化设计,对优化前后两种发射工况的最大变形进行了比较分析,分析结果表明,对该部件的优化是比较成功的。
本文的研究结果对今后的火箭发射车武器系统的动力学仿真分析和结构化研究有一定的参考意义。
To improve the firing dispersion and the flexibility of the weapon is the need of modern war and the development trend of the weapon investigation. Dynamic simulation is a very important way to improve firing dispersion and structure optimization is the mostly way to improve the flexibility. By the dynamics simulation of one lunch truck’s firing process. According the load’s analysis of the collimation body, its intensity and rigidity and displacement is analyzed with finite element method, and its structure optimization has been done.
This paper, which focused on the theory and method of the multi-body dynamics and structure optimization, has finished such studies as follows:
The three dimension model has been built, which provide the necessary conditions for the building of the dynamics equivalent model. The vibration velocity and acceleration of the storage-transportation-launch case by the firing dynamics simulation, which provide the necessary data to estimate the firing dispersion.
Launch stability has been got with multi-body dynamic simulation , the result of the simulation is consistent with that obtained from the traditional programming ways.
The loads of the collimation body when launch were exported to provide necessary data for the finite element analysis and the structure optimization.
Detailed finite element has been established .By the finite element analysis of the model in 24°and 57°conditions, the displacement and the stress have been got, which make us know the distributing of the stress and the transmogrification of the part.
The effect of structure’s deformation on angle of fire has been studied by using classical dynamics, the results show that the effects is smallness.
Local Optimization has been done where the largest stress concentration in. The results show that the optimization on the part is successfully.
The result of this paper has a certain extend reference meaning for the reduce weight of the rocket weapon system for the future.
本文以多体动力学和结构有限元理论和方法为核心,主要做了以下工作:
建立了某自行火箭发射车全炮三维实体模型,为建立该火箭发射车系统的动力学等效模型提供了必要条件,进行了发射动力学仿真,得到了贮运发射箱端口的振动线速度和线加速度曲线,获得了火箭弹运行速度变化趋势,为评价火箭武器系统密集度提供了数据。
用动力学仿真方法和经典力学理论方法分别计算了发射车稳定性,用经典力学理论方法对模型正确性进行了校验。
输出了该火箭发射车瞄准机在发射状态下的载荷,为有限元分析和结构优化提供了必需的数据。
建立了该火箭发射车瞄准机的有限元模型,分为24°和57°两种工况,对模型进行了有限元强度分析,得出了关键部位的变形和应力值,对其应力和变形分布有了具体的了解。
运用经典力学分析方法对瞄准机变形对射角变化影响情况进行了分析,结果表明瞄准机变形对射角的影响较小。
运用结构有限元理论和方法,对瞄准机的结构进行了优化设计,对优化前后两种发射工况的最大变形进行了比较分析,分析结果表明,对该部件的优化是比较成功的。
本文的研究结果对今后的火箭发射车武器系统的动力学仿真分析和结构化研究有一定的参考意义。
To improve the firing dispersion and the flexibility of the weapon is the need of modern war and the development trend of the weapon investigation. Dynamic simulation is a very important way to improve firing dispersion and structure optimization is the mostly way to improve the flexibility. By the dynamics simulation of one lunch truck’s firing process. According the load’s analysis of the collimation body, its intensity and rigidity and displacement is analyzed with finite element method, and its structure optimization has been done.
This paper, which focused on the theory and method of the multi-body dynamics and structure optimization, has finished such studies as follows:
The three dimension model has been built, which provide the necessary conditions for the building of the dynamics equivalent model. The vibration velocity and acceleration of the storage-transportation-launch case by the firing dynamics simulation, which provide the necessary data to estimate the firing dispersion.
Launch stability has been got with multi-body dynamic simulation , the result of the simulation is consistent with that obtained from the traditional programming ways.
The loads of the collimation body when launch were exported to provide necessary data for the finite element analysis and the structure optimization.
Detailed finite element has been established .By the finite element analysis of the model in 24°and 57°conditions, the displacement and the stress have been got, which make us know the distributing of the stress and the transmogrification of the part.
The effect of structure’s deformation on angle of fire has been studied by using classical dynamics, the results show that the effects is smallness.
Local Optimization has been done where the largest stress concentration in. The results show that the optimization on the part is successfully.
The result of this paper has a certain extend reference meaning for the reduce weight of the rocket weapon system for the future.
引文
[1]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
[2]姚昌仁,唐国梁,宋廷伦.火箭导弹发射动力学.北京:北京理工大学出版社,1996,8
[3]姚昌仁,张波.火箭导弹发射装置设计.北京:北京理工大学出版社,1998,9
[4]姚昌仁,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)
[5]芮筱亭.多体系统发射动力学.北京:国防工业出版社,1995
[6]裴胤.基于WIDSS的火箭发射车虚拟样机设计及动力学仿真.[博士论文],南京理工大学.2002
[7]章定国,张福祥.火箭发射系统动力学控制.南京理工大学学报,2002,26(2):139～143
[8]刘延柱,等.多刚体系统动力学.高等教育出版社,1980
[9]王良明.弹炮多体系统动力学.力学与实践,1994(5)
[10]洪嘉振.多体系统动力学—理论、计算方法和应用.上海交通大学出版社,1992,9
[11]刘又午,等.多体系统动力学.天津大学出版社,1991
[12]朱小松.集装箱火箭发射车系统海上发射动态防真与性能分析.[硕士论文],南京理工大学,2004,6
[13]李杰峰.某防空火箭发射车的不等间隔齐射分析.[硕士论文],南京理工大学,2005,6
[14]郑建荣.ADAMS-虚拟样机技术.机械工业出版社,2002
[15]郑建荣.ADAMS——虚拟样机技术入门与提高.北京:机械工业出版社,2004,1
[16] MSC.Software(著),李军,陶永忠(译).MSC.ADAMS FSP基础培训教程.北京:清华大学出版社,2004
[17]裴胤,胡光宇,乐贵高,马大为.多管火箭发射车系统发射动力学仿真研究.南京理工大学学报,2003(1),40-43
[18]张胜三,王心谦.多管火箭发射车动力学仿真研究.导弹与航天运载技术,2001(6):47-52
[19] Wempner G A, Lee S K. Analysis of Missile Launchers Part o Phase 1(Multi一degree of Freedom Models).AD 263892
[20] Dynamic Analysis of shipping container suspension system for the ASROC Launched Version of the Harpoon missile RGM-84A-1. AD-A051422
[21] Simun R R, Peterson R S. Missile Transporter Vibration Analysis. The shock and Vibration Bulletin,1962 Bulletin 30 part III
[22] Cost T L Weeks G E. Free Flight Rocket Accuracy-Effect of Bending during Launch phase. AIAA-80-152
[23] Crosheck J E. Balloting phenomena in Rocket一Launcher Firings. AD608262
[24] Christensen D E,Richardson R L. A Multiple Rocket Launchers simulation一Report II.AD-A 041269
[25] Artillery Research Missile Launcher Development Program. AD 771066
[26] Stippes M. Final Report Analysis of Missle Launchers. AD 291777
[27]徐新辉.基于ANSYS分析的龙门起重机箱形主梁优化设计.[硕士论文],武汉理工大学,2005,3
[28]曾攀.有限元分析及应用.北京:清华大学出版社,2004
[29]刘金辉.考虑弹性变形的机翼气动-结构多学科优化设计.[硕士论文],西北工业大学,2005,3
[30]周传月,滕万秀,张俊堂.工程有限元与优化分析应用实例教程.北京:科学出版社,2005
[31] ADAMS reference book Version12.0.Mechanical Dynamics Inc, 2000
[32] ADAMS/Solver.Version12.0.Mechanical Dynamics Inc, 2000
[33] ADAMS/View.Version12.0.Mechanical Dynamics Inc, 2000
[34]李亚智,赵美英,万小朋.有限元法基础与程序设计.北京:科学技术出版社,2004
[35]林金木.有限单元法变分原理与应用.第1版.湖南:湖南大学出版社,2003
[36]朱伯芳.有限单元法原理与应用.第1版.北京:水利电力出版社,1979
[37]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
[38]康新中,马春茂,魏孝达.火炮系统建模理论.北京:国防工业出版社,2003,1
[39]张克健.车辆地面力学.第1版.北京:国防工业出版社,2002,1
[2]姚昌仁,唐国梁,宋廷伦.火箭导弹发射动力学.北京:北京理工大学出版社,1996,8
[3]姚昌仁,张波.火箭导弹发射装置设计.北京:北京理工大学出版社,1998,9
[4]姚昌仁,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)
[5]芮筱亭.多体系统发射动力学.北京:国防工业出版社,1995
[6]裴胤.基于WIDSS的火箭发射车虚拟样机设计及动力学仿真.[博士论文],南京理工大学.2002
[7]章定国,张福祥.火箭发射系统动力学控制.南京理工大学学报,2002,26(2):139～143
[8]刘延柱,等.多刚体系统动力学.高等教育出版社,1980
[9]王良明.弹炮多体系统动力学.力学与实践,1994(5)
[10]洪嘉振.多体系统动力学—理论、计算方法和应用.上海交通大学出版社,1992,9
[11]刘又午,等.多体系统动力学.天津大学出版社,1991
[12]朱小松.集装箱火箭发射车系统海上发射动态防真与性能分析.[硕士论文],南京理工大学,2004,6
[13]李杰峰.某防空火箭发射车的不等间隔齐射分析.[硕士论文],南京理工大学,2005,6
[14]郑建荣.ADAMS-虚拟样机技术.机械工业出版社,2002
[15]郑建荣.ADAMS——虚拟样机技术入门与提高.北京:机械工业出版社,2004,1
[16] MSC.Software(著),李军,陶永忠(译).MSC.ADAMS FSP基础培训教程.北京:清华大学出版社,2004
[17]裴胤,胡光宇,乐贵高,马大为.多管火箭发射车系统发射动力学仿真研究.南京理工大学学报,2003(1),40-43
[18]张胜三,王心谦.多管火箭发射车动力学仿真研究.导弹与航天运载技术,2001(6):47-52
[19] Wempner G A, Lee S K. Analysis of Missile Launchers Part o Phase 1(Multi一degree of Freedom Models).AD 263892
[20] Dynamic Analysis of shipping container suspension system for the ASROC Launched Version of the Harpoon missile RGM-84A-1. AD-A051422
[21] Simun R R, Peterson R S. Missile Transporter Vibration Analysis. The shock and Vibration Bulletin,1962 Bulletin 30 part III
[22] Cost T L Weeks G E. Free Flight Rocket Accuracy-Effect of Bending during Launch phase. AIAA-80-152
[23] Crosheck J E. Balloting phenomena in Rocket一Launcher Firings. AD608262
[24] Christensen D E,Richardson R L. A Multiple Rocket Launchers simulation一Report II.AD-A 041269
[25] Artillery Research Missile Launcher Development Program. AD 771066
[26] Stippes M. Final Report Analysis of Missle Launchers. AD 291777
[27]徐新辉.基于ANSYS分析的龙门起重机箱形主梁优化设计.[硕士论文],武汉理工大学,2005,3
[28]曾攀.有限元分析及应用.北京:清华大学出版社,2004
[29]刘金辉.考虑弹性变形的机翼气动-结构多学科优化设计.[硕士论文],西北工业大学,2005,3
[30]周传月,滕万秀,张俊堂.工程有限元与优化分析应用实例教程.北京:科学出版社,2005
[31] ADAMS reference book Version12.0.Mechanical Dynamics Inc, 2000
[32] ADAMS/Solver.Version12.0.Mechanical Dynamics Inc, 2000
[33] ADAMS/View.Version12.0.Mechanical Dynamics Inc, 2000
[34]李亚智,赵美英,万小朋.有限元法基础与程序设计.北京:科学技术出版社,2004
[35]林金木.有限单元法变分原理与应用.第1版.湖南:湖南大学出版社,2003
[36]朱伯芳.有限单元法原理与应用.第1版.北京:水利电力出版社,1979
[37]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
[38]康新中,马春茂,魏孝达.火炮系统建模理论.北京:国防工业出版社,2003,1
[39]张克健.车辆地面力学.第1版.北京:国防工业出版社,2002,1