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

【作者】 杨勇；

【导师】 马大为； 朱忠领；

【作者基本信息】 南京理工大学 ， 兵器发射理论与技术， 2009， 硕士

【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。更多还原

【Abstract】 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.更多还原