机载多管火箭系统振动特性研究  

Vibration characteristics of airborne multiple launch rocket systems

作　　者：张驰[1] 芮筱亭[1] 戎保[1] 王国平[1] 

机构地区：[1]南京理工大学发射动力学研究所,江苏南京210094

出　　处：《振动工程学报》2013年第1期15-19,共5页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(11102089);新世纪优秀人才支持计划资助项目(NCET-10-0075);高等院校博士点基金资助项目(20113219110025);国防基础科研计划资助项目(B26211004)

摘　　要：多管火箭系统振动特性是科学评价机载多管火箭系统动态性能和提高密集度的重要依据。应用多体系统传递矩阵法,建立了某机载多管火箭武器系统动力学模型,从理论、计算、试验三方面研究了机载多管火箭系统的振动特性。建立了某机载多管火箭武器系统固有振动特性数值计算和试验测试方法,实现了对机载多管火箭刚柔耦合多体系统不同装载情况下固有振动特性的快速计算,数值计算结果得到了模态试验的验证。建立的机载多管火箭武器系统振动特性计算方法具有无需建立系统总体动力学方程、涉及系统矩阵阶次、计算速度快等优点。The vibration characteristics of airborne multiple launch rocket system is very important for estimating its dynamic performance and increasing its firing dispersion. The dynamics model of airborne multiple launch rocket system is built using the transfer matrix method of multibody system, and its vibration characteristics are studied from the aspects of theory, calcu- lation, and test. The calculation algorithm and modal test method for vibration characteristics of rigid-flexible coupling airborne multiple launch rocket system are developed. Based on the proposed method, the numerical simulation for vibration character- istics of an airborne multiple launch rocket system is given, and the results obtained by the simulation and modal test have good agreements, which validate the proposed method. When using this method to study the vibration characteristics of airborne multiple launch rocket systems, the global dynamic equations of system is not needed, the order of system matrix is low, and the computational speed is high.

关 键 词：多体系统 机载多管火箭 模态试验 传递矩阵法 振动特性 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]