某远程多管火箭振动特性研究  

STUDY ON THE VIBRATION CHARACTERISTICS OF LRMLRS

作　　者：芮筱亭[1] 王国平[1] 贠来峰[1] 陆毓琪[1] 王公廉[1] 赵克升[2] 

机构地区：[1]南京理工大学,南京210094 [2]中国白城兵器试验中心,白城137001

出　　处：《振动与冲击》2005年第1期8-12,共5页Journal of Vibration and Shock

基　　金：国防科技预研重点项目

摘　　要：建立了某远程多管火箭动力学模型,从理论、计算、试验三方面对远程多管火箭的振动特性进行研究。用 多体系统传递矩阵法,计算了刚弹耦合远程多管火箭多体系统固有振动特性。进行了模态试验,计算结果与模态试验结 果吻合较好。The dynamics model of Long-Range Multiple Launch Rocket System (LRMLRS) is established. The vibration characteristics are studied from three aspects: theory, simulation and test. By using Transfer Matrix Method of Multibody System (MS-TMM), the vibration characteristics of LRMLRS coupled with rigid bodies and flexible bodies are computed. The modal test is carried out. Good agreement is achieved between the results of simulation and experiment.

关 键 词：远程多管火箭炮 传递矩阵法 振动特性 模态试验 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]