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.
出处
《振动与冲击》
EI
CSCD
北大核心
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
关键词
远程多管火箭炮
传递矩阵法
振动特性
模态试验
Experiments
Matrix algebra
Missile launching systems
Modal analysis
Models
Theory
Vibrations (mechanical)
