摘要
多管火箭系统总传递方程的自动推导和动力学快速计算是多管火箭系统动力学设计的关键。针对某新型多管火箭,建立多管火箭多体系统发射动力学模型及其拓扑结构,根据符号约定和各元件传递方程,建立了某多管火箭系统总传递方程自动推导方法,提高了多管火箭多体系统建模效率和程式化水平。建立了多管火箭系统动力学可视化仿真系统,实现了新型多管火箭动力学快速可视化仿真,并得到了试验验证。为新型多管火箭动力学设计提供了理论基础。
Automatic deduction of overall transfer equation and dynamic rapid simulation for a multiple launch rocket system （MLRS） are the key to its dynamic design. Here, a new type MLRS, its muhibody system launch dynamic model and topological structure were built. According to sign conventions and transfer equations of elements, an automatic method to deduce the overall transfer equation of the new type MLRS was proposed. Its modeling efficiency and programming level were improved. A dynamic visual simulation system for the new type MLRS was established, its launch dynamic behavior was simulated rapidly and validated with tests. The results provided a theoretic foundation for the dynamic design of the new type MLRS.
出处
《振动与冲击》
EI
CSCD
北大核心
2015年第4期30-34,共5页
Journal of Vibration and Shock
基金
高校博士点基金(20113219110025)
国家自然科学基金(11102089
11472135)
国防基础科研计划资助(B2620132013)
新世纪优秀人才支持计划资助(NCET-10-0075)
关键词
新型多管火箭
多体系统传递矩阵法
总传递方程
可视化仿真
new type multiple launch rocket system
transfer matrix method for multibody systems
overall transferequation
visual simulation
