多管火箭总传递方程自动推导和动力学可视化仿真方法研究  

Automatic deduction for overall transfer equation of a multiple launch rocket system and its dynamic visual simulation method

作　　者：辛松[1] 芮筱亭[1] 芮雪[1] 张建书[1] 王国平[1] 

机构地区：[1]南京理工大学发射动力学研究所,南京210094

出　　处：《振动与冲击》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)

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.

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 

分 类 号：TB122[理学—工程力学] TB124[理学—力学]