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

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

The automatic deduction method to overall transfer equation and rapid simulation of launch dynamics of Multiple Launch Rocket Systems (MLRS) are the key to the dynamic design of MLRS. For a new type MLRS, the multibody system launch dynamics model and its topological graph are developed. According to sign conventions and transfer equation of elements, an automatic method to develop the overall transfer equations for the new type MLRS is developed. The modeling efficiency and programming level are improved. The visual simulation system for dynamics of MLRS is established, and the launch dynamics are simulated rapidly and validated by test. The theory base for dynamic design of a new MLRS is provided.