CAJ | 학술논문

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。
다관화전계통총전체방정적자동추도화동역학쾌속계산시다관화전계통동역학설계적관건。침대모신형다관화전，건립다관화전다체계통발사동역학모형급기탁복결구，근거부호약정화각원건전체방정，건립료모다관화전계통총전체방정자동추도방법，제고료다관화전다체계통건모효솔화정식화수평。건립료다관화전계통동역학가시화방진계통，실현료신형다관화전동역학쾌속가시화방진，병득도료시험험증。위신형다관화전동역학설계제공료이론기출。
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 multibody 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.