摘要
概述了弹射装置的组成、结构及其工作过程 ,将其物理模型进行简化 ,以气压传动动力学、机构动力学和流体力学为理论基础 ,建立了描述高压氮气驱动下弹射装置运动的数字仿真模型 .求得了弹射装置的动特性参数随时间的变化规律 ,对导弹俯仰角、俯仰角速度的控制原理和方法进行了研究 ,并分析了氮气作动筒、弹射连杆机构、导弹的结构参数。
Construction and working principle of a missile launcher is first conducted. A physical and mathematical model is developed for describing nitrogen launching system (NLS) based on the dynamics of pneumatics and mechanisms, and a digital simulation program is set up to analyze dynamic performance of NLS. A new method is given to control and calculate the pitching angle and pitching velocity. The paper also analyzes the effects of the total displacement, the diameter of synchronous, the flow coefficient of pneumatic cavity on dynamic performance of NLS.
出处
《弹道学报》
EI
CSCD
北大核心
2001年第4期17-23,共7页
Journal of Ballistics
