摘要
建立了空气动力和姿控发动机推力复合控制弹体的数学模型,为理论弹道和控制弹道的计算提供了参考;同时采用小扰动法推导了俯仰通道和滚动通道的简化模型,为空气动力和姿控发动机推力复合控制系统进行初步设计提供了依据。
Mathematical model of missiles of aerodynamics and attitude control engine compound control is presented, which provides reference for the calculation of theoretical trajectory and controlled trajectory ;What＇s more, according to the method of little disturbance ,the simplified model of pitching and rolling plane is derived, so preliminarily combined control system can be designed.
出处
《现代防御技术》
北大核心
2005年第6期43-46,共4页
Modern Defence Technology
关键词
姿控发动机
复合控制
数学模型
Attitude control engine
Compound control
Mathematical model
