摘要
为提高大攻角飞行时具有非线性特性的姿态系统的控制精度,在弹头俯仰运动的非线性数学模型基础上,以弹头攻角为被控制信号,尾翼偏角指令为输入信号,设计了一种全状态反馈非线性姿态控制律,并进行了仿真试验。结果表明,所设计的控制律的稳态精度高、动态响应快。
To improve the control precision of attitude system with nonlinear characteristic in large angle of attack flying, a nonlinear full state attitude control law was designed based on the nonlinear model of pitch motion for reentry missile in this paper, in which the angle of attack was served as the output and command of the tail fin deflection as its input. The analysis of simulation results showed that the control law designed had high steady precision and fast dynamic response.
出处
《上海航天》
北大核心
2006年第1期8-11,共4页
Aerospace Shanghai
基金
航天支撑技术基金03HG01
关键词
再入弹头
姿态控制
俯仰运动
非线性控制律
攻角
尾翼偏角
Reentry missile
Attitude control
Pitch motion
Nonlinear control law
Angle of attack
Tail fin deflection
