防空导弹大攻角飞行姿态控制系统设计  

Attitude Control for Large Angle-of-attack of Antiaircraft Missile

作　　者：吴催生[1] 张科[1] 田进[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《航天控制》2006年第2期14-16,21,共4页Aerospace Control

摘　　要：针对防空导弹大攻角飞行这样一个非线形、时变、耦合系统,提出了一种基于模型参考时变全程滑态变结构控制方法,分别针对滚动通道、俯仰/偏航耦合通道进行了设计分析,最后进行了六自由度仿真,得到了满意的结果。Based on the time-varying sliding-mode variable structure control theory, a new design method for the nonlinear, time-varying and coupling system of flying phrase with large angle of attack is proposed. Design for roll channel and pitch/yaw coupling channel is also analyzed respectively. Finally, the 6-DOF simulation results prove the outstanding feature of this design.

关 键 词：变结构控制 大攻角飞行 六自由度仿真 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]