摘要
弹道导弹在助推段需要滚动突防,减少强激光照射的驻留时间,可以有效地对抗激光反导,但姿态稳定的实现则有很大的不同。利用经典控制理论和多变量频域理论设计了导弹的自动驾驶仪,仿真结果表明,对静不稳定导弹的一级助推段可以实现低滚速下的稳定飞行。
To survive the laser's attack, ballistic missiles can spin to reduce the dwell time of the beam at a particular point on the missile. The realzation of stability is different from before. We design the missile's autopilot by the method of classical control theory and MFD technology. The simulation result shows that the unsteady aerodynamic ballistic missile can fly stablly at the low spinning rate during the first boosting phase.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2004年第2期9-12,共4页
Journal of National University of Defense Technology
关键词
弹道导弹
助推段
滚动
突防
ballistic missile
boost phase
spinning
penetration
