摘要
为了减小脉冲发动机工作时喷流与外流场对弹体和气动舵面产生的耦合作用,提高气动力/直接力复合控制系统的性能,文中提出一种气动力/直接力切换控制方案,即在导弹末端攻击目标时断开气动力控制回路,只用直接侧向力控制。采用变结构控制设计飞行控制系统,实现气动力与直接力的平滑切换。数字仿真结果表明该方法能有效地提高导弹自动驾驶仪的快速性、鲁棒性,减小直接力机构与气动舵面之间的操纵耦合,显著改善导弹的脱靶量。
In order to reduce the coupling function which produces to the body and the air operated rudder of missile by the pulse engine and the outflow field, and improve the system of performance of aerodynamic/reaction-jet when the pulse engine works. This paper proposed one kind of switching-control project of aerodynamic/reaction-jet, which only uses the direct side force and cut off the aerodynamic control loop at the end of attacking. Using variable structure control design flight control system, and realizes the smooth switch between aerodynamic and jet. Digital simulation results indicated that the method can improve the missile autopilot rapid, robust and effectively reduced the operation coupling between the direct force organization and the aerodynamic control surface, significantly improved the missile＇s miss distance.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第2期83-86,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
气动力/直接力复合控制
侧向喷流
非线性
变结构控制
aerodynamic/reaction-jet multi-controller
lateral jet
nonlinear
variable structure control
