摘要
针对传统的侧滑转弯(STT)控制机动能力相对不高和倾斜转弯(BTT)控制在机动上有一定的时延等缺点,以空射导弹为例,将导弹的飞行过程划分为三个阶段,采用混合BTT/STT逻辑将导引头输出的过载信号转换为攻角、侧滑角和滚转角指令信号,并且分别设计了导弹俯仰-偏航通道和滚转通道滑模变结构控制器,使其能够准确跟踪给定的攻角、侧滑角、滚转角指令。为了减小变结构控制器的抖振影响,采用了将切换控制连续化的方法。最后通过仿真验证混合BTT/STT控制逻辑的可行性和变结构控制器设计的有效性。
To solve the problems that traditional skid-to-turn（STT） control can not perform high g maneuvers and bankto-turn（BTT） control do not have satisfied response time, three phases are divided appropriately during the missile flight. Hybrid BTT/STT control logic is applied during these phases to transform accelerations to commands of angle of attack, sideslip angle and bank angle. Variable structure methodology is applied in designing of pitch-yaw channel and roll channel controllers aiming to track command signals. With the purpose to reduce chattering, continuous switch control is adopted. Finally, simulation results proved the feasibility of hybrid BTT/STT control logic and the validity of the controllers.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第1期23-26,30,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
