BTT导弹自动驾驶仪的积分LQG控制设计  

BTT Missile Autopilot Design Using Integral LQG Control

作　　者：孙宝彩[1] 林德福[1] 祁载康[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《弹箭与制导学报》2007年第3期18-22,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为实现BTT导弹准确跟踪指令的要求,将LQG积分多变量控制应用于BTT导弹的自动驾驶仪设计中。以某飞机型BTT导弹为例,根据其气动特点建立了俯仰独立、偏航-滚转耦合的气动模型,并分别设计了俯仰及偏航-滚转通道自动驾驶仪,对设计结果进行仿真。仿真表明所设计的自动驾驶仪能够很好地跟踪指令,且具有一定的抗噪声干扰能力。In order to track the command input, the integral LQG multivariable control is used in the BTT missile autopilot design. Take the BTT missile with airplane figure for example, the lateral-roll coupled and pitch self dynamics model was set Up according to the flight condition. Two autopilots were designed and the simulation had been finished. The results showed that the system can track the command accurately and has the capacity to reject noise disturbance.

关 键 词：倾斜转弯导弹 自动驾驶仪 积分LQG控制 卡尔曼滤波器 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]