应用现代控制理论研究BTT导弹自动驾驶仪  

MODERN CONTROL THEORY FOR STUDY OF AUTOPILOT FOR BANK-TO-TURN MISSILE

作　　者：李秋月[1] 李忠应[2] 

机构地区：[1]中国航天工业总公司第三研究院 [2]北京航空航天大学

出　　处：《战术导弹技术》1996年第1期1-9,共9页Tactical Missile Technology

摘　　要：用现代控制理论中的状态空间法来研究倾斜转弯导弹自动驾驶仪。该方法适用于俯仰和偏航轴之间由于高速滚动产生的陀螺和哥氏加速度交联耦合。设计时假定滚动速率保持恒定但不等于零,从而使自动驾驶仪俯仰和偏航通道之间的交叉耦合取决于滚动速率。自动驾驶仪的增益设计成滚动速率和动压的函数,用最小二乘法曲线拟合,为每个增益选择数学模型。The state-space techniques of modern control theory are used to develop a methodology for the design of autopilots for bank-to-turn missiles. The methodology accommodates the gyroscopic and coriolis cross-coupling between the pitch and the yaw axes that result from the high roll rates that may be present. The design assumes that the roll rate is constant but not zero, and it results in an autopilot structure in which there are cross-couplings between the pitch and yaw channels that are dependent on the roll rate. The autopi- lot gains are scheduled as functions of the dynamic pressure and the roll rate, the model is selected for each gain by a least squares curve fitting.

关 键 词：导弹 自动驾驶仪 调节器 控制理论 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]