反作用射流控制导弹的自动驾驶仪H_∞设计方法  

Blended Aero & Reaction Jet Missile Autopilot Design Using H_∞ Techniques

作　　者：李友年[1] 贾晓洪[1] 王海波[1] 刘忠[2] 

机构地区：[1]中国空空导弹研究院,洛阳471009 [2]西安交通大学机电系,西安710049

出　　处：《系统仿真学报》2005年第7期1771-1773,共3页Journal of System Simulation

基　　金：航空科学基金(03D12004)

摘　　要：空气舵与反作用射流复合控制的导弹,由于侧向喷流与外流场的相互作用,其空气动力学特性比传统空气舵控制要复杂的多,一般难以建立较为准确的数学模型,因此要求其自动驾驶仪具有更好的鲁棒性。用H∞控制理论,对具有这种复合控制的自动驾驶仪进行了设计,通过权函数的合理选择,可以控制空气舵和反作用射流发动机的混合工作方式,同时具有满意的鲁棒稳定性能。仿真结果表明,H∞控制理论用于这类导弹的自动驾驶仪设计是可行的。For a missile under combined aerodynamic surface and reaction jet control ,because of the interaction of the lateral jet flow with the freestream aero-dynamic flow, aero dynamics is much more complex than that of a conventional aero-fin controlled missile. It’s difficult to build a mathematical model which is comparatively acuurate , so its autopilot should be more robust than that of a conventional missile. The use of H∞ control theory was demonstrated to design the longitudinal autopilot for a missile under such blended control. A suitable blended mode and satisfactory robust performances can be gained by appreciate weights. The simulation results show that H∞ control theory is feasible for such autopilot design.

关 键 词：反作用射流控制 复合控制 自动驾驶仪 H∞控制 

分 类 号：TP273.3[自动化与计算机技术—检测技术与自动化装置]