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.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2005年第7期1771-1773,共3页
Journal of System Simulation
基金
航空科学基金(03D12004)
