摘要
基于线性系统特征结构配置和模型跟踪方法 ,以及优化工具 ,提出了可以有效抑制抖动的多模型切换控制策略 ,并用该策略设计了 BTT导弹俯仰 /偏航通道的自动驾驶仪。在导弹的整个飞行轨道上选取了若干点 ,分别建立起描述 BTT导弹俯仰 /偏航运动的线性时不变数学模型。对各个线性时不变模型 ,分别用特征结构配置方法设计反馈控制器对系统进行镇定。为了使导弹过载跟踪制导指令 ,又基于模型跟踪方法设计了前馈控制器。当导弹跨越不同特征点区域时 ,控制器要进行切换。为了减小切换时的抖动 ,针对切换后的特征结构配置反馈控制器 ,利用优化工具合理选取其自由度。仿真结果表明 ,所提出的方法令导弹的输出过载准确跟踪制导指令 。
Based on the eigenstructure assignment and model following theories for linear systems, and the optimization tool, a multi model switching control policy with the capability of chattering attenuation is proposed, and applied to the pitch/yaw channel autopilot design of BTT missile. Several characteristic operating points are selected along the missile's whole flight trajectory, and the time invariant systems, which describe the pitch/yaw motion of BTT missile, are then set up. For each time invariant system, based on the eigenstructure assignment method, a feedback controller is designed to stabilize it, and a feedforward controller is designed by using the model following method, so that the closed system is able to track the guidance command. While the missile's flight state comes from the neighborhood of an operating point into that of the next one, the controller switches from one into another. Because of the abrupt variation of the controller, chattering is inevitable in the switching process. The authors treat the difference of the two system's outputs on a switching point as the evaluation index, and expect to attenuate the chattering by selecting the degree of freedoms of the controller. Simulation results demonstrate the validity of the proposed method in command tracking and switching chattering attenuation.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2002年第3期268-271,共4页
Acta Aeronautica et Astronautica Sinica
