摘要
以大攻角飞行条件下的防空导弹为研究对象,提出了包含有界干扰输入和不确定性参数的弹体模型,建模分析了测量噪声和舵机随动机构的不确定性,分别应用H∞和μ综合对俯仰通道控制器进行了分析设计,仿真验证了控制器良好的动态性能和鲁棒性能。
With high angle-of-attack of fighting antiaircraft missile as the research object, the missile model with bounded disturbance input and uncertain parameters was proposed, the noise measurement and the uncertainty of actuator servomechanism were analyzed, and H∞ control and μ synthesis was applied in the analysis and design of pitch channel controller. The experimental simulation results verified the good dynamic performances and robustness performance of the controller.
出处
《导弹与航天运载技术》
北大核心
2011年第4期45-48,共4页
Missiles and Space Vehicles
关键词
大攻角飞行
参数不确定性
鲁棒控制
鲁棒性能
High angle-of-attack
Parameter uncertainty
Robust control
Robust performance
