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针对吸气式高超声速巡航飞行器发动机进气道关闭、进气道打开、发动机点火工作3个状态下俯仰通道气动系数和配平舵偏角变化大的特点,设计了一种基于参考模型的自适应滑模攻角控制律。在滑模控制中引入了自适应参数调节律来逼近不确定的模型参数变化和外界干扰,有效地改善了飞行器俯仰通道的动态和稳态性能,同时对于气动系数和配平舵偏角的变化具有自适应性。数学仿真结果表明,所设计的控制律具有良好的指令跟踪性能和抗干扰能力。
In view of the characteristics of the aerodynamic coefficient of the pitch channel and the large variation of the trim angle of the aspirated hypersonic cruise vehicle engine with the intake port closed, the intake port opened and the engine being ignited, a design based on reference model Sliding mode angle of attack control law. In the sliding mode control, the adaptive parameter tuning law is introduced to approximate the uncertain model parameter changes and external disturbances, which effectively improves the dynamic and steady state performance of the aircraft pitch channel. At the same time, the change of aerodynamic coefficient and trim angle is Adaptability. The results of mathematical simulation show that the designed control law has good instruction tracking performance and anti-interference ability.