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针对高超音速飞行器飞行控制中被控对象模型参数不确定性的特点,应用简单自适应控制方法设计其纵向控制律。论述高超音速飞行器纵向运动的动力学模型和参考模型的建立,以及基于此参考模型用简单自适应理论设计飞行控制律的方法,并且通过数值仿真进行鲁棒性能验证。仿真结果表明,所设计的控制律可以根据参考模型与实际系统输出之差自适应地调节控制增益,对模型参数不确定性具有较好的抑制作用,设计方法可行。
Aiming at the characteristics of the uncertainty of the model of the hypersonic vehicle in the flight control, a simple adaptive control method is used to design its longitudinal control law. The establishment of dynamic model and reference model for the longitudinal motion of hypersonic vehicle and the design of flight control law using simple adaptive theory based on this reference model are discussed. The robust performance is verified by numerical simulation. The simulation results show that the designed control law can adjust the control gain adaptively according to the difference between the reference model and the actual system output, and has a good restraining effect on the model parameter uncertainty. The design method is feasible.