In order to deal with uncertain parameters of a general hypersonic vehiclet longitudinal movement control law is designed based on the theory of simple adaptive control. How to establish a longitudinal movement model and a reference model and how to design adaptive control law with adaptive control theory are illustrated. Numerical simulation is done to validate robustness of the flight control law. Simulation results show that the control performance can satisfy with adaptively regulate control coefficients due to the errors of the outputs between the refernce model and the hypersonic vehicle. This method is effective and dealt with the problem of uncertain parameters preferably.%针对高超音速飞行器飞行控制中被控对象模型参效不确定性的特点,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.
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