中文摘要：

研究了一种大升阻比的高超声速飞行器的再入制导问题．应用基于特征模型的自适应控制理论，提出了一种跟踪参考阻力加速度的制导方法，同时通过跟踪飞行方位角，来修正飞行器侧向航程．这种基于特征模型的自适应控制方法不需要通过数据拟合来获得气动升力与阻力的解析表达式，克服了飞行器在再入飞行中，气动数据不断变化时造成的困难．通过跟踪飞行方位角来修正倾斜角指令，可以获得比倾斜角翻转方法更精细的对侧向航程的控制能力．六自由度仿真结果表明，文中设计的制导方法可以达到调整侧向航程的目的，但其代价是损失总航程．

英文摘要：

A novel drag acceleration tracking guidance law is proposed for a hypersonic reentry vehicle with high lift-drag ratio. By applying the characteristic model-based adaptive control method, a drag acceleration tracking guidance method is proposed together with a flight azimuth angle tracking used to modify lateral distance. The characteristic model-based adaptive control method do not need the analytical form of the aerodynamic lift and drag forces, which are often obtained by curve fitting of the trimmed flight data. This is especially advantageous when the reentry vehicle makes a flight through a large regime and the aerodynamic parameters vary greatly. The flight azimuth angle tracking command is used to modify the banking command, thus changing the lateral distance slightly without bank reversal. Six degree-of- freedom simulation results demonstrated that the guidance law proposed in this paper is effective but at the cost of the loss of total distance.