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中文摘要：
针对高超声速飞行器再入过程中强耦合、大扰动和大范围变化的气动参数的问题，基于特征建模的思想，分析动力学方程的耦合特点，采用分散控制的方案，把原非线性动力学方程用一个二阶时变差分方程组形式的特征模型描述，建立了攻角、侧滑角和滚转角三通道特征模型，并给出了黄金分割自适应的姿态控制方法．最后，针对类X-20高超声速飞行器进行数值仿真，仿真结果充分验证了这种自适应控制器的有效性．
英文摘要：
In response to the difficulties such as strong coupling effect, drastic variation of flight environment, and large uncertainty of aerodynamic forces and external disturbances in the course of reentry of hypersonic vehicles, the coupling property of plant is analyzed, a decentralized control scheme is adopted and the original nonlinear dynamics model is described as a set of characteristic models comprised of the angle of attack, sideslip angle and roll angle channels. Moreover, a golden section adaptive attitude controller is presented. At last, some simulations for the X-20-like hypersonic vehicle are given to fully verify the effectiveness of this method.
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