中文摘要：

针对高超声速飞行器纵向模型具有非线性、强耦合及不确定性等特点,提出高超声速飞行器建模与控制一体化设计方法。该方法首先以具有典型结构的高超声速飞行器几何外形为研究对象,结合高超声速空气动力学的有关理论,建立飞行器的非线性纵向模型方程;然后在不同飞行条件下获取多个平衡点,分析飞行的气动特性,进而在每一个平衡点上设计具有非线性解耦控制能力的控制器,并将得到的多平衡点控制参数结合起来,进行插值计算,实现多平衡点的连续飞行;最后的仿真结果表明,本文提出的方法是切实可行的。

英文摘要：

Since hypersonic vehicle involves characteristic of nonlinearity, strong coupling,uncertainty and so on, the method of integrated design on the modeling and control for hypersonic vehicle is proposed. This method first regards geometrical shape with typical structure of hypersonic vehicle as research object, and establishes vehicle＇ s nonlinear longitudinal model equations combining with the theories of hypersonic aerodynamics; Then gets several trim points at various flight conditions, and analyzes flight aerodynamic characteristics, further designs the controller with nonlinear decoupling control ability in each trim point, and integrates controls parameters obtained of several trim points, thereby realizes non-stop flight in several trim points by interpolation calculation; Finally, the simulation results show that the method introduced in this paper is feasible.