面向控制的高超声速飞行器六自由度建模与分析

针对一类三维高超声速飞行器构型，给出了刚体飞行器六自由度模型综合建模法.采用斜激波与Prandtl-Meyer膨胀波关系式等空气动力学理论，计算飞行器机身表面的气动力、控制面受力及推力.采用逐步回归的曲线拟合方法，建立了飞行器面向控制的曲线拟合模型，并分析了六自由度模型的动态特性.结果表明，曲线拟合模型降低了机理推导模型的复杂度，并保留了气动与推进系统的耦合性，为飞行器控制器设计提供依据.

Control-oriented Modeling and Analysis of a Six-DOF Hypersonic Vehicle

For a three-dimensional hypersonic aircraft configuration, a six-degree-of-freedom integrated modeling method for rigid aircraft is presented. Using the mechanism analysis method, the oblique shock and Prandtl-Meyer flow theory and the aerodynamic theory are used to estimate the aerodynamic force, control surface force, and the aircraft thrust. The control-oriented model is established using the curve-fitting method of gradual regression, and the dynamic characteristics of the model are analyzed. The simulation results show that the curve-fitting model reduces the complexity of the mechanism derivation model and retains the coupling characteristics of aerodynamic and propulsion systems, thus providing a basis for aircraft controller design.