变化风场下近空间飞行器机体/发动机一体化飞行力学建模与分析

Flight Dynamics Modeling of Airframe/Engine Integrated Near Space Vehicle in Varying Wind Field

近空间飞行器飞行包络大、环境变化复杂、参数变化激烈,对其开展飞行控制技术研究工作的首要问题是对此复杂系统基本物理规律准确把握和描述,并依此建立其机理运动模型。针对机体/发动机一体化设计的近空间飞行器,系统地进行了飞行力学分析,并推导了变化风场下近空间飞行器在高超声速条件下的完整的6-自由度12-状态的动力学方程和运动学方程,体现出变化风场的影响和推力矢量的作用。随后,对其在不同条件下的开环控制特性进行了仿真研究,直观表现了系统的快时变、强耦合、强非线性和不确定性等特点。所得结果可用于未来高超声速飞行器轨迹管理、飞行控制等问题的概念设计和仿真研究。

The first question of flight control design for near space vehicle （NSV） is to describe its characteristics of motion and to build a kinematic model. An airframe/engine integrated designed hypersonic NSV is studied in this paper. First, the flight mechamics of NSV is systematically analyzed and then a set of six-degree-of-freedom twelve-state equations are derived to describe the motion of NSV under the condition of varying wind field and thrust vector control. After that, the open-loop control characteristics at different conditions are studied by simulation analysis. It is demonstrated that the characteristics of the developed model, such as serious nonlinearity, fast time-variying, intense coupling and strong uncertainty. The model can be used in the study of conceptual design and flight control for new generation hypersonic vehicle.