吸气式高超声速飞行器分离动力学建模及仿真

Modeling and simulation of air-breathing hypersonic vehicles separation dynamics

针对吸气式高超声速飞行器的分离飞行任务,分析了分离过程中验证飞行器的运动及受力特点。基于动力学特点,将分离过程分解为不同的子飞行段,并根据子飞行段的动力学特征及分离条件要求,提出了分离过程中的控制需求及策略,建立了飞行器纵向三自由度分离飞行动力学与控制系统仿真数学模型。作为验证,以X-43A高超声速飞行器分离试验为例,对其级间分离过程进行Matlab/Simulink仿真分析。仿真结果与高阶系统仿真结果进行比较后表明,飞行器气动系数时间响应、运动参数时间响应以及控制面动态过程均能合理体现分离运动的特征,建立的分离飞行动力学与控制系统仿真模型有实际意义,能够实现两级飞行器的成功分离。

This paper presents a dynamic and control simulation model for air-breathing hypersonic vehicle in separation flight phase. The HXRV＇ s （ Hyper-X research vehicle） motion and force characteristics are analyzed. The control requirements are examined and control strategies are discussed in separation phase. Consequently, the 3-DOF flight dynamic and control system model of HXRV longitudinal separation was established on the basis of analyzing the force characteristics and the control strategies. As demonstration, the simulations of the model in the Matlab/Simulink environment were implemented for the X-43A. Simu- lation results of the study were compared with the simulation results obtained from the high DOF system. The comparison indicates that the time response of aerodynamic coefficients, motion states and the dynamic processes of control surface can reasonably reflect the features of the movement of HXRV in separation phase. The findings show that the proposed model is practical.