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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。
Aiming at the separate mission of the aspirated hypersonic vehicle, the movement and force characteristics of the aircraft during the separation process are analyzed. Based on the dynamic characteristics, the separation process is decomposed into different sub-flight segments. Based on the dynamic characteristics of the sub-flight segments and the requirements of the separation conditions, the control requirements and strategies in the separation process are proposed, and the vertical three-DOF separation flight Dynamics and Control System Simulation Mathematical Model. As a verification, taking the X-43A hypersonic vehicle separation test as an example, the interstage separation process was simulated by Matlab / Simulink. The simulation results show that the time response of aerodynamic coefficient, the time response of the kinematic parameters and the dynamic process of the control surface can all reflect the characteristics of the separation motion reasonably. The established simulation model of the separation flight dynamics and control system has practical Meaning, to achieve the successful separation of two-stage aircraft.