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高超声速飞行器的动力学建模对于进行控制系统的设计和仿真来说是非常重要的。与传统的飞行器相比,由于其飞行的速度和高度跨度大、变化快,高超声速飞行器的飞行动力学特性相当复杂。为了研究高超声速飞行器的一些本质的动力学特性,选择再入段进行分析,建立了再入段的高超声速动力学模型。利用风洞实验数据,建立了空气动力学数据库,并且对模型进行了不确定性分析。在模型的基础上,讨论了高超声速飞行器再入段的控制系统的设计方法。最后,在MATLAB/SIMULNK中进行了控制系统仿真,仿真结果表明在60公里到着陆点控制系统能够很好地控制动力学模型跟踪制导指令。
Dynamic modeling of hypersonic vehicles is very important for the design and simulation of control systems. Compared with the traditional aircraft, the flying dynamics of the hypersonic vehicle is rather complicated due to its large and fast flight speed and altitude. In order to study some essential dynamic characteristics of the hypersonic vehicle, the reentry section was selected for analysis, and the hypersonic kinetic model of the reentry section was established. Using the wind tunnel experimental data, an aerodynamic database was established and the uncertainty analysis of the model was carried out. Based on the model, the design method of control system of hypersonic vehicle reentry section is discussed. Finally, the control system simulation is carried out in MATLAB / SIMULNK. The simulation results show that the control system can control the kinetic model tracking and guidance commands well from 60 km to the landing site.