摘要
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。
Flight dynamics modeling of hypersonic vehicles is of prime importance for the design and simulation of control system. Hypersonic vehicles feature unique and complex flight dynamics characteristics due to variations of wide speed and altitude range, which are not existent with conventional airplanes. The purpose of this research is to model a hypersonic vehicle in the reentry phase and provide an insight into the inherent dynamics. Based on data acquired from tunnel, an aerodynamic database was built. The uncertainty of model was discussed. Furthermore, the design method of control system was introduced Finally, nonlinear simulations of a control system using MATLAB/SIMULINK show that the designed control system can track attitude demands from 60 kilometer to landing site.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2009年第2期534-537,共4页
Journal of System Simulation
