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为了给高超声速轨迹预测问题提供先验知识,研究了面向轨迹预测的高超声速飞行器气动性能分析问题。首先,简要介绍了高超声速再入滑翔飞行器的基本性能,从拦截的角度分析了对其滑翔段进行轨迹预测的必要性。其次,以HTV-2为例,采用斜激波理论、活塞理论、Prandtl-Meyer方程及粘性力工程计算方法对临近空间高超声速环境下飞行器的受力情况进行了分析建模。然后,对目标机动性能进行了仿真分析,仿真结果与相关文献报道较一致,证明了建模仿真方法的可行性。最后,基于以上建模仿真,给出了一组适用于临近空间高超声速飞行器滑翔段目标跟踪和轨迹预测的气动参数,并进行了仿真验证,为下一步研究基于拦截的高超声速飞行器轨迹预测提供了理论基础和方法指导。
In order to provide a priori knowledge of hypersonic trajectory prediction problems, the aerodynamic performance analysis of hypersonic vehicles with trajectory prediction is studied. First of all, the basic performance of hypersonic reentry gliding aircraft is briefly introduced. The necessity of trajectory prediction of gliding section is analyzed from the perspective of interception. Secondly, HTV-2 is taken as an example to analyze and model the force of the aircraft under the hypersonic environment with the oblique shock theory, piston theory, Prandtl-Meyer equation and viscous force engineering method. Then, the simulation of the target maneuverability is carried out. The simulation results are consistent with those reported in the relevant literature, which proves the feasibility of the modeling and simulation method. Finally, based on the above modeling and simulation, a set of aerodynamic parameters suitable for the target tracking and trajectory prediction of the gliding segment of the near-space hypersonic vehicle are given and verified by simulation. These aerodynamic parameters are provided for the future research of intercept-based hypersonic vehicle trajectory prediction The theoretical basis and methodological guidance.