临近空间飞行器基于气动力热约束的飞行轨迹控制优化研究

Trajectory Control Optimization Study of Near Space Vehicle Based on Aerodynamic Thermal Constraints

采用计算流体力学(CFD)方法获得不同工况下飞行器流场的气动特性。通过对多个工况点下流场热力学状态的分析与对比,给出高超声速飞行器飞行过程中的热流密度、温度场与气动特性的数值分布,并依据这些数据对飞行器的上升段、巡航段和俯冲段进行飞行轨迹的一体化优化设计与总体飞行仿真。

The aerodynamic characteristics of flight vehicle flow field under different working conditions were obtained with computational fluid dynamics （CFD）. Through analysis and comparison of flow field thermodynamic state under multiple operating points, the numerical distribution of the heat flux value, temperature field and aerodynamic characteristics in the course of hypersonic flight was presented. Based on these data, integrated optimization design of the trajectory and the overall flight simulation were conducted for the ascent stage, cruising stage and diving stage of the vehicle.