摘要
为了计算再入飞行器的可压流场特性,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再入飞行过程中的气动加热率与气动特性的数值分布,并依据这些数据对再入飞行器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 reentry 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 aerodynamic heating rate and aerodynamic characteristics in the course of reentry flight was presented. Based on these data, integrated optimization design of the trajectory and the overall flight simulation were conducted.
出处
《导弹与航天运载技术》
北大核心
2013年第3期5-8,14,共5页
Missiles and Space Vehicles
关键词
高超声速
再入飞行器
气动热力学
数值仿真计算
轨迹优化
总体飞行仿真
Hypersonic
Reentry vehicle
Aerothermodynamics
Numerical simulation and calculation
Trajectory optimization
Overall flight simulation
