By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
The Doppler Radar data fitting method of the first flight segment trajectory in a free flight test of rocket assisted and base bleed projectiles was presented.
提出了复合增程弹起始飞行段弹道多普勒雷达数据拟合方法。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
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