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1.Advances in Solid Rocket-Ramjet Engine
固体火箭-冲压发动机的研究进展收藏指正
2.This paper established the mathematical models of integral solid rocket ramjet, aerodynamics and trajectory, and wrote the corresponding C++ code.
本文建立了固体火箭冲压发动机性能计算、导弹气动性能计算和弹道仿真分析等分系统的数学模型，并编制了相应的C++计算程序模块。收藏指正
3.Three-dimension reaction flow-field of secondary combustion for solid rocket ramjet is numerically calculated by using k-ε two-equation model and EBU combustion model.
用k ε湍流模型以及EBU燃烧模型,对固体火箭冲压发动机二次燃烧三维反应流场进行了数值计算,研究了空气射流与富燃燃气射流动量之比、射流速度和燃气发生器喷管数量对二次燃烧的影响。收藏指正
4.In addition, the USAF continues to fund development work of the Aerojet (formerly Atlantic Research) Variable Flow Ducted Rocket ramjet system as a future propulsion option for an extended range AAM.
此外，美国空军继续投资于航空喷气研究所（原来的大西洋研究所）的可变喷流管火箭发动机系统，将其作为增程空空导弹的未来推进选项。收藏指正
5.With zonal patched grid technology and second-order zonal solver method, the numerical simulation on inlet complex flow field of solid rocket ramjet assisted range projectiles with different struts shapes was made at different Mach numbers.
摘要结合分区对接网格技术和二阶精度区域分解算法，对某冲压增程弹丸进气道在不同来流攻角和不同侧向支柱形状工况下的内外复杂流场进行了数值模拟。收藏指正
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