| 1. | Genetic algorithm applied to integral design optimization of missile propelled by solid rocket ramjet
固体火箭冲压发动机导弹一体化遗传算法优化设计 |
| 2. | Contrast study on cold - flow mixing effect and combustion efficiency of afterburning chamber of solid rocket ramjet
固冲发动机补燃室冷流掺混效果与燃烧效率对比研究 |
| 3. | The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet
超声速进气道及补燃室的设计与性能研究是固体火箭冲压发动机的两大关键技术。 |
| 4. | During the study of solid rocket ramjet ( srr ) , ablation of afterburner thermal insulation is a serious problem , which cannot be ignored
固冲发动机补燃室绝热层的烧蚀问题是目前固冲发动机研制过程中所面临的一个重要问题。 |
| 5. | As the air - breathing engine , the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant , but also by flight condition
作为吸气式发动机,其性能不仅取决于发动机本身结构和推进剂性能,与飞行状态也有密切的联系。 |
| 6. | For studying the performance of solid rocket ramjet under the influence of different flight conditions , it ' s significant to simulate the integrated flow field of inlet and combustor
因此,开展超声速进气道/补燃室流场一体化数值模拟研究对于考查飞行状态对于火箭冲压发动机性能的直接影响具有重要的现实意义。 |
| 7. | 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。 |
| 8. | The determination of solid rocket ramjet thrust and testing method are the important basis of the developing engine . an experimental program evaluating solid rocket - ramjet in nwpu connected - pipe facility is underway
我国发展中远程、超音速导弹计划已经启动，其动力装置首选固体火箭冲压发动机，而地面试验技术是发动机研究重要基础。 |
| 9. | In order to determination the thrust , the thrust definition and many control parameters are analyzed discussed , which mass flow rate and flight altitude are involved . it is difficult to measure the flight thrust of solid rocket ramjet directly
通过讨论高空飞行推力与地面可测试参数的关系，得到了固体火箭冲压发动机高空飞行状态下推力折算方法，并开发相应的计算程序。 |
| 10. | 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。 |
