| 1. | Application of plif in research on supersonic combustion
平面激光诱导荧光技术在超声速燃烧中的应用 |
| 2. | Preliminary experimental investigation on supersonic combustion phenomena with shocktunnel
激波风洞中超声速燃烧现象的初步实验研究 |
| 3. | By simulated supersonic combustion in ‘ double - chamber ’ , wall - pressure value is compared with experimented data . the simulated values accord well with experimented data
通过对“双燃室”结构的数值模拟,将壁面压力值与实验值对比,其计算值较好地符合了实验值。 |
| 4. | Combustion with releasing heat effectively in supersonic flow is one of the most important , as well as the most difficult , technologies in researching and developing supersonic combustion ramjet
超音速流动状态下的高效燃烧过程是研制超燃冲压发动机最重要也是难度最大的关键技术之一。 |
| 5. | To analyze particularly the shear flow and chemical reaction procedure occurred in supersonic turbulent combustion field , supersonic combustion mechanism is surveyed on by reading papers thoroughly
为细致分析超音速湍流燃烧流场的剪切流动及化学反应过程,针对超音速燃烧机理进行了深入的文献调研。 |
| 6. | The domestic research plan has been proposed and undertaken in nowadays . the progress in subsonic and supersonic combustions has been attained , but the ejecting mode and mode match of rbcc has just been begun
国内已制定了研究计划并正在开展，其中亚燃和超燃模态的研究取得了相当的进展，但引射模态以及模态匹配的研究还刚刚起步。 |
| 7. | The flame holding technology based on cavity in supersonic combustion was studied systematically and comprehensively . the interaction between gas / liquid injection and cavity flow were studied in non - reaction flows
论文选取基于凹腔的超声速燃烧火焰稳定技术为研究对象,对凹腔燃烧流动过程和凹腔火焰稳定器性能进行了全面深入研究。 |
| 8. | In the range of flight mach number mo = 3 ~ 7 , in order to take the advantage of ramjet and scramjet , a fix - shaped dual - mode scramjet , in which both subsonic and supersonic combustion can be obtained , is used for hypersonic vehicle
在飞行马赫数m _ = 3 - 7的范围内，为充分发挥冲压发动机的性能优势，高超声速飞行器采用了既能在亚声速燃烧模态，又能在超声速燃烧模态下工作的固定几何形状的双模态冲压发动机。 |
| 9. | Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system , called rocket - based - combined - cycle ( rbcc ) , which has multiple operating woke modes , including ejecting , subsonic combustion , supersonic combustion and rocket mode , with each mode operating at varying flying stage . rbcc has prominent potential of high efficiency and low cost , and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile . it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage
火箭基组合动力循环( rbcc ， rocketbasedcombinedcycle )将传统的火箭发动机和吸气式发动机的优点集中组合到一个具有多种工作模态(包括引射、亚燃、超燃及火箭模态)的发动机里，在不同的飞行阶段启用不同的工作模态，因此具有大幅提高航天推进系统经济性与高效性的潜在优势，并可能发展成为下一代单级可重复使用航天器以及高超声速导弹武器的动力系统。 |
