| 1. | One approach consists of varying only the total flow thereby maintaining the same thrust chamber hardware .
有一种方法是仅改变推进剂总流量，而推力室结构保持不变。 |
| 2. | Progress of the composite thruster abroad
国外复合材料推力室技术研究进展 |
| 3. | On optimizing pin - fin shape for efficient cooling of turbine blades
层板发汗冷却推力室的传热特性 |
| 4. | Heat transfer in four parallel connecting thrust chambers with radiation cooling was analyzed
摘要分析了四机?联全辐射冷却推力室的热特点。 |
| 5. | Also , the analysis of the system with only one pair of operating thrust chambers was performed
对仅有两对角推力室工作、另一对推力室不工作时的温度分布特点也作了分析。 |
| 6. | In this paper , the characteristics of tripropellant rocket engine was studied in two different ways : experiment and simulation
本文从实验、仿真两个方面对三组元液体火箭发动机推力室的工作过程进行了研究。 |
| 7. | The result proves that the circular temperature change caused by the radiation between the chambers is mostly decided by the dimensionless distance l / d and is foreign to the original wall temperature
计算表明，推力室之间的辐射传热引起的周向温度畸变，主要取决于推力室间的相对间距l / d ，而与原壁温水平无关。 |
| 8. | As to the simulation , the inner flow field of thrust chamber was simulated . here the thrust chamber was treated as a two - dimension problem . the simulation model involved injection , mixing and combustion of gaseous propellant
仿真方面，对三组元发动机推力室的稳态燃烧过程进行了数值模拟，分析了推进剂各组元和各燃烧产物组分在推力室内的分布。 |
| 9. | The relationship between thermal contact resistance and surface roughness is discussed . the influence of outer space heat flow on spacecraft on the orbit is analyzed , and a balance temperature of spacecraft on the orbit is calculated
通过计算空间外热流对航天器在轨温度的影响，得到航天器在轨平衡温度。最后完成瞬态温度场的模拟计算，对推力室在轨温度进行数值仿真。 |
| 10. | The energy equation of the thrust chamber wall was developed by omitting radical heat conduction and only considering the radiation heat transfer of the four chambers , the radiation leakage through nozzle exit , the axial and circular heat conduction
忽略径向导热，考虑推力室外向的相互及自身辐射交换、内壁经喷口的辐射泄漏以及周向和轴向的传导热量，建立了推力室壁的能量方程。 |
