And then, as now, the heart of the system will remain the thrust chamber.
然后，和现在一样，系统的核心仍将是推力室。
Operating process of thrust chamber in spacecraft propulsion system is studied.
研究了飞船推进系统推力室工作过程。
Some propellant droplets may not evaporate within the confines of the thrust chamber.
有些推进剂可能在推力室内并未汽化。
A sample of rocket engine thrust chamber with cooling channels was successfully manufactured by APEF.
成功制造出带冷却通道的火箭发动机推力室身部样件。
The properties of additive methyl silicone and the mechanism of heat flux reduction in the thrust chamber are described.
叙述了添加剂——甲基硅酮的性质和用添加剂降低推力室热流强的机理。
Our discussion here, however, will be concerned with more basic aspects of those engines-in particular, the rocket engine thrust chamber.
我们这里的讨论，不过，将关注更多的基本方面，这些引擎-尤其是，火箭发动机推力室。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
建立了单组元发动机推力室系统（包括结构部件如隔热框、催化床、喷管等）的传热模型。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrust chamber.
液体火箭发动机发汗冷却推力室的结构层板可能出现受热皱损。
According to this can be compiled general program and has been calculated unsteady temperature history for any thrust chamber with radiation cooling.
据此编制通用程序，可以计算任意辐射冷却推力室的不稳定温度场。
A new calculation method was proposed for the typical structure of the platelet transpiration flux in the rocket thrust chamber based on the test data of another chamber.
针对典型的层板发汗冷却结构，提出了利用一个推力室的实验数据来计算另一推力室所需发汗流强的方法。
To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber, a method of computing temperature field in thrust chamber was developed.
为了能够快速而准确地得到再生冷却推力室的温度分布，建立了一种计算再生冷却推力室温度场的方法。
Then using this method, influence of gas wall material, gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber was investigated. The results were satisfactory.
然后使用这种方法研究了气壁材料、气壁厚度和冷却液流量对推力室再生冷却的影响，获得了比较满意的结果。
The chamber successfully achieved a full thrust of 100000 Ibf.
腔室成功达到了100000 Ibf 的全推力。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
When the coil power, the pilot valve by the spring return, pilot hole closed throttle valve chamber pressurized by the piston return spring and thrust, the electromagnetic valve is closed.
当线圈断电时，先导阀芯靠弹簧复位，先导孔关闭，阀腔由活塞节流孔增压和复位弹簧的推力，电磁阀关闭。
Normally Open: When the coil is energized, the pilot hole closed, the valve chamber and pressurized by the piston return spring throttle thrust, the electromagnetic valve is closed.
常开：当线圈通电时，先导孔关闭，阀上腔由活塞节流孔增压和复位弹簧的推力，电磁阀关闭。
When the coil power, the pilot valve by the spring return, pilot hole closed, the valve chamber and pressurized by the piston return spring throttle thrust, the electromagnetic valve is closed.
当线圈断电时，先导阀芯靠弹簧复位，先导孔关闭，阀上腔由活塞节流孔增压和复位弹簧的推力，电磁阀关闭。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
本文讨论了单室双推力星形装药固体火箭发动机的结构优化方法。
The main four-chamber engines designed by V. P. Glushko and new control engines from s. P. Korolev for controlling the thrust vector were installed in these units.
这些子级上安装了瓦·彼·格鲁什科设计的四推力室主发动机和谢·帕·科罗廖夫设计的用来控制推力矢量的新型姿态控制发动机。
As the length of secondary combustion chamber increases, the thrust, specific impulse and combustion efficiency increase respectively.
随着补燃室长度的增大，发动机推力、比冲和燃烧效率均提高。
As the length of secondary combustion chamber increases, the thrust, specific impulse and combustion efficiency increase respectively.
随着补燃室长度的增大，发动机推力、比冲和燃烧效率均提高。
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