喷管是激光推力器的重要组成部分。
The nozzle is one of the most important parts a laser thruster .
该塞式喷管基本上体现了塞式喷管的优点。
This type of plug nozzle embodies the main advantages of plug nozzles.
接上压井和放喷管线。
首次得到喷管侧向推力随压强和时间变化的曲线。
At last, changeful curves of thrust misalignment followed pressure and time are obtained.
尤其是喷管平衡流的计算方法文中作了详细的阐述。
The calculating method of equilibrium flow in nozzle is described ein detail.
喷管声导纳的数值计算结果与实验测得的结果非常吻合。
Numerial results of nozzle acoustic admittance is in found to be in good agreement with experiment results.
这台发动机由一个进气道，一个燃烧室和一个尾喷管组成。
This engine consists of an inlet, a combustor, and a nozzle .
强调最小喷管长度转向采用锐边喉管道的喷管设计的极限值。
The emphasis on the minimum nozzle length was carried to the limit with the design of nozzle with sharpedged throats.
固体火箭发动机喷管的烧蚀预示是喷管结构分析的重要一环。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.
防喷管组合的上部包括一个高压的润滑脂注入部分和密封元件。
The top of the lubricator assembly includes a high-pressure grease-injection section and sealing elements.
对大型运载火箭的固体助推器，通常采用摆动喷管推力向量控制。
The deflecting nozzle thrust vector control is usually used in a large solid booster.
推进剂的燃烧特性及喷管堵盖打开压强对点火升压过程有较大影响。
Propellant property and nozzle closure opening pressure have an important effect on the ignition transient.
钟的发动机喷管，这是加工从单一的一块钢，可见在尾部结束火箭。
The bell of the motor nozzle, which was machined from a single piece of steel, is visible at the aft end of the rocket.
另外，本文还讨论了新型喷管设计理论、思路和工程化等相关问题。
Furthermore, some related topics about nozzles design and engineering also have been discussed.
本文提供了考虑化学反应非平衡和振动非平衡的喷管流动计算方法。
This paper presents a calculating method about the nozzle flow that considers chemical nonequilibrium and vibrational nonequilibrium.
用有限元素法数值模拟了固体火箭发动机喷管内缝隙的流场和热环境。
The flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.
重点对喉部引射主喷管和燃料副喷管的不同结构、滞止参数进行探讨。
The discussing emphases are structural and stagnation parameters of ejecting nozzles and secondary fuel nozzles.
通过计算温度场和应力场，分析了喷管在发动机工作过程中的结构完整性。
Structure integrality of nozzle during the working process of motor was analyzed by calculating temperature field and stress field.
研究结果表明，喷管内的分离激波是影响轴对称矢量喷管性能的重要因素。
The investigation shows that the separation shock wave gives an important effect on internal performance of axisymmetric vectoring nozzle.
这些结果为HYTEN喷管的工程设计、优化和概念验证提供了基本的物理图像。
All these results have provided physical vision for engineering design, optimization and concept verification of HYTEN nozzle.
本工作是用作者提出的迎风格式计算轴对称喷管的定常超音流动问题的一个尝试。
This paper is on an application of the upwind difference scheme proposed by the author in a previous paper.
开展了高压强条件下的喷管烧蚀试验研究，揭示了压强对喷管烧蚀率的影响规律。
The relation between pressure and instantaneous linearity erosion rate was obtained through nozzle ablation experiments under high pressure.
为了了解塞式喷管性能，采用固体推进剂对塞式喷管单元发动机进行了模拟实验。
To find out the performance characteristic of aerospike nozzle, the simulated tests were a aerospike engine unit using solid propellant.
最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。
Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.
而冲量耦合系数对点火区与聚光系统内表面的距离及喷管长度等参数并不十分敏感。
And the impulse coupling coefficient is not sensitive to nozzle length and the distance between ignition zone and inner surface of nozzle.
从NS方程出发，采用二阶精度的NND格式对塞式喷管的流场进行了数值模拟。
The numerical simulations of the flow field around and aerospike nozzle cell were completed base on N S equations with Second order NND scheme.
这种方法以拉伐尔喷管内非对称流动理论为基础，首先着眼于减少气动偏心，然后考虑效率。
The method, based on the theory of non-symmetric flow in Lavol nozzle, aims first at the Angle of reducing the gas dynamic misalignment, and then at the Angle of efficiency.
研究表明，补燃室压强的变化对燃烧效率的影响是有限的，喷管损失主要与喷管结构尺寸有关；
The results show that the effect of combustion efficiency on chamber pressure is limited, nozzle loss is mainly caused by its structure and size.
研究表明，补燃室压强的变化对燃烧效率的影响是有限的，喷管损失主要与喷管结构尺寸有关；
The results show that the effect of combustion efficiency on chamber pressure is limited, nozzle loss is mainly caused by its structure and size.
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