How can a rocket engine that generates 5,000 degree steam and 13,800 pounds of thrust form icicles at the rim of its nozzle?
一个能制造出5000度高温蒸汽和13800磅推力的火箭推进器，是怎样使喷口边缘结冰的呢？
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。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.
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。
Good references for solid rocket motor nozzle design and research are provided.
可为固体火箭发动机喷管的设计与研究提供有效参考。
The condensed phase particle size distribution affects the combustion chamber and nozzle efficiency of solid rocket motors to some extent.
凝聚相微粒尺寸分布对固体火箭发动机燃烧室效率和喷管效率有影响。
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. Wave decline method is used in the experimental research.
应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼，并用波衰减对比法进行了试验研究。
The equations of transverse movement when nozzle connected rigidly with rocket and related boundary conditions form the basis for analyses.
发动机喷管与火箭固联时的横向运动方程序及其相应的边界条件是分析工作的基础。
A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.
提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；
The design of the nozzle of the rocket assisted engine with the base bleed compound extended range shrapnel is introduced in this paper.
经射击试验证明文中所述对增程弹火箭助推发动机喷管设计具有一定的指导意义。
During the ground test of solid rocket motors, after the reversal nozzles are opened, the shock wave enters the primary nozzle. This phenomenon makes tested data processing difficult.
带反喷管固体火箭发动机地面实验时，在其反向喷管打开后，激波进入主喷管情况下，会给数据处理带来困难。
Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor.
应用有限单元法研究固体火箭发动机不稳定燃烧中的喷管阻尼，并用波衰减对比法进行了试验研究。
The bell of the motor nozzle, which was machined from a single piece of steel, is visible at the aft end of the rocket.
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。
Approximately 60 liters of water are then forced through a rocket nozzle under the seat.
然后大约60公升的水就会被压入座椅下方的火箭喷嘴。
The erosive property and principle of copper-infiltrated graphite as solid rocket motor(SRM) throat insert and tailpipe nozzle bushing are presented.
介绍了石墨渗铜材料作为固体火箭发动机（SRM）喉衬与长尾管衬套的烧蚀特性和机理。
Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis.
通过热和结构计算，对固体火箭发动机喷管缝隙设计进行了分析。
The flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.
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。
Then, the experiment of flow separation in the nozzle was done with a solid rocket motor, and the inside pressure data along the axis of the nozzle was gotten.
然后，利用某型号固体火箭发动机进行喷管分离流试验，测得了喷管壁面上沿轴向的压强分布数据。
The 3d motion parameter measurement of a rocket motor nozzle is a premiss for accurately controlling the nozzle, and the calibration equipment is the key to ensure motion testing at a high precision.
火箭发动机喷管三维运动参数的测试是对其精确控制的前提，其校准装置是保证测试精度的关键。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
The scarfed nozzle is used in engines which can produce reversal thrust, or to produce revolving torque on turbine rocket engines at high speed.
斜切喷管+常用于产生反向推力，或产生旋转力矩使火箭高速旋转的涡轮式火箭发动机中。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
The calibration equipment is used to calibrate the visual testing system for rocket nozzle 3D motion, and supplies the standard position and motion parameters for static and dynamic calibration.
本校准装置是用来校准用于测试火箭喷管三维运动的视觉系统，为其提供标准的静态和动态运动参数。
The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响，找到了逐步提高推力的措施。
It's indicated that the design of the nozzle of the rocket assisted engine is to direction advantage in engineering by the experiment.
经射击试验证明文中所述对增程弹火箭助推发动机喷管设计具有一定的指导意义。
The plume from the attitude controlling rocket motor nozzle has an obvious effect on the aircraft in vacuum.
姿态控制发动机真空环境下工作产生的羽流对航天器造成的影响非常明显。
Milling grooves on aerospace rocket-engine-nozzle surface is an important process.
铣槽加工是大型航天火箭喷管制造中的关键工序。
Based on a nozzle structure in solid rocket motor, a calculation model is developed. The vibration and mode analysis of the model using subspace iteration method are presented in the paper.
针对某固体发动机喷管结构，建立计算模型，给出了用大型特征值问题求解的子空间迭代法。
Numerical 3d simulation and research on inner nozzle and outlet flow field of solid rocket motor of long range missile designed by Russia using STAR-CD computational fluid software.
采用STAR - CD计算流体软件对某俄式发动机的喷管内流场及喷管出口处流场进行了三维的数值仿真与研究。
Numerical 3d simulation and research on inner nozzle and outlet flow field of solid rocket motor of long range missile designed by Russia using STAR-CD computational fluid software.
采用STAR - CD计算流体软件对某俄式发动机的喷管内流场及喷管出口处流场进行了三维的数值仿真与研究。
应用推荐