motor nozzle的例句大全

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。

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Altitude performance prediction of perigee kick motor nozzle

近地点变轨发动机高空喷管性能预示研究

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The characteristic velocity, area of nozzle throat and other parameters are calculated by using the static test results of solid rocket motor ( SRM) and introducing generalized pressure coefficient and thrust coefficient.

利用发动机地面试验结果，引入广义的压强系数和推力系数，计算了发动机的特征速度、喷管喉部面积等参数。

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Simulation and Experiment of Thrust Performance for Solid Rocket Motor with Angle-cut Nozzle

斜切喷管固体火箭发动机推力特性仿真与试验

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The expulsion of the exhaust products through the nozzle at high velocity produces thrust, the "power" of a rocket motor.

驱逐排气产品通过喷嘴高速产生的推力，“权力”的一个火箭发动机。

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Measuring method of opening time and operating synchronism of the reverse nozzle closures of solid rocket motor during thrust termination test was studied.

研究了固体火箭发动机推力终止试验时，反向喷管堵盖打开时间及同步性测量方法。

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Nozzle is an important part of the thrust vector control system of solid rocket motor and high-performance design of a nozzle plays an important role in the performance of the motor.

喷管是固体火箭发动机推力向量控制系统的重要组成部分，高效能的喷管设计对发动机的性能至关重要。

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Numerical Simulation and Experimental Validation of Chemical Reaction Viscous Turbulent Flow Field in the Nozzle of Liquid Rocket Motor

液体火箭发动机喷管化学反应黏性流场数值模拟和实验验证

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Based on the foreign jointing technique between the advanced filament-wound chamber and nozzle, the paper analyzes the jointing modes between chamber and nozzle of an all-composite solid rocket motor and technical approaches, and puts forward the relevant design parameters to give a refrence to designers.

结合国外先进固体发动机纤维缠绕壳体与喷管连接的技术，分析了实现全复合材料固体发动机壳体-喷管的连接方式，技术途径，并提出了有关设计参数，可供设计人员参考。

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Two-dimensional axisymmetric transient thermal analysis for a composite construction nozzle of solid rocket motor is performed by finite element method in this paper.

以固体火箭发动机复合结构喷管为对象，用有限元法进行了二维轴对称瞬态热分析。

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Rotating acceleration has inevitable influence on the work process of Solid Rocket Motor: flow of combustion chamber and nozzle is changed; the pressure, mass flow rate and the specific impulse of Solid Rocket Motor are affected by the spinning.

旋转产生的加速度必然对固体火箭发动机的工作过程产生影响：使燃烧室和喷管中的燃气流动发生变化，对燃烧室工作压力质量流率及冲量产生影响。

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Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/ HTPB hybrid rocket motor.

利用二维轴对称N-S方程和组分方程对选用液氧/端羟基聚丁二烯推进剂的固液混合火箭发动机喷管流动进行了计算。

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Moreover infrared characteristics of a rocket motor nozzl was calculated, and effective and net radiative heat flux of the nozzle in mid-wave infrared band 2~ 6 μ m, long-wave infrared band 8~ 14 μ m and full wave band were analyzed.

还计算了一火箭发动机尾喷管的辐射特性，分析了该喷管在中波红外波带2~6μm和长波红外波带8~14μm及全波长的有效辐射和净辐射热流。

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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。

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cold gas simulation on aft-end internal flow for solid rocket motor with submerged nozzle

含潜入喷管发动机尾部流场冷流模拟

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so it's important to study the characteristics of high pressure gas draw-jet water pump with laval nozzle and use waste gas from motor.

所以对带拉瓦尔管并应用发动机排出的高压废气引射喷水泵的特性研究非常必要。

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and the motor is started to rotate, the suction nozzle rotates, and correction of chip angle error is finished.

启动旋转电机，吸嘴转动，完成芯片角度误差的校正。

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performance analysis of the scarfed reversal nozzle in solid rocket motor

斜切反喷管性能分析

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Taking aft-end igniter design for a rocket motor for example, design methods for ignition sequence, amorce quantity estimation and nozzle closure were described respectively.

以某型号发动机尾部点火设计为研究对象，对点火序列设计、点火药量的估算、喷管堵片的设计方法进行了阐述。

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Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.

结果显示喉栓能够有效改变发动机燃烧室压力和推力，满足发动机推力控制要求。

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