可为固体火箭发动机喷管的设计与研究提供有效参考。
Good references for solid rocket motor nozzle design and research are provided.
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.
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。
Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis.
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.
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.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
介绍了固体火箭发动机喷管硬质泡沫塑料堵盖的设计方法与试验过程。
Design methods and test process of nozzle closure made of hard foamed plastics for SRM are introduced.
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。
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 design of the nozzle of the rocket assisted engine with the base bleed compound extended range shrapnel is introduced in this paper.
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。
The equations of transverse movement when nozzle connected rigidly with rocket and related boundary conditions form the basis for analyses.
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。
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.
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。
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.
对摆喷管推力矢量方式，获得了推力、侧向力、推力矢量角随发动机喷管偏角以及水深的变化规律。
For the movable TVC, the thrust and lateral forces with respect to nozzle deflection angles and the depth of water were obtained.
应用计算流体力学软件FLUENT，对固体火箭发动机喷管内的二维两相粘性湍流进行数值模拟。
A fully coupled two-phase viscid nozzle flow of SRM is numerically simulated with FLUENT software.
J - 10 B战机还有四种黑色的天线条附着在机身外部，一种较大的在座舱一侧，一种较小的在机身后部靠近发动机喷管的位置。
The J-10B has four black antenna arrays attached externally to the fuselage, a larger one on either side of the cockpit and a smaller one on either side of the rear fuselage near the engine nozzle.
10 B战机还有四种黑色的天线条附着在机身外部，一种较大的在座舱一侧，一种较小的在机身后部靠近发动机喷管的位置。
The J-10B has four black antenna arrays attached externally to the fuselage, a larger one on either side of the cockpit and a smaller one on either side of the rear fuselage near the engine nozzle.
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 .
从理论上证明：对这两类发动机的两相喷管流动特性可以通过一个共同的组合参数——当量排气速度来进行分析；
Theoretically, it is proved that for both these engines, the properties of two-phase flow in nozzle can be analysed with a common combined parameter which is equivalent to exhaust velocity.
本文应用an SY S有限元分析软件，完成了对某型号固体火箭发动机珠承喷管摆动接头的有限元分析。
Finite element software of ANSYS has been used for making a finite element analysis of a certain type of ball-socket nozzle's pendulous socket in solid-rocket engine.
试验结果表明，在保证推力不确定度优于1.0%的条件下，拉瓦尔喷管发动机高空模拟试验的模拟偏差容限约为14%。
The test result shows that maximum tolerance of the simulated ambient pressure deviation is about 14% under which the engine thrust uncertainty remains less than 1.0%.
尾喷管是发动机的重要部件，其连接采用电子束焊接方法，对质量要求很高。
As an important part of engine, the welding quality of the tail pipe should be ensured when jointing it using the electron beam welding.
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.
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。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
四个向外倾斜的喷管把固体火箭发动机的排气流分成四个相等的尾巴。
Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.
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。
The condensed phase particle size distribution affects the combustion chamber and nozzle efficiency of solid rocket motors to some extent.
本文对某固液混合发动机复合结构喷管进行了流动与传热数值模拟，并与试验结果进行了对比分析。
The paper presents a digital simulation analysis result of flow and heat transfer of a compound structure nozzle of hybrid motor, and also presents their comparison with experiments.
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。
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.
在直管脉冲爆震发动机上安装不同类型的喷管，利用推力传感器测量了不同频率下发动机的瞬态推力和平均推力。
Test results from an experimental investigation of the effect of nozzle on the thrust of a straight tube pulse detonation engine are presented.
在直管脉冲爆震发动机上安装不同类型的喷管，利用推力传感器测量了不同频率下发动机的瞬态推力和平均推力。
Test results from an experimental investigation of the effect of nozzle on the thrust of a straight tube pulse detonation engine are presented.
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