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。
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。
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。
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。
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。
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；
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。
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。
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。
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。
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。
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。
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。
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