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 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 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。
Structure integrality of nozzle during the working process of motor was analyzed by calculating temperature field and stress field.
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。
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。
Failure was caused by an experimental "burst diaphram" installed in the B-200 motor, which restricted gas flow through the nozzle.
失败的原因是实验“水管爆裂，连续”，安装在B- 200型汽车，限制气体流量通过喷嘴。
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。
The basic principle is though three root ball screw control platform, by the measurement of nozzle, three motor to adjustable height accordingly, easily implemented leveling!
其基本原理就是平台通过三根滚珠丝杠控制，上面对应三个电机，经过喷头测量，三个电机相应调节高度，很轻松实现了调平。
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。
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。
The motor case is a steel cylinder closed tight at one end. the other end is the open throat and nozzle.
发动机壳体为一个其一端为密封的钢铸圆柱缸体，另一端则为敞口的喉道及喷管。
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.
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。
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。
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。
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。
In this part, calculation methods of the productivity, air-cushion pressure, air flow quantity, nozzle area, capacity of ventilator and electric motor are given out systematically.
系统给出了气垫带式输送机生产率、气垫压力、空气流量、气孔面积、鼓风机和电机功率的计算方法。
The hollow-axis motor drives the offset nozzle and rotates the arc on the tip of wire at high speed, so as to ensure enough penetration into the sidewalls in narrow gap welding.
在该系统中，焊丝穿过电机的空心轴后从导电嘴的偏心孔送出，电机带动导电杆和偏心导电嘴旋转，从而使焊丝端部的电弧以一定直径高速旋转，以保证窄间隙焊接接头具有足够的侧壁熔深。
Analysis shows that after three-time ignition and operation of motor, the temperature of nozzle case rises spirally.
分析认为，发动机三次启动点火工作，温度呈螺旋上升。
Analysis shows that after three-time ignition and operation of motor, the temperature of nozzle case rises spirally.
分析认为，发动机三次启动点火工作，温度呈螺旋上升。
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