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.
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.
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.
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.
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。
The scarfed nozzle is used in engines which can produce reversal thrust, or to produce revolving torque on turbine rocket engines at high speed.
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.
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.
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。
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.
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.
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.
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。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
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。
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.
无喷管固体火箭发动机是一种区别于传统发动机的新型火箭发动机，它涉及到的基础知识面广，系统工作过程复杂。
The nozzleless solid rocket motor is a new type of motor which differs from the traditional motor, refers to many subjects and has a very complex system process.
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；
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.
此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。
This technique is available for the design of SRM with reverse nozzle.
采用SIMPL E算法的可压缩形式求解固体火箭发动机燃烧室喷管内的全速度统一流场；
United flow field at all flow speeds in the chamber and nozzle of SRM is solved by using the compressible form of the SIMPLE algorithm.
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。
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.
对某锥柱形装药固体火箭发动机(SRM)燃烧室和喷管的内流场进行了三维两相一体化计算。
This paper makes a 3-d two-phase flow united calculation of the inner flow field of chamber and nozzle in certain SRM.
对某锥柱形装药固体火箭发动机(SRM)燃烧室和喷管的内流场进行了三维两相一体化计算。
This paper makes a 3-d two-phase flow united calculation of the inner flow field of chamber and nozzle in certain SRM.
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