固体火箭发动机设计是一项复杂的系统工程。
Solid rocket motor design is a complicated systems engineering.
本文介绍了固体火箭发动机水下推力矢量特性试验。
The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper.
提出了一种旋转固体火箭发动机的内弹道计算方法。
A method of internal ballistic calculation for spinning solid rocket motor has been presented in this paper.
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.
作为一个例子，计算了一个固体火箭发动机壳体的强度。
As an example, the strength of a solid fuel rocket engine shell is calculated.
本文提出了一种推力可调的固体火箭发动机的设想方案。
A conception of adjustable solid propellant rocket motor was proposed.
介绍一种固体火箭发动机燃烧室壳体纤维缠绕芯模的设计。
This article introduces a designing means of mold of the fibre winding solid rocket motor combustion chamber shell.
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.
介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
本文讨论了单室双推力星形装药固体火箭发动机的结构优化方法。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
对过载状态下固体火箭发动机燃烧室内二相流动进行了数值研究。
Two phase flow in the solid rocket motor combustion chamber under overload condition is studied with numerical method.
研制了一种固体火箭发动机集成方案设计系统软件SRMCAD。
An integrated conceptual design software system for solid rocket motors SRMCAD is developed.
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.
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.
结合算例说明了该方法在固体火箭发动机结构完整性分析中的适用性。
Calculating examples are given to illustrate the application of the method on structure integral analysis of solid rocker motor.
介绍了固体火箭发动机壳体裙的结构、用途及采用复合材料裙体的优点。
Both the structure and the use of solid rocket motor case skirts are presented. The advantages of the composite skirts are introduced.
该文的结果对固体火箭发动机装药结构完整性分析计算有重要的实用价值。
The results of this paper are of practical significance to grain structural integrity analysis and computation of solid rocket engines.
而且，这一成果为整个固体火箭发动机领域流场的一体化计算打下了基础。
In addition, this achievement provides the basis of integrative performance calculation for all kinds of solid rocket motors.
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.
结果表明，该模型精度较高，在固体火箭发动机研究方面具有较好的工程应用价值。
The results show that the model with high precision will find promising engineering application in research of solid rocket motors.
基于不可压和近似不可压粘弹性有限元法，对固体火箭发动机药柱进行了三维分析。
Three-dimension analysis of solid rocket motor grain was presented based on incompressible and nearly incompressible viscoelastic finite element method.
用于固体火箭发动机壳体和工业贮罐的纤维缠绕压力容器，爆破压强是重要的设计参数。
The burst pressure of filament wound pressure vessels which is applied to solid rocket motor case and gas tank in industry is an important design parameter.
因此，进行固体火箭发动机药柱的不确定结构分析具有重要的理论价值和工程实际意义。
So it has important value both on theory and practical application to perform uncertain structural analysis for SRM grain.
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 erosive property and principle of copper-infiltrated graphite as solid rocket motor(SRM) throat insert and tailpipe nozzle bushing are presented.
分析了固体火箭发动机药柱在长期贮存过程中，由于温度载荷谱的变化所引起的力学响应。
Stress analysis of solid propellant motor when temperature varies in storage is presented in this paper.
通过提出一个“Y假设”，本文求得了一个固体火箭发动机线性声振荡燃烧的三维理论模型。
On the assumption of "Y", a three-dimensional model is obtained for the linear acoustic combustion in a rocket motor.
本文采用理论分析和数值仿真方法对大长径比固体火箭发动机点火瞬态过程进行了系统研究。
This dissertation integrates theoretical analysis and numerical simulation method to investigate the ignition transient process of large aspect ratio solid rocket motors.
本文采用理论分析和数值仿真方法对大长径比固体火箭发动机点火瞬态过程进行了系统研究。
This dissertation integrates theoretical analysis and numerical simulation method to investigate the ignition transient process of large aspect ratio solid rocket motors.
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