Solid rocket motor design is a complicated systems engineering.
固体火箭发动机设计是一项复杂的系统工程。
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。
GA to resolve process route optimization of solid rocket motor shell is studied.
研究了基于遗传算法的固体发动机壳体工艺流程面向成本优化问题。
A software system for solid rocket motor test data analysis and management is introduced.
介绍了一种固体火箭发动机试验数据分析处理及管理系统。
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。
Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.
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。
The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper.
本文介绍了固体火箭发动机水下推力矢量特性试验。
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 steady process of solid rocket motor modulated by the vortex valve is investigated theoretically.
对涡流阀调节固体火箭发动机压强的稳态过程进行了理论研究。
A method of internal ballistic calculation for spinning solid rocket motor has been 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。
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 influence of structure axial vibration on the internal ballistics of solid rocket motor was investigated.
文中研究了固体发动机结构的轴向振动对燃烧室内弹道性能的影响。
This paper deals with the study of the external thermal insulation coating for a solid rocket motor (SRM) case.
介绍某固体发动机壳体外防热涂层的研究情况。
This article introduces a designing means of mold of the fibre winding solid rocket motor combustion chamber shell.
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。
Its ignition transient process plays an important role in determining whether a solid rocket motor can work normally.
星形是固体火箭发动机常用的装药形式，而其点火瞬时过程对发动机能否正常工作起着极为重要的作用。
Two phase flow in the solid rocket motor combustion chamber under overload condition is studied with numerical method.
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。
NASA's Space Shuttle Program conducted the final test firing of a reusable solid rocket motor Feb. 25 in Promontory, Utah.
2月25日，美国航天局航天飞机组在犹他州海角对可回收的液态火箭引擎进行了最后的测试。
Two-phase flow field of spinning solid rocket motor is simulated, and gas-particle of two-phase is analyzed in this paper.
本文对旋转固体火箭发动内的两相流场进行了数值模拟，主要目的是研究燃烧室—喷管内气相和颗粒相在旋转情况下的流动特性。
The rocket is long and slender, and fatter on top because its second stage is thicker than its solid rocket motor-powered first stage.
火箭又长又细，上部有点粗，因为它的第二级比固体燃料火箭发动机驱动的第一级要厚。
Both the structure and the use of solid rocket motor case skirts are presented. The advantages of the composite skirts are introduced.
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。
Angular stiffness and elastomer shear strain on maximum swinging Angle are important indexes in flexible joint design of solid rocket motor.
角刚度(又称弹性比力矩)及弹性件在最大摆角下的剪切应变是固体发动机柔性接头设计的重要指标。
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。
Three-dimension analysis of solid rocket motor grain was presented based on incompressible and nearly incompressible viscoelastic finite element method.
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。
And a more satisfied result is obtained by analysing the living example of the structure reliability for some solid rocket motor at the test sample stage.
通过对某型号发动机试样阶段结构可靠性实例分析，得出了较满意的结果。
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.
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。
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；
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.
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 liner is a polymeric elastomer coating between propellant and insulation layer or case. The liner-forming is a special step in production of solid rocket motor.
衬层是推进剂与绝热层或壳体之间的高分子弹性体涂层，衬层成型是固体火箭发动机生产中的一种特种工序。
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. 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。
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