The rocket consists of a giant core stage flanked by two solid rocket boosters, each slightly larger than the first stage of Ares I.
火箭有一个巨大的核心，两侧是两个固体火箭助推器，每个比战神i的第一级稍微大一些。
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。
But in launch position, the orbiter is perched on the side of its 15-story external fuel tank and flanked by two solid rocket boosters.
但在发射点，轨道器一面是15层楼高的外挂燃料箱，两侧是两个固体火箭助推器。
A shuttle on the launch pad measures 184 feet (56 meters) tall from the tip of the external tank down to the aft skirts of its twin solid rocket boosters.
从外部燃料箱的顶端至船尾固体火箭助推器的裙摆，发射台上的航天飞机高184英尺(56米)。
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。
NASA is now checking on the damage of lightning on Endeavor and its solid rocket booster.
国家航空航天署正在检查奋进号航天飞机及其固体火箭助推器是否被闪电损坏。
An integrated conceptual design software system for solid rocket motors SRMCAD is developed.
研制了一种固体火箭发动机集成方案设计系统软件SRMCAD。
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。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
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。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
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。
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 flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.
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 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 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。
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。
MDO method can improve design quality for solid rocket booster, and greatly reduce iterative times and shorten design period.
采用MDO方法，可提高固体火箭助推器的设计质量，大大减少设计迭代次数，从而缩短设计周期。
The results show that the model with high precision will find promising engineering application in research of solid rocket motors.
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。
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。
The results of this paper are of practical significance to grain structural integrity analysis and computation of solid rocket engines.
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。
Design optimization of solid rocket booster was carried out by using traditional and multi-disciplinary design optimization (MDO) method.
采用传统设计优化方法和多学科设计优化(MDO)方法进行了固体火箭助推器设计优化。
The condensed phase particle size distribution affects the combustion chamber and nozzle efficiency of solid rocket motors to some extent.
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。
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 ablative property requirements and the studies on the insulation layer of solid rocket engine in oxidizer rich environment were presented.
介绍了富氧环境下固体火箭发动机对绝热层性能的要求，以及在该特殊条件下对绝热层所开展的研究工作。
Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.
采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。
Results of subscale engine test show that the insulation (PFDH-2) can be used for heat protection of oxidizer rich solid rocket engine chamber.
试车结果表明，PFDH - 2绝热层可以对富氧环境下工作的发动机燃烧室实施有效热防护。
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。
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。
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