Supposedly, it was developed by NASA as a solid rocket fuel.
据说，这种东西最早是由NASA作为固体火箭燃料而研发的。
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。
The external tank and solid rocket boosters are waiting in the VAB .
航天飞机外贮箱和火箭推进器就在该中心等待装配。
The gleaming white Ares I-X, at its core, is a giant solid rocket booster.
闪闪发亮的白色战神i - X的核心是一个巨型固体燃料火箭推进器。
Did one of the solid rocket boosters somehow burn through its casing?
是否是其中一个助推火箭的外壳因某种原因被烧穿？
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。
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。
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。
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。
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。
The object was too light to be a brick, but it was the same density as a piece of foam from a solid rocket booster.
这一物体太轻了而不可能是一个砖，然而它和固体燃料助推器上的泡沫的密度是相同的。
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。
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 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。
The initial Shuttle design predicted neither foam debris problems nor poor sealing action of the Solid Rocket Booster joints.
航天飞机的初始设计即没有预料到泡沫脱落问题也没有预料到固体火箭助推器连接密封性能这么差。
In addition, this achievement provides the basis of integrative performance calculation for all kinds of solid rocket motors.
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。
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。
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。
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。
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。
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)。
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 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。
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