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。
A conception of adjustable solid propellant rocket motor was proposed.
本文提出了一种推力可调的固体火箭发动机的设想方案。
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。
Phenolic resins have been applied in rocket motor to offer high properties and low cost.
酚醛树脂以其价格低廉、耐热性能优异，在火箭发动机上得到广泛应用。
Study of suppression after-burning with some additive on rocket motor exhaust is introduced.
介绍了几种添加剂抑制火箭发动机喷焰二次燃烧的实验研究。
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。
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。
The plume from the attitude controlling rocket motor nozzle has an obvious effect on the aircraft in vacuum.
姿态控制发动机真空环境下工作产生的羽流对航天器造成的影响非常明显。
There is a rocket motor on the satellite by which the direction of the satellite can be changed if necessary.
在卫星上还有一个火箭马达，必要时可以用它来改变卫星的方向。
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 safety demolding system is designed for main core demoulding from the NEPE high-energy rocket motor in safety.
安全脱模系统是为了解决NEPE推进剂装药发动机主芯棒脱模而研制的专用设备系统。
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。
On the assumption of "Y", a three-dimensional model is obtained for the linear acoustic combustion in a rocket motor.
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。
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。
The green destruction and reclamation technology of obsolete rocket motor charge in America and Russia is summarized.
综述美国和俄罗斯废弃火箭发动机装药绿色销毁与回收技术。
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。
Rocket motor test shows that the new UDMH/NTO bipropellant can satisfy the requirement of gel propellant of rocket motor design.
发动机试验表明：新的UDMH/NTO双组元凝胶体系能够满足发动机设计对凝胶推进剂的要求。
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。
Space debris made news on March twelfth when a part of an old rocket motor about ten centimeters in size threatened the International Space Station.
空间碎片在三月二十日那天就制造了一个新闻：一个大约十厘米大小的旧火箭马达威胁着国际空间站。
To achieve the right mixture of propellant, the patent presents a hybrid rocket motor that would use 3-d stereolithography to essentially print the fuel.
为了准确地得到推进剂混合物，专利方案里展示了一个利用3 - D立体平版印刷术打印出燃料的混合动力火箭发动机。
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。
This web page presents the test report detailing the first static test (KDX-001) conducted on the Kappa-DX rocket motor, as well as post-test analysis.
这个网页介绍了测试报告，详细说明第一静力试验(kdx- 001)上进行了河童的dx火箭发动机，以及后的测试分析。
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。
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。
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。
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