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。
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 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。
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。
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。
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。
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。
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 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。
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 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。
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 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。
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。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
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 paper established the internal ballistics equation for the high-low pressure launcher with tandem construction when the rocket motor is ignited in the launch tube.
本文建立了火箭发动机在管内点燃情况下，串联结构的高低压无后座力发射器的内弹道方程，并对试验弹进行了数值计算。
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。
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。
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。
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 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。
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；
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。
Taking system optimization design of SRM as the example, physical programming of was proven to be efficient in modelling of decision-making uncertainty during the solid rocket motor design.
以固体火箭发动机总体方案优化设计为例，证明了物理规划方法作为固体火箭发动机设计决策不确定性建模方法的有效性。
Simulating the temperature field of a rocket motor (including propellant) by numerical method is an effective way to get real-time temperatures of the rocket propellant.
对火箭发动机(包含发射药)的非稳态温度场进行数值模拟是确定火箭发射药实时温度的一种有效方法。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
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。
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。
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。
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