Once the satellite structure, shrunk through this method, is connected with the rocket model, coupled loads computation can then be conducted.
用这种方法减缩之后的卫星结构和火箭模型结合后，可以进行载荷耦合计算工作。
The centerpiece was an ornate model rocket on a green fauna launching pad.
餐桌中心的绿色火箭发射场模型上摆着一座精美的火箭模型。
Groovy templates aren't rocket science. They're simply a means for facilitating the separation of a view from its model.
Groovy模板并不是火箭科学，它们只不过是一种简化从模型中分离视图过程的手段。
Metzger and colleagues have used similar measures to model how a rocket plume could scatter dust and boulders in the low-gravity environment of the moon, threatening nearby lunar outposts.
Metzger和他的同事运用类似的手段去为在月球低重力环境下月球基地附近的浮尘和巨石对火箭升空的影响建模。
You're right. I've learned a lot about spaceships from Mr. Brown and then I made this model rocket. I wish I could go into space some day.
你说得对。我从布朗老师那儿了解到了很多有关宇宙飞船的信息，然后我做了这个火箭模型。我希望有一天我也能飞上太空。
Silvis introduced the second portion of the discussion group by holdingup a Rocket ereader, circa 1998, along with a late-model Kindle.
Silvis让讨论小组进入第二阶段的议程，他拿了一个大约生产于1998年的Rocket ereader和时下的代表Kindle。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
首先采用集中参数法，建立了挤压式供应系统的液体火箭发动机各部件的静态及动态数学模型。
Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.
建立了任意斜交曲线坐标系下液体火箭发动机(LRE)内部工作过程的气液两相湍流化学反应流模型。
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。
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。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
最后，基于模型数据，应用神经网络识别了液体火箭发动机的几种故障模式。
In this thesis. Based on the accurate six freedom degrees kinetic equations of the air rocket, an optimizing model of calculating air rocket dispersion is established.
本文在精确的六自由度运动方程的基础上，建立了计算航空火箭弹散布的优化模型。
The practical examples show that reliability distribution method and reliability growth model for the rainfall-enhancement and anti-hail rocket and its units are feasible.
实际算例表明，对增雨防雹火箭及其单元，采用上述可靠性分配方法和可靠性增长模型是可行的。
A gas flow model with laser plasma as heat source was developed based on axial symmetric Euler equations in the laser propulsion rocket engine absorption chamber.
以轴对称非定常欧拉方程为基础，建立了激光推进火箭发动机吸收室内纯气相单组分、以激光等离子体为内热源的流场模型。
A numerical model was employed to analyze the tangential combustion instability in liquid rocket engine.
建立了液体火箭发动机切向不稳定燃烧数值分析模型并进行了初步分析。
The loss factors in liquid rocket turbine are analysed in detail and a related mathematical model and calculation method is proposed.
分析了液体火箭发动机中所用涡轮的各种损失因素，并建立了相应的数学模型，给出了计算方法。
According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper.
根据固体火箭发动机绝热防护模型，提出了一种嵌金属丝端燃装药绝热层设计方法。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
The manufacture quality of solid rocket engine is ensured by the constant temperature pushing core model.
恒温插芯可以确保固体火箭发动机的制造质量，远程控制可以避免事故突发带来的人员伤亡。
This paper presents computation and analysis of tangential mode of high frequency combustion instability in FY-20 liquid propellant rocket engine by means of the annular instability model.
本文用环形不稳定性计算模型计算、分析了FY -20液体火箭发动机的切向高频燃烧不稳定性。
The main contents and conclusions in the paper including: Estiablished the steady numerical models of pintle controlled solid rocket motor, and verified the model with the theoretical experiment data.
建立了喉栓发动机稳态流场的数值模型，用原理试验结果对数值模型进行了校验。
As the fault data-base of the diagnosis system is improved, the model will play an important role in accurately and rapidly diagnosing the fault position of test system for solid rocket motor.
通过对诊断系统的故障数据库的不断完善，该模型将在固体发动机地面试验测试系统中准确、快速地确定故障部位发挥重要作用。
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。
Finally, a certain model of airborne rocket as an example for calculation, the optimum attack condition curve about attack distance and dive Angle of armed helicopter is drawn.
最后，以某型航空火箭弹为例进行计算，得到关于距离和俯冲角的最佳攻击条件曲线。
In this paper, is developed a physical model with the ignition process taken into account, for the internal ballistics calculation of solid propellant rocket motors.
本文根据提出的考虑点火过程的内弹道计算的物理模型，建立了数学方程。
This paper presents a no-contact temperature measurement for a small rocket engine jet exhaust, for a shock wave on nose cone of a model in a jet exhaust and for a model surface of various materials.
本文叙述了用光学法测量小发动机燃气流火焰温度、燃气流中模型前端的激波温度及不同材料的模型表面温度。
This paper presents a no-contact temperature measurement for a small rocket engine jet exhaust, for a shock wave on nose cone of a model in a jet exhaust and for a model surface of various materials.
本文叙述了用光学法测量小发动机燃气流火焰温度、燃气流中模型前端的激波温度及不同材料的模型表面温度。
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