rocket model的例句大全

Oh, we're not actually going to stomp our rocket model.

哦，我们并不是真的要踩我们的火箭模型。

Nowadays, the six-component model based on the six-component test stand has been mainly used to measure the thrust misalignment of the solid rocket motor.

目前，国内外主要采用六分力试验台进行火箭发动机推力矢量偏心测量。

Loss model of solar array power caused by rocket motor plume flow contamination

在轨发动机羽流污染导致太阳帆板电功率损失计算模型

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。

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。

Using k-ε turbulence model and one step eddy-dissipation model, numerical studies on the reacting flow field of solid rocket ramjet with secondary air inlets were carried out. Influence of mass flow ratio on combustion efficiency and temperature field was analyzed.

采用k-ε湍流模型及单步涡扩散化学反应模型，对二次进气结构的固体冲压发动机补燃室的反应流场进行数值模拟，分析了二次进气流量比对燃烧效率与温度场分布的影响。

By studied the physics and mathematics model of the test-bed of thrust misalignment testing system for solid-propellant rocket motor, the data-processing software for six-component testing system is developed, and then the special parameters of the six-component data are extracted;

在对固体火箭发动机推力偏心测试台架进行物理与数学模型深入分析的基础上，开发了六分力测试系统的数据处理软件，对采集到的六分力数据进行特征提取；

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 combustion model for the high-pressure liquid hypergolic bipropellant rocket engine

高压自燃双组元液体火箭发动机燃烧模型

A mathematical model describing combustion in a high pressure liquid hypergolic bipropellant ( UDMH/ H2O4) rocket engine combustor has been developed.

本文提出了一个高压液体双组元自燃推进剂火箭发动机燃烧室计算模型。

The effect of initial propellant temperature on rocket engine combustion stability for hypergolic propellant ( MMH/ NTO) is studied. A physics model for initial propellant temperature effecting evaporation rate has been developed in this paper.

对自燃推进剂（MMH/NTO）初始温度对火箭发动机燃烧稳定性的影响进行了研究，从推进剂初始温度对蒸发速率的影响规律出发，发展了初始温度大小影响蒸发速率的物理模型。

A Dynamic Model for Rocket Launcher With Coupled Rigid and Flexible Motion

一个刚柔耦合的火箭发射架动力学模型

The model of ship-borne rocket launcher system is simplified and built by virtual prototype technology.

通过虚拟样机技术对舰载火箭炮系统进行简化和建模。

The target-detection model of acoustic torpedo is analyzed, and the model of fire efficiency is given, while the optimum falling zone of rocket assisted torpedo is confirmed by calculating.

本文首先深入研究了声自导鱼雷对目标的检测模型，进而建立了基于蒙特卡罗法的射击效率计算模型，通过仿真计算确定了火箭助飞鱼雷的最优落水区。

Then we use FLUENT to establish the quasi-steady and unsteady numerical models of pintle thrust controlled solid rocket motor, and verify the model with internal ballistic of pintle controlled solid rocket motor.

然后用FLUENT建立了喉栓式固体火箭发动机准稳态流场和非稳态流场的数值模型，用内弹道计算结果对数值模型进行了校验。

The Wind Compensation of Ballistic Trace of a Low Altitude Sounding Rocket with the Translation Model from Variable Wind to Constant Wind

探空火箭风场补偿及等效弹道风转化

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。

On Carrier Rocket Engine Working-Process Research System Model and its Application

运载火箭发动机工作过程研究体系模型的研究

Based on the principle of analytical hierarchy process ( AHP), an incomplete hierarchy model for the evaluation of design schems of rocket launchers is built up. According to the characters of this model and applying the theory of fuzzy membership functions, an improved algorithm is proposed.

基于层次分析法的原理构建了面向火箭弹发射器设计方案评判的不完全层次模型，依据该模型的特点，引入了模糊隶属函数理论，提出一种AHP改进算法。

Calculation and Establishment of Interior Ballistics Model for Ejection Gun of Rocket Ejection Seat

火箭弹射座椅弹射动力系统内弹道模型建立与计算