喷管

基本解释 (translations)

effuser

与喷管相关的网络例句 [注：此内容来源于网络，仅供参考]

An adaptive grid scheme controlling cell area is used to generated grids in the divergent section of symmetric annular nozzle, and the generated grids are used in the flowfield calculation through the uncoupled way. The elliptic equations are used to generate grids in three dimensional regions of FDN divergent section, the source terms used in the equations employ a mathematical form which is independent of the boundary shape and of the boundary grid point distribution, the free parameters contained in the source terms are determined by the two restraint conditions, the intersection angle of transverse grid lines with boundaries and the local curvature of the transverse grid lines at the boundaries, and the interior grid distribution controlled directly by the grid point distribution assigned on the boundaries is realized, it makes the grid more clustering near the nozzle wall. For the generated grids in the whole computational regions have a good smoothness and orthogonality, the accuracy of calculation in the flowfield is ensured.

对轴对称的环形喷管采用控制网格面积的自适应网格方法对扩散段部分进行了网格生成，并通过非耦合方式应用于喷管的流场计算中；对强制偏流喷管扩散段内的三维区域采用椭圆型方程进行网格生成，方程中的源项采用了与边界形状和边界网格点分布无关的数学形式，源项内的自由参数由横向网格线与边界的交角及横向网格线在边界处的局部曲率两个约束条件来确定，实现了由边界上的网格分布直接控制内部的网格点，使壁面附近具有较密集的网格，并且在整个计算区域内的网格都具有良好的光滑性和正交性，从而保证了流场计算的准确性。

Nozzle is one of the most important components used in SRM. The nozzle is subjected to the cautery and concussion of the heat gas, so the thermal effect and related thermal-structure couple effect to the nozzle structure become the important factor affecting the load carrying capability of the nozzle. Well, the following investigation contents are accomplished in this paper.

喷管是固体火箭发动机关键部件之一，喷管在工作过程中承受着高温燃气的烧蚀和冲刷，所产生的热效应和由此带来的热—结构耦合效应已经成为喷管强度和稳定工作必须考虑的重要因素。

The relationship between pressure and temperature of the combustion chamber and the performance of microthruster are also obtained.

对不同几何参数和热力参数下的微喷管的流场和温度场以及微喷管的性能进行了研究，得出了各个参数在微喷管设计中的设计原则，及与其性能之间的关系。

Physical and numerical models were establishedased on NˉS c ontrol equations and RNG kˉεturbulence model, the interior flow fields of the nozzles were analyzed through num erical method, both the flow parameters change trend and thrust speciality of the asymmetry quadrate nozzle were resea rched.

文中建立了非对称方形尾喷管及传统轴对称尾喷管的物理数学模型，基于N S方程和RNG kε湍流模型，对两种尾喷管三维内流场进行了数值分析，研究了非对称方形尾喷管内部流动参数的变化趋势及其推力特性。

To compute the infrared properties of vectored nozzles, heat transfer and temperature on the wall must be considered also. With requirement of increasing thrust-weight ratio, gas temperature of engine becomes higher and higher, effectively cooling models must be applied on the nozzles.

计算矢量喷管的红外特性还涉及到计算喷管的换热及温度分布，随着对战机推重比要求的不断提高，发动机排气的温度水平越来越高，必须考虑对喷管采取有效的冷却方式。

So far, most research about vectored nozzles is numerical simulations of internal flow field and manuverbility. However, research about their infrared properties, especially systematically research about spectral properties is very sparce.

目前国际上对矢量喷管内流场的数值计算，矢量喷管的机动性能的研究比较多，然而对矢量喷管红外辐射特性的研究非常少，特别是系统地研究矢量喷管壁面和出口平面的光谱辐射特性方面的工作特别少。

In this paper, the author studied the infrared properties of several kinds of vectored nozzles, including axial-sysmmetrical vectored nozzle, circular-to-rectangular vectored nozzle and spherical-traversing vectored nozzle, both in after-burning condition and non-after-burning condition. This work will fill in the gaps in this field of our country.

本文研究了当前国际上已经出现的几种形状的矢量喷管——轴对称矢量喷管、圆转方矢量喷管、球面过渡段矢量喷管，在加力与非加力状态下的红外辐射特性，此项研究将填补我国在矢量喷管红外辐射特性研究领域的空白。

In order to design optimum nozzle for air-air missile solid rocket motor, the mass model of solid rocket motor, the nozzle specifice impulse model of solid rocket motor and the objective function are established. Five different type of nozzles are choosen lor calculation: Conical, parabolidal,two different arcs,quadiatic polynominal and cubic polynominal.

以两种空-空导弹固体火箭发动机喷管作为算例，为此，建立固体火箭发动机的质量模型，喷管的质量比冲模型和目标函数模型，选择五种喷管扩散段内型面：锥形喷管，抛物线喷管，双圆弧喷管，二次多项式喷管和三次多项式喷管，进行优化设计，利用优化理论，成功地完成了五个设计变量的优化问题。

To reveal aft end internal flow feature of a solid rocket motor with submerged nozzle, a two dimension cold flow test model with rectangular channel was designed The cold gas simulation was based on geometric similarity and aerodynamic analogy Mean and fluctuating velocity field was measured using phase doppler particle analyzer It showed that the flow separates at upstream of the submerged nozzle and reattaches on the tip of the nozzle nose A relatively steady recirculation zone formed in...

为了揭示含潜入喷管的固体火箭发动机尾部流动特征，按照几何相近和气动相似原则设计了通道为矩形的二维冷流实验模型，利用相位多普勒粒子分析仪对燃烧室尾部气流的时均速度和湍流脉动速度进行了测量。实验结果表明气流在潜入喷管入口上游发生分离，再附点位于喷管前端部外侧，背壁空腔内形成一个较为稳定的回流区，流场的轴向和横向湍流强度都比较大

The force on the jet pipe in the hole jetted is analyzed, and it is indicated that the resistance on the jet pipe is the main factor influencing the feeding of jet pipe.

分析了喷管在喷孔内的受力，指出喷管在喷孔内所受的阻力是影响喷管送进的主要因素，据此调节喷管送进控制液缸控制腔的压力可控制送进速度和限制最大推力。

与喷管相关的网络解释 [注：此内容来源于网络，仅供参考]

constrictor nozzle：收敛形喷管

constricting nozzle 压缩喷嘴,收缩嘴 | constrictor nozzle 收敛形喷管 | construction materials of the main parts 主要构件的结构材料

Desolator ready：辐射喷管准备就绪

I'm your man.我听你指挥. | Desolator ready.辐射喷管准备就绪. | Ready for melt-down.准备溶化敌人.

divergent nozzle：扩散喷管

cultivated species 栽培种 | divergent nozzle 扩散喷管 | livestock product 畜产品

nozzle：喷管

此次的硅深刻蚀工艺原理如下:(1)把ClF3气体由喷管(Nozzle)喷入真空设备内;(2)根据喷管(气压:10帕)和真空设备(气压:大气压以下)间的气压差,使喷管喷出的ClF3气体的分子和原子隔热膨胀,形成名为"气体团簇(GasCluster)"的数百万~数千万个分子集合体,

tail pipe：船尾喷管

tail pipe 泵吸管尾管船尾喷管 | tail pipe 船尾喷管 | tail pipe 尾管

canted nozzle：倾斜喷管

三角刮刀;三棱刮刀 cant scraper | 倾斜喷管 canted nozzle | 倾斜喷管 canted venturi

canted nozzle：扭曲喷管, 曲线型喷管, 斜置喷嘴

cantaxin | 康塔克辛(成药, 合成的维生素C) | canted nozzle | 扭曲喷管, 曲线型喷管, 斜置喷嘴 | canteen | 小卖部, 食具箱, 饭盒, (军用)水壶

throatless nozzle：无喉部喷管

throatable nozzle 喉部可调喷管 | throatless nozzle 无喉部喷管 | through-wall air conditioner 过墙式空调器

propelling nozzle：推进喷管,推力喷管

procurement rapair parts list==>采购备件清单 | propelling nozzle==>推进喷管,推力喷管 | proportional burner==>比例调节烧嘴,配比燃烧器

Spouts：喷管

210013 排灌设备 Watering devices | 210027 喷管 Spouts | 210027 喷管 Spouts