尾翼

三角形就成了尾翼。

The triangles will be the tail fins .

那架飞机有一个长长的尾翼。

The aircraft has a long tail fin .

X型尾翼布局对无人机静稳定性的影响

Study on the Impact of X-Tail on Static Stability for an UAV

这或许意味着V型尾翼在超音速巡航时会被锁定。

This might mean that the V-tails could be locked out in normal cruising flight .

尾翼筒机器人TIG填丝焊接工艺

Welding Technology of Robotic TIG Filling-wire for Wing of Cylinder

简单介绍空化器及尾翼联合控制的反馈线性化方法及滑模控制算法，并对两种控制算法分别进行MATLAB仿真，用以检验控制效果。

The method using feedback linearization of combined control of cavitation device and empennage and synovial control algorithm are simulated by MATLAB to test control effects .

贴隔板法形成尾翼型EFP的试验研究及数值模拟

Experimental Study on Explosively Formed Projectiles with Fins and Numerical Simulation

四点起爆形成带尾翼EFP的试验研究

Experimental Research on EFP with Fins Formed by Four Detonating Points

带尾翼EFP形成的三维数值模拟研究

3D Numerical Simulation Research on the Formation of Explosively Formed Penetrator with Fins

贴隔板法在尾翼EFP成型中的应用研究

The Application Study of Affixed Cover in Forming Process of EFP with Fins

采用TVD有限体积格式对尾翼稳定脱壳穿甲弹弹托脱落时的流场进行了数值模拟。

Using TVD finite cubage format , the numerical simulation of APFSDS sabots discatding is proceeding .

带与不带4个等尾翼回转体的尾部流动的LDV测量

Stern Flow Measurements by LDV Unit on an Axisymmetric Body with and without Four Identical Tailplanes

GENH-4直升机与这幅素描中的直升机一样，也没有尾翼。

As in the drawing , the GEN H-4 has no tail .

尽管克莱斯勒（Chrysler）、林肯（Lincoln）和德索托（Desoto）的几款老爷车都有巨大的尾翼，但其中没有任何一款车型达到了凯迪拉克的高度。

Other cars Chryslers , Lincolns , and DeSotos had massive tail fins , but none took them to the heights that Cadillac did .

针对某无人战斗机所采用的V形尾翼布局，通过求解N-S方程的数值计算方法，得到了上反与下反V形尾翼气动布局的纵向力矩值。

Aimed at the vee tail of an UCAV , the longitudinal moments of up vee tail and down vee tail are calculated by the method of solving N-S equations .

外部输入舵机（尾翼）复位命令后，姿态控制电路输出PWM脉冲信号进行舵机复位，并启动FLASH进入写状态，记录数据。

After the external input servo ( empennage ) reset command , posture control circuit output PWM pulse signal to reset the servo and start FLASH into the writing mode to record data .

采用以N-S方程为主控方程的数值模拟方法，进行固定尾翼鸭式气动布局导弹的气动特性和流场数值模拟。

To investigate the rolling control characteristics of canard-controlled missile with fixed-tail , a numerical simulation method based on N-S formulation was conducted .

尾翼稳定脱壳穿甲弹（APFSDS）是杀伤地面装甲目标的利器。

APFSDS is the main weapon that kills the armor target in battlefield .

利用Fluent软件对三维带弹翼/尾翼的喷流绕流干扰流场进行了数值模拟。

Fluent was used to simulate the flowfield of 3-D complex flowfield of rocket-missile with wings and empennages induced by the interaction by base jet and the flow around the body .

文中还运用此方法计算了带尾翼LOTTE飞艇的附加质量，用以在数值分析其运动时使用。

The added mass of the airship LOTTE is also computed for its numerical moving analysis .

应用在药型罩表面贴附惰性隔板的方法可以研制出尾翼稳定的爆炸成型弹丸（EFP）。

Attaching covers on the shaped liner , an explosively formed projectile ( EFP ) with stabilizing fins can be produced .

还介绍了把该方法使用于F－7尾翼载荷和F－6操纵面铰链力矩导数的参数识别的研究实例，并对其进行了相应的评述。

The examples of adopting this method to identify the load on tail of F-7 and the derivatives of hinge moment of control surface of F-6 are presented , and some relevant evaluation to them is also given .

采用多点起爆方式，设计了带尾翼翻转型爆炸成形弹丸（EFP）试验装置。

The test set of the Explosively Formed Projectile ( EFP ) with star shaped tail was designed with a multi-point initiation .

对典型的尾翼EFP形成技术进行总结，分析贴片方法形成尾翼EFP的原理和特点。

Some typical technology which can produce EFP with star-shaped tail are summarized and generalized , and the principle and characteristic of foil method is analyzed .

但在蒙扎，这支意大利车队给两台F10都配备了相同的低下压力尾翼总成。

But at Monza , the Italian team are running the same low-downforce package on both F10s .

早期的设计研究展示了一种顶端零重叠，有着F-117类似的倾斜尾翼的连翼布局飞机；

Early design studies showed a joined wing with zero overlap at the tips and F-117-like canted tail fins ;

尾翼式锚&中远ZY-3型锚的研制

Development of tail-fin type & cosco ZY-3 anchor

本文以30mm尾翼稳定脱壳穿甲弹为研究对象，对其膛内发射动态强度、振动特性和结构优化设计问题进行了系统而深入的理论分析、数值模拟和计算研究。

This thesis presents theoretic analysis , numerical simulation and calculational studies on dynamic launching strength and vibration analysis during launching and structure optimization design of 30 fin-stabilited sabot-discarded penetrator .

本文系统阐述了该算法的基础理论，并利用SPH算法对飞机典型结构雷达罩、机尾翼前缘模型进行了鸟撞仿真研究，得到了很有意义的结论。

Related basic theory of the algorithm is elaborated . The bird strike simulation research on aircraft typical structures such as radome and leading edge of wing and empennage are conducted too and meaningful conclusions was obtained .

KJ8602A以在垂直尾翼顶端、两个翼尖和前机身下的几个外部安装天线为特征。

The KJ8602A features several external antennae mounted on the vertical fin tip , both wingtips , and underneath the forward fuselage .