垂直尾翼

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 .

武装直升机垂直尾翼的初步设计

Preliminary Design Consideration for vertical Fin of Armed Helicopter

飞机垂直尾翼的非线性结构设计

Non - linear design of the vertical-tail of a plane

侧滑的飞机在垂直尾翼上引起侧力。

The sideslipping airplane gives rise to a side force on the vertical tail .

垂着的尾巴立即竖起来，晃动着。飞机的垂直尾翼部分的稳定器。

A stabilizer that is part of the vertical tail structure of an airplane .

通过确定主要受力构件，对传力进行分析，对垂直尾翼结构进行了有限元分析，得出了垂直尾翼应力和位移的数值结果。

By analyzing main loaded components and force transferring , the spatial displacements and three-dimensional stresses are calculated .

基于三维有限元数值分析，对飞机的重要部件垂直尾翼进行结构设计。

Based on the three-dimensional nonlinear finite element method , the structural design is made on the vertical-tail of a plane in this paper .

飞机垂直尾翼的持续涡流载荷会导致垂直尾翼的疲劳损伤，影响飞行器的飞行性能和飞行安全，因此对尾翼进行振动主动控制是非常有必要的。

Continuous vortex load on the aircraft vertical tail may lead to fatigue damage , even affect the performance of the aircraft and the safety of flight . Therefore , it is significant to control the vibration of the vertical tail .

60年代末期以来，美国陆军根据越南战争的经验，对武装直升机垂直尾翼的设计提出了更严格的要求，以便确保在尾桨失效后直升机能安全着陆或返回。

Since the late 1960 's , US Army , following the experience in Vietnam , Puts forword more strict requirements for vertical fin design of armed helicopter in order to ensure it fly back safely after suffering tail rotor loss .

为了改善其横向稳定性，设计了两种复合材料夹层板，将其安装在垂直尾翼下面，并进行了一系列的飞行试验来研究安装伸出的垂直嵌板的效果。

To improve the lateral stability , two types of composite sandwich panel have been designed and attached to the vertical tail of Velocity-173 . A series of flight test has been performed to measure the effects of the extended vertical tail .