empennage

Preliminary Analysis of Non-linear Vibration Characteristic of Aircraft Empennage

飞行器尾翼结构的非线性动态特性初步分析

Study on Isothermal Forming Technology for Complex Empennage

复杂尾翼等温成型工艺研究

The effect of empennage spread on flight attitude was analyzed and validated by flight test data .

本文介绍了使用双镜头狭缝摄影对某武器系统外弹道飞行姿态测试的方法及可行性分析。

The moveable horizontal surface of the empennage used for pitch trim .

飞机尾翼的可动水平面，用来控制俯仰配平。

Numerical Simulation Study of Performance of Empennage Forming of Liner with Five Concave Arc Margins Cutted

五凹弧切边罩尾翼成形三维模拟研究

Optimization of superplastic forming process for empennage

尾翼超塑成形工艺方案优化

Effectively Analyzing Aeroelastic Model Empirical Design for Empennage Non-Lift Type Buffeting and Its Wind Tunnel Test Data

尾翼气动弹性抖振模型设计与抖振试验研究

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 .

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。

This article describes a method converting aerodynamic load to FEM node load which is applied in the FEM analysis of aircraft wing and empennage structures .

介绍一种节点载荷转换方法，并用于某飞机各个翼面结构的有限元分析。

The boundary layer measurement has also been executed on the afterbody of the fuselage with empennage and engine cabins .

并应用微型总压管进行了后体的边界层测量实验，得到了边界层平均速度分布。

Influence of empennage on flow over upswept after-body

尾翼对民机后体流动特性的影响

Based on test and simulation of aircraft windshield , the anti-bird impact design guide line of aircraft typical structures for radome and leading edge of wing and empennage is discussed .

最后在对飞机典型结构风挡、雷达罩、机尾翼前缘的试验与仿真研究的基础上，对飞机典型结构的抗鸟撞设计准则进行了探讨。

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 .

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。

The modeling of rotor unsteady aerodynamics and rotor / fuselage / empennage aerodynamic interaction have been the bottleneck in the high-fidelity mathematical modeling of helicopter flight dynamics .

旋翼非定常气动力建模以及旋翼与直升机其它部件的气动干扰建模一直是影响直升机飞行动力学数学模型置信度的瓶颈。

It is reported that the ice mostly occurs in wing and empennage . The traditional deicing suffers the high energy consumption , heavy weight and the limitation of the deicing efficiency .

结冰最易出现在机翼和尾翼，传统的除冰方法不仅能耗高，重量较大而且效果有限。

The research purpose of this paper is to analysis the flight dynamic performance for unmanned aerial vehicle ( UAV ) without empennage and to evaluate its operation and stable performance . Then offer some reference to design and development .

本文的研究目的是对无尾式无人机的飞行动力学特性进行分析研究，初步评价其操纵与稳定性能，从而为飞机的设计与研制提供一定的参考。

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 .

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。

Utilizing the functions of CATIA software in Reverse Engineering deals with point cloud data of mobile empennage that is gained from laser measuring and reconstitute the curved surface . Gains the solid model that Rapid Prototyping requires .

在逆向工程中应用CATIA软件处理激光测量的方法得到的汽车尾部局部点云数据，进行曲面重构，获昨快速原型所需的实体模型。

The utility model relates to a toy plane which is composed of a plane body , wings , an empennage , an electric machine , batteries , propellers , a driving device , direction wheels , etc.

新型空陆玩具飞机，由机身、机翼、尾翼、电机、电池、螺旋桨、传动装置、方向轮等组成。

Two methods are used in this paper to analysis the flight dynamic performance for UAV without empennage by qualitative and quantitative analysis . One is calculating two longitudinal modes by linearizing the basic motion equations . The other is three-dimensional flight simulation research with complete motion equations .

文章主要运用了基本运动方程线化进行基本模态计算分析和建立全量方程进行三维虚拟飞行仿真研究两种方法来定量与定性的分析与评估无尾式无人机的飞行动力学特性。

The tailless aircrafts are regarded as a developing way of the new type aircrafts , which have non-linear characteristic of strong coupling in the lateral-directional mode and in between lateral-directional mode and longitudinal mode due to lack of empennage and even fuselage .

无尾飞机是新型飞机的研究方向，由于其没有尾翼甚至机身，导致横侧向模态自身以及横侧向模态与纵向模态之间存有强耦合非线性特性。

The design is successfully applied to a load-simulated test bed of missiles ' wing and its empennage clung to a certain institute . The accepted experiments of control method and software have been done , through which the tests of the products have been completed .

论文将其设计成功的应用于某研究所的导弹弹翼、尾翼负载模拟实验台，完成了控制律和软件的验收实验，成功的进行了产品测试。