empennage

英

美

n.  尾翼；尾翼面；尾部; 缩写词为EMP

复数：empennages　

英英释义

noun

• the rear part of an aircraft
  Synonym:tailtail assembly

双语例句

• 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。
• Optimization of superplastic forming process for empennage
  尾翼超塑成形工艺方案优化
• 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。
• 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。
• 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。
• 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。
• 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。
• 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。
• 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