此外走进尾桨或主旋翼是一个安全关切的旁观者。
Additionally walking into the tail rotor or main rotor is a safety concern for bystanders.
问：在哪里尾桨？
对剪刀式尾桨的气动特性进行了实验和分析研究。
An experimental and analytical investigation on the aerodynamic characteristics of a helicopter scissors tail rotor has been made.
该尾桨保持偏航在检查的同时伺服驱动的电梯照顾间距。
The tail rotor keeps yaw in check while a servo-driven elevator takes care of pitch.
但由于无尾桨系统要耗费更多的发动机功率，性能表现不好。
But the performance is poor because requires more power from the engine.
本文采用CFD方法分析了悬停状态下涵道尾桨的流场特性。
The flow field characteristic of a helicopter ducted tail rotor in hovering were analyzed using CFD method in this paper.
耐用半封闭式尾桨变速箱保护尾桨齿轮同时也可以很容易地查阅。
The durable semi-enclosed tail rotor gearbox protects the tail rotor gears while at the same time allowing easy inspection.
探讨了发动机功率、空速、飞行高度等因素对尾桨故障试飞的影响。
It investigates influence of the factors such as engine power, airspeed and flight altitude on the tail rotor failure flight test.
为适应舰载和空运的要求，“铺路鹰”采用了可折叠的主旋翼和尾桨。
For shipboard operations and to ease air transportability Pave Hawks are equipped with folding rotor blades and tail stabilator.
然后，建立了一个剪刀式尾桨气动特性计算的分析模型，并进行了验证。
A free wake analytical model is then developed for predicting the aerodynamic characteristics of a scissors tail rotor and validated by numerical examples.
增加一个桨叶(主桨有5个叶片，尾桨有4个)，并使用了改进的排气系统。
Adding a rotor blade (it had five on the main rotor and four on the tail) and using a modified exhaust system were among them.
针对常规单旋翼带尾桨直升机，讨论不同特性的入流模型在直升机数值仿真中的作用。
For the classical helicopter of single main rotor with tail rotor, the effect of inflow models with different characteristics on helicopter trim and digital simulation were discussed in this paper.
研究剪刀式尾桨气动噪声的混沌特性，并应用混沌理论进行了直升机尾桨气动噪声信号分析。
Chaos characteristics of the aerodynamic noise are discussed and the aeroacoustic noise signals on helicopter scissors tail rotor is analyzed by the chaos theory.
以常规单旋翼带尾桨直升机为对象，讨论均匀与非均匀入流模型对直升机飞行数值仿真的影响。
For the current helicopter of single main rotor with tail rotor, the effect of inflow models with different characteristics on helicopter trim and digital simulation was discussed.
本文以风洞试验数据为依据，对在任意方向水平作用下的机身、垂尾和尾桨气动特性进行了研究。
This peper is based on the wind tunnel experiment data and studies the air dynamic performance of fuselage, horizontal stabilizer and fin under level wind in any direction.
汽车烧伤很快(或者我应该说，塑胶组件在汽车熔体)由于电力需求的尾桨是要远远大于我所料。
The motor burns out quickly (or I should say that the plastic component in the motor melts) as the power demand of the tail rotor is much larger than that I expected.
在直升机的阐述头和尾桨变速箱都必须是一个非常高规格的设计使用最好的材料和需要频繁和昂贵的维修。
In a helicopter the articulated head and tail rotor gearbox are required to be a very high specification design using the best materials and requiring frequent and costly maintenance.
文中首先给出自动驾驶仪的调节规律，继而列出装备有自动驾驶仪的单旋翼带尾桨式直升机的无量纲运动方程。
At first, control law of the autopilot equipment was given, then the non-dimensional dynamic equations of the single rotor helicopter with autopilot equipment were derived.
第八名：贝尔uh - 1IROQUOIS(惠)是一种军用直升机搭载单涡轮轴发动机，具有双桨叶主旋翼和尾桨。
Number 8. BELL UH-1 IROQUOIS (HUEY) is a military helicopter powered by a single turboshaft engine, with a two-bladed main rotor and tail rotor.
引入尾流收缩比因子，并将大速度时的涵道等效为圆形机翼，建立了一个适合于直升机悬停和前飞状态涵道尾桨气动特性分析的动量理论方法。
The shroud at high speed is modeled as an elliptic wing in order to construct a momentum theory method to investigate the aerodynamic characteristics of ducted tail rotor in hover and forward flight.
Z - 9b型特点是一个改进11浆叶涵道尾桨，减阻内置螺旋浆采用宽弦、全-复合浆叶而不是像在AS 365n1型中的13片全-金属浆叶。
The Z-9B variant features a modified 11-blade Fenestron faired-in tail rotor with wider-chord, all-composite blades instead of 13 all-metal blades as in as 365n1.
螺旋桨表面和它的尾涡面离散为四边形双曲面元，每个面元上布置等强度偶极子和源汇分布。
The surface of propeller and its trailing vortex is divided into a number of small hyperboloidal quadrilateral panels with constant source sink and doublet distributions.
某舰的螺旋桨尾轴长期处在恒定载荷作用下，虽然尾轴应力在弹性极限范围内，但是尾轴局部还是很容易发生微量的塑性变形。
Tiny deformation will appear in the local of the propeller shaft of certain ship which is endured an invariableness load, although the shaft stress is within the elastic limit range.
采用了一个修正的螺旋桨尾涡模型，来模拟导管螺旋桨尾涡片的扭曲变形及分离现象。
A modified trailing vortex wake model of propeller is introduced to describe the distortion and separation of the trailing vortex sheet.
采用了一个修正的螺旋桨尾涡模型，来模拟导管螺旋桨尾涡片的扭曲变形及分离现象。
A modified trailing vortex wake model of propeller is introduced to describe the distortion and separation of the trailing vortex sheet.
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