Connection apparatus for a helicopter rotor blade, comprising.
连接装置的直升机转子叶片，其中包括。
This paper presents a simulation method of the defective lag damper fault on a helicopter rotor test rig.
提出了一种在模型直升机旋翼故障试验台上模拟减摆器失效故障方法。
A refined aeroelastic model of a helicopter rotor blade with swept tips is established based on model matching.
以动力学模型和气动模型相匹配为原则，建立了后掠桨尖旋翼的细致气弹模型。
The design and the construction of a data acquisition and preprocessing system for a helicopter rotor test rig are described.
介绍了某直升机旋翼试验台的振动数据采集和预处理系统的设计和组成。
While similar to a helicopter rotor in appearance, the autogyro's rotor must have air flowing up and through the rotor disk in order to generate rotation.
虽然与直升机外观相似，但自转旋翼机必须依靠向上流过桨叶地气流维持旋翼地旋转，产生将飞行器维持在空中地升力以及向前飞行地推力。
A rotor blade, specially for a helicopter rotor, which blade is made of reinforced plastics and a process for making this blade in a single molding operation.
一转子叶片，特别是为直升机旋翼，叶片制成的增强塑料和一个过程，使这种刀片在一个单一成型的运作。
To fly the aircraft in anything other than a hover the control vanes are used to create a force vector to tilt the machine in the desired direction much like a Helicopter rotor.
飞行中的飞机以外的悬停控制叶片被用来创造一个倾斜力向量机在希望的方向就像直升机旋翼。
The vortex wake and its induced velocity of a helicopter rotor operating near the ground at low forward speeds have been studied using a simplified free wake-ground vortex model.
本文用一简化自由涡模型模拟旋翼尾涡系，用一简单涡模拟地面涡，对近地低速飞行时旋翼尾涡系的畸变及其引起的诱导速度变化作了研究。
The aeroelastic analysis of a helicopter rotor blade with the controlled oscillating trailing edge flap is presented by building an aeroelastic model of the new concept rotor blade.
通过建立带受控振荡附翼的新概念旋翼气动弹性分析模型，研究了采用受控振荡附翼的直升机旋翼气动弹性特性及其在降低旋翼振动载荷方面的有效性。
This means it can hover like a helicopter, but when flying forward can reduce the speed of the main rotor because the wings provide part of the lift.
这意味着它能像一架直升机那样作空中悬停，而在向前飞行时，又能降低主旋翼的速度，因为它的一对短翼提供了部分升力。
It's a single rotor helicopter powered by batteries made by US Hybrid.
萤火虫项目是一种单旋翼直升机，使用美国混合动力(US Hybrid)公司制造的电池。
A series of tests to do that were conducted on a UH-60A Blackhawk helicopter rotor in a NASA wind tunnel from January to May 2010.
而一系列试验将于2010年1月至3月NASA的风洞中、在一个UH - 60A黑鹰直升机的转子上进行。
This means it can hover like a helicopter, but when flying forwards can reduce the speed of the main rotor and let the wings provide part of the lift.
这意味着它能像直升机一样悬停，但向前飞时可能减少主旋翼的速度并让这两个短翼提供部分提升力。
But unlike an aircraft, when a helicopter is flying forwards the air passing over its rotor blades does so at different speeds.
但是与飞机不同的地方在于，当直升机向前飞行时，空气是以不同的速度流过旋转的叶片的。
This means it can hover like a helicopter, but when flying forwards can reduce the speed of the main rotor and let the wings provide part of the lift. Its propellers give the extra oomph.
立方直升机的这种配置让他可以像直升机一样盘旋，但在向前飞行时，主旋翼的转速可以将下来，让两侧的机翼提供升力，在此情况下，两台螺旋桨推进器就能发挥大作用了。
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.
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。
The airfoil member according to claim 1, configured as a rotor blade for a helicopter.
翼型会员根据权利要求1 ，配置为转子叶片为直升机。
A test method of measuring rigid modal behavior of column rotor helicopter on landing gear is suggested in this paper.
本文基于模态分析理论和试验技术，提出了一套测定纵列式旋翼直升机在起落架上的刚体模态特性试验方法。
Dave Thomas: A helicopter has four main controls: foot pedals, collective pitch lever , cyclic, and throttle. The foot pedals control the tail rotor.
戴夫·托马斯：直升机有四个主要的控制器：脚踏板、总距操纵杆、周期变距操纵杆以及气门。
Dynamic stability and control laws of a hingeless rotor helicopter were studied.
研究了无铰直升机动稳定性、操纵性和控制问题。
A reasonable criterion of vortex ring state boundary for helicopter is acquired based on model rotor tests.
通过模型旋翼试验得到了合理的直升机涡环边界判据，并由此计算得到了直升机通用涡环状态边界。
With a simple change to the mission setup menu in FSX, the Tilt Rotor can be used to complete all the helicopter missions available as standard.
以一个简单的更改的任务菜单中设置FSX，转子的倾斜可以用来完成所有任务的直升机可作为标准。
The helicopter has a five-blade main rotor and a four-blade tail rotor.
直升飞机有一个五浆叶主旋翼和一个四浆叶尾旋翼。
To analyze helicopter rotor dynamic stability with a high degree of accuracy, accurate and reliable damping coefficient determinations of rotor structure are needed.
为了提高旋翼动稳定性理论模型的分析精度，需要精确地确定旋翼系统的结构阻尼系数。
This paper introduces a method of making selection of helicopter tail rotor parameter optimization using computer optimum techniques.
本文介绍采用计算机优化技术进行直升机尾桨参数优化选择的方法。
By the analysing foreign icing test result, the considered design factors of rotor icing protection are presented, which are used as a reference to helicopter icing protection design and test.
根据国外直升机结冰试验结果，提出了旋翼防冰设计应考虑的因素，可供直升机防冰设计和试验时参考。
As a critical part of helicopter, rotor blade anti-fatigue design technique is one of the key to improving safety life and decreasing cost.
作为直升机的关键动部件，桨叶的抗疲劳设计技术是提高桨叶安全寿命，降低桨叶使用成本的关键。
According to requirement of the shimmy damper's structure and performance of a kind of helicopter rotor system, the paper presents a new kind of metal rubber-steel cable shimmy damper firstly.
参照某型直升机旋翼系统对减摆阻尼器的结构及性能的要求，首次研制了一种金属橡胶-钢丝绳索型减摆器。
According to requirement of the shimmy damper's structure and performance of a kind of helicopter rotor system, the paper presents a new kind of metal rubber-steel cable shimmy damper firstly.
参照某型直升机旋翼系统对减摆阻尼器的结构及性能的要求，首次研制了一种金属橡胶-钢丝绳索型减摆器。
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