Connection apparatus for a helicopter rotor blade, comprising.
连接装置的直升机转子叶片，其中包括。
The flow field of the helicopter rotor is characterized by unsteady phenomena.
旋翼的流场呈现很强的非定常现象。
The helicopter rotor blade deicing technique is greatly important to ensure the flight safe - ty.
直升机旋翼桨叶除冰技术对保证直升机飞行安全是十分重要的。
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。
The adaptive optimal decoupling control method of helicopter rotor concordant loading system was discussed.
研究了直升机旋翼协调加载系统的自适应最优解耦控制问题。
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。
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 paper mainly introduces the function, the hardware and software of the monitoring system of the helicopter rotor testing device.
本文详细介绍直升机旋翼实验台实时监视报警系统的功能，硬件配置以及软件设计方法。
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。
Research shows that, it is suitable for rotor dynamics, dynamic analysis of helicopter rotor blades fuselage systems and piping systems contained flow fluid.
研究表明，本方法适用于转子动力学，直升机旋翼-机身耦合系统以及具有流体流动的管道系统的动力分析。
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 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。
Based on the rotor free-wake model and the rotor trim model, an analytical method is developed for the prediction of helicopter rotor induced velocities on missile trajectory.
应用自由尾迹方法和旋翼配平模型，建立了一个悬停和前飞状态旋翼在导弹发射线上的诱导速度计算模型。
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 whole measuring process is controlled by microcomputer. The quick accurate automatically measuring of helicopter rotor common taper is given. The system accuracy is analyzed.
本文给出了测试系统的原理、软件及硬件配置，测量过程由微机控制实现对直升机旋翼共锥废的快速、精确、自动测量，并分析了该系统的精度。
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。
It is a characteristic of the helicopter rotor and its engine installation, and the engine control in this condition is a typical integration control of the helicopter and the engine.
直升机自转进入和退出是直升机机动飞行经常遇到的状态，它的特性是由直升机旋翼和发动机的安装特性共同决定的，该状态的发动机控制是典型的直升机与发动机的综合控制。
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。
The wake geometry feature of helicopter rotor in hovering is visualized by experimental method in this paper and the preceding wake geometry model is updated according to the experimental results.
本文用试验的方法显示了悬停状态旋翼的尾迹几何形状，并以试验结果为依据对现有的尾迹几何模型进行了修正。
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。
Then there's increasing the number of rotor blades. This helps because each additional blade carries less of the weight of the helicopter, and thus produces less noise.
增加旋翼桨叶数量也是一种方法，这使得每片桨叶负载的直升机重量降低了，因此产生的噪音更小。
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。
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。
When the helicopter began getting away from the pilot he pulled back on the cyclic which controls the pitch of the rotor blades only to find the aircraft unresponsive.
当直升机开始与飞行员脱离的时候，他向后扳用来控制转翼叶片变矩的操纵杆，但直升机毫无反应。
Once you set the rotor size, you pretty much have determined the thrust air speed (if you know the mass of the helicopter).
一旦旋翼大小固定，几乎决定了空气推进速度(如果你知道直升机重量)。
The complete rotor, engines, clutches, and rotor-air compressors (Fig. 14) were to have been identical to the units then under development for the XHRH-1 assault helicopter.
完整的转子，发动机，离合器和转子空气压缩机(图14)是已被相同的单位则正在开发中的XHRH - 1攻击直升机。
应用推荐