Connection apparatus for a helicopter rotor blade, comprising.
连接装置的直升机转子叶片，其中包括。
A new way to solve dynamical response of rotor blade in helicopter.
提出了一种全新的计算旋翼桨叶动力响应的方法。
A new way to solve dynamical response of rotor blade in helicopter.
提出一种面向设计的复合材料旋翼桨叶结构动力优化方法。
Gravity center modification method can be used in high-load rotor blade design...
重心线调节法可应用于高负荷叶片设计。
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 simple puff of air will send the rotor blade spinning and get the LED lights glowing.
简单的空气粉扑将发送转子叶片旋转并获得LED灯发光。
Rotor blade vibration measurement kept the high-speed rotating blades stable in property.
高速旋转叶片在使用中性能稳定。
Gravity center modification method can be used in high-load rotor blade design in engineering.
重心线调节法可应用于高负荷叶片设计。
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。
The cause of water erosion in the end rotor blade of 100 MW steam turbine is analyzed with solution proposal.
对神木发电有限公司100MW汽轮机末级动叶片水蚀原因进行了分析，并提出了解决方案。
The numerical method of determining the water droplet impingement property of rotor blade in hover was studied.
介绍了直升机在悬停状态下，求解旋翼水滴撞击特性的数值方法。
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 of structure and dynamics of a rotor blade is based on its section characteristic of composite blade.
复合材料桨叶剖面特性是旋翼桨叶设计的最基本原始参数，也是桨叶结构设计、动力学设计和结构分析的基础。
As to the selection of rotor blade number for light and medium helicopter, 4 blade and 5 blade rotor are typical.
而旋翼桨叶片数的选择，对轻型和中型直升机来讲，4片桨叶旋翼和5片桨叶旋翼具有典型意义。
Practical application shows that this system can solve the problems appeared in the rotor blade digital design effectively.
实际应用表明，该系统能够有效地解决桨叶数字化设计过程中的出现的问题。
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.
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。
Thermal analysis on the first stage turbine rotor blade has been completed based on the CFD results under calculated conditions.
根据某型涡喷发动机计算状态叶片流场计算结果，对该发动机高压涡轮转子叶片进行了热分析；
Rotor blade connection according to claim 4 wherein the intermediate layers are covered with electrically controlled piezo elements.
转子叶片连接据索赔4其中，中间层是涵盖与电控压电元素。
Rotor blade connection according to claim 1 wherein the support beam and the intermediate layers comprise a fiber reinforced material.
转子叶片方面，根据权利要求1其中，支撑梁和中间层组成，纤维增强材料。
When the rotor blade with the traditional high quality steel stator supporting the use of common, it does not produce adhesion, low noise.
当叶片转子与传统的优质钢定子共同配套使用时，它不会产生粘连，噪音低。
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。
Tip clearance flow in a radial inflow turbine rotor blade under stage environment was investigated by 3-dimensional viscous flow simulation.
对微型燃机向心透平叶轮顶部间隙流动在级环境下进行了全三维粘性数值模拟。
The results show that, the influence of stator clocking effects on the stator blade's unsteady aerodynamic loads is larger than that on the rotor blade.
结果表明，时序效应对静叶片气动负荷的影响明显高于动叶片的。
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。
The research on the rotor blade-vortex interaction (BVI) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field.
旋翼桨-涡干扰噪声问题是直升机气动声学领域的一个研究热点和难点。
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。
In addition, the wake interaction of upstream blade row and the expansion wave at rotor exit also cause an unsteady force acting on the downstream rotor blade surface.
此外上游静子尾迹以及动叶尾缘出口膨胀波等也是产生转子叶片表面非定常力的因素。
In addition, the wake interaction of upstream blade row and the expansion wave at rotor exit also cause an unsteady force acting on the downstream rotor blade surface.
此外上游静子尾迹以及动叶尾缘出口膨胀波等也是产生转子叶片表面非定常力的因素。
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