英汉例句

• 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。

• 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。

• 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。

• combining dynamic design for a type of helicopter rotor blade, numerical examples in engineering application are given.

  结合某直升机旋翼桨叶的动力学设计，给出了应用的数值算例。

• helicopter rotor noise is one of the most important problems among helicopter manufacture. the problem is so complex and involves many domains that lots of researchers are interested in.

  直升机旋翼噪声是直升机工业发展面临的重大问题之一，因其问题复杂，涉及的学科多，一直吸引众多研究者的注意。

• 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。

• 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。

• 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。

• aeroelastic model is developed to analyze aeroelastic stability of helicopter rotor blade with swept tips.

  通过建立具有后掠桨尖旋翼气弹稳定性的分析模型 ，研究后掠桨尖旋翼气弹的稳定性。

• 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.

  通过建立带受控振蕩附翼的新概念旋翼气动弹性分析模型，研究了采用受控振蕩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 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。

• an analytical prediction method for helicopter rotor noise due to the ingestion of atmospheric turbulence is summarized.

  本文简述了一种直升机旋翼与大气湍流入流相干扰产生的噪声预估方法。

• in this paper a kind of fatigue design method of helicopter rotor system in detail engine design phase is presented.

  本文介绍了工程设计阶段直升机旋翼系统部件强度设计的流程和方法。

• a support beam for connecting a lift generating wing section of a helicopter rotor blade with a rotor hub, said support beam comprising.

  支持梁连接电梯发电翼的第一个直升机旋翼叶片与转子枢纽的地位，表示支持梁，包括。

• the coupled flap-lag flutter stability of a helicopter rotor blade in hover is investigated by using a finite element formulation based on the principle of minimum potential energy.

  本文用基于最小位能原理的有限元方法研究了直升机悬停时旋翼浆叶挥舞—摆振耦合颤振。

• 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。

• 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。

• 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。

• 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。

• a grid generation technique for helicopter rotor computational fluid dynamics (cfd) including actual blade flapping and pitching motions is presented.

  提出了一个考虑桨叶实际的挥舞和变距运动的旋翼cfd网格生成方法。

• 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。

• results show that the method is simple and provides a foundation for the development of the helicopter rotor diagnosing and monitoring system.

  该诊断方法简捷可行，为进一步开发旋翼状态监测与故障诊断系统提供技术基础。

• 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。

• 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。

• 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。

• surface pressure data from 3 d unsteady free wake panel method has been used to predict the helicopter rotor blade vortex (bvi) interaction noise.

  由三维自由尾迹非定常板元方法计算的三元非定常气动力出发，计算直升机旋翼桨涡干扰噪声。