旋翼

基于遗传算法的双旋翼系统的PID控制器设计

PID Controller Design Based on Genetic Algorithms for Twin Rotor MIMO System

双旋翼系统的PID参数整定与神经网络辨识

PID Parameters Tuning and Neural Network Identification of the Twin Rotor MIMO System

在1,000英尺的高度飞行时，他听到旋翼发出一种奇怪的噪音。

Flying at 1,000 ft , he heard a peculiar noise from the rotors .

计入桨叶运动的旋翼CFD网格设计技术

Grid Generation Technique for Helicopter Rotor CFD Including Blade Motions

用Newton子迭代方法计算前飞旋翼粘性绕流

Numerical simulation of the viscous flow past a helicopter rotor in forward flight using newton-like sub-iterations

直升机旋翼桨叶动态RCS特性研究

Dynamic RCS Behavior of Helicopter Rotating Blades

研究以降低直升机旋翼激振力为目标的复合材料桨叶结构动力学减振优化设计，分析了桨叶结构特性及桨尖后掠角等参数对N次/转旋翼桨毂振动载荷的影响。

A Model Analysis and Damping Optimization of Motorcycle Frame Structure The paper presents an analytical study of the helicopter rotor vibratory load reduction design optimization with aeroelastic stability constraints .

南航2m直径旋翼模型试验装置的测量系统

Introduction to the Measurement System of a 2m Diameter Rotor Model Test Facility of NUAA

本文用改进的双时间法和重叠网格通过求解可压缩的欧拉和N－S方程计算了悬停旋翼流场。

The flowfield for a rotor a blade in hover was computed using an improved dual time method by numerically solving the compressible Euler and Navier Stokes equations on embedded grids .

给出了三维Euler方程数值模拟悬停状态旋翼流场的方法和模型。

A numerical method based on solutions of Euler equations is used for calculating the flowfield over a lifting rotor in hovering .

应用FLOQUET理论分析直升机旋翼-机身耦合动不稳定性

An application of Floquet theory to analyse helicopter rotor-fuselage coupling dynamic instability

为了研究剪刀式旋翼的气动特性，在2m直升机旋翼模型试验台上进行了试验研究。

Experiments were conducted on a 2m helicopter model rotor test rig to investigate the aerodynamic characteristics of a scissors rotor .

为了描述四旋翼这样的典型的非线性对象，采用多个ARX模型组合的方法。

So as to represent the nonlinear object , the quad-rotor , a bunch of ARX models are adopted .

该方法运用了Jameson的旋转差分技术，并采用等效迎角方法计入旋翼尾迹的影响。

Jameson ′ s rotating finite difference methods is adopted and the wake effect is considered by introducing an equivalent angle of attack .

用上述方法对旋翼跨音速流场的高速脉冲（HSI）噪声进行了预测，计算结果与实验数据一致；

A rotor high-speed impulsive ( HSI ) noise is calculated and a comparison with available experimental data is made , and good agreement was demonstrated .

为验证计算方法的合理性，以ROBIN机身为算例，分别对孤立旋翼和旋翼/机身模型进行了模拟，并与实验结果进行了比较分析。

In order to verify the reasonableness of method , the isolated rotor and rotor / fuselage of the ROBIN are simulated . Then the results are compared with the experimental datas .

等拉力系数配平前飞时，旋翼各操纵角～前进比曲线和前飞需用功率～前进比曲线与德国宇航院（DLR）的试验结果比较一致。

In hover , and rotor control angles and power required versus advance ratio in forward flight with constant thrust coefficient at trim condition .

考虑离心力的影响，应用Hamilton原理建立了桨叶的摆振运动方程，并用广义Galerkin法对方程进行求解，分析了微型直升机旋翼桨叶变速度旋转时在摆振平面内的弯曲振动。

The equation for the rotor blade lag was derived using the Hamilton principle and solved using the extended Galerkin method . The blade lagging motion for the condition of varying angular velocities was analyzed .

以一种常见的旋翼翼型为例，探讨了两种旋翼桨叶翼型绕流数值模拟方法，即Jameson有限体积中心格式和有限体积通量修正Jameson/TVD混合格式。

Two methods based on Jameson scheme and Jameson / flux correction TVD ( Total Variation Diminishing ) mixed scheme are constructed to simulate the flow around rotor airfoil .

用有限体积法、三维N-S方程对旋翼近地飞行时的尾迹及地面涡进行了数值模拟。

A finite volume method is used to solve the3 D Navier Stokes equations to imitate the flow field and performance characteristics of a rotor in a forward flight near the ground .

旋翼载荷分析RASAP-I系统的几个特点

Some distinguishing features of rotor load analysis system rasap-i

为表明方法的有效性，分别以UH－1和H－34两种直升机旋翼为算例，计算了不同前飞状态的自由尾迹形状，展示出小速度时尾迹畸变和叶尖涡卷绕的重要特征。

As examples , the calculations on free wake of UH 1 and H 34 rotors are performed for different advance ratios , and the feature of highly distorted free wake shapes and the strong tendency toward a rapid wake roll up for low speed case are exhibited .

利用最新发展的直升机旋翼气动声学程序计算了某模型旋翼桨涡干扰（BVI）噪声，叶片表面非定常压力脉动数据由最新实验获得。

A newly developed helicopter rotor aeroacoustics code and newly obtained unsteady surface pressure data on the blade of a model helicopter rotor are used to predict rotor blade vortex interaction noise .

双旋翼多输入多输出系统TRMS由于非线性和强耦合，难以建立数学模型和控制，故提出PID参数模糊自整定的控制方法。

Because of the non-linearity and close coupling , it is difficult to establish mathematics model and control for twin rotor multi-input and multi-output system ( TRMS ) . Therefore , the self-adjusting control measure of PID parameter fuzzy is proposed .

在非结构网格上应用聚合多重网格技术来加速Euler方程的收敛过程。基于非结构动态嵌套网格，将聚合多重网格方法引入到旋翼的前飞流场计算中。

An agglomeration multigrid algorithm has been developed to accelerate the convergence of the Euler equations to a steady state on unstructured meshes . An agglomeration multigrid method was applied to numerical calculation of rotor forward flight flow based upon the unstructured dynamic overset grids .

应用该模型，对后掠桨尖的UH－60A旋翼在悬停时的桨叶载荷分布进行了计算，并与相应的试验结果作了对比。

As examples , a comparison in hover with the experimental data on the UH-60A rotor with a swept tip is given , and the calculation on the blade section loading of a tapered-tip blade is made and compared with the result of a rectangular reference blade .

本文介绍了旋翼电热防冰系统及其加热元件的主要技术参数，并根据UH-1H旋翼防冰试验结果，就空气动力旋翼防冰/除冰热效率的影响，进行了初步分析。

This paper describes the rotor ice-protected system and parameter of thermo - element . The effect of aerodynamic on the rotor deicing thermal efficiency is analysed with testing results of an ice-protected UH-1H .

本文采用Peters-He非定常动态入流模型，同时附加尾迹弯曲的影响，建立了旋翼尾迹弯曲非定常动态入流模型用于计算旋翼倾转过程中的诱导入流速度。

By using the Peters-He unsteady dynamic inflow model and considering the wake bending effects , a rotor wake bending unsteady dynamic inflow model for computing the induced velocity during tilting process has been established .

旋翼塔信号传输系统干扰的排除方法

The Method of Remove Disturb of Signal Transmission of Rotor Tower

遥控小型倾转旋翼机飞行控制系统研究

Synthesis of Remote Control System of a Small Tilt Rotor Aircraft