rotor model

An analytical model of tilt-rotor/ pylon/ wing coupled aeroelastic stability is presented and the dynamic equations are derived for a new semi-articulated, soft-inplane tilt-rotor aircraft.

针对新型半铰接式、摆振柔软的倾转旋翼机，建立了旋翼/动力舱/机翼气动弹性稳定性分析模型，并导出了系统的动力学方程。

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Some Improvements of Data Acquisition and Processing System for Helicopter Rotor Model Test Stand

直升机旋翼模型试验台的数据采集与处理系统的若干改进

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Established the aerodynamic model of the airscrew, studied the rolling channel control model of the tilt rotor.

建立了倾转旋翼机的螺旋桨动力学模型，分析研究了倾转旋翼机滚动通道模型。

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The main characteristics of the rotor model, control and excitation system, power and transmission system, measurement system, data acquisition and processing system, safety and warning system, display system and master console are briefly described.

本文对旋翼模型、操纵与激振系统，动力、传动系统，测量系统，数据采集与处理系统，安全监控与报警系统，以及中央控制台与显示系统等的主要特点均作了简略叙述；

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Based on a Jeffcott rotor model with nonlinear radial rub force, the approach to chaos is studied when the forcing frequency and nondimensional unbalanced mass are treated as control variables.

对具有质量偏心仅考虑径向碰摩力非线性的Jeffcott转子模型，研究了其通向混沌的路径。

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Mathematical model and formulations of a new tilt-rotor aircraft for aeroelastic stability analysis

新型倾转旋翼机气动弹性稳定性分析模型

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In this thesis, a numerical simulation method for the combined tilt-rotor/ wing/ fuselage flowfield has been established by solving the Euler equations coupled with the momentum source model.

本文结合动量源模型，建立了以欧拉方程为主控方程的倾转旋翼机旋翼/机翼/机身流场的数值模拟方法。

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Test performance comparison of rotor model with two kinds of tip shape of blade

两种桨尖形状旋翼模型试验特性对比

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A model of rotor system is studied in this paper. Transfer matrix method is utilized to calculate the rotor dynamic behavior and the influence of a crack on rotor dynamic behavior is considered especially.

选取转子支承系统为研究对象，利用传递矩阵方法计算转子系统的动力特性，目的在于探求裂纹对转子动力特性的影响。

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A Mathematical Model of Tilt-rotor Flight Dynamics and Investigation of Flight Control in Transition Mode

倾转旋翼飞机过渡模式动力学建模与控制研究

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A complete tilt rotor aircraft flight control model was developed to enable design of tilt rotor aircraft.

建立倾转旋翼机数学模型是设计其合理的飞行控制律的基础。

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A model is developed for the calculation of the initial rotor tip vortex core radius aiming at eliminating the empirical parameters of the tip vortex in rotor free-vortex wake analysis.

建立了一个旋翼桨尖涡初始涡核半径计算模型，用于消除旋翼自由尾迹分析中桨尖涡涡核半径依靠经验设定的现状。

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Research of Dual Model Reference Adaptive Control System for Tilt-Rotor Aircraft

倾转旋翼机模型参考自适应双重控制系统研究

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This mathematical model could be used for design and simulation of the control system of tilt rotor aircraft.

该数学模型可为倾转旋翼航空器的控制系统设计与仿真提供参考。

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And respectively set up two kinds of flow induced force model, as also as rotor model.

并且分别建立了两种气流力的模型，以及转子模型。

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