看一看，你会看到3d模型直升机的优质和创意！
Take a look and you'll see quality and creative 3d model of helicopter!
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。
This paper presents a simulation method of the defective lag damper fault on a helicopter rotor test rig.
一种遥控模型直升机的快装式旋翼，用于装配微型遥控模型直升 机。
The utility model relates to a package rotor of a remote control model helicopter, which is used for assembling a micro remote control model helicopter.
通过声音、灯光和整个机身的振动三个效果的综合作用，使得模型直升机的模拟射击效果非常逼真。
The comprehensive effects of the voice, light and the vibration of the whole helicopter body make the simulating shooting effect of the model helicopter be very realistic.
本实用新型可以使玩具模型直升机的升降控制稳定，在操纵模型飞机下降时不会发生摔到在地的情况。
The utility model can stabilize the lift control of the model helicopter, and avoid the occurrence of falling to the ground when manipulating the model helicopter to land.
救灾工作人员们可以俯瞰灾区的三维模型以寻找生还者或指挥救难直升机。
Relief workers could fly through a model of a disaster area to look for survivors and guide rescue helicopters.
提出了直升机模型桨叶颤振试验技术及试验方法。
An experimental technique and method for flutter research of helicopter blade model are proposed.
模型79与此同时，麦继续寻求出路的原则和设计开发的简单新华- 20喷气直升机。
MODEL 79 Meanwhile, McDonnell continued to seek an outlet for the principles and design simplicity developed in the XH-20 ramjet helicopter.
对某新型直升机垂直起落状态“地面共振”初步分析，采用经典的空间动力模型进行计算。
This paper described the primary analysis of a new model helicopter ground resonance in taking off and landing by employed classical spatial dynamic model.
提出了一砷能有效地对直升机模型进行辨识的鲁棒选择模型的新方法。
To identification the model structures of helicopter efficiently, a new robust criterion for model structure selection is developed.
计算结果表明，神经网络模型能够准确预测桨叶负扭度对直升机涡环状态的影响。
The result shows that the model of neural network can predict the effect of blade negative-twist on helicopter vortex-ring state.
最后采用算例直升机数据，进行了定直飞行的配平计算和操纵响应分析，结果证明了模型的合理性和有效性。
Finally the trim calculation and response analysis are carried out with the example helicopter's data. The results validate the rationality and validity of the model.
研究了一种无人直升机飞行力学模型辨识方法。
A method is presented for unmanned helicopter flight dynamics model identification.
论文首先介绍了直升机旋翼加载系统的结构，在建立了单通道加载系统的数学模型的基础上，分析了加载系统的动念性能。
First, the structure of helicopter airscrew loading system was introduced, On the basis of single channel loading system's math model, the system's dynamic performance was analyzed.
论文结合实际的工程项目，以某型号直升机旋翼气动载荷模拟为研究内容，对加载系统的组成、系统数学模型进行分析和研究。
In this thesis, the aerodynamic load simulation of one type of helicopter airscrew is studied, and the system's structure and its mathematic model are analyzed.
以此为基础，建立了电控旋翼直升机的飞行动力学模型。
Then the flight dynamics model of the ECR helicopter was constructed.
本文提出了一个较通用的直升机机动科目分段函数描述方法，该方法可以对ads - 33e -PRF规定的大部分任务科目建立逆仿真所需的数学模型。
A general mathematical method with subsection function is given to describe helicopter maneuver, most of mission task elements (MTE) defined in ADS-33E-PRF can be modeled.
应用该方法建立了直升机旋翼自转着陆过程的仿真模型，给出了全量模型和模型调整过程。
The simulation model for landing process of a helicopter with rotator self-rotating is built with the proposed method. The whole model and model tuning method are also given.
建立带吊挂直升机飞行操纵性分析的理论分析模型。
To analyze the handling quality of a helicopter with the heavy slung-load, this paper presents a theoretical analysis model.
准确的飞行数据对于建立无人直升机数学模型至关重要。
It is important to get accurate data in system identification in unmanned helicopter.
研究直升机悬停状态时其动力学模型非最小相位且不稳定特性的设计问题。
A study on the method of design is presented for helicopter hover with nonminimumphase unstable characteristics.
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。
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.
提出了一种基于集员辨识理论的直升机全耦合飞行动力学模型参数辨识方法。
A method based on the set-membership identification theory for the parameter identification of a helicopter fully coupled flight dynamics model is presented.
在此基础上，建立了直升机全耦合飞行动力学模型集员辨识的两步法。
Then a two-step method for the set-membership identification of a helicopter fully coupled flight dynamics model is established.
无人直升机操纵响应特性研究的关键是有准确的旋翼诱导速度模型。
The key to investigate control response characteristics of unmanned helicopter is to determine the correct induced velocity model.
并以欧拉方程为基础，结合动态入流模型，计算了某型无人直升机的操纵响应特性。
On the basis of Euler equation, the control response characteristics of a kind of unmanned helicopter is calculated incorporating dynamic inflow model.
在时域内建立了直升机粘弹减摆器的非线性模型。
A time domain model incorporating nonlinear dynamic behavior of elastomeric lag dampers is developed.
和实际飞行数据进行的比较表明，模型有相当的准确性，可以用于直升机增稳系统的控制设计。
Real flight data verify that the model is fairly accurate, and can be used in the design of stable augment control system of the helicopter.
和实际飞行数据进行的比较表明，模型有相当的准确性，可以用于直升机增稳系统的控制设计。
Real flight data verify that the model is fairly accurate, and can be used in the design of stable augment control system of the helicopter.
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