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.
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。
This paper described the primary analysis of a new model helicopter ground resonance in taking off and landing by employed classical spatial dynamic model.
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。
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.
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 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.
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 following pictures are made from a model of a helicopter with a camera attached to it.
以下的图片是在一个直升飞机上利用摄相机拍摄的。
To identification the model structures of helicopter efficiently, a new robust criterion for model structure selection is developed.
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。
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.
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。
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。
The result shows that the model of neural network can predict the effect of blade negative-twist on helicopter vortex-ring state.
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。
A method is presented for unmanned helicopter flight dynamics model identification.
研究了一种无人直升机飞行力学模型辨识方法。
The key to investigate control response characteristics of unmanned helicopter is to determine the correct induced velocity model.
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。
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.
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。
The Hughes Model 300 is an American three-seat version of the Hughes 269 light helicopter.
美国休斯300型是休斯269型的三座轻型直升机改进型。
Through analyzing the radiate characteristic of the armed helicopter in theories, the operating range model of a staring IRST system for the armed helicopter was established.
通过对武装直升机的红外辐射特性进行分析，建立了凝视型IRST系统对武装直升机的作用距离模型。
A system configuration of helicopter simulation is given and a mathematical model of helicopter hovering is set up as to development helicopter simulating system in Marine search and rescue simulator.
为了研制海上搜救模拟器的直升机模拟系统，给出了直升机模拟的系统结构，建立了直升机的悬停数学模型。
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。
To analyze the handling quality of a helicopter with the heavy slung-load, this paper presents a theoretical analysis model.
建立带吊挂直升机飞行操纵性分析的理论分析模型。
In this paper, the case helicopter is modeled and trimmed, and the result shows that the model is conformed to the movement of the helicopter.
以某直升机为算例，建模并配平，结果表明，该模型符合直升机运动规律。
A method based on the set-membership identification theory for the parameter identification of a helicopter fully coupled flight dynamics model is presented.
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。
Then a two-step method for the set-membership identification of a helicopter fully coupled flight dynamics model is established.
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。
A reasonable criterion of vortex ring state boundary for helicopter is acquired based on model rotor tests.
通过模型旋翼试验得到了合理的直升机涡环边界判据，并由此计算得到了直升机通用涡环状态边界。
The rotor model test system is the basic and most important test facility for the research of helicopter theory and technology, and also for the development of a new helicopter.
旋翼模型试验系统是开展直升机理论与技术研究、新机研制的最基本和最重要的试验设备。
First, the simplified dynamics and kinematics model of attack helicopter air-combat are created, and the specific method on simplification of the model is given.
首先建立了简化的武装直升机空战动力学和运动学模型，阐明了模型简化的具体方法；
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。
On the basis of Euler equation, the control response characteristics of a kind of unmanned helicopter is calculated incorporating dynamic inflow 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。
Finally, the effect of the helicopter engine inlet and outlet was analyzed using a simplified engine model and the rotor-fuselage-engine interactions were obtained.
最后运用简单的发动机模型分析了发动机进出口对直升机流场的影响。
According to the three degree of freedom (3dof) helicopter model, this paper present a novel robust controler based on LQR and fuzzy theory.
本文针对三自由度直升机模型设计了基于线性二次型调节器(LQR)和模糊逻辑的鲁棒控制器。
The toy helicopter also has the advantages that the utility model is firm in structure and hard to be damaged.
本玩具直升飞机还具有结构坚固、不易损坏的优点。
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 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。
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