| 1. | The contradiction between bracing rigidity and aerodynamic interference can be resolved by this system
该系统能解决支架的支撑刚度与气动干扰之间的矛盾。 |
| 2. | The rotor / wing aerodynamic interactions of the tilt rotor vehicle in hover is described in this dissertation
本文主要研究的是倾转旋翼飞行器悬停状态时，旋翼机翼之间的气动干扰问题。 |
| 3. | When the tilt rotor vehicle is in hover , the aerodynamic download of the rotor flowfield imposes on the wing . in this time , the rotor / wing interaction is severe
倾转旋翼飞行器悬停时，旋翼的下洗流刚好作用在机翼上，此时，旋翼机翼间的气动干扰非常剧烈。 |
| 4. | By adopting the full state feedback approach and using the modeling aerodynamic interference as feedback nonlinearities , a new autopilot for uav close formation flight is designed
采用全状态量反馈，同时将气动干扰作为非线性反馈，设计出一套适用于无人机近距离编队飞行的自动驾驶仪。 |
| 5. | The analysis of the results from the numerical simulation shows fairly good effect and it concludes the method can be effectively used to solve the different problems of the similar fields
本文的主要工作是为对空载发射导弹提供发射初始弹道数据，重点和难点在于机?弹气动干扰力的数值计算。 |
| 6. | Furthermore , because rotors are mounted on the tips of the wing , the rotor / pylon / wing aerodynamic interactions are also included in the model . such factors reflect the unsteady and nonlinear characteristics in the model
此外,倾转旋翼飞机的旋翼安装在翼尖,旋翼/发动机短舱/机翼之间的气动干扰是建模的一个难点。 |
| 7. | Finally , an iterative method coupled between rotor free wake model and lifting wing panel model is given . by the method , the aerodynamic interaction of the rotor on its wing for tilt - rotor aircraft in hover are computed and discussed
最后，建立了一个耦合的旋翼机翼气动干扰分析方法，计算分析了悬停状态旋翼流场对机翼的气动干扰影响。 |
| 8. | After the data is analyzed , the software of fluent is used to calculate the flowfield . in order to make the calculation results agree with the experimental data , the model of the calculation has been modified based on the results of the experiment data
详细分析比较旋翼机翼间的气动干扰试验数据后，应用fluent软件进行分析计算，根据试验结果修正计算模型，使计算结果与试验结果趋于一致。 |
| 9. | This paper provides a powerful method for the compatibility design of aircraft with external store , a missile , by calculating fast , conveniently and effectively the relative trajectory and relative attitude of the store with respect to aircraft during the separation process
此外，为了有效击中目标，需要掌握投放初始阶段外挂物姿态和运动轨迹数据。因此，研究机载发射过程中的弹机气动干扰力，考虑其对导弹发射后的弹道仿真初始参数的影响十分必要。 |
| 10. | Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor , kinetic behavior of rotor , rotor / wing aerodynamic interactions , etc . ) . in order to carry on further research and experimentation of these project , national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench . base on need of this bench , this paper study / design pitch control system on it
随着对倾转旋翼飞行器的深入研究,倾转旋翼的气动特性、动力学特性、旋翼/机身间的气动干扰等课题方面已有一定的理论成果出现。为了对这些课题进行深入研究和试验验证,我校直升机旋翼动力学国防科技重点实验室着手建造了倾转旋翼模型实验台。 |
