| 1. | 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。
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| 2. | A simulation of the guidance scheme applied to the example tilt rotor vehicle exhibits satisfactory behavior in the presence of wind and initial errors
仿真结果表明,在初始扰动和有风作用下,垂直距离偏差均达到很小。
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| 3. | Thus the flight dynamic characteristics and control features in the conversion mode are the key technologies in the whole tilt rotor design
过渡模式飞机的气动布局改变主要体现在纵向平面内,所以本文主要研究过渡模式下飞机纵向通道的动力学特性和控制系统设计。
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| 4. | 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。
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| 5. | The model developed here is suitable for the tilt rotor aircraft during hover , transition and cruise . the longitudinal equations of motion provide a foundation for further investigation on tilt - rotor flight dynamics
文中所建模型具有较高精度,适合于飞行包线内的所有模式,为倾转旋翼飞机飞行动力学的进一步研究提供了基础。
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| 6. | A mathematical model reflecting the tilt rotor unsteady and nonlinear aerodynamic characteristics in the longitudinal channel is presented in the paper . in the full flight envelope , the rotor thrust continues tilting and the aerodynamic forces of each component change as a function of airspeed and nacelle angle
在整个飞行包线内,旋翼的推力矢量方向不断变化,飞机各部件的气动力随发动机短舱倾角和空速的变化而变化,因而飞机的飞行动力学有很强的非定常、非线性特性。
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| 7. | Variable diameter rotor is an effective method to improve the aerodynamic performance of tilt - rotor in both hover and cruise state . on the basis the research before , the variable diameter tilt rotor structure design has been finish , and in virtue of the technology of virtual prototyping to simulate and analyze the kinetic , dynamic and intensity property of it
变直径倾转旋翼能有效的改善倾转旋翼机悬停和巡航状态下的气动效率,本文提出了变直径倾转旋翼试验模型设计方案,完成了可变直径倾转旋翼的结构设计,并利用虚拟样机技术对变直径倾转旋翼的运动特性、结构动力学特性以及结构强度进行了分析、研究。
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