1) rotor shaft tilting angle
旋翼轴倾角
2) tiltrotor
倾转旋翼
1.
Modeling and analytical investigation on rotor/wing aerodynamic interaction for tiltrotor aircraft;
倾转旋翼机旋翼对机翼气动干扰的建模及分析
2.
Calculated method and parametric effect investigation of wing download of tiltrotor aircraft;
倾转旋翼机机翼向下载荷的计算方法及参数影响分析
3.
Experiment on aeroelastic characteristics of tiltrotor aircraft in transition flight;
倾转旋翼/机翼耦合系统过渡状态气弹动力学试验研究
3) tilt rotor
倾转旋翼
1.
Multidisciplinary design optimization for aerodynamics/structural dynamics of tilt rotor blade;
倾转旋翼桨叶空气动力学/结构动力学多学科优化设计研究
2.
Considering the operational characters of tilt rotor/propeller,a design method for tilt rotor/propeller is presented.
针对小型倾转螺旋桨独特的工作特性,在研究国外有关倾转旋翼桨叶设计现状的基础上,本文运用了遗传算法对桨叶的参数进行了寻优设计分析,以满足不同飞行状态的性能要求。
3.
The new-concept variable diameter tilt rotor (VDTR) which has a combined aerodynamic advantage of a large-diameter rotor in hovering flight and a small-diameter rotor in cruise flight represents a key developmental direction of the tilt rotor.
新概念变直径倾转旋翼综合了悬停时大尺寸旋翼和巡航时小尺寸旋翼的气动优点,是倾转旋翼飞行器的一个重要发展方向。
4) tilt-rotor
倾转旋翼
1.
<Abstrcat> In the present paper, the rotor wake of tilt-rotor aircraft is classified into the steady wake in hover and forward flight and the unsteady wake in transition flight, and a rotor free-wake analytical method for tilt-rotor aircraft has been developed based upon the Weissinger-L lifting-surface theory and rolled-up tip vortex model.
将倾转旋翼机的旋翼尾迹问题区分为二类,即悬停和前飞等状态的定常尾迹以及过渡飞行状态的非定常尾迹。
2.
In this paper, the aerodynamic interactions between rotor/wing/ fuselage of tilt-rotor in hover and transition flight was calculated.
本文计算了倾转旋翼飞行器悬停状态和过渡飞行状态的旋翼/机翼/短翼/机身之间的气动干扰和气动特性,分析了其特点,并进行了初步的试验验证。
3.
This thesis is aimed at the interaction aerodynamics problem on the rotor flowfield of a helicopter and a tilt-rotor aircraft by applying the rotor vortex theory and the panel method, and the major contributions of the author s research work are as follows:Based on the blade Weissinger-L model, rotor roll-up tip vortex model .
本文采用涡流理论方法和面元方法，对直升机和倾转旋翼机的旋翼下洗流场的干扰空气动力学问题进行了较为深入的研究。
5) wing incidence
翼倾角<火>
6) rotor shaft
旋翼轴
1.
One type of helicopter rotor shaft is the key fatigue part that drives rotor to revolve.
某型直升机旋翼轴是驱动旋翼旋转的关键疲劳部件,本文主要介绍了对该型直升机主旋翼轴载荷的测试方法:应变片的选择及测点布置,测试原理,测试结果及分析。
2.
This paper introduces the whole process of load testing for a main rotor shaft,including the testing requirements,principle, devices and major processes.
介绍了直11型主旋翼轴载荷测试的整个过程,包括测试要求、测试原理、测试设备和主要测试过程。
补充资料：双旋翼共轴式直升机
Image:11741642504817628.jpg
双旋翼共轴式直升机
双旋翼共轴式直升机
双雄翼共轴式直升机药基本特征是：两副完全相同的旋翼，一上一下安装在同一根旋翼轴上，两旋翼间有一定间距。两副旋翼的旋转方向相反，它们的反扭矩可以互相抵消。这样，就用不着再装尾桨了。直升机的航向操纵靠上下两旋翼总距的差动变化来完成。
双旋翼共轴式直升机主要优点是结构紧凑，外形尺寸小。这种直升机因无尾桨，所以也就不露要装长长的尾梁，机身长度也可以大大缩短。有两副旋翼产生升力，每副旋翼的直径也可以缩短。机体部件可以紧凑地安排在直升机重心处，所以飞行稳定性好，也便于操纵。与单旋翼带尾桨直升机相比，其操纵效率明显有所提高。此外。共轴式直升机气动力对称，其悬停效率也比较高。
研制共轴式直升机取得最大成功的是俄罗斯的卡莫夫设计局，该设计局研制出了庞大的“卡”系列直升机，它们基本上都是双旋翼共轴式布局。除大量民用直升机外，如卡-26、卡-226等，军用直升机也有不凡表现，卡-25曾是前苏联舰载反潜直升机食主力，新研制的战斗直升机卡-50、卡-52则更令人瞩目。北京航空航天大学飞行器设计与应用力学系的轻型飞机室研制的“蜜蜂－16”轻型单座直升机也采用了共轴双旋翼形式。
双旋翼共轴式直升机的主要缺点是操纵机构复杂。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。