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公开(公告)号：US20120070288A1
公开(公告)日：2012-03-22
申请号：US13237075
申请日：2011-09-20
申请人： Marc HÖFINGER
发明人： Marc HÖFINGER
IPC分类号： B64C11/18
CPC分类号： B64C27/72 , B64C23/005 , B64C2027/7261 , B64C2230/28 , Y02T50/166 , Y02T50/34
摘要： A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end and a rear end and mounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial or spanwise axis of the rotor blade. The flap has a basic position in which it lies flat against the upper surface of the main body. Further, the flap is passively swiveled by aerodynamic forces and inertial forces about its swivel axis to raise above the upper surface of the main body, and a reset force acts upon the flap to reset it into its basic position on the surface of the main body.
摘要翻译： 用于旋转翼飞行器的从动水平转子的转子叶片包括细长主体，其包括前缘，后缘以及在前缘和后缘之间延伸的上表面。 转子叶片还包括具有前端和后端的至少一个翼片，并且在其前端处安装到主体上，围绕与转子叶片的径向或翼展轴线平行延伸的旋转轴线旋转。 翼片具有基本位置，其平放在主体的上表面上。 此外，翼片通过围绕其旋转轴线的空气动力和惯性力被动地旋转，以在主体的上表面上方升高，并且复位力作用在翼片上以将其复位到主体的表面上的基本位置 。
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2.发明授权Apparatus and method for roll moment equalization at high advance ratios for rotary wing aircraft 有权用于旋转翼飞机的高提前比例的滚动力矩均衡装置和方法公开(公告)号：US09205919B1
公开(公告)日：2015-12-08
申请号：US13999366
申请日：2014-02-13
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.
摘要翻译： 公开了一种用于以高提前比率均衡滚动力矩的方法，包括通过推力源在空速下向前推动飞行器，并以相对于空速的角速度旋转飞机的转子，以有效地引起正向 当叶片沿退回方向移动时，由于叶片在退回方向上的空气流过，在每个叶片上的总升力。 转子包括在转子毂周围以相等的角度间隔放置的偶数个叶片。 调节循环桨距和转子迎角的一个或两个，使得由于反向气流而导致的后退叶片的滚动力矩由于提升而在前进叶片上的滚动力矩的0.3至0.7倍之间。
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公开(公告)号：US09022313B2
公开(公告)日：2015-05-05
申请号：US13335541
申请日：2011-12-22
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A method and apparatus for enabling high speed flight in a rotorcraft are disclosed. The method may include executing a flight with a rotorcraft. The flight may include a first portion and second portion ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. Once sufficient airspeed is obtained, the flight may transition to the second portion. Wherein, substantially all of the weight of the rotorcraft may be supported by one or more fixed wing surfaces of the rotorcraft. Thus, during the second portion, the rotor may be completely unloaded. To keep the rotor stable by turning, the rotor may be powered during the second portion by an engine of the rotorcraft by way of a prerotation system.
摘要翻译： 公开了一种用于在旋翼航空器中实现高速飞行的方法和装置。 该方法可以包括执行具有旋翼航空器的飞行。 飞行可以包括顺序排列的第一部分和第二部分。 在第一部分期间，旋翼航空器可以独自在自转中与转子一起飞行。 一旦获得足够的空速，飞行可以转变到第二部分。 其中，旋翼航空器的基本上所有的重量可以由旋翼航空器的一个或多个固定翼面支撑。 因此，在第二部分期间，转子可以完全卸载。 为了通过转动来保持转子稳定，转子可以在第二部分期间由旋转飞机的发动机通过预旋转系统供电。
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公开(公告)号：US20180072410A1
公开(公告)日：2018-03-15
申请号：US15261811
申请日：2016-09-09
发明人： Neldon P. Johnson
IPC分类号： B64C27/473 , B64C27/72
CPC分类号： B64C27/473 , B64C27/30 , B64C27/72 , B64C2027/7261
摘要： A VTOL rotor assembly for a compound VTOL aircraft, the VTOL rotor assembly having a rotor sleeve, a pair of rotor blades which are extendable from the rotor sleeve for vertical take off and landing and retractable to the rotor sleeve as forward air speed exceeds the stall speed for the compound VTOL aircraft, and a rotor hub for connecting the rotor sleeve to a rotor power assembly. Rotor blade motivators controlled by a rotor blade controller determine the pitch of the respective rotor blades through interaction of the pilot of the VTOL aircraft with the rotor blade controller.
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公开(公告)号：US08939394B1
公开(公告)日：2015-01-27
申请号：US13199677
申请日：2011-09-07
IPC分类号： B64C27/02 , B64C27/72 , B64C27/615
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A combined fixed and rotary wing aircraft may operate in vertical takeoff mode relying on the rotary wing, exclusively, and may completely change over to flight support by the fixed wing at higher advance ratios. Advance ratios may exceed not only the typical advance ratios of less than 0.5 but may exceed 1, and may even exceed 2. At the higher advance ratios, the rotary wing may be completely unloaded, the aircraft relying on the fixed wing for vertical support and airfoil lift. To maintain stability in the rotary wing, configuration, autorotation must continue. To power autorotation, without presenting a large area and drag, an anemometer-type flap system may selectively open and close to increase drag on the retreating blades, and provide minimum drag on the advancing blades.
摘要翻译： 组合的固定和旋转翼型飞机可以独立地依靠旋翼以垂直起飞模式运行，并且可以以更高的提前比例以固定翼完全转变为飞行支撑。 提前比率不仅可以超过小于0.5但可能超过1的典型提前比例，而且可能超过1，甚至可能超过2.在较高的提前比例下，旋翼可以完全卸载，飞机依靠固定翼进行垂直支撑， 翼型升降机。 为了保持旋转翼的稳定性，配置必须继续。 为了对自动驾驶进行自动驾驶，没有呈现大面积和拖曳，风速计式翼片系统可以选择性地打开和关闭，以增加后退叶片上的阻力，并且在推进的叶片上提供最小的阻力。
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公开(公告)号：US20140255184A1
公开(公告)日：2014-09-11
申请号：US13785892
申请日：2013-03-05
发明人： Drew Sutton
IPC分类号： F01D7/00
CPC分类号： F01D7/00 , B64C23/06 , B64C27/467 , B64C27/615 , B64C27/72 , B64C2027/7261 , B64C2230/14 , B64C2230/26 , B64C2230/28 , F01D5/145 , Y02T50/162 , Y02T50/166 , Y02T50/34 , Y02T50/66
摘要： A rotor blade includes an active flap and an airflow disturber configured to selectively alter airflow across the active flap.
摘要翻译： 转子叶片包括活动翼片和气流干扰器，其配置成选择性地改变穿过活动翼片的气流。
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公开(公告)号：US20120168568A1
公开(公告)日：2012-07-05
申请号：US13335541
申请日：2011-12-22
IPC分类号： B64C27/26
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A method and apparatus for enabling high speed flight in a rotorcraft are disclosed. The method may include executing a flight with a rotorcraft. The flight may include a first portion and second portion ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. Once sufficient airspeed is obtained, the flight may transition to the second portion. Wherein, substantially all of the weight of the rotorcraft may be supported by one or more fixed wing surfaces of the rotorcraft. Thus, during the second portion, the rotor may be completely unloaded. To keep the rotor stable by turning, the rotor may be powered during the second portion by an engine of the rotorcraft by way of a prerotation system.
摘要翻译： 公开了一种用于在旋翼航空器中实现高速飞行的方法和装置。 该方法可以包括执行具有旋翼航空器的飞行。 飞行可以包括顺序排列的第一部分和第二部分。 在第一部分期间，旋翼航空器可以独自在自转中与转子一起飞行。 一旦获得足够的空速，飞行可以转变到第二部分。 其中，旋翼航空器的基本上所有的重量可以由旋翼航空器的一个或多个固定翼面支撑。 因此，在第二部分期间，转子可以完全卸载。 为了通过转动来保持转子稳定，转子可以在第二部分期间由旋转飞机的发动机通过预旋转系统供电。
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8.发明授权公开(公告)号：US09902492B1
公开(公告)日：2018-02-27
申请号：US14756420
申请日：2015-12-04
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C2027/7261
摘要： A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.
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公开(公告)号：US09464532B2
公开(公告)日：2016-10-11
申请号：US13785892
申请日：2013-03-05
发明人： Drew Sutton
IPC分类号： F01D7/00 , B64C23/06 , B64C27/467 , B64C27/615 , B64C27/72 , F01D5/14
CPC分类号： F01D7/00 , B64C23/06 , B64C27/467 , B64C27/615 , B64C27/72 , B64C2027/7261 , B64C2230/14 , B64C2230/26 , B64C2230/28 , F01D5/145 , Y02T50/162 , Y02T50/166 , Y02T50/34 , Y02T50/66
摘要： A rotor blade includes an active flap and an airflow disturber configured to selectively alter airflow across the active flap.
摘要翻译： 转子叶片包括活动翼片和气流干扰器，其配置成选择性地改变穿过活动翼片的气流。
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公开(公告)号：US09193456B2
公开(公告)日：2015-11-24
申请号：US13237075
申请日：2011-09-20
申请人： Marc Höfinger
发明人： Marc Höfinger
CPC分类号： B64C27/72 , B64C23/005 , B64C2027/7261 , B64C2230/28 , Y02T50/166 , Y02T50/34
摘要： A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end and a rear end and mounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial or spanwise axis of the rotor blade. The flap has a basic position in which it lies flat against the upper surface of the main body. Further, the flap is passively swiveled by aerodynamic forces and inertial forces about its swivel axis to raise above the upper surface of the main body, and a reset force acts upon the flap to reset it into its basic position on the surface of the main body.
摘要翻译： 用于旋转翼飞行器的从动水平转子的转子叶片包括细长主体，其包括前缘，后缘以及在前缘和后缘之间延伸的上表面。 转子叶片还包括具有前端和后端的至少一个翼片，并且在其前端处安装到主体上，围绕与转子叶片的径向或翼展轴线平行延伸的旋转轴线旋转。 翼片具有基本位置，其平放在主体的上表面上。 此外，翼片通过围绕其旋转轴线的空气动力和惯性力被动地旋转，以在主体的上表面上方升高，并且复位力作用在翼片上以将其复位到主体的表面上的基本位置 。
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