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公开(公告)号：US09611036B1
公开(公告)日：2017-04-04
申请号：US14544796
申请日：2015-02-18
发明人： Jehan Zeb Khan
CPC分类号： B64C27/001 , B64C27/02 , B64C27/52 , G05D19/00
摘要： A method and apparatus for reducing flapping loads imposed on a rotor are disclosed. The method may include flying a rotorcraft comprising an airframe, a rotor, a mast extending to connect the rotor to the airframe, a tilt mechanism, at least one sensor, and a computer system. The computer system may obtain in real time, from the at least one sensor, data characterizing at least one flapping load experienced by the rotor during the flying. Using the data, the computer system may issue at least one command to the tilt mechanism. In response to the command, the tilt mechanism may reorient the mast with respect to the airframe. This reorienting may lower the flapping load experienced by the rotor.
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公开(公告)号：US09604722B1
公开(公告)日：2017-03-28
申请号：US14602884
申请日：2015-01-22
发明人： David L. Groen
IPC分类号： B64C27/473 , B64C27/72 , B64C27/02
CPC分类号： B64C27/473 , B64C27/023 , B64C2027/4736 , B64C2027/7222
摘要： A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver.
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3.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：US20150142219A1
公开(公告)日：2015-05-21
申请号：US14288957
申请日：2014-05-28
IPC分类号： B64C27/02
CPC分类号： B64C27/027 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/82 , B64C2027/8272
摘要： Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.
摘要翻译： 公开了在低空速和发动机故障中的一个或两个情况下控制旋翼航空器的偏航的装置和方法。 可以使用偏航推进装置，例如空气喷射器或风扇。 气动风扇可以被释放到围绕风扇外部的通道的压缩空气驱动。 用于偏航推进装置和其它系统的动力可由与转子接合的液压泵和/或发电机提供。 低速偏航控制可以由位于支柱的流管内的辅助方向舵提供。 辅助方向舵可以在不使用时向下折叠并与方向舵控制器脱离。 用于产生水平升降机不平衡的装置也可以使用定位在转子的下冲液内的尾臂，包括压缩空气通风口或横向或后缘翼片。
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公开(公告)号：US20170066539A1
公开(公告)日：2017-03-09
申请号：US15280116
申请日：2016-09-29
CPC分类号： B64D27/24 , B64C11/00 , B64C27/025 , B64C27/18 , Y02T50/64
摘要： Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. The generator may be used to charge a battery during autorotation or descending. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.
摘要翻译： 公开了在低空速和发动机故障中的一个或两个情况下控制旋翼航空器的偏航的装置和方法。 偏航推进在低速时提供横摆力矩。 偏航推进装置可以是空气喷射器或风扇。 气动风扇可以被释放到围绕风扇外部的通道的压缩空气驱动。 风扇可以由液压动力驱动。 用于偏航推进装置和其它系统的动力可由与转子接合的液压泵和/或发电机提供。 发电机可以用于在自动或下降期间为电池充电。 低速偏航控制可以由位于支柱的流管内的辅助方向舵提供。 辅助方向舵可以在不使用时向下折叠并与方向舵控制器脱离。
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公开(公告)号：US20160001881A1
公开(公告)日：2016-01-07
申请号：US14665047
申请日：2015-03-23
CPC分类号： B64C27/72 , B64C27/18 , B64C27/26 , B64C2027/7227 , Y02T50/34
摘要： A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a plurality of blades defining ducts along the length thereof and vents in fluid communication with the ducts. Flow from through the vents may be controlled by valves with piezoelectric actuators. The valves may be adjusted to achieve a lift profile suited for an operational mode such as vertical, autorotative, or unloaded flight. The lift profile may vary along the length of the blade and may vary cyclically with rotation of the blade. The lift profile may be chosen to approximate a figure of merit for the rotor suitable for a given operational mode.
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公开(公告)号：US09278754B2
公开(公告)日：2016-03-08
申请号：US14288957
申请日：2014-05-28
CPC分类号： B64C27/027 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/82 , B64C2027/8272
摘要： Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.
摘要翻译： 公开了在低空速和发动机故障中的一个或两个情况下控制旋翼航空器的偏航的装置和方法。 可以使用偏航推进装置，例如空气喷射器或风扇。 气动风扇可以被释放到围绕风扇外部的通道的压缩空气驱动。 用于偏航推进装置和其它系统的动力可由与转子接合的液压泵和/或发电机提供。 低速偏航控制可以由位于支柱的流管内的辅助方向舵提供。 辅助方向舵可以在不使用时向下折叠并与方向舵控制器脱离。 用于产生水平升降机不平衡的装置也可以使用定位在转子的下冲液内的尾臂，包括压缩空气通风口或横向或后缘翼片。
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