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公开(公告)号：US08950700B2
公开(公告)日：2015-02-10
申请号：US13282938
申请日：2011-10-27
CPC分类号： B64C27/18 , B64C27/025 , B64C27/12 , B64C27/26 , B64C27/28 , B64C27/82 , B64C2027/8245 , B64C2027/8272 , B64C2027/8281
摘要： Apparatus and methods is used for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure. 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. 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. A power take-off engages a rotor and is engaged in response to detecting a loss of engine power.
摘要翻译： 在低空速和发动机故障中的一个或两个的情况下，装置和方法用于控制旋翼航空器的偏航。 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。 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。 动力输出与转子啮合并响应于检测发动机功率的损失而啮合。
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公开(公告)号：US20120104157A1
公开(公告)日：2012-05-03
申请号：US13282938
申请日：2011-10-27
CPC分类号： B64C27/18 , B64C27/025 , B64C27/12 , B64C27/26 , B64C27/28 , B64C27/82 , B64C2027/8245 , B64C2027/8272 , B64C2027/8281
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. 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。 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：US20120104153A1
公开(公告)日：2012-05-03
申请号：US13282780
申请日：2011-10-27
CPC分类号： B64C27/82 , B64C27/025 , B64C2027/8245 , B64C2027/8254
摘要： A rotorcraft is disclosed. The rotorcraft may include a rotor having at least one tip nozzle, a compressor having an outlet for compressed air, and a network of conduits connecting the outlet of the compressor with the tip nozzle. In operation, the compressor may deliver a flow of compressed air to the tip nozzle. As the flow of compressed air exits the at least one tip nozzle, it may cause rotation of the rotor. This rotation may prerotate the rotor and shorten the take off distance required by the rotorcraft. Take off of the rotorcraft may be accomplished without ever adding fuel to the flow of compressed air to the tip nozzle.
摘要翻译： 公开了一种旋翼飞机。 旋翼航空器可以包括具有至少一个尖端喷嘴的转子，具有用于压缩空气的出口的压缩机以及将压缩机的出口与尖端喷嘴连接的管道网络。 在操作中，压缩机可以将压缩空气流传送到尖端喷嘴。 随着压缩空气的流动离开至少一个尖端喷嘴，它可能引起转子的旋转。 这种旋转可以预旋转转子并缩短旋翼航空器所需的起飞距离。 离心旋翼航空器可以实现，而不会向压缩空气流向顶部喷嘴添加燃料。
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公开(公告)号：US09022314B1
公开(公告)日：2015-05-05
申请号：US13199684
申请日：2011-09-07
IPC分类号： B64C27/605 , B64C27/52 , B64C27/18 , B64C27/02 , B64C27/00
CPC分类号： B64C27/605 , B64C27/025 , B64C27/18 , B64C27/52 , B64C2027/002
摘要： A rotor system of a reactive drive rotary wing maintains rigidity and stiffness and resists slack and backlash by mounting swashplate actuators to a flange rigidly secured to the mast, and may be monolithic therewith. A mast tilt actuator and a mast pivot may secure to the mast flange, with vibration suppressors. A shroud may provide a sealed fluid path for airflow therethrough encircling portions of the rotor hub and restricting airflow between the rotor hub and shroud. A rotor cavity, in fluid communication with blade ducts (hollow portions of the blade spars), and either or both contoured to reduce pressure losses, may assist in temperature control, and may feed into tip jets on the blades.
摘要翻译： 反作用驱动旋转翼的转子系统通过将斜盘致动器安装到刚性地固定到桅杆上的凸缘上而保持刚度和刚度并抵抗松弛和间隙，并且可以与其一体化。 桅杆倾斜致动器和桅杆枢轴可以用振动抑制器固定到桅杆法兰上。 护罩可以提供密封的流体路径，用于穿过转子毂的环绕部分的气流并限制转子毂和护罩之间的气流。 与叶片管道（叶片翼形件的中空部分）流体连通的转子腔以及为减少压力损失而成形的两者或两者可有助于温度控制，并且可以进料到叶片上的尖端喷嘴中。
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公开(公告)号：US08915465B1
公开(公告)日：2014-12-23
申请号：US13199721
申请日：2011-09-07
CPC分类号： B64C27/32 , B64C27/58 , B64C27/625 , F01M5/005 , F01M11/02 , F01M2001/0253
摘要： A rotor system is disclosed for a reactive drive rotary wing aircraft. Rigidity of the rotor is enhanced and play between flight controls and the rotor are eliminated by mounting swashplate actuators to a flange rigidly secured to the mast. Thermal management of the rotor is performed in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. Thermal management of a rotor may be performed by oil and air flow.
摘要翻译： 公开了一种用于无功驱动旋翼飞机的转子系统。 通过将斜盘致动器安装到刚性地固定在桅杆上的凸缘上，提高了转子的刚性，并且可以避免飞行控制和转子之间的冲击。 执行转子的热管理，以避免轴承故障或轴承预载的损失。 方法包括调节在一个或多个桅杆轴承，斜盘轴承和主轴轴承上泵送的油温。 无源或主动地通过转子吸入的空气的温度也可被调制以将轴承温度保持在预定范围内。 还公开了用于减少由于通过转子的气流引起的部件上的压力损失和阻力的结构。 转子的热管理可以通过油和空气流进行。
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公开(公告)号：US20130168491A1
公开(公告)日：2013-07-04
申请号：US13544874
申请日：2012-07-09
IPC分类号： B64C27/72
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.
摘要翻译： 旋翼航空器可以包括机身和连接到机身的转子。 转子可以包括沿着其长度限定管道的多个叶片和与管道流体连通的通风口。 通过通风口的流量可以由具有压电致动器的阀门控制。 可以调整阀门以实现适合于诸如垂直，自转或无负载飞行的操作模式的升力曲线。 提升轮廓可以沿着叶片的长度而变化，并且可随着叶片的旋转而周期性变化。 可以选择升力曲线以近似适于给定操作模式的转子的品质因数。
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公开(公告)号：US09260186B1
公开(公告)日：2016-02-16
申请号：US13199712
申请日：2011-09-07
IPC分类号： B64C27/605 , F16C33/66 , F01M5/00 , B64C27/18
CPC分类号： B64C27/605 , B64C27/025 , B64C27/18 , B64C27/26 , F01M5/005 , F16C19/525 , F16C33/667 , F16C37/007 , F16C2229/00 , F16C2326/43
摘要： A rotor system for a reactive drive rotary wing maintains the rigidity of the rotor and eliminates play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods perform thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. The rotor includes structures for reducing pressure losses and drag on components due to air flow through the rotor. A rotor facilitates thermal management by oil and air flow.
摘要翻译： 用于无功驱动旋转翼的转子系统保持转子的刚度，并且通过将斜盘致动器安装到刚性地固定到桅杆的凸缘上来消除飞行控制器和转子之间的游隙。 装置和方法对转子进行热管理，以避免轴承故障或轴承预载的损失。 方法包括调节在一个或多个桅杆轴承，斜盘轴承和主轴轴承上泵送的油温。 无源或主动地通过转子吸入的空气的温度也可被调制以将轴承温度保持在预定范围内。 转子包括用于减少由于空气流过转子而导致的部件上的压力损失和阻力的结构。 转子有助于通过油和空气流进行热管理。
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8.发明授权Heliplane rotor thermal management for maintaining dimensional stability 有权Heliplane转子热管理，用于维持尺寸稳定性公开(公告)号：US08950699B1
公开(公告)日：2015-02-10
申请号：US13199681
申请日：2011-09-07
CPC分类号： B64C27/32 , B64C13/12 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/48 , B64C27/56 , B64C27/605 , B64C27/72 , B64C2027/4736 , B64D31/04 , F16C33/667 , Y10T74/20612
摘要： A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods are disclosed for thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed.
摘要翻译： 公开了一种用于无功驱动旋翼飞机的转子系统。 公开了用于维持转子的刚性并且通过将斜盘致动器安装到刚性地固定到桅杆的凸缘上来消除飞行控制器和转子之间的作用的装置和方法。 公开了用于转子的热管理的装置和方法，以避免轴承故障或轴承预载的损失。 方法包括调节在一个或多个桅杆轴承，斜盘轴承和主轴轴承上泵送的油温。 无源或主动地通过转子吸入的空气的温度也可被调制以将轴承温度保持在预定范围内。 还公开了用于减少由于通过转子的气流引起的部件上的压力损失和阻力的结构。 还公开了通过油和空气流促进热管理的转子。
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公开(公告)号：US08931728B1
公开(公告)日：2015-01-13
申请号：US13199682
申请日：2011-09-07
CPC分类号： B64C27/18 , B64C27/025 , B64C27/08 , B64C27/26 , B64C27/28
摘要： A rotorcraft is disclosed. The rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and at least one rotor blade having a tip jet. The rotorcraft may further include a plurality of compressors for generating compressed air and a network of conduits connecting the outlets of the plurality of compressors with every tip jet of the rotor. The rotorcraft may further include a control system preventing back flow through each outlet of the plurality of compressors.
摘要翻译： 公开了一种旋翼飞机。 旋翼航空器可以包括机身和连接到机身的转子。 转子可以包括轮毂和至少一个具有尖端射流的转子叶片。 旋翼航空器还可以包括用于产生压缩空气的多个压缩机和连接多个压缩机的出口与转子的每个尖端喷嘴的管道网络。 旋翼航空器还可以包括控制系统，该控制系统防止通过多个压缩机的每个出口的回流。
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公开(公告)号：US20130037653A1
公开(公告)日：2013-02-14
申请号：US13605951
申请日：2012-09-06
摘要： An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof.
摘要翻译： 公开了一种具有安装在机身上的发动机和螺旋桨的飞机。 一个尾翼安装在飞行器上，并且包括第一和第二水平稳定器，该水平稳定器在水平稳定器处分开的距离大于螺旋桨的流管的直径。 方向舵在水平稳定器之间延伸并且位于螺旋桨的流管内。 舱壁从驾驶舱向后定位并垂直于机身的纵向轴线定向。 尾气和发动机通过将发动机安装在尾翼和隔板的下边缘之间的舱壁安装到机身上。 起落架可以靠近其下边缘安装到隔板。
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