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公开(公告)号：US20160311528A1
公开(公告)日：2016-10-27
申请号：US15089576
申请日：2016-04-03
Applicant: Skylift Global
Inventor： Reza Nemovi , Robert Bartlett
CPC classification number: B64C27/82 , B64C27/08 , B64C27/14 , B64C27/28 , B64C27/52 , B64C27/68 , B64C27/80 , B64C29/0033 , B64C39/024 , B64C2027/8209 , B64C2027/8254 , B64C2201/024 , B64C2201/042 , B64C2201/088 , B64C2201/108 , B64C2201/162 , B64C2201/165
Abstract: An improved vehicle with superior performance and reliability. The vehicle, such as an unmanned aerial vehicle, is capable of vertical takeoff and landing, uses three swashless, variable-pitch vertical lift main rotors with a yaw tail rotor system. Two rear main rotors are optionally tiltrotors, which pivot to increase forward speed without the increased coefficient of drag inherent in tilting the entire vehicle. The three main rotors are positioned in an equilateral triangular configuration, improving balance, increasing load-bearing strength, and making it more compact in size. Movements are controlled through changes in pitch of the rotors, allowing the motors to maintain constant governed rotations per minute, maximizing drivetrain efficiency. Vehicle configurations disclosed herein allow for smaller vehicle size with greater performance than prior art vehicles.
Abstract translation: 具有优异性能和可靠性的改进型车。 诸如无人驾驶飞行器的车辆能够垂直起飞和着陆，使用具有偏航尾部转子系统的三个无斜杠，可变俯仰垂直升降主转子。 两个后部主转子是可选的倾斜旋转器，其枢转以增加前进速度，而不会在整个车辆倾斜时固有的增加的阻力系数。 三个主转子位于等边三角形结构中，改善了平衡，增加了承载力，并使其尺寸更加紧凑。 通过转子间距的变化来控制运动，允许电机每分钟保持恒定的转动旋转，从而最大限度地提高传动系效率。 本文公开的车辆配置允许具有比现有技术车辆更大的性能的较小车辆尺寸。
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52.发明授权Device for assisting in piloting hybrid helicopter, hybrid helicopter provided with such device, and method implemented by such device 有权用于协助驾驶混合直升机，配备这种装置的混合直升机的装置以及由这种装置实施的方法公开(公告)号：US09272778B2
公开(公告)日：2016-03-01
申请号：US14489831
申请日：2014-09-18
Applicant: Airbus Helicopters
Inventor： Paul Eglin
Abstract: A hybrid helicopter includes a rotary wing, two half-wings with respective propellers, and an engine installation continuously driving the rotary wing and the propellers by meshing with a mechanical interconnection system. A piloting assistance device for the hybrid helicopter is configured to determine maximum mean pitch (βmax) applicable to the propellers without exceeding the power available for the propellers. The piloting assistance device is configured to determine the maximum mean pitch (βmax) as a function of the current mean pitch of the blades of the propellers as measured in real time, a maximum power that can be delivered by the engine installation, a current power being delivered by the engine installation, and a relationship determining a power gradient (GRD) as a function of pitch for the propellers.
Abstract translation: 混合动力直升机包括旋转翼，具有相应螺旋桨的两个半翼，以及通过与机械互连系统啮合连续地驱动旋转翼和螺旋桨的发动机设备。 用于混合式直升机的驾驶辅助装置被配置成确定适用于螺旋桨的最大平均间距（＆bgr; max），而不超过螺旋桨的可用功率。 引导辅助装置被配置为根据实时测量的螺旋桨叶片的当前平均间距确定最大平均间距（＆bgr; max），发动机安装可以传递的最大功率， 由发动机安装输送的当前动力以及确定作为螺旋桨的沥青的函数的功率梯度（GRD）的关系。
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公开(公告)号：US20160001878A1
公开(公告)日：2016-01-07
申请号：US14768476
申请日：2014-02-06
Applicant: NES&TEC CO.,LTD.
Inventor： Ki-Seong LEE
CPC classification number: B64C27/28 , B64C3/38 , B64C3/58 , B64C9/323 , B64C39/024 , B64C2201/088 , B64C2201/108 , B64C2201/185 , B64C2201/187
Abstract: Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings.
Abstract translation: 披露了一个简单的降落无人机。 无人机包括：螺旋桨改变方向; 支撑螺旋桨的螺旋桨塔; 连接到螺旋桨塔的主体; 主翼相对于主体的水平轴对称地布置，并且具有围绕主体的重心的一对孔; 一对辅助翼分别设置在该对孔中; 以及致动器，其通过所述一对辅助翼连接到固定到所述主翼的基轴，并且控制所述一对辅助翼的角度。
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公开(公告)号：US09162748B2
公开(公告)日：2015-10-20
申请号：US13699998
申请日：2011-07-22
Applicant: John Brunken, Jr.
Inventor： John Brunken, Jr.
CPC classification number: B64C5/02 , B64C1/1415 , B64C1/26 , B64C27/28 , B64C29/0033 , B64D27/02
Abstract: An aircraft includes a fuselage, wings attached to the fuselage, a door in an aft portion of the fuselage for providing access to an interior portion of the fuselage, a first and second vertical stabilizer attached to the aft portion of the fuselage, and a horizontal stabilizer transversely attached to the first and second vertical stabilizers. The fuselage further comprises a first side member adjacent to a first side of the door and a second side member adjacent to a second side of the door, and the first side member extends into the first vertical stabilizer and the second side member extends into the second vertical stabilizer; additionally both the first and second side members further extend substantially the vertical depth of the fuselage along the aft door.
Abstract translation: 一架飞机包括一个机身，机身附着在机身上，一个机身后部的一个门，用于提供进入机身内部的通道，一个连接到机身后部的第一和第二垂直稳定器，以及一个水平 横向地附接到第一和第二垂直稳定器的稳定器。 机身还包括与门的第一侧相邻的第一侧构件和与门的第二侧相邻的第二侧构件，并且第一侧构件延伸到第一竖直稳定器中，而第二侧构件延伸到第二侧构件中 垂直稳定器 此外，第一侧构件和第二侧构件进一步基本上沿着后门延伸机身的垂直深度。
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公开(公告)号：US20150115096A1
公开(公告)日：2015-04-30
申请号：US14564775
申请日：2014-12-09
Applicant: The Boeing Company
Inventor： Glenn T. Rossi
CPC classification number: B64C27/26 , B64C27/28 , B64C29/0033 , B64C29/02 , B64C37/02 , B64C39/003 , B64C39/024 , B64C2201/082 , B64C2201/206 , B64D5/00
Abstract: A compound rotorcraft including a rotary wing aircraft having a fuselage and at least one rotor and a fixed-wing aircraft coupled to the rotary wing aircraft, wherein the rotary wing aircraft can fly on the rotor or the fixed-wing aircraft, and wherein the fixed-wing aircraft is detachable from the rotary wing aircraft to fly independently.
Abstract translation: 一种复合旋翼航空器，其包括具有机身的旋翼飞机和至少一个转子以及耦合到旋转翼飞行器的固定翼飞行器，其中所述旋翼飞机可以在所述转子或所述固定翼飞行器上飞行，并且其中所述固定 飞机可以从旋翼飞机上拆下来独立飞行。
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Patent Agency Ranking
公开(公告)号：US08998125B2
公开(公告)日：2015-04-07
申请号：US13576612
申请日：2010-06-15
Applicant: Charles Hollimon , Dudley E. Smith , David Ludolph
Inventor： Charles Hollimon , Dudley E. Smith , David Ludolph
CPC classification number: B64C29/0033 , B64C27/28 , B64C27/30
Abstract: A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.
Abstract translation: 一种用于旋翼航空器的可折叠转子系统，所述可折叠转子系统包括与驱动轴可操作地相关联的转子组件，所述驱动轴可与发动机相关联，所述转子组件包括连接到夹紧销的转子叶片。 旋转斜盘可操作地与夹紧销相关联，以便选择性地改变转子叶片的间距。 叶片折叠致动器可操作地与抓持销相关联，使得叶片折叠致动器构造成围绕叶片折叠轴线折叠和展开转子叶片。 在飞机模式期间，旋翼航空器可以停止和折叠转子叶片，使得旋翼飞机依靠来自发动机的推力用于推进。 转子叶片以螺旋折叠路径折叠，使得转子叶片在折叠过程中保持基本上沿边缘或羽状。 螺旋折叠路径使转子叶片在旋翼飞机飞行期间被折叠时所经历的空气动力学阻力最小化。
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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
Applicant: Jacob Johannes van der Westhuizen
Inventor： Jacob Johannes van der Westhuizen
CPC classification number: B64C27/18 , B64C27/025 , B64C27/08 , B64C27/26 , B64C27/28
Abstract: 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.
Abstract translation: 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：US08915464B2
公开(公告)日：2014-12-23
申请号：US13592772
申请日：2012-08-23
Applicant: Jean-Jacques Ferrier , Paul Eglin
Inventor： Jean-Jacques Ferrier , Paul Eglin
Abstract: An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).
Abstract translation: 包括机身（2）的飞机（1），具有在机身（2）上串联布置的两个反转主转子（12）的旋转翼（10），至少一个推进构件（20）和发电厂 30）。 每个推进构件（20）由机身的后部（3）承载。 飞机（1）包括互连系统（40），其在发电厂（30）和旋转翼（10）之间提供永久连接，除非发生故障或训练期间，飞机（1）具有差速控制 用于控制主转子（12）的叶片的循环间距以控制飞行器（1）偏航的装置（50），以及用于抑制每个推进构件（20）的禁止装置（60）。
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公开(公告)号：US20140169963A1
公开(公告)日：2014-06-19
申请号：US13715006
申请日：2012-12-14
Applicant: Raymond George Carreker
Inventor： Raymond George Carreker
Abstract: A direct orientation vector rotor (DOVER) for use on rotary wing aircraft includes a gear set for multidirectional rotor orientation based on the spherical coordinate system; an inclination mechanism, wherein the rotor is moved from the 0° horizontal position to an inclined position; a rotational turret, wherein the rotor is moved along the azimuth and wherein the inclination mechanism is housed; and a motion-adapted gear lubrication housing.
Abstract translation: 用于旋翼飞机的直接定向矢量转子（DOVER）包括基于球面坐标系的多向转子定向齿轮组; 倾斜机构，其中转子从0°水平位置移动到倾斜位置; 旋转转台，其中所述转子沿着所述方位角移动，并且其中容纳所述倾斜机构; 和运动适配齿轮润滑壳体。
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公开(公告)号：US20140060004A1
公开(公告)日：2014-03-06
申请号：US13584286
申请日：2012-08-13
Applicant: Thomas M. Mast , Keith C. Pedersen , David L. Miller , Steven Ray Ivans
Inventor： Thomas M. Mast , Keith C. Pedersen , David L. Miller , Steven Ray Ivans
IPC: B64C27/28
CPC classification number: B64C27/28 , B64C15/02 , B64C29/0033 , B64D33/04
Abstract: The exhaust system is located on each nacelle of a tiltrotor aircraft. The exhaust system includes a vector nozzle that is selectively rotatable in relation to each nacelle in order to achieve certain performance objectives. The vector nozzle can be oriented to provide maximum flight performance, reduce infrared (IR) signature, or even to reduce/prevent ground heating.
Abstract translation: 排气系统位于倾斜旋翼飞机的每个机舱上。 排气系统包括可相对于每个机舱选择性地旋转的矢量喷嘴，以便达到某些性能目标。 矢量喷嘴可以定向以提供最大的飞行性能，减少红外（IR）签名，甚至减少/防止地面加热。
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