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公开(公告)号：US10343771B1
公开(公告)日：2019-07-09
申请号：US16269227
申请日：2019-02-06
发明人： James Kaiser , William Vatis
IPC分类号： B64C27/10 , B64C27/20 , B64C27/14 , B64D35/06 , B64C27/50 , B64D17/80 , B64D27/24 , B64C25/06 , B64C27/82
摘要： A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.
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公开(公告)号：US20190185142A1
公开(公告)日：2019-06-20
申请号：US15845967
申请日：2017-12-18
摘要： A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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公开(公告)号：US20190168866A1
公开(公告)日：2019-06-06
申请号：US16182107
申请日：2018-11-06
摘要： There is disclosed a multicopter vertical takeoff and landing (VTOL) aircraft. The aircraft comprises am airframe with spatial design, a pilot seat, a cockpit, controls, engine units, engine compartment, control system, remote control system. The airframe consists of a central section and, at least, two peripheral sections, wherein peripheral sections can be folded up or down, or be retracted under the central section. The central section and peripheral sections of the airframe have spatial design. Each of the peripheral sections comprises at least three standard engine compartments which are connected to each other. Inside each engine compartment there is an engine unit which comprises at least one engine and at least one horizontally rotating propeller together with the control hardware. Each engine unit is an autonomous member of the distributed control system (DCS).
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公开(公告)号：US10287010B2
公开(公告)日：2019-05-14
申请号：US15341905
申请日：2016-11-02
摘要： An aircraft has a fuselage, a first rotor assembly having a first rotor hub and first rotor blades pivotably coupled to the first rotor hub and a second rotor assembly having a second rotor hub and second rotor blades pivotably coupled to the second rotor hub. The first and second rotor blades have deployed configurations extending generally radially from the fuselage and stowed configurations extending generally parallel with the fuselage. A sequencing cam, positioned between the first and second rotor hubs, is coupled to the second rotor blades. The sequencing cam has a retracted orientation when the second rotor blades are in the stowed configuration and an extended orientation when the second rotor blades are in the deployed configuration in which the sequencing cam props support arms of the first rotor blades preventing transition of the first rotor blades from the deployed configuration to the stowed configuration.
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公开(公告)号：US20190055003A1
公开(公告)日：2019-02-21
申请号：US16130172
申请日：2018-09-13
发明人： Dongdong LUO , Wenbing SU , Wei SUN , Hailang ZHANG
摘要： The present application discloses a foldable propeller, a power assembly and an unmanned aerial vehicle. The foldable propeller includes: a propeller hub, at least two blade assemblies, and a connecting member used for pivotally connecting the propeller hub and the blade assemblies, where each blade assembly is rotatable with respect to the propeller hub, and a rotation axis of each blade assembly is perpendicular to an axial central line of the propeller hub. In the foldable propeller provided by the embodiments of the present application, the blade assemblies can be folded upward or downward with respect to the propeller hub, improving spatial utilization and portability. Moreover, when applied to a tilt-rotor unmanned aerial vehicle, the foldable propeller can further be folded during flight, reducing a flight resistance.
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公开(公告)号：US10189563B2
公开(公告)日：2019-01-29
申请号：US14557995
申请日：2014-12-02
发明人： Moritz Buesing
摘要： A beam for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion, a blade connection portion, a first flexure portion located between the hub connection portion and the blade connection portion and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis of the blade, said bending stiffness being smaller than that of the hub connection portion and that of the blade connection portion and a shear portion located between the hub connection portion and the blade connection portion and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis of the blade and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion and that of the blade connection portion.
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公开(公告)号：US20180057162A1
公开(公告)日：2018-03-01
申请号：US15251128
申请日：2016-08-30
摘要： A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.
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公开(公告)号：US09718542B2
公开(公告)日：2017-08-01
申请号：US13803009
申请日：2013-03-14
摘要： A blade attachment (1, 20) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head (13) at an end of the flexbeam body (16, 17). A control cuff (4, 22) encloses and extends along at least a predominant portion of the flexbeam (3, 21). A separable junction arrangement between the flexbeam head (13), the control cuff (4, 22) and the root end of the airfoil blade (2) is mechanical with removable fasteners. The removable fasteners comprise a main bolt (7) and at least one supporting bolt (8).
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公开(公告)号：US09573683B2
公开(公告)日：2017-02-21
申请号：US14697597
申请日：2015-04-27
申请人： Arch Aerial LLC
发明人： Benjamin Martin , Rebecca Rapp
CPC分类号： B64C39/024 , B64C27/08 , B64C27/50 , B64C2201/024 , B64C2201/027 , B64C2201/108
摘要： A multi-rotor UAV having a pull pin mechanism that engages and disengages the rotor arms from a deployed, in-flight position to a storage or transport configuration, thus making the UAV more portable and capable of carrying larger payloads with the flexibility of folding into a smaller configuration or profile for transport, such as in a backpack. The device includes a rotor arm utilization of a pull pin mechanism to lock and unlock the position of the arms, and a proprietary frame.
摘要翻译： 多转子无人机具有拉动销机构，其将转子臂从部署的飞行位置接合和分离到存储或运输配置，从而使无人机更加便携并且能够承载更大的有效载荷，具有折叠的灵活性 较小的配置或配置文件用于运输，如背包。 该装置包括利用拉销机构的转臂来锁定和解锁臂的位置以及专有框架。
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公开(公告)号：US09550566B2
公开(公告)日：2017-01-24
申请号：US15166005
申请日：2016-05-26
IPC分类号： B64C29/00 , B64C39/00 , B64C39/06 , B64C27/20 , B64C3/18 , B64C27/50 , B64C27/82 , B64D27/16 , B64D37/04 , B64C15/12 , B64D41/00
摘要： A disc-shaped aircraft including an airfoil having a convex upper surface and a planar lower surface with the edges of the surfaces meeting at the periphery of the disc and having a plurality of rotational mini turbine jets affixed sequentially at the edge of the circumference of the disc, the turbine jets effecting vertical, horizontal, and directional thrust under computer and pilot control. Stable flight is maintained by an internal gyroscopic counter-rotating rotor blade system, individual control of the turbine jets, and a series of retractable flaps.
摘要翻译： 一种盘形飞机，其包括具有凸上表面的翼型和平面的下表面，其表面的边缘在盘的周边相交，并且具有多个旋转的微型涡轮机喷射，其顺序地固定在该圆周的边缘的边缘处 圆盘，涡轮喷气机在计算机和飞行员控制下实现垂直，水平和方向推力。 稳定的飞行由内部陀螺式反向转动叶片系统，涡轮喷气机的单独控制和一系列可缩回的襟翼保持。
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