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公开(公告)号：US11745877B2
公开(公告)日：2023-09-05
申请号：US17348771
申请日：2021-06-16
申请人： Yao-Chang Lin
发明人： Yao-Chang Lin
CPC分类号： B64C39/08 , B64C1/16 , B64C3/10 , B64C3/32 , B64C5/02 , B64C9/00 , B64C11/001 , B64C25/36 , B64C2009/005
摘要： A biplane flying device includes a fuselage, an upper wing, a lower wing, a first propulsion assembly and a second propulsion assembly. The upper wing is connected to one side of the fuselage. The upper wing has a first end and a second end opposite to each other. The lower wing is connected to the fuselage and opposite to the upper wing. The lower wing has a third end and a fourth end opposite to each other. The first end is opposite to the third end, and the second end is opposite to the fourth end. The first propulsion assembly is connected between the first end, the third end and the fuselage. The second propulsion assembly is connected between the second end, the fourth end and the fuselage.
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公开(公告)号：US20230249801A1
公开(公告)日：2023-08-10
申请号：US18013558
申请日：2020-07-01
申请人： WESTLAKE UNIVERSITY
发明人： Wei LI , Liping ZHANG , Bing LUO , Zhenhua WANG , Weicheng CUI
摘要： A wing structure for a vehicle, and a vehicle. The wing structure comprises at least one multi-connecting-rod structure. The multi-connecting-rod structure is arranged in a direction extending from the main body of a vehicle to a wingtip, each multi-connecting-rod mechanism comprises a plurality of connecting rods, and connecting rods which are adjacent to each other are connected by means of a motor. The present technical solution provides a wing structure having the feature of a morphing wing having a large range in both chordwise and spanwise directions. The wing structure has the capability of changing airfoil and changing a pitch angle within a large range, the capability of twisting along a spanwise direction at a distal portion, the capability of swinging perpendicularly within a large range along the plane in which the main body of the vehicle is located, and the capability of swinging longitudinally within a large range along the main body of the vehicle, adjustment can be performed on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.
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公开(公告)号：US11643204B2
公开(公告)日：2023-05-09
申请号：US17115677
申请日：2020-12-08
发明人： Ivan Ermanoski
CPC分类号： B64C39/024 , B64C3/10 , B64C11/46 , B64C29/02 , B64D9/00 , B64D27/24 , G05D1/102 , B64C2201/128 , B64D2041/005
摘要： An unmanned aerial vehicle (UAV) for gas transport is disclosed. The UAV includes a fuselage enclosing a volume, and a gas reservoir enclosed within the fuselage, filling at least a majority of the volume. The gas reservoir is configured to receive and store a gas at a pressure no greater than 100 bar. The UAV also includes a propulsion system having at least one engine, each of the at least one engine coupled to a prop that is driven by the at least one engine using energy derived from the gas stored in the gas reservoir. The UAV also includes a control system communicatively coupled to the propulsion system and configured to operate the unmanned aerial vehicle to autonomously transport the gas. The UAV may have a footprint while on the ground, and the footprint of the UAV may be no larger than three standard parking spaces.
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公开(公告)号：US11485472B2
公开(公告)日：2022-11-01
申请号：US17331997
申请日：2021-05-27
申请人： COFLOW JET, LLC
发明人： Gecheng Zha
摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.
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公开(公告)号：US20220332417A1
公开(公告)日：2022-10-20
申请号：US17348771
申请日：2021-06-16
申请人： Yao-Chang Lin
发明人： Yao-Chang Lin
摘要： A biplane flying device includes a fuselage, an upper wing, a lower wing, a first propulsion assembly and a second propulsion assembly. The upper wing is connected to one side of the fuselage. The upper wing has a first end and a second end opposite to each other. The lower wing is connected to the fuselage and opposite to the upper wing. The lower wing has a third end and a fourth end opposite to each other. The first end is opposite to the third end, and the second end is opposite to the fourth end. The first propulsion assembly is connected between the first end, the third end and the fuselage. The second propulsion assembly is connected between the second end, the fourth end and the fuselage.
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公开(公告)号：US20220177131A1
公开(公告)日：2022-06-09
申请号：US17477263
申请日：2021-09-16
申请人： Joby Aero, Inc.
摘要： A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.
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公开(公告)号：US11279478B2
公开(公告)日：2022-03-22
申请号：US16444686
申请日：2019-06-18
摘要： An aircraft that is convertible between a helicopter mode and an airplane mode. The aircraft includes a fuselage with a longitudinal axis and a vertical axis and distributed propulsion array that surrounds the vertical axis when the aircraft is operating the helicopter mode and surrounds the longitudinal axis when the aircraft is operating in the airplane mode.
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公开(公告)号：US20210371103A1
公开(公告)日：2021-12-02
申请号：US17136585
申请日：2020-12-29
IPC分类号： B64C39/06 , B64C11/28 , B64C27/50 , B64C3/16 , B64C3/10 , B64C27/08 , B64C29/00 , B64C27/12 , B64D27/24 , B64D31/00 , B64C29/02 , B64C1/06 , B64C39/02
摘要： An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more motors are disposed within or attached to the spokes. Three or more propellers are proximate to a leading edge of the one or more spokes, distributed along the one or more spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight.
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公开(公告)号：US11174019B2
公开(公告)日：2021-11-16
申请号：US16179940
申请日：2018-11-03
申请人： Joby Aero, Inc.
摘要： A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.
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公开(公告)号：US11117676B2
公开(公告)日：2021-09-14
申请号：US16042267
申请日：2018-07-23
IPC分类号： B64D27/24 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64C29/00 , B64D27/02 , B64D27/26 , H02K7/18
摘要： An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.
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