-
公开(公告)号：US20240278903A1
公开(公告)日：2024-08-22
申请号：US18171347
申请日：2023-02-18
申请人： The Boeing Company
发明人： Robert E. Grip , John J. Brown
摘要： There is provided an extendable compression chain system for extending a structure. The system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. The extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. The extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. The modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. The extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.
-
公开(公告)号：US12054253B2
公开(公告)日：2024-08-06
申请号：US17673842
申请日：2022-02-17
申请人： Amit Regev
发明人： Amit Regev
CPC分类号： B64C39/024 , B64C3/38 , B64C27/027 , B64C27/20 , B64C27/28 , B64U10/13 , B64U2201/10
摘要： A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.
-
公开(公告)号：US12006031B2
公开(公告)日：2024-06-11
申请号：US17366749
申请日：2021-07-02
IPC分类号： B64C29/00 , B64C3/10 , B64C3/32 , B64C3/38 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/40 , H02K7/18
CPC分类号： B64C29/0025 , B64C3/10 , B64C3/32 , B64C3/38 , B64C29/00 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/026 , B64D27/40 , F05D2220/76 , F05D2270/093 , H02K7/1823
摘要： An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
-
公开(公告)号：US11952112B2
公开(公告)日：2024-04-09
申请号：US17734861
申请日：2022-05-02
发明人： Tobias Schreck , Bernhard Schlipf
摘要： A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body.
-
公开(公告)号：US20230393572A1
公开(公告)日：2023-12-07
申请号：US18090488
申请日：2022-12-29
申请人： Colugo Systems Ltd.
发明人： Amit REGEV
CPC分类号： G05D1/0016 , B64C3/385 , B64C29/0033 , B64C39/024 , B64U10/13
摘要： A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and on ore more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.
-
公开(公告)号：US20230278704A1
公开(公告)日：2023-09-07
申请号：US17687366
申请日：2022-03-04
摘要： Example air vehicles including freewings and related methods are disclosed herein. An example air vehicle includes a fuselage; a freewing coupled to the fuselage, the freewing pivotable relative to the fuselage; and a rotor carried by the freewing, the rotor pivotable independently of the freewing.
-
公开(公告)号：US11673661B2
公开(公告)日：2023-06-13
申请号：US17329312
申请日：2021-05-25
发明人： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
IPC分类号： B64C29/00 , B64C27/28 , A61L9/12 , H02J7/00 , H02J50/10 , B64C21/06 , B64D27/14 , B64D27/24 , H02P9/04 , B64C3/38 , B64D27/02
CPC分类号： B64C29/0033 , A61L9/122 , B64C21/06 , B64C27/28 , B64C29/00 , B64D27/14 , B64D27/24 , H02J7/0042 , H02J50/10 , H02P9/04 , A61L2209/133 , B64C3/385 , B64C29/0008 , B64D2027/026 , B64D2221/00 , Y02T50/60
摘要： A propulsion system of an aircraft has at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position, and a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan. During a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between the plurality of unducted fans and the plurality of ducted fans such that the at least one unducted fan is a primary source of thrust.
-
公开(公告)号：US11634208B2
公开(公告)日：2023-04-25
申请号：US16924812
申请日：2020-07-09
申请人： Jilin University
发明人： Zhihui Zhang , Zhenglei Yu , Xiaolong Zhang , Wei Yan , Yanlong Shao , Yunhong Liang , Qingping Liu , Qingquan Zhang , Yuting Liu
IPC分类号： B64C3/38 , B33Y10/00 , B33Y50/02 , B33Y70/00 , B33Y80/00 , B29C64/118 , B29C64/393 , B64C3/18 , B64C39/00 , B64C39/02 , B29L31/30 , B64U10/40 , B64U30/12
摘要： A rigid-flexible coupled unmanned aerial vehicle (UAV) morphing wing and an additive manufacturing method thereof are disclosed. A shape memory alloy (SMA) strip/wire for controlling the wing upward deformation and an SMA strip/wire for controlling the wing downward deformation are arranged alternately, and a plurality of reinforcing ribs are arranged at intervals on the SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation are arranged on a flexible substrate, and are wrapped with an insulating covering. The SMA strips/wires for controlling the wing upward deformation and the SMA strips/wires for controlling the wing downward deformation each are provided with an electric heating element.
-
公开(公告)号：US11603193B2
公开(公告)日：2023-03-14
申请号：US16505445
申请日：2019-07-08
申请人： Donghyun Kim , Heng Yang
发明人： Donghyun Kim , Heng Yang
摘要： An aircraft convertible between fixed-wing and hovering orientations includes a fuselage. The aircraft includes a main wing pair comprising two opposing wings attached to the fuselage, where each wing of the two opposing wings includes a fixed wing section attached to the fuselage and a movable wing section rotatably mounted to the fixed wing section. The aircraft includes at least a first propulsor mounted to the movable wing section of each of the two opposing wings. The aircraft includes at least a first rotation mechanism attached to the fixed wing section and movable wing section of each of the two opposing wings, the at least a first rotation mechanism configured to rotate the movable wing section between a first movable wing section position parallel to the fixed wing section and a second movable wing section position perpendicular to the fixed wing section.
-
公开(公告)号：US11535371B2
公开(公告)日：2022-12-27
申请号：US16647824
申请日：2018-09-06
发明人： Andrew Dudley Moore
IPC分类号： B64C29/00 , B64C3/38 , B64C9/16 , B64C27/52 , B64C39/06 , B64D27/24 , B64C9/00 , B64C27/80 , B64C27/82 , B60L15/20 , B64C13/00
摘要： A vertical take-off and landing (VTOL) aircraft (10) includes a fuselage and first and second forward wings (20, 22), each wing (20, 22) having a fixed leading edge and a trailing control surface (50) which is pivotal about a generally horizontal pivot axis. The aircraft (10) includes first and second electric motors (60) each having rotors (70), the electric rotors (70) being pivotal with the trailing control surface (50) between a first position in which each rotor (70) has a generally vertical axis of rotation, and a second position in which each rotor (70) has a generally horizontal axis of rotation, a control system (90) is configured to selectively operate the first electric motor (60) and the second electric motor (60) at different rotational speeds to generate a turning moment to pivot the control surface (50) about the pivot axis (33).
-
-
-
-
-
-
-
-
-
搜索结果
822 条记录 (耗时 0.028 秒)
