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公开(公告)号：WO2023087602A1
公开(公告)日：2023-05-25
申请号：PCT/CN2022/085244
申请日：2022-04-06
Applicant: 中山福昆航空科技有限公司
Abstract: 一种可拆卸固定翼无人机，该无人机包括机身、尾椎（20）、第一机翼（31）和第二机翼（32），其中：机身一侧连接着第一机翼（31），机身另一侧连接着第二机翼（32），尾椎（20）与机身的截面处设置有固定框（21），固定框（21）将尾椎（20）和机身连接于一体；机身的截面设置有一个以上卡口（141）和第三弹簧按钮（142）；固定框（21）包括多个横杆（212）和一个以上的第三插销（211），多个横杆（212）组成一个横截面框，一个以上的第三插销（211）固定在横截面框上；一个以上的第三插销（211）中的一个第三插销（211）卡在一个以上的卡口（141）中的一个卡口（141）上，固定框（21）的一横杆（212）内壁卡扣在第三弹簧按钮（142）上。将无人机设计成可拆卸，对机翼以及机身进行快速拆卸，方便装箱运输，具有良好的便利性。
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公开(公告)号：WO2023062689A1
公开(公告)日：2023-04-20
申请号：PCT/JP2021/037595
申请日：2021-10-11
Applicant: 三共木工株式会社
Inventor： 野村 誠
IPC: B64C27/26
Abstract: 飛行体は、エアクラフトとして飛行するための構成と、エアクラフトとして飛行するための制御系統と、マルチコプタとして飛行するための構成と、マルチコプタとして飛行するための制御系統と、を備え、エアクラフトとしての飛行が制御不能の場合に、前記マルチコプタとして飛行するための構成及び制御系統により、マルチコプタとして飛行することができ、マルチコプタとしての飛行が制御不能の場合に、前記エアクラフトとして飛行するための構成及び制御系統により、エアクラフトとして飛行することができる。
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公开(公告)号：WO2022260555A1
公开(公告)日：2022-12-15
申请号：PCT/RU2022/000183
申请日：2022-06-01
Inventor： СОЛОДОВНИКОВ, Юрий Владимирович
Abstract: Изобретение относится к области авиации, в частности к конструкциям винтокрылых летательных аппаратов. Летательный аппарат содержит фюзеляж, несущие плоскости, оперение, толкающий воздушный винт, размещенный на хвостовой оконечности фюзеляжа, или тянущий воздушный винт на носовой оконечности фюзеляжа, или реактивный двигатель. Толкающие воздушные винты размещены с опорой на элементы планера летательного аппарата таким образом, что воздушные винты находятся под планером летательного аппарата. При этом плоскости их вращения отнесены ниже планера летательного аппарата и ориентированы горизонтально. Воздушные винты, находящиеся под планером летательного аппарата, отнесены от поверхности элементов планера, с опорой на которой они расположены, на расстояние, составляющее не менее 15% диаметра воздушных винтов. Обеспечивается высокая весовая и энергетическая эффективность.
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公开(公告)号：WO2022190370A1
公开(公告)日：2022-09-15
申请号：PCT/JP2021/010133
申请日：2021-03-12
Applicant: 川崎重工業株式会社
Inventor： 吉尾 匡史
Abstract: コンパウンドヘリコプタ（１０）は、胴体（２０）と、前記胴体の進行方向に対して、前記胴体から右側方へ延びる第１主翼（３１）及び左側方に延びる第２主翼（３２）と、前記胴体よりも上側に設けられたメインロータ（４０）と、前記第１主翼に設けられ、前記進行方向を正としたとき、正の推力を発生させる第１プロペラ（５０）と、前記第２主翼に設けられ、正及び負の推力を発生させる第２プロペラ（６０）と、を備え、前記第１プロペラの諸元が前記第２プロペラの諸元とは異なる。
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公开(公告)号：WO2021242535A2
公开(公告)日：2021-12-02
申请号：PCT/US2021/032258
申请日：2021-05-13
Applicant: PTERODYNAMICS INC.
Inventor： PETROV, Val
Abstract: Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.
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Patent Agency Ranking
公开(公告)号：WO2021236576A1
公开(公告)日：2021-11-25
申请号：PCT/US2021/032874
申请日：2021-05-18
Applicant: ARCHER AVIATION, INC.
Inventor： BOWER, Geoffrey C. , MUNIZ, Thomas P. , ADCOCK, Brett , GOLDSTEIN, Adam
Abstract: A vertical take-off and landing aircraft (100) includes a fuselage (102), at least one wing (104) connected to the fuselage, a plurality of rotors (112) connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft and a plurality of prop rotors (114) connected to the at least one wing and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft
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公开(公告)号：WO2021232141A1
公开(公告)日：2021-11-25
申请号：PCT/CA2021/050475
申请日：2021-04-09
Applicant: HORIZON AIRCRAFT INC.
Inventor： ROBINSON, Eric Brian , ROBINSON, Eric Brandon
Abstract: An aircraft airfoil disclosed herein has a forward skin structure at least partially defining a leading edge of the airfoil and an aft skin structure at least partially defining a trailing edge of the airfoil. At least one of the forward skin structure and the aft skin structure is movable relative to the other of the forward skin structure and the aft skin structure between a closed position, in which at least one thrust fan positioned between the leading edge and the trailing edge is at least partially covered, and an open position, in which the at least one thrust fan is less covered than in the closed position.
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公开(公告)号：WO2021029947A2
公开(公告)日：2021-02-18
申请号：PCT/US2020/036936
申请日：2020-06-10
Applicant: SUPPES, Galen J.
Inventor： SUPPES, Galen J.
IPC: B64C3/38 , B64C27/52 , B64C9/04 , B64D35/04 , B64C19/02 , B64C13/16 , B64D27/24 , B64D31/02 , B64C29/00 , B64C17/04 , B64C27/28 , B64C29/02 , B64C13/28 , B64C27/26 , B64C39/08 , B64C39/12 , B64C1/26 , B64C11/46 , B64C15/02 , B64D31/12 , B64D33/08
Abstract: A multicopter incorporates a front tiltwing, modular single-circuit motor, hybrid electric-fuel engine, modular injection-molded structures, and operational algorithms to reduce weight, increase efficiency, reduce greenhouse gas footprint, and improve safety. The multicopter has three failsafe modes of emergency landing with an engine have two modes of failsafe operation. The dicopter version of the multicopter has inherent flight stability from either propulsor with passive aerodynamic actuation.
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公开(公告)号：WO2020250010A1
公开(公告)日：2020-12-17
申请号：PCT/IB2019/054910
申请日：2019-06-12
Inventor： VOLOSCSUK, Andras
Abstract: The subject of the invention is an operating method for convertible aircrafts, in particular convertible UAVs, more specifically the method of transition from helicopter mode to gyroplane mode and vice versa. The subject of the invention also includes the UAV configured to perform said method, the aircraft being equipped with a fuselage (4), wings (11) attached to said fuselage (4), tail (6), swashplate (8), main rotor (9), and at least one propeller (10) and at least one motor (5) on each wing (11).
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公开(公告)号：WO2019204688A1
公开(公告)日：2019-10-24
申请号：PCT/US2019/028259
申请日：2019-04-19
Applicant: HI-LITE AIRCRAFT
Inventor： HYMER, Jeffrey
Abstract: A VTOL fixed wing aircraft capable of high-speed forward flight. The aircraft has a main wing internally reinforced with front and aft spars. Spar boxed are located in roll-balanced locations along the wing. Each spar box serves as a connection point for a support linkage that supports a leading-edge and trailing-edge propulsion unit. The leading-edge propulsion unit is fitted with a puller propeller and designed for articulated movement between a VTOL position in front of the wing leading edge and a forward flight position below the wing leading edge. The trailing-edge propulsion unit is fitted with a pusher propeller and designed for articulated movement between a VTOL position in behind the wing trailing edge and a forward flight position above the wing leading edge. The propeller includes a propulsor thrust ring having an aerodynamic profile and a thrust nozzle to capture and vector radial air leakage into thrust.
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