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公开(公告)号：US20240278913A1
公开(公告)日：2024-08-22
申请号：US18569965
申请日：2022-07-06
发明人： Daichi WADA , Atsushi OSEDO
CPC分类号： B64C39/026 , B64C3/56 , B64C15/02 , B64D45/00
摘要： This flight equipment (100) includes a thrust device (10) that provides thrust during flight, wings (20) that maintain an attitude during flight and change a direction of flight, a control unit that controls strength of an output from the thrust device (10), and an attachment and detachment unit (30) that can be worn or removed by a user (H).
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公开(公告)号：US20240150011A1
公开(公告)日：2024-05-09
申请号：US18333513
申请日：2023-06-12
CPC分类号： B64C15/02 , B64C27/20 , B64C39/024 , B64D1/22 , B64D47/08
摘要： A method for unmanned delivery of an item to a desired delivery location includes receiving, at an unmanned vehicle, first data representative of an approximate geographic location of the desired delivery location, receiving, at the unmanned vehicle, second data representative of a fiducial expected to be detectable at the desired delivery location, using the first data to operate the unmanned vehicle to travel to the approximate geographic location of the desired delivery location, upon arriving at the approximate geographic location of the desired delivery location, using the second data to operate the unmanned vehicle to detect the fiducial; and upon detecting the fiducial, using the fiducial to operate the unmanned vehicle to deliver the item.
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公开(公告)号：US11912406B2
公开(公告)日：2024-02-27
申请号：US16939451
申请日：2020-07-27
CPC分类号： B64C31/036 , B64C11/001 , B64C11/48 , B64C15/02 , B64D5/00 , B64D27/02 , B64D2027/026
摘要： Current foot-launched 2-stroke commercial PPG offerings can meet the specified threshold (and in some cases, objective) requirements for flight ceiling, payload capacity and range with little to no modification. We will discuss those in the next section. The APES system enhances the effectiveness and lethality of the PPG-equipped unit by reducing weight of the PPG, increasing reliability and redundancy, reducing pilot workload, and seamlessly integrating with UAV's and UGV's. System improvements in the following areas is assessed: Series hybrid-electric powertrain, Coaxial propellers. Localization, autopilot, and formations, Auto landing and other advanced features, Integration with unmanned systems, and Launch Considerations.
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公开(公告)号：US11591083B2
公开(公告)日：2023-02-28
申请号：US16953479
申请日：2020-11-20
发明人： Jamey D. Jacob , Weng Kheong Loh
摘要： An embodiment of the present disclosure relates to an unmanned flying robotic object that contains a wheeled mechanism that encircles its spherical exoskeleton. This feature allows the flying spherical vehicle to readily transform into a ground maneuverable vehicle. A robotic motor with differential speed capability is used to operate each wheel to provide effective ground maneuverability. There are examples provided herein of wheel configurations suitable for use with an embodiment. One is the straight- (or parallel) wheel design, and another is tilted-wheel design as are illustrated and discussed hereinafter. One embodiment of an unmanned flying robotic object taught herein is foldable.
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5.发明授权公开(公告)号：US11485505B2
公开(公告)日：2022-11-01
申请号：US15576996
申请日：2016-05-27
申请人： BOMBARDIER INC.
摘要： An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.
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公开(公告)号：US20220315207A1
公开(公告)日：2022-10-06
申请号：US17349269
申请日：2021-06-16
申请人： BETA AIR, LLC
摘要： An aircraft for neutralizing flight comprising a fuselage, at least a power source, a plurality of laterally extending elements attached to the fuselage, a plurality of downward directed propulsors attached to the plurality of laterally extending elements and electrically connected to at least a power source, wherein the plurality of downward directed propulsors have a rotational axis offset from a vertical axis by a yaw-torque-cancellation angle, and a flight controller configured to include a notification unit.
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公开(公告)号：US11427306B2
公开(公告)日：2022-08-30
申请号：US16359342
申请日：2019-03-20
申请人： The Boeing Company
IPC分类号： B64C29/00 , B64C15/02 , B64C29/04 , B64C39/02 , F04D13/06 , F04D13/12 , F04D15/00 , B64D27/18
摘要： A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The UAV includes ducted fans which are with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.
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公开(公告)号：US20220204158A1
公开(公告)日：2022-06-30
申请号：US17331292
申请日：2021-05-26
发明人： Kun-Yang CHEN , Kai-Tse LIN , Chenchang LI , Zhiyang YU , Yin-Hua HSU
摘要： A carrier aircraft, comprising: a body for carrying at least one object or passenger; and multiple rotatable fan devices disposed on two sides of said body; wherein an angle of rotation of one of said rotatable fan devices can be changed, such that said carrier aircraft flies along a direction at an angle, said angle being between 0 degrees to 30 degrees.
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公开(公告)号：US11072421B2
公开(公告)日：2021-07-27
申请号：US16150183
申请日：2018-10-02
发明人： Xichen Shi , Marcel Veismann , Christopher J. Dougherty , Stephanie Rider , Soon-Jo Chung , Morteza Gharib , Kyunam Kim , Salar Rahili
IPC分类号： B64C27/26 , B64C11/00 , B64C11/02 , B64C39/02 , B64C27/52 , B64C29/02 , B64C3/56 , B64C27/20 , B64C29/00 , B64C27/56 , B64C15/02 , B64C23/00
摘要： An automated flying transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to generate lift and a plurality of rotors that can generate lift as well as forward thrust from which a fixed wing portion of the air transport vehicle will begin to generate additional lift allowing for a sustained flight.
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公开(公告)号：US10661893B2
公开(公告)日：2020-05-26
申请号：US15832299
申请日：2017-12-05
申请人： Yao-Chang Lin
发明人： Yao-Chang Lin
摘要： A lightweight flying vehicle includes a carrier body, at least two fan-tube propulsion devices, two steering devices and a flight wing. The fan-tube propulsion devices are respectively disposed at two opposite sides of the carrier body and have a sufficient propulsion force. The steering device is disposed on a moving line of the airflow discharged from the fan-tube propulsion devices and is configured to change a direction of the airflow discharged from the air discharge opening, so that the lightweight flying vehicle is in a high-speed flight mode. The flight wing can provide a lift power in the high-speed flight mode.
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