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公开(公告)号：US20240182167A1
公开(公告)日：2024-06-06
申请号：US18218964
申请日：2023-07-06
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
摘要： A vehicle includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.
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公开(公告)号：US11634215B2
公开(公告)日：2023-04-25
申请号：US17086210
申请日：2020-10-30
申请人： Yang Woo Nam
发明人： Yang Woo Nam
IPC分类号： B64C27/20 , B64C27/08 , B64D27/24 , B64C29/00 , B64C11/00 , B64C15/12 , B64C27/52 , B64D27/16 , B64D27/26
摘要： A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.
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公开(公告)号：US20220024586A1
公开(公告)日：2022-01-27
申请号：US17450096
申请日：2021-10-06
申请人： ZIPAIR
发明人： Frankie ZAPATA
摘要： A propulsion device has a body including a platform and a thrust unit, the thrust unit including a first thermal thruster configured to eject a gaseous flow along an axis normal to the platform, the body of the propulsion device including support means of the thrust unit, wherein said thrust unit includes a first electrical secondary thruster configured to correct the attitude of the propulsion device.
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公开(公告)号：US11091247B1
公开(公告)日：2021-08-17
申请号：US15880315
申请日：2018-01-25
IPC分类号： B64C27/08 , B64C15/12 , B64C13/18 , B64D31/06 , B64D45/00 , G05D1/08 , B64C13/04 , B64C29/00 , B64C13/50
摘要： A geometry-based flight control system is disclosed. In various embodiments, a set of inceptor inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is computed, including by taking into consideration dynamically varying effectiveness of one or more actuators based on a current dynamic state of the aircraft. An output comprising for each actuator in the optimal mix a corresponding set of one or more control signals associated with the set of actuator parameters computed for that actuator is provided.
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公开(公告)号：US11066163B2
公开(公告)日：2021-07-20
申请号：US15789192
申请日：2017-10-20
摘要： Systems and methods to form distributed and reconfigurable aerial vehicle configurations are described. An aerial vehicle configuration may include a plurality of aerial vehicles that are connected to a payload via respective tethers in order to complete a task, e.g., delivery of the payload to a location. The plurality of aerial vehicles selected as part of the aerial vehicle configuration may be of various types and may form a particular initial configuration. During operation, the aerial vehicle configuration may be modified based on changes to various operating parameters associated with aerial vehicles, the aerial vehicle configuration, the task, and/or the environment. The modifications may include changing positions, altitudes, and/or orientations of aerial vehicles with respect to each other and/or the payload, releasing aerial vehicles from the configuration, or adding new aerial vehicles to the configuration.
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公开(公告)号：US20210053672A1
公开(公告)日：2021-02-25
申请号：US17045757
申请日：2019-04-05
申请人： PRADES IMASD, S.L.
IPC分类号： B64C11/00 , B64C9/00 , B64D27/24 , B64D27/02 , B64D35/00 , B64C27/52 , B64C15/12 , B60L50/60 , B60L8/00 , B64C29/00 , B64D17/00 , B64C31/036
摘要： A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance.
The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.-
公开(公告)号：US10858092B2
公开(公告)日：2020-12-08
申请号：US15770254
申请日：2016-10-28
申请人： Yang Woo Nam
发明人： Yang Woo Nam
IPC分类号： B64C27/20 , B64C27/08 , B64D27/24 , B64C29/00 , B64C11/00 , B64C15/12 , B64C27/52 , B64D27/16 , B64D27/26
摘要： A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.
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公开(公告)号：US10737765B2
公开(公告)日：2020-08-11
申请号：US15972461
申请日：2018-05-07
摘要： An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto and operable to tilt about a single axis. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal is operable to tilt the respective propulsion system relative to the airframe in the longitudinal direction to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.
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公开(公告)号：US10597144B2
公开(公告)日：2020-03-24
申请号：US15828548
申请日：2017-12-01
申请人： Hadie Fotouhie
发明人： Hadie Fotouhie
摘要： During flight of a jet aircraft the essential steering movements, such as roll, pitch and yaw maneuvers, are normally performed via control surfaces on its wings and its tail sections. This invention allows for swiveling of jet engines mounted under wings of the jet aircraft, to direct exhaust gases upward, downward or sideways to some limited extent to achieve more agile air maneuvers compared to traditional fixed under the wing-mounted jet engines. The idea of performing more agile air maneuvers is realized by swiveling and pivoting the jet engine under the wings of the jet aircraft about a pivot point mounted along an engine nacelle to enable highly efficient pitch and roll motions in flight, as well as making efficient and agile yaw type motion in flight by swiveling and pivoting the jet engines underneath the wings.
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公开(公告)号：US10279907B2
公开(公告)日：2019-05-07
申请号：US15113368
申请日：2015-01-27
摘要： Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.
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