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公开(公告)号：US20240270403A1
公开(公告)日：2024-08-15
申请号：US18644352
申请日：2024-04-24
发明人： Woo Suk JUNG , Gwi Taek KIM , Yoon Cheol JEON , Hyun Ki CHO
摘要： An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.
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公开(公告)号：US20230009569A1
公开(公告)日：2023-01-12
申请号：US17837892
申请日：2022-06-10
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
摘要： A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.
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公开(公告)号：US20220333624A1
公开(公告)日：2022-10-20
申请号：US17853665
申请日：2022-06-29
申请人： JETOPTERA, INC.
发明人： ANDREI EVULET
摘要： A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.
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公开(公告)号：US11472560B2
公开(公告)日：2022-10-18
申请号：US16856442
申请日：2020-04-23
申请人： ROLLS-ROYCE plc
摘要： A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.
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公开(公告)号：US20220219806A1
公开(公告)日：2022-07-14
申请号：US17642457
申请日：2020-09-11
申请人： Alexandru Balan
发明人： Alexandru Balan
摘要： This present disclosure relates generally to propulsion systems and, more particularly, to adaptive ducted fan propulsion systems for use with aircraft such as unmanned aerial vehicles. Embodiments of ADF systems in accordance with the present disclosure feature automatic, fast operation, increase the intake section of the air mass fed to a propeller, and can increase thrust by 35%-40% as compared to existing ducted fans.
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公开(公告)号：US11325699B2
公开(公告)日：2022-05-10
申请号：US16833618
申请日：2020-03-29
IPC分类号： B64C11/00 , B64C21/04 , B64C29/00 , B64D27/16 , B64C11/48 , B64D35/06 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C19/00 , B64C27/26 , B64C27/30 , B64C9/20 , B64C21/08 , B64C27/78 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
摘要： A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.
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公开(公告)号：US11167844B2
公开(公告)日：2021-11-09
申请号：US16833628
申请日：2020-03-29
IPC分类号： B64C27/22 , B64C29/00 , B64C27/30 , B64C15/14 , B64C21/00 , B64C27/78 , B64C27/26 , B64D33/04 , B64C3/10
摘要： An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes first and second engines, a binary lift fan system, first and second forced air bypass systems and first and second exhaust systems. The engines have turboshaft and turbofan modes. The lift fan system includes ducted fans in a tandem longitudinal orientation. In the VTOL orientation of the aircraft, the engines are in the turboshaft mode coupled to the lift fan system such that the engines provide rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engines are in the turbofan mode coupled to the forced air bypass systems such that the bypass air combines with the engine exhaust in the exhaust systems to provide forward thrust generating the wing-borne lift.
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公开(公告)号：US20200023987A1
公开(公告)日：2020-01-23
申请号：US16221383
申请日：2018-12-14
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： B64D33/04 , B64C39/02 , B64C15/14 , B64C9/38 , B64C15/00 , B64C21/00 , B64D27/10 , B64C21/04 , B64D27/18 , B64D29/02 , B64D33/02 , F02K1/36 , F02K1/00 , F02C3/04 , F02C6/04
摘要： A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.
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公开(公告)号：US20190217951A1
公开(公告)日：2019-07-18
申请号：US15870216
申请日：2018-01-12
申请人： Byron J. Willner
发明人： Byron J. Willner
CPC分类号： B64C39/001 , B64C15/14 , B64D27/02
摘要： The present invention is directed to a saucer type hovercraft having at least a pair of selectively counter-rotating lift and stabilization rings. The rings are held in place by correspondingly shaped circular bearing tracks and are powered by thrusters and electromagnets such that a central shaft is not needed. A wireless control system is used to control both speed and direction of rotation of the wings.
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公开(公告)号：US20180334247A1
公开(公告)日：2018-11-22
申请号：US15601601
申请日：2017-05-22
申请人： The Boeing Company
发明人： Robert Michael Lee
CPC分类号： B64C15/14 , B64D33/04 , F02K1/40 , F02K1/763 , F05D2220/90
摘要： Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.
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