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公开(公告)号：US11834154B2
公开(公告)日：2023-12-05
申请号：US16813718
申请日：2020-03-09
申请人： NCTAR, LLC
摘要： A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
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2.发明授权公开(公告)号：US11787524B2
公开(公告)日：2023-10-17
申请号：US17452973
申请日：2021-10-29
申请人： The Boeing Company
发明人： Robert E. Grip , Neal A. Harrison
CPC分类号： B64C1/26 , B64C3/14 , B64C3/16 , B64C2003/149
摘要： An aircraft includes a fuselage and a pair of wings. Each wing is coupled to the fuselage at a wing-fuselage joint, and is supported by a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint. The strut-fuselage joint is located below and at least partially aft of the wing-fuselage joint. The wing generates a lifting force when air passes over the wing. The lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint. The wing and/or the strut has a structural arrangement configured to counteract the vertical moment.
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公开(公告)号：US11535375B2
公开(公告)日：2022-12-27
申请号：US16628731
申请日：2018-07-06
申请人： ISTANBUL TEKNIK UNIVERSITESI , MITOS MIKRODALGA GORUNTULEME SISTEMLERI MUHENDISLIK SANAYI VE TICARET LIMITED SIRKETI
发明人： Guray Ali Canli , Ibrahim Akduman , Ismail Kurtoglu , Mehmet Cayoren , Pelin Yavuz Gundogdu , Ibrahim Ozkol , Hasan Ercan , Muhammet Tarik Tamyurek
IPC分类号： B64C29/02 , B64D27/02 , B64C39/02 , B64B1/40 , B64B1/58 , B64C3/38 , B64C5/00 , B64C19/00 , B64C39/08 , B64D27/04 , B64D27/24 , B64D35/04 , B64C3/10 , B64C3/16 , B64C17/06
摘要： An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.
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公开(公告)号：US11267570B2
公开(公告)日：2022-03-08
申请号：US16356276
申请日：2019-03-18
申请人： Joby Aero, Inc.
发明人： Ian Andreas Villa , Mark Moore , Robert Alan McDonald , Henry Thome Won , Adam Chase , Alex Michael Gary , Cory Seubert
IPC分类号： B64C29/00 , B64C23/00 , B64C5/08 , B64C9/00 , B64D11/06 , B64D27/24 , B64F1/36 , B64C3/16 , B64C25/06
摘要： A vertical takeoff and landing (VTOL) aircraft, configured to transport passengers and/or cargo, uses propellers during vertical flight and wings during forward flight to generate lift. The VTOL aircraft includes a front wing and a rear wing connected by inboard booms. The rear wing may include a wingtip boom attached to each free end of the wing. A propeller may be attached to each inboard boom and each wingtip boom. The propellers attached to the inboard booms may be stacked propellers including at least two co-rotating propellers. The aircraft can also include a cruise propeller attached to the tail region of the fuselage, where the cruise propeller is configured to rotate in a plane approximately perpendicular to the fuselage to generate thrust during forward flight.
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公开(公告)号：US20210276726A1
公开(公告)日：2021-09-09
申请号：US17191549
申请日：2021-03-03
申请人： Wisk Aero LLC
发明人： Ilan Kroo
摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
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公开(公告)号：US20210188421A1
公开(公告)日：2021-06-24
申请号：US17123468
申请日：2020-12-16
摘要： A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.
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公开(公告)号：US20210003074A1
公开(公告)日：2021-01-07
申请号：US16969738
申请日：2019-02-15
IPC分类号： F02C7/045 , F02K1/38 , F15D1/00 , B64C21/10 , B64C21/02 , B64C3/14 , B64C3/16 , B64C7/02 , B64C11/18 , B64C5/00 , B64C5/06
摘要： An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.
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公开(公告)号：US10829206B2
公开(公告)日：2020-11-10
申请号：US15429829
申请日：2017-02-10
摘要： An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.
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公开(公告)号：US20200239126A1
公开(公告)日：2020-07-30
申请号：US16701487
申请日：2019-12-03
申请人： BOMBARDIER INC.
摘要： An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly including a wing body; and at least one protruding portion connected to the wing body. The protruding portion extends aftwardly from an aft side of the wing body assembly, a leading edge of the wing body assembly defining a leading edge line, a trailing edge of the wing body assembly defining a trailing edge line extending between the inboard end and the outboard end, the trailing edge including a trailing edge of the protruding portion, the trailing edge line being a smooth line, a chord distance being defined longitudinally from the leading edge line to the trailing edge line, the chord distance at a center of the protruding portion being greater than the chord distance inboard of protruding portion and outboard of the protruding portion.
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公开(公告)号：US20190176981A1
公开(公告)日：2019-06-13
申请号：US15836771
申请日：2017-12-08
摘要： The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode.
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