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公开(公告)号：US11447238B2
公开(公告)日：2022-09-20
申请号：US16217756
申请日：2018-12-12
发明人： Scott Rewerts , Yuichi Kawamura , Kui Ou , Michimasa Fujino , Kazuhisa Mahiko
摘要： A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.
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22.发明授权公开(公告)号：US11440644B2
公开(公告)日：2022-09-13
申请号：US16797342
申请日：2020-02-21
摘要： An exemplary aircraft includes a wing positioned below a vertical rotor, the wing extending to an outboard end, and an anhedral winglet extending from the outboard end through an angular transition to a tip, the anhedral winglet having an external surface exposed to the rotor downwash and the external surface is contoured to generate local wing lift in response to the rotor downwash.
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公开(公告)号：US11414180B2
公开(公告)日：2022-08-16
申请号：US16662520
申请日：2019-10-24
发明人： Denys Custance , Daren Healy
摘要： An aircraft assembly with a hot air exhaust outlet. The aircraft assembly has an assembly surface over which a hot-air exhaust flow from the hot-air exhaust outlet is exhausted. The aircraft assembly also has a vortex generator with a flow surface. The flow surface lies in an air flow over the vortex generator. The flow surface is arranged to interrupt the hot-air exhaust flow and generates a flow vortex to cool the air flow over the assembly surface.
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公开(公告)号：US20220161920A1
公开(公告)日：2022-05-26
申请号：US17534802
申请日：2021-11-24
申请人： Brown University
发明人： Matteo DI LUCA , Kenneth BREUER
摘要： A free-streamline airfoil includes a lower surface which is flat or contoured, and an upper surface that is curved or made of discrete flat elements approximating a curved surface, the upper surface presenting a cavity, a cavity width in an airfoil chordwise direction shorter than the airfoil chord, a position and depth of the cavity triggering a turbulent flow over the airfoil's suction side while preserving the airfoil physical integrity.
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公开(公告)号：US11333160B2
公开(公告)日：2022-05-17
申请号：US16999454
申请日：2020-08-21
申请人： Brien Aven Seeley
发明人： Brien Aven Seeley
IPC分类号： F04D29/18 , B64C11/20 , F04D29/38 , B64C11/18 , B64C11/00 , B64C11/08 , B64C11/06 , B64C11/16 , B64C23/06 , B64C27/00
摘要： A propeller system combines innovative strategies to create a new methodology to reduce propeller or rotor noise. The propeller is specifically aimed for ultra-quiet electrically powered aircraft for use in high proximity aviation, but its low-noise advantages will extend to other purposes. The propeller blade includes geometries, along with size and operational limitations that minimize rotational and vortex noise, vibration and span-wise air flow on the blade. To further reduce noise, the propeller provides greater relative thrust on the inboard portions of the blade than do conventional propellers and provides less than conventional relative thrust including negative thrust at the outermost portions of the blade. The propeller blade includes stepped changes in local blade stiffness at calculated intervals that can reduce resonant blade vibrations and their resultant noise. This ultra-quiet propeller design can also be used for quieting hovercraft, drones, surveillance aircraft, indoor fans, wind tunnels and other applications.
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公开(公告)号：US11299255B2
公开(公告)日：2022-04-12
申请号：US16468235
申请日：2017-11-16
申请人： BOMBARDIER INC.
发明人： Fassi Kafyeke , Marc Langlois
摘要： A slat (50) for an aircraft wing comprises a leading edge (51) defining a leading edge line (61), a trailing edge (52) defining a trailing edge line (62), the leading and trailing edges line defining a slat plane, the chord distance (69) extending normal to the leading edge and measured along the slat plane; an inboard edge extending between the leading and trailing edges; and an outboard edge (56) extending between the leading and trailing edges. The outboard edge comprises a first side portion having a projection on the plane defining a first side line (63), and a second side portion having a projection on the plane defining a second side line (64), the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line as it extends toward the inboard and trailing edges. A wing assembly and an aircraft including the slat are also disclosed.
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公开(公告)号：US20220097825A1
公开(公告)日：2022-03-31
申请号：US17463471
申请日：2021-08-31
摘要： A Short Takeoff and Landing (STOL) aircraft has a fuselage with an axis and an engine providing thrust, a first aileron at an end of a first wing, a second aileron at an end of a second wing, a first slot having a length through the first wing proximate the first aileron, orthogonal to the axis; a second slot having a length through the second wing proximate the second aileron, orthogonal to the axis; a first electric motor in the first wing driving a first two-blade propeller in the first slot, a second electric motor in the second wing driving a second two-blade propeller in the second slot, and a control mechanism enabling a user to drive the first and second electric motors in a same rotary direction, to reverse the rotary direction, and to drive the first and second motors at a same rpm.
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公开(公告)号：US11279469B2
公开(公告)日：2022-03-22
申请号：US16317273
申请日：2017-07-12
发明人： Hans-Jorg Petscher , Volker Kassera
摘要： The invention relates to a wing with two winglets (9-12) and a respective airplane. An upstream winglet (9, 11) broadens a region of inclined airflow and a downstream winglet (10, 12) produces a thrust contribution therein.
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公开(公告)号：US20220024564A1
公开(公告)日：2022-01-27
申请号：US17297880
申请日：2019-12-18
摘要： An aircraft wing is disclosed including a closed surface wing tip device which includes an element or actuator within the wing tip for deforming/morphing the shape of the wing tip between geometrical configurations having different aerodynamic properties, for example including one with better overall fuel efficiency for a shorter journey and one with overall fuel efficiency better suited for a longer journey. The device includes a lower winglet with an essentially planar portion spaced apart from the main body of the wing by a blended transition region which is shaped such that the curvature of the local dihedral increases in the outboard direction. The device includes an upper aerofoil structure which with the winglet essentially forms the closed surface. There is also disclosed an aircraft wing tip device having a sigmoid shaped (e.g. S-shaped) aerofoil structure blending in with a main wing of the aircraft.
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公开(公告)号：US20210269144A1
公开(公告)日：2021-09-02
申请号：US17325592
申请日：2021-05-20
IPC分类号： B64C23/06
摘要： An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.
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