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公开(公告)号：US20240132212A1
公开(公告)日：2024-04-25
申请号：US18483338
申请日：2023-10-08
Applicant: Textron Aviation Inc.
Abstract: An electric aircraft includes a forward wing and an aft wing both located on a top side of a fuselage and both having an upward dihedral angle. The forward wing has a straight or slightly forward-swept leading edge. The aft wing has a swept leading edge. A plurality of propeller engines are located on a leading-edge side of the forward wing. A single propeller engine may be located on a top side of an aft end of the fuselage; alternatively, a plurality of propeller engines are located on the aft wing on either its leading or trailing edge. The propeller engines are each powered by an electric motor. An unobstructed cargo door is located on a side of the fuselage, aft of the forward wing.
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公开(公告)号：USD1026788S1
公开(公告)日：2024-05-14
申请号：US29843103
申请日：2022-06-17
Applicant: Textron Aviation Inc.
Designer： Gonzalo Eduardo Mendoza , Corey Wailes Hagemeister , Kelly Ray Laflin
Abstract: FIG. 1 is a perspective view of the winglet showing our new design;
FIG. 2 is a front view of the winglet of FIG. 1;
FIG. 3 is a rear view of the winglet of FIG. 1;
FIG. 4 is a top view of the winglet of FIG. 1;
FIG. 5 is a bottom view of the winglet of FIG. 1;
FIG. 6 is a side view of the winglet of FIG. 1;
FIG. 7 is another side view of the winglet of FIG. 1; and,
FIG. 8 is a perspective view of the winglet of FIG. 1 shown in an environment of use installed on wings of an aircraft.
In FIGS. 1-8, the broken lines in the drawings depict portions of the winglet that form no part of the claimed design. The dot-dash broken lines depict the bounds of the claimed design and form no part thereof. The additional broken lines shown in FIG. 8 depict environmental structure only and form no part thereof.-
Patent Agency Ranking
公开(公告)号：USD1026789S1
公开(公告)日：2024-05-14
申请号：US29843109
申请日：2022-06-17
Applicant: Textron Aviation Inc.
Designer： Gonzalo Eduardo Mendoza , Corey Wailes Hagemeister , Kelly Ray Laflin
Abstract: FIG. 1 is a perspective view of the winglet showing our new design;
FIG. 2 is a front view of the winglet of FIG. 1;
FIG. 3 is a rear view of the winglet of FIG. 1;
FIG. 4 is a top view of the winglet of FIG. 1;
FIG. 5 is a bottom view of the winglet of FIG. 1;
FIG. 6 is a side view of the winglet of FIG. 1;
FIG. 7 is another side view of the winglet of FIG. 1; and,
FIG. 8 is a perspective view of the winglet of FIG. 1 shown in an environment of use installed on wings of an aircraft.
In FIGS. 1-8, the broken lines in the drawings depict portions of the winglet that form no part of the claimed design. The dot-dash broken lines depict the bounds of the claimed design and form no part thereof. The additional broken lines shown in FIG. 8 depict environmental structure only and form no part thereof.-
公开(公告)号：US20250145271A1
公开(公告)日：2025-05-08
申请号：US18934165
申请日：2024-10-31
Applicant: Textron Aviation Inc.
IPC: B64C1/14 , B64D27/33 , B64D27/355 , B64D27/357
Abstract: An aircraft having unobstructed cabin door access includes a hybrid power drive with a combustion engine connected to an electricity generating machine. Components of the hybrid power drive are positioned throughout the aircraft to provide a weight distribution having an aft bias. The aircraft further includes a forward swept wing and a cabin door positioned forward of the forward swept wing, such that access into a fuselage of the aircraft via the cabin door is unobstructed by the forward swept wing.
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公开(公告)号：US20240375770A1
公开(公告)日：2024-11-14
申请号：US18644280
申请日：2024-04-24
Applicant: Textron Aviation Inc.
Inventor： Kelly Ray Laflin , Gonzalo Eduardo Mendoza , Corey Wailes Hagemeister
IPC: B64C23/06
Abstract: Wingtip devices configured to extend from the outboard ends of aircraft wings are designed to effectively reduce induced drag, but they necessarily produce form and skin-friction drag, and they may produce interference and compressibility drag. The present disclosure describes a scythe-shaped wingtip device (or ‘winglet’ or ‘extending member’) suitable for reducing the induced drag of an aircraft wing while minimizing other types of drag. A cutout in the wingtip device reduces the wetted area of the wingtip to minimize non-induced drag while the wingtip device still reduces induced drag like a conventional wingtip device. The cutout is configured in a trailing edge of the wingtip device.
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公开(公告)号：US20240228036A9
公开(公告)日：2024-07-11
申请号：US18483338
申请日：2023-10-09
Applicant: Textron Aviation Inc.
Abstract: An electric aircraft includes a forward wing and an aft wing both located on a top side of a fuselage and both having an upward dihedral angle. The forward wing has a straight or slightly forward-swept leading edge. The aft wing has a swept leading edge. A plurality of propeller engines are located on a leading-edge side of the forward wing. A single propeller engine may be located on a top side of an aft end of the fuselage; alternatively, a plurality of propeller engines are located on the aft wing on either its leading or trailing edge. The propeller engines are each powered by an electric motor. An unobstructed cargo door is located on a side of the fuselage, aft of the forward wing.
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公开(公告)号：US20230406484A1
公开(公告)日：2023-12-21
申请号：US18337130
申请日：2023-06-19
Applicant: Textron Aviation Inc.
Inventor： Gonzalo Eduardo Mendoza , Corey Wailes Hagemeister , Kelly Ray Laflin
IPC: B64C23/06
CPC classification number: B64C23/069
Abstract: A tandem split divergent winglet for an aircraft includes a forward sail extending from an outboard end of a wing of the aircraft having a cant angle in a first direction, and an aft sail extending partially from the forward sail and partially from the outboard end of the wing. The aft sail has a cant angle in a second direction opposite the first direction. For aircraft having a low wing, the forward sail includes an upwards cant angle and the aft sail includes a downwards cant angle. For aircraft having a high wing, the forward sail includes a downwards cant angle, and the aft sail includes an upwards cant angle. Light emitted from an integrated light formed within the aft sail is blocked from reaching a cockpit window of the aircraft by the forward sail.
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