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.

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.

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：US20250108909A1

公开(公告)日：2025-04-03

申请号：US18477984

申请日：2023-09-29

Applicant: Textron Aviation Inc.

Inventor： Kelly Ray Laflin ,  Robert Glynn Wiegers

IPC: B64C7/02 ,  B64C21/04 ,  B64D27/20 ,  B64D27/26

Abstract: A low drag nacelle and pylon fairing for an aircraft includes a fairing configured to provide a low drag connection between a pylon and a nacelle. The fairing includes an aft-facing face formed between the nacelle and a trailing edge of the pylon with the aft-facing face being configured with a vent for exhausting air in the same direction as engine jet exhaust flow. The fairing includes aerodynamically formed curves providing a larger aft-facing face compared with traditional fairing arrangements. A substantial improvement in drag reduction is achieved by venting air into the space immediately beyond the aft-facing face.

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.