公开(公告)号：US11161592B2

公开(公告)日：2021-11-02

申请号：US16567519

申请日：2019-09-11

Applicant: Textron Innovations Inc.

Inventor： George Ryan Decker ,  Steven Allen Robedeau, Jr. ,  Tjepke Heeringa ,  David Gordon Carlson

IPC: B64C3/26 ,  B64C3/18 ,  B64C1/00 ,  B64C29/00

Abstract: A wing assembly for an aircraft includes a torque box sleeve having an open end and a plurality of integral sides including leading, aft, top and bottom sides that jointlessly form a continuous surface having a generally airfoil shape. The wing assembly includes an internal support subassembly having a plurality of ribs coupled to a central spar. The internal support subassembly is formed into a single component outside the torque box sleeve and inserted into the open end of the torque box sleeve as the single component. The internal support subassembly is coupled to an interior of the torque box sleeve.

公开(公告)号：US12134458B2

公开(公告)日：2024-11-05

申请号：US17866753

申请日：2022-07-18

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Tjepke Heeringa

IPC: B64C1/06 ,  B21D13/10 ,  B21D53/92 ,  B32B3/28 ,  B32B7/05 ,  B32B15/01 ,  B64F5/10

Abstract: One embodiment includes a rib structure to be used, for example, in any number of aerospace applications, the rib structure, comprising a first piece having a first curvature in a first plane; and a second piece having a second curvature in a second plane that is different from the first plane. The first piece and the second piece are bonded together to form the rib structure. In certain embodiments, the first piece further comprises a plurality of discontinuous flanges to interface with a plurality of skin surfaces. In other examples, the first piece includes an aft spar interface for bonding to a surface. In some implementations, the first piece includes a forward spar interface for bonding to a surface. Manufacturing of the airframe/aircraft parts, panels, and rib components can include any suitable composites, alloys, titanium, aluminum, artificial materials, sheet metal, etc.

公开(公告)号：US20240017812A1

公开(公告)日：2024-01-18

申请号：US17866753

申请日：2022-07-18

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Tjepke Heeringa

IPC: B64C1/06 ,  B64F5/10 ,  B32B3/28 ,  B32B7/05 ,  B32B15/01 ,  B21D53/92 ,  B21D13/10

CPC classification number: B64C1/065 ,  B64F5/10 ,  B32B3/28 ,  B32B7/05 ,  B32B15/01 ,  B21D53/92 ,  B21D13/10 ,  B32B2605/18 ,  B32B2250/02

Abstract: One embodiment includes a rib structure to be used, for example, in any number of aerospace applications, the rib structure, comprising a first piece having a first curvature in a first plane; and a second piece having a second curvature in a second plane that is different from the first plane. The first piece and the second piece are bonded together to form the rib structure. In certain embodiments, the first piece further comprises a plurality of discontinuous flanges to interface with a plurality of skin surfaces. In other examples, the first piece includes an aft spar interface for bonding to a surface. In some implementations, the first piece includes a forward spar interface for bonding to a surface. Manufacturing of the airframe/aircraft parts, panels, and rib components can include any suitable composites, alloys, titanium, aluminum, artificial materials, sheet metal, etc.

公开(公告)号：US20240021943A1

公开(公告)日：2024-01-18

申请号：US17812759

申请日：2022-07-15

Applicant: Textron Innovations Inc.

Inventor： William A. Amante ,  Tjepke Heeringa

IPC: H01M50/249 ,  H01M50/271 ,  H01M50/233 ,  B60L53/80 ,  B60L50/64

CPC classification number: H01M50/249 ,  H01M50/271 ,  H01M50/233 ,  B60L53/80 ,  B60L50/64 ,  H01M2220/20

Abstract: A modular airfoil-shaped battery disposed in a wing of an aircraft is presented. In one embodiment, the present disclosure provides for a system configured to have batteries or battery modules stored and accessible through access openings in the forward wing spar. The access openings in the forward spar can provide access for battery insertion and removal, as well as electrical and thermal management connections. Such forward spar access openings can be a relatively small, as the access opening need to only be as large as the battery cross section. A battery can comprise one or more battery modules based on the application requirements. The aircraft battery can be distributed among more, smaller battery modules. The battery modules can be placed in different locations in the wing. For example, the battery modules can be placed proximate an aircraft fuselage to achieve a better center of gravity.