公开(公告)号：US20250121926A1

公开(公告)日：2025-04-17

申请号：US19002889

申请日：2024-12-27

Applicant: Textron Innovations Inc.

Inventor： Charles David Hogue ,  James Everett Kooiman ,  Joseph Richard Carpenter, JR. ,  David G. Carlson ,  Jonathan Alexander Freeman

IPC: B64C1/06 ,  B64C27/26

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith. The plurality of stiffening beads may be integrated with the side panel and extend parallel to one another.

公开(公告)号：US20240317382A1

公开(公告)日：2024-09-26

申请号：US18188132

申请日：2023-03-22

Applicant: Textron Innovations Inc.

Inventor： Charles David Hogue ,  James Everett Kooiman ,  Joseph Richard Carpenter, JR. ,  David G. Carlson ,  Jonathan Alexander Freeman

IPC: B64C1/06

CPC classification number: B64C1/061 ,  B64C27/26

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

公开(公告)号：US11738493B2

公开(公告)日：2023-08-29

申请号：US17242014

申请日：2021-04-27

Applicant: Textron Innovations Inc.

Inventor： David G. Carlson ,  Douglas K. Wolfe ,  James A. Cordell

IPC: B23P19/10 ,  B32B27/02 ,  B33Y10/00 ,  B29C48/05 ,  B29C63/00 ,  B64C11/16 ,  B64C3/00 ,  B29C70/52 ,  B29C64/118 ,  B29C33/38 ,  B64F5/10 ,  B29C65/78 ,  B29C65/00 ,  B25B11/02 ,  B29C70/54 ,  B29K105/10 ,  B29K105/14 ,  B29L31/00 ,  B29L31/08 ,  B29L31/30

CPC classification number: B29C48/05 ,  B25B11/02 ,  B29C33/3842 ,  B29C63/0069 ,  B29C64/118 ,  B29C65/78 ,  B29C65/7802 ,  B29C66/721 ,  B29C66/7311 ,  B29C66/73111 ,  B29C66/73112 ,  B29C70/52 ,  B29C70/541 ,  B29C70/543 ,  B32B27/02 ,  B64C3/00 ,  B64C11/16 ,  B64F5/10 ,  B23P2700/01 ,  B29K2105/106 ,  B29K2105/14 ,  B29K2995/0044 ,  B29L2031/08 ,  B29L2031/082 ,  B29L2031/3076 ,  B29L2031/3079 ,  B29L2031/3082 ,  B29L2031/3085 ,  B29L2031/3088 ,  B29L2031/757 ,  B32B2262/0215

Abstract: In one embodiment, a method includes fastening a plurality of components of a composite structure in an assembly fixture, wherein the assembly fixture comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the assembly fixture further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the assembly fixture; and heating the assembly fixture in an autoclave to bond the plurality of components of the composite structure.

公开(公告)号：US12214857B2

公开(公告)日：2025-02-04

申请号：US18188132

申请日：2023-03-22

Applicant: Textron Innovations Inc.

Inventor： Charles David Hogue ,  James Everett Kooiman ,  Joseph Richard Carpenter, Jr. ,  David G. Carlson ,  Jonathan Alexander Freeman

IPC: B64C1/06 ,  B64C27/26

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

公开(公告)号：US11628601B2

公开(公告)日：2023-04-18

申请号：US17378232

申请日：2021-07-16

Applicant: Textron Innovations Inc.

Inventor： David G. Carlson

IPC: B29C33/38 ,  B29C33/40 ,  B29C70/46 ,  B29C70/20 ,  B29C70/88 ,  B29C48/18

Abstract: One embodiment is an apparatus including a mold configured to manufacture a composite structure at a heated temperature. The mold includes a first mold tool configured to mold a first portion of the composite structure, wherein the first mold tool comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands; and an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the first mold tool; and a second mold tool configured to mold a second portion of the composite structure.