公开(公告)号：US20250033798A1

公开(公告)日：2025-01-30

申请号：US18358854

申请日：2023-07-25

Applicant: THE BOEING COMPANY

Inventor： Remmelt A. STAAL ,  Gary D. OAKES ,  Arne K. LEWIS

IPC: B64F5/40 ,  B23P6/00

Abstract: The present disclosure provides a method of repairing a hat stringer. The method includes arranging a repair stringer in a mounting location that is one of a plurality of possible mounting locations along a cross section of a hat stringer. In each of the plurality of possible mounting locations, at least a portion of an internal profile of the repair stringer matches at least a portion of a profile of an internal cavity defined by the hat stringer. A cross-sectional area of the repair stringer as viewed along a first direction is less than a total cross-sectional area of the hat stringer as viewed along the first direction. The method also includes coupling the repair stringer with a stringer of the hat stringer in the mounting location. Repair stringers and repaired hat stringers are also provided.

公开(公告)号：US20240343414A1

公开(公告)日：2024-10-17

申请号：US18299421

申请日：2023-04-12

Applicant: THE BOEING COMPANY

Inventor： Remmelt A. STAAL ,  Arne K. LEWIS ,  Justin H. REGISTER

IPC: B64F5/40 ,  B29C73/10 ,  B29C73/30

CPC classification number: B64F5/40 ,  B29C73/10 ,  B29C73/30

Abstract: The present disclosure provides repair systems, repair components, and methods for repairing composite structure systems using a set number of prefabricated repair components including a repair component and various shims which are fabricated to repair multiple composite members in a composite structure system.

公开(公告)号：US20230158759A1

公开(公告)日：2023-05-25

申请号：US18152537

申请日：2023-01-10

Applicant: The Boeing Company

Inventor： Melissa H. LEWIS ,  Arne K. LEWIS ,  Blake A. BERTRAND ,  Pradeep KRISHNASWAMY ,  Baris YUKSELOGLU

IPC: B29C73/10 ,  B32B3/26 ,  B32B5/26

CPC classification number: B29C73/10 ,  B32B3/266 ,  B32B5/26 ,  B32B2262/106 ,  B29K2307/04

Abstract: A hole plug that can be used during rework or repair of a composite fiber assembly includes various features that allow placement of a vacuum force to the surface being reworked or repaired. In some implementations, the hole plug can include a plurality of nubs positioned around a shank. The nubs can secure the hole plug to the composite fiber assembly until a cure of an adhesive. The hole plug can further include a plurality of longitudinally oriented grooves extending along the shank and positioned between the plurality of nubs, and can include a notch positioned circumferentially around the shank. The grooves and notch can be used as adhesive carriers that assist with dispersal of a sufficient volume of the adhesive onto other portions of the shank and the composite fiber assembly during insertion of the hole plug into a hole in the composite fiber assembly.

公开(公告)号：US20190016107A1

公开(公告)日：2019-01-17

申请号：US15646606

申请日：2017-07-11

Applicant: The Boeing Company

Inventor： Blake A. BERTRAND ,  Arne K. LEWIS

IPC: B32B43/00 ,  B32B37/12 ,  B32B7/12

CPC classification number: B32B43/00 ,  B29C73/10 ,  B32B7/12 ,  B32B37/12

Abstract: Provided is a method a method for reworking an article. The method includes forming a patch over an area of a composite structure requiring rework. The forming includes placing a first film-adhesive over the area of the composite structure requiring rework, wherein the first film-adhesive extends over a first surface area of the structure including beyond an entirety of the area requiring rework, placing a first pre-cured ply stack over the first film-adhesive, wherein the first pre-cured ply stack extends over a second surface area of the composite structure; placing a second film-adhesive over the first pre-cured ply stack, wherein the second film-adhesive extends over a third surface area of the composite structure; and placing a second pre-cured ply stack over the second film-adhesive, wherein the second pre-cured ply stack extends over a fourth surface area of the composite structure.