Aircraft comprising composite structural component, and method for forming composite structural component

Patent metadata

Field	Value
Publication number	US-11529776-B2
Application number	US-201916529464-A
Country	US
Kind code	B2
Filing date	Aug 1, 2019
Priority date	Aug 1, 2019
Publication date	Dec 20, 2022
Grant date	Dec 20, 2022

Abstract

A method for fabricating a composite wing structural component for an aircraft is described. The method comprises extruding a filler material into each mold channel of a plurality of mold channels of a die to form a plurality of filler segments, removing the plurality of filler segments from the plurality of mold channels of the die, and arranging the plurality of filler segments in a space in the composite structural component, the space being defined by a radius of the composite structural component, such that the filler segments are in end-to-end contact. The method further comprises curing the plurality of filler segments in the space to fuse the plurality of filler segments.

First claim

The invention claimed is:

1. A method of fabricating a composite structural component for an aircraft, the method comprising:
extruding a filler material into each mold channel of a plurality of mold channels of a die to form a plurality of filler segments;
removing the plurality of filler segments from the plurality of mold channels of the die;
arranging the plurality of filler segments in a space in the composite structural component, the space being defined by a radius of the composite structural component, such that the filler segments are in end-to-end contact; and
curing the plurality of filler segments in the space to fuse the plurality of filler segments.

2. The method of claim 1 , wherein each mold channel is angularly offset from adjacent mold channels around a polygonal circumference of the die, and wherein extruding the filler material into each mold channel of the plurality of mold channels of the die comprises rotating the die between each extrusion.

3. The method of claim 2 , wherein rotating the die between each extrusion comprises rotating the die between each of six to ten extrusions.

4. The method of claim 1 , wherein extruding the filler material into each mold channel comprises extruding the filler material into the mold channels having a length of between eight and twelve feet.

5. The method of claim 1 , wherein each mold channel is laterally offset from one or more adjacent mold channels on a substantially planar surface of the die, and wherein extruding the filler material into each mold channel comprises changing a relative lateral position of the die and an extrusion orifice between each extrusion.

6. The method of claim 1 , further comprising applying pressure to the filler material while extruding the filler material into each of the plurality of mold channels.

7. The method of claim 1 , further comprising removing the plurality of filler segments from the plurality of mold channels after a cooling period.

8. The method of claim 1 , wherein curing the plurality of filler segments comprises heating the plurality of filler segments.

9. The method of claim 1 , wherein curing the plurality of filler segments bonds the plurality of filler segments to other portions of the composite structural component to form a unitary structure.

10. The method of claim 1 , further comprising arranging a plurality of dies, each die of the plurality of dies comprising a plurality of mold channels, and sequentially extruding the filler material into each mold channel of each die of the plurality of dies.

11. The method of claim 1 , wherein arranging the plurality of filler segments in the space comprises arranging the plurality of filler segments in a space where a web and a flange of the composite structural component meet.

12. The method of claim 11 , wherein arranging the plurality of filler segments in the space where the web and the flange of the composite structural component meet comprises arranging the plurality of filler segments in a space where a web and a flange of a stringer for the aircraft meet.

13. The method of claim 12 , wherein arranging the plurality of filler segments in the space where the web and the flange of the stringer for the aircraft meet comprises arranging the plurality of filler segments in a space where a web and a flange of a blade stringer for the aircraft meet.

14. The method of claim 1 , wherein the method of fabricating the composite structural component comprises a method of fabricating an aircraft wing.

Assignees

• Boeing Co

Inventors

• Tran Davis
• Langabeer Jr Richard Jameson
• Song Weidong

Classifications

• B29L2031/3085

  Wings · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B29L2031/3082

  Fuselages · CPC title

• B64C2027/4736

  from composite materials · CPC title

• B29K2307/04

  Carbon · CPC title