Composite barrel sections for aircraft fuselages and other structures

• US 8,382,037 B2
• Filed: 03/02/2012
• Issued: 02/26/2013
• Est. Priority Date: 04/06/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Biornstad, Robert D., Blankinship, Bruce C., George, Terry J., Ingram, William H.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US13/411,439
• Publication Number:
  US 20120219764A1
• Time in Patent Office: 361 Days
• Field of Search: 244/119, 244/123.1, 244/117.R, 244/131, 244/123.12, 244/132, 244/120, 416/230
• US Class Current: 244/119
• CPC Class Codes: B29C 53/587 having a non-uniform wall-structure, e.g. with inserts, perforations, locally concentrated reinforcements
• CPC Class Codes: B29C 70/32 on a rotating mould, former or core
• CPC Class Codes: B29C 70/382 Automated fiber placement [AFP]
• CPC Class Codes: B29C 70/44 using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• CPC Class Codes: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs
• CPC Class Codes: B29L 2031/3082 Fuselages
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24636 Embodying mechanically interengaged strand[s], strand-portion[s] or strand-like strip[s] [e.g., weave, knit, etc.]

Abstract

Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are herein. A composite aircraft panel manufacturing assembly comprises a skin, a stiffener, a tubular bladder, and at least one ply of fabric. The stiffener comprises first and second flange portions bonded to the skin. The stiffener further comprises an interior surface, spaced apart from the skin, and extending between the first and second flange portions. The tubular bladder extends longitudinally between the interior surface of the stiffener and the skin. The at least one ply of fabric extends around the bladder and is bonded to the interior surface of the stiffener and an adjacent portion of the skin between the first and second flange portions.

Claims

1. A composite aircraft panel manufacturing assembly comprising:

a skin;

a stiffener having first and second flange portions bonded to the skin, the stiffener further including an interior surface extending between the first and second flange portions, wherein the interior surface is spaced apart from the skin and at least a portion of the interior surface faces toward the skin;

a tubular bladder extending longitudinally between the interior surface of the stiffener and the skin; and

at least one ply of fabric extending around the bladder and bonded to the interior surface of the stiffener and an adjacent portion of the skin between the first and second flange portions.

2. The composite aircraft panel manufacturing assembly of claim 1, wherein the fabric forms a tube contacting the interior surface of the stiffener and the skin between the first and second flange portions.

3. The composite panel manufacturing assembly of claim 1, wherein the stiffener has a hat-shaped cross-section.

4. The composite panel manufacturing assembly of claim 1, wherein the skin includes a plurality of automatically placed unidirectional fibers.