Compliant stiffener for aircraft fuselage

Patent metadata

Field	Value
Publication number	US-9359061-B2
Application number	US-16379805-A
Country	US
Kind code	B2
Filing date	Oct 31, 2005
Priority date	Oct 31, 2005
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

First claim

What is claimed is:

1. An aircraft fuselage nose section having a longitudinal axis, and comprising:
a unitary circumferentially extending composite skin;
a plurality of composite fiber stiffeners;
each stiffener including at least one foot, at least one sidewall, and a cap,
the at least one foot bonded to an interior circumference of the composite skin,
each stiffener extending in a circumferential direction,
said plurality of composite fiber stiffeners spaced orthogonally with respect to the longitudinal axis to define a spaced parallel array,
each stiffener defining a continuous circumferential structural component of the nose section,
the cap spaced apart from the skin;

wherein the cap includes plies of carbon fibers that extend at an angle with respect to the circumferential direction;
wherein the cap further includes plies of glass fibers that extend orthogonally with respect to the longitudinal axis; and
wherein the interior circumference of the composite skin is stringerless.

2. The nose section of claim 1 , wherein the plies of the carbon fibers are interleaved with the plies of the glass fibers.

3. The nose section of claim 1 , wherein the glass fibers and the carbon fibers are configured to protect the nose section against strike impact loads.

4. The nose section of claim 1 , wherein the carbon fibers are oriented at angles of +60 degrees and −60 degrees with respect to the circumferential direction.

5. The nose section of claim 1 , wherein the glass fibers are S-2 fibers or fiberglass.

6. The nose section of claim 1 , wherein the stiffener is a hat stiffener.

Assignees

• Kismarton Max U
• Andrews Francis E
• Koch William J
• Boeing Co

Inventors

• Kismarton Max U
• Andrews Francis E
• Koch William J

Classifications

• B64C1/12

  Construction or attachment of skin panels · CPC title

• B29C70/202

  arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] (B29C70/207 takes precedence) · CPC title

• B29K2105/108

  arranged in parallel planes and crossing at substantial angles (B29K2105/206 takes precedence) · CPC title

• B29K2105/246

  Uncured, e.g. green · CPC title

• B29C70/44

  using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding · CPC title