Composite structural member having an undulating web and method for forming the same

• US 20060237588A1
• Filed: 03/31/2005
• Published: 10/26/2006
• Est. Priority Date: 03/31/2005
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Application Number:
  US11/096,795
• Publication Number:
  US 20060237588A1
• Time in Patent Office: Days
• US Class Current: 244/119
• CPC Class Codes: B64C 1/065 Spars
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: E04C 2003/0452 H- or I-shaped
• CPC Class Codes: E04C 3/07 at least partly of bent or otherwise deformed strip- or sheet-like material
• CPC Class Codes: E04C 3/29 built-up from parts of different material, i.e. composite structures
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to the first direction by a web portion, the web portion further including a periodic or a non-periodic undulation extending in the first direction. A first reinforced polymer-based substrate is fixedly coupled to the first flange portion, and a second reinforced polymer-based substrate is fixedly coupled to the second flange portion.

Claims

16-1. The method of claim 16, wherein forming a web portion into a desired non-planar shape includes forming a web portion into at least one of a periodic undulating shape and a non-periodic undulating shape.

20. An aerospace vehicle, comprising:

a fuselage;

wing assemblies and an empennage operatively coupled to the fuselage; and

a composite structural member positioned in at least one of the wing assemblies, the fuselage and the empennage, the composite structural member further comprising;

a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to the first direction by a web portion, the web portion further including a non-planar portion extending in the first direction;

a first reinforced polymer-based substrate fixedly coupled to the first flange portion; and

a second reinforced polymer-based substrate fixedly coupled to the second flange portion.

21. The aerospace vehicle of claim 20, wherein the non-planar portion comprises at least one of a periodic undulation portion and a non-periodic undulation portion.

22. The aerospace vehicle of claim 20, wherein the non-planar portion includes a periodic undulation comprising at least one of an approximately sinusoidal undulation, a triangular wave undulation and a square wave undulation.