Composite structural truss element

• US 5,469,686 A
• Filed: 09/27/1993
• Issued: 11/28/1995
• Est. Priority Date: 09/27/1993
• Status: Expired due to Fees

• Current Assignee: Rockwell International Corporation
• Original Assignee: Rockwell International Corporation
• Inventors: Pykiet, Kenneth L.
• Primary Examiner(s): Friedman, Carl D.
• Assistant Examiner(s): SMITH, CREIGHTON H
• Application Number:
  US08/127,026
• Time in Patent Office: 792 Days
• Field of Search: 52/782, 52/785, 52/790, 52/800, 52/807, 52/808, 52/7441.1, 52/745.18, 52/745.19, 428/116, 156/155, 156/173, 244/123, 244/124
• US Class Current: 52/793.11
• CPC Class Codes: B29C 70/342 using isostatic pressure
• CPC Class Codes: B29C 70/347 combined with compressing after the winding of lay-ups having a non-circular cross-section, e.g. flat spiral windings
• CPC Class Codes: B29D 24/004 the structure having vertical or oblique ribs
• CPC Class Codes: B29L 2024/006 multi-channelled
• CPC Class Codes: E04C 2/3405 spaced apart by profiled spacer sheets
• CPC Class Codes: E04C 2002/3477 spaced apart by tubular elements parallel to the sheets
• CPC Class Codes: Y10T 428/24149 Honeycomb-like

Abstract

A method for forming a structurally reinforced panel member, and the panel itself, is disclosed. The method requires disposing a first set of sheets of curable composite material atop a tool forming surface, wrapping a plurality of mandrels with a second set of sheets of curable composite material, arranging the wrapped mandrels in side by side relation atop the first set of sheets, curing the structural assembly, and then removing the mandrels from the cured structural assembly. In this way, the structural assembly includes interior channels obtained when the mandrels are removed from the cured structural panel member. The material portions defining the channels provide increased strength for the structural assembly.

Claims

1. A structurally reinforced panel member, comprising:

a first layer of cured composite material,

a plurality of discrete, elongated, tubular sections of cured composite material disposed side-by-side atop said layer,

a second layer of cured composite material disposed atop said plurality of tubular sections,

said first and second layer and said tubular sections of cured composite material being integrally formed as a unitary structure.

2. The structurally reinforced panel member of claim 1, wherein said tubular sections are arranged parallel to one another.

3. The structurally reinforced panel member of claim 2, wherein said tubular sections are disposed between said first and second layers.

4. The structurally reinforced panel member of claim 2, wherein at least two of said tubular sections are fluidly coupled to one another.

5. The structurally reinforced panel member of claim 1, wherein said discrete, elongated, tubular sections each comprise a substantially cylindrically shaped tube.

6. The structurally reinforced panel member of claim 4, and further including means for moving fluid through said tubular sections.

7. The structurally reinforced panel member of claim 6, wherein said fluid is a coolant.

8. The structurally reinforced panel member of claim 1, wherein one of said first or second layers of cured composite material is a vehicle skin which requires cooling, and said tubular sections define channels for carrying coolant to cool the aircraft skin.

9. The structurally reinforced panel member of claim 8, wherein the surfaces of said channels are sealed.

10. The structurally reinforced panel member of claim 9, wherein the material used for sealing the channel surfaces is Tedlar.

11. A method for forming a structurally reinforced panel member, comprising:

arranging a first plurality of sheets of curable composite material atop a tool forming surface to form a first uncured face sheet member,

wrapping a second plurality of sheets of curable composite material around each one of a plurality of tubular mandrels to form a plurality of wrapped tubular members,

arranging said wrapped tubular members in side by side relationship adjacent one another atop said first uncured face sheet member,

disposing a third plurality of sheets of curable composite material atop said wrapped tubular members to form a second uncured face sheet member, said first and second uncured face sheet members and said wrapped tubular members constituting a structural assembly,

curing said structural assembly to unitarily connect the face sheets with the tubular members, and

removing said mandrels from said cured structural assembly to yield a plurality of tubular elements arranged side by side between the two face sheets,

said cured structural assembly including interior channels obtained when said mandrels are removed from said cured tubular members, the walls of said tubular elements providing increased strength for said structural assembly.

12. The method of claim 11, and further including the step of removing said mandrels from said cured structural panel member by a mechanical process.

13. The method of claim 12, wherein said step of removing the mandrels from said structural panel member includes a step of chem-milling said mandrels.

14. The method of claim 12, further including the step of fluidly coupling selected ones of said tubular elements.