Tubular composite strut having internal stiffening and method for making the same

Patent metadata

Field	Value
Publication number	US-10464656-B2
Application number	US-201414500480-A
Country	US
Kind code	B2
Filing date	Sep 29, 2014
Priority date	Nov 3, 2011
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A system and method for forming a strut. A strut comprises a laminated composite tube having a substantially hollow interior and a pair of longitudinal stiffeners attached to opposite sides of the laminated composite tube.

First claim

What is claimed is:

1. A strut comprising:
a laminated composite tube having a substantially hollow interior; and
a pair of substantially hollow longitudinal stiffeners attached to the laminated composite tube only at diametrically opposite locations on the laminated composite tube, wherein each of the longitudinal stiffeners is trapezoidal in cross sectional shape.

2. The strut of claim 1 , wherein the pair of longitudinal stiffeners is located within the substantially hollow interior of the laminated composite tube.

3. The strut of claim 1 , further comprising a fitting on at least one end of the laminated composite tube that attaches to a structure.

4. The strut of claim 3 , wherein the fitting includes an opening having an axis and that receives an elongate pin to connect the fitting to the structure.

5. The strut of claim 4 , wherein each stiffener of the pair of longitudinal stiffeners is substantially symmetric about a plane perpendicular to the axis of the opening.

6. The strut of claim 3 , wherein:
the fitting includes a plurality of outer steps; and
the laminated composite tube includes groups of plies respectively overlapping the outer steps, wherein the outer steps and the groups of plies form a single stepped shear joint.

7. The strut of claim 3 , wherein the fitting is metal and is attached to the laminated composite tube by a single shear joint.

8. The strut of claim 1 , further comprising:
a second pair of stiffeners within the substantially hollow interior of the laminated composite tube and attached to the laminated composite tube.

9. The strut of claim 8 , wherein:
the second pair of stiffeners is substantially symmetric about a plane substantially parallel to a central axis of an opening of a fitting on one end of the laminated composite tube that attaches to a structure; and
each of the second pair of stiffeners is trapezoidal in cross sectional shape.

10. The strut of claim 1 , wherein each of the pair of longitudinal stiffeners is a laminated composite and is cocured with the laminated composite tube.

11. A strut for transferring loads in compression or tension, comprising:
an elongate tube having a wall formed of multiple laminated composite plies;
a fitting on each end of the elongate tube that attaches the elongate tube to a structure;
a single shear bond joint between each fitting and the elongate tube; and
substantially hollow composite stiffeners attached only to the wall of the elongate tube at diametrically opposite locations on the elongate tube for stiffening the elongate tube, wherein each of the longitudinal stiffeners is trapezoidal in cross sectional shape.

12. The strut of claim 11 , wherein:
each fitting attaches the elongate tube to the structure with a pin and transfers loads to the tube about a longitudinal axis of each pin; and
the composite stiffeners are located inside the elongate tube and include a first pair of opposing stiffeners aligned along an axis substantially perpendicular to the longitudinal axis of each pin.

13. The strut of claim 12 , wherein the composite stiffeners include a second pair of opposing stiffeners aligned along an axis extending substantially parallel to the longitudinal axis of each pin.

14. The strut of claim 11 , wherein:
each fitting includes an outer wall having a plurality of outer steps; and
the elongate tube includes groups of plies respectively overlapping the outer steps and forming a single stepped shear joint.

15. The strut of claim 11 , wherein each of the composite stiffeners is a laminated composite and is cocured with the elongate tube.

16. The strut of claim 11 , wherein each of the composite stiffeners extends substantially an entire length between each fitting.

17. An aircraft strut for transferring loads in compression or tension, comprising:
an elongate tube having a wall formed of multiple laminated composite plies;
a fitting on each end of the tube adapted to attach the elongate tube to a structure with a pin;
a single stepped shear bond joint between each of the fittings and the elongate tube; and
composite stiffeners within the elongate tube attached only to the wall for stiffening the elongate tube, and wherein:
each fitting transfers loads to the elongate tube about a longitudinal axis of the pin, and the composite stiffeners include at least a first pair of substantially hollow opposing stiffeners aligned along an axis substantially perpendicular to the axis of the pin;
each of the composite stiffeners has a substantially trapezoidal cross sectional shape;
the composite stiffeners further include a second pair of opposing stiffeners aligned along an axis extending substantially parallel to the pin axe;
each fitting includes an outer wall having a plurality of outer steps, and an inner wall; and
the elongate tube includes groups of plies respectively overlapping the outer steps.

Assignees

• Boeing Co

Inventors

• Stewart Samuel Ray

Classifications

• B29L2031/748

  Machines or parts thereof not otherwise provided for (conveyor belts B29L2031/7092; driving belts B29L2031/7094; bearings B29L2031/04) · CPC title

• B29C53/822

  Single use mandrels, e.g. destructible, becoming part of the wound articles (B29C53/825 takes precedence) · CPC title

• B29C53/587

  having a non-uniform wall-structure, e.g. with inserts, perforations, locally concentrated reinforcements · CPC title

• B29C53/585

  the cross-section varying along their axis, e.g. tapered, with ribs, or threads, with socket-ends · CPC title

• F16C7/026

  made of fibre reinforced resin · CPC title