Composite structural element and torsion box

Patent metadata

Field	Value
Publication number	US-9827737-B2
Application number	US-201514627255-A
Country	US
Kind code	B2
Filing date	Feb 20, 2015
Priority date	Feb 21, 2014
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

This relates to a composite structural element, in particular a rib or a spar, specifically for use in a torsion box of an aircraft structure such as a vertical tailplane, wherein the structural element defines a coordinate system with a first axis “a” wherein the structural element comprises a substantially planar main section defining a coordinate system with a first axis “a” extending along the longitudinal axis “L” of the structural element and a second axis “b” extending perpendicular to said longitudinal axis “L” within the planar main section and defining an angle of +90° with the first axis “a”, wherein the structural element contains a lay-up of single plies consisting of a fiber-reinforced composite material with a substantially unidirectional fiber orientation.

First claim

What is claimed is:

1. A composite structural torsion box rib or torsion box spar comprising:
a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within a planar main section and defining an angle of +90° with the first axis; wherein the main section comprises a lay-up of single plies comprised of a fiber-reinforced composite material with a substantially unidirectional fiber orientation, wherein the lay-up comprises at least one pair of a first and a second ply which are arranged in the lay-up such that the direction of fiber orientation extends in the coordinate system at an angle in the range of substantially −17° to −23° for the first ply and substantially +37° to +43° for the second ply; and wherein the first ply is directly adjacent to the second ply.

2. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the direction of fiber orientation of the first ply extends in the coordinate system at an angle of approximately −20°.

3. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the direction of fiber orientation of the second ply extends in the coordinate system at an angle of approximately +40°.

4. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the first ply forms an outermost layer of the lay-up.

5. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up comprises at least part of a web of the structural element.

6. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the structural element is configured as a unitary member comprising the lay-up.

7. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up further comprises at least one ply with a direction of fiber orientation extending in the coordinate system at an angle in the range of substantially −3° to +3°.

8. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up further comprises at least one ply with a direction of fiber orientation extending in the coordinate system at an angle in the range of substantially +87° to +93°.

9. The composite structural torsion box rib or torsion box spar of claim 1 , further comprising at least two stiffeners extending substantially in a direction of +90° in the coordinate system along the planar main section of the structural element.

10. The composite structural torsion box rib or torsion box spar of claim 9 , wherein the area between the two stiffeners has an aspect ratio as defined by the ratio of its longest and shortest extension of not less than 1.5.

11. The composite structural torsion box rib or torsion box spar of claim 9 , wherein area between the two stiffeners has an aspect ratio as defined by the ratio of its longest and shortest extension of not more than 4.0.

12. The composite structural torsion box rib or torsion box spar of claim 10 , wherein area between the two stiffeners has an aspect ratio as defined by the ratio of its longest and shortest extension of not more than 4.0.

13. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up does not comprise more than 32 plies.

14. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up does not exceed a thickness of 8 mm.

15. The composite structural torsion box rib or torsion box spar of claim 1 , wherein the lay-up comprises a first pair of the first and the second ply and a second pair of the first and the second ply, wherein the first and second pair are symmetrically arranged within the lay-up about a geometric center plane of the lay-up.

16. A composite structural torsion box rib or torsion box spar comprising:
a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within a planar main section and defining an angle of +90° with the first axis; wherein the main section comprises a lay-up of single plies comprised of a fiber-reinforced composite material with a substantially unidirectional fiber orientation, wherein the lay-up comprises at least one pair of a first and a second ply which are arranged in the lay-up such that the direction of fiber orientation extends in the coordinate system at an angle in the range of substantially −17° to −23° for the first ply and substantially +37° to +43° for the second ply, wherein the lay-up comprises a first pair of the first and the second ply and a second pair of the first and the second ply, wherein the first and second pair are symmetrically arranged within the lay-up about a geometric center plane of the lay-up, and wherein in each pair of plies, the first ply is directly adjacent the second ply.

17. An aircraft structural torsion box comprising:
a composite structural element having a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within a planar main section and defining an angle of +90° with the first axis, wherein the main section is formed from a lay-up of single plies comprised of a fiber-reinforced composite material with a substantially unidirectional fiber orientation, wherein the lay-up comprises at least one pair of a first and a second ply which are arranged in the lay-up such that the direction of fiber orientation extends in the coordinate system at an angle in the range of substantially −17° to −23° for the first ply and substantially +37° to +43° for the second ply; and wherein the first ply is directly adjacent to the second ply.

18. The aircraft structural torsion box of claim 17 wherein the lay-up comprises a first pair of the first and the second ply and a second pair of the first and the second ply, wherein the first and second pair are symmetrically arranged within the lay-up about a geometric center plane of the lay-up.

Assignees

• Airbus Operations Gmbh

Inventors

• Selyugin Sergey
• Balzer Jan-Ronald

Classifications

• B32B5/26 Primary

  another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} · CPC title

• Y10T428/24116

  Oblique to direction of web · CPC title

• B32B2307/542

  Shear strength · CPC title

• B32B2307/544

  Torsion strength; Torsion stiffness · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title