Stringer with plank ply and skin construction for aircraft

1. A composite assembly, comprising:

a composite skin of an aircraft comprising a plurality of composite plies;

a composite stringer secured to the composite skin, wherein:

a first composite plank ply is positioned between a first pair of composite plies of the plurality of composite plies of the composite skin;

the first composite plank ply has a width dimension less than a width dimension of the plurality of composite plies of the composite skin;

a second composite plank ply positioned within the plurality of composite plies of the composite skin;

the second composite plank ply has the width dimension of the first plank ply; and

the first composite plank ply and the second composite plank ply extend along a length of a wing of the aircraft, with the first composite plank ply and the second composite plank each comprising a plurality of unidirectional fibers which extend along the length of the wing of the aircraft; or

the first composite plank ply and the second composite plank ply extend along a central length of a fuselage of the aircraft, with the first composite plank ply and the second composite plank ply each comprising a plurality of unidirectional fibers which extend along the central length of the fuselage of the aircraft.

2. The composite assembly of claim 1 , wherein the composite stringer comprises one of an I-stringer, hat stringer, J-stringer, blade stringer or Z-stringer.

3. The composite assembly of claim 1 , wherein the composite skin extends along a length and a width of a wing of an aircraft.

4. The composite assembly of claim 3 , wherein the composite stringer extends along the length of the wing of the aircraft.

5. The composite assembly of claim 1 , further comprising the second composite plank ply is positioned between a second pair of composite plies of the plurality of composite plies of the composite skin.

6. The composite assembly of claim 1 , further includes

a third composite plank ply which has the width dimension of the first and second composite plank plies wherein the second plank ply is positioned between the first and the third composite plank plies.

7. The composite assembly of claim 5 , wherein the first and second composite plank plies interleave with the first and second pair of composite plies of the plurality of composite plies of the composite skin of the wing, respectively.

8. The composite assembly of claim 5 , wherein:

the first and second pair of composite plies of the plurality of composite plies of the composite skin of the wing are positioned within the first half of the stack of the plurality of composite plies of the composite skin of the wing; and

the first half of the stack of the plurality of composite plies of the composite skin of the wing is positioned on an interior side of the skin of the aircraft opposing an exterior side of the skin of the aircraft.

9. The composite assembly of claim 1 , wherein the composite skin extends along a central length direction of the fuselage and in a curvilinear direction about the central length of the fuselage of the aircraft.

10. The composite assembly of claim 9 , further comprising a second composite plank ply positioned between a second pair of composite plies of the plurality of composite plies of the composite skin of the fuselage.

11. The composite assembly of claim 10 wherein, the first and second composite plank plies each has the same width dimension which extends in the curvilinear direction about the central length of the fuselage.

12. The composite assembly of claim 10 wherein, the first and second composite plank plies each has a different width dimension which extends in the curvilinear direction about the central length of the fuselage.

13. The composite assembly of claim 10 , wherein the first and second composite plank plies interleave with the first and second pair of composite plies, respectively, of the plurality of composite plies of the composite skin of the fuselage.

14. The composite assembly of claim 10 wherein:

the first and second pair of composite plies of the plurality of plies of the composite skin of the fuselage are positioned within the first half of the stack of the plurality of plies of the composite skin of the fuselage; and

the first half of the stack is positioned on an interior side of the skin of the fuselage of the aircraft opposing an exterior side of the skin of the fuselage of the aircraft.

15. A method for assembling a composite assembly, comprising the steps of:

laying up a plurality of composite plies for a composite skin of an aircraft;

positioning a first composite plank ply between a first pair of composite plies of the plurality of plies of the composite skin wherein the first composite plank ply has a width dimension less than a width dimension of the plurality of composite plies of the composite skin;

positioning a second composite plank ply within the plurality of composite plies for the composite skin, wherein the second composite plank ply has the width dimension of the first composite plank ply, wherein:

the first composite plank ply and the second composite plank ply extend along a length of a wing of the aircraft, with the first composite plank ply and the second composite plank ply each comprising a plurality of unidirectional fibers which extend along the length of the wing of the aircraft; or

the first composite plank ply and the second composite plank ply extend along a central length of a fuselage of the aircraft, with the first composite plank ply and the second composite plank ply each comprising a plurality of unidirectional fibers which extend along the central length of the fuselage of the aircraft; and

laying up a composite stringer for securement to the composite skin.

16. The composite assembly of claim 8 , wherein a second half of the stack is positioned adjacent to an exterior of the aircraft and has an absence of a composite plank ply positioned within the second half of the stack of the plurality of composite plies of the composite skin of the wing.

17. The composite assembly of claim 14 , wherein a second half of the stack positioned adjacent to an exterior of the aircraft has an absence of a composite plank ply positioned within the second half of the stack of the plurality of composite plies of the composite skin of the fuselage.

18. The composite assembly of claim 1 , wherein at least a portion of the composite stringer is positioned in overlying relationship with the first composite plank ply.

19. The method of assembling of claim 15 , wherein the first composite plank ply and the first pair of composite plies are positioned within a first half of a stack of the plurality of composite plies of the composite skin positioned adjacent an interior of an aircraft with an absence of a composite plank ply within a second half of the stack positioned adjacent to an exterior of the aircraft.

20. The method of assembling of claim 15 , wherein at least a portion of the composite stringer is positioned in overlying relationship with the first composite plank ply.