Stringer stiffened composite panels having improved pull-off strength
Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
1. A stringer comprising:
a first surface;
a second surface located opposite the first surface, the second surface to be coupled to a composite structure of an aircraft;
an edge extending from the second surface toward the first surface, the edge having a thickness of at least 0.10 inches; and
a chamfer extending from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
2. The stringer of claim 1 , wherein the angle is approximately fifteen degrees.
3. The stringer of claim 1 , wherein the second surface is parallel to the first surface, and the edge is perpendicular to the second surface.
4. The stringer of claim 1 , further comprising:
a first ply forming the first surface and the chamfer;
a second ply forming the second surface and at least a portion of the edge; and
a plurality of additional plies located between the first ply and the second ply, respective ones of the additional plies being laterally staggered relative to one or more successively-layered ones of the additional plies.
5. The stringer of claim 4 , wherein the first ply has a first lateral extent, wherein the second ply has a second lateral extent, and wherein the additional plies include:
a third ply located between the first play and the second ply, the third ply having a third lateral extent less than the first lateral extent and less than the second lateral extent; and
a fourth ply located between the third ply and the second ply, the fourth ply having a fourth lateral extent less than the third lateral extent.
6. The stringer of claim 5 , wherein the additional plies further include a fifth ply located between the fourth ply and the second ply, the fifth ply having a fifth lateral extent greater than the fourth lateral extent, less than the first lateral extent, and less than the second lateral extent.
7. The stringer of claim 6 , wherein the fifth lateral extent is less than the third lateral extent.
8. The stringer of claim 5 , wherein the additional plies further include a fifth ply located between the fourth ply and the second ply, the fifth ply having a fifth lateral extent less than the fourth lateral extent.
9. The stringer of claim 1 , further comprising a stiffener segment, the stiffener segment including the first surface, the second surface, the edge, and the chamfer.
10. An apparatus comprising:
a composite structure of an aircraft;
a stringer coupled to the composite structure, the stringer comprising:
a first surface;
a second surface located opposite the first surface and coupled to the composite structure;
an edge extending from the second surface toward the first surface, the edge having a thickness of at least 0.10 inches; and
a chamfer extending from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
11. The apparatus of claim 10 , wherein the angle is approximately fifteen degrees.
12. The apparatus of claim 10 , wherein the second surface is parallel to the first surface, and the edge is perpendicular to the second surface.
13. The apparatus of claim 10 , wherein the stringer further comprises:
a first ply forming the first surface and the chamfer;
a second ply forming the second surface and at least a portion of the edge; and
a plurality of additional plies located between the first ply and the second ply, respective ones of the additional plies being laterally staggered relative to one or more successively-layered ones of the additional plies.
14. The apparatus of claim 10 , wherein the stringer further comprises a stiffener segment, the stiffener segment including the first surface, the second surface, the edge, and the chamfer.
15. The apparatus of claim 14 , wherein the angle and the thickness are configured to increase a pull-off load of the stiffener segment in relation to the composite structure.
16. The apparatus of claim 14 , wherein the angle and the thickness are configured to reduce a peeling moment of the stiffener segment in relation to the composite structure.
17. A method comprising coupling a stringer to a composite structure of an aircraft, the stringer including:
a first surface;
a second surface located opposite the first surface, the second surface to be coupled to the composite structure;
an edge extending from the second surface toward the first surface, the edge having a thickness of at least 0.10 inches; and
a chamfer extending from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.
18. The method of claim 17 , further comprising:
forming the chamfer; and
curing the stringer subsequent to the chamfer being formed and prior to the stringer being coupled to the composite structure.
19. The method of claim 17 , further comprising:
forming the chamfer; and
co-curing the stringer and the composite structure subsequent to the chamfer being formed and subsequent to the stringer being coupled to the composite structure.
20. The method of claim 17 , wherein the stringer further includes:
a first ply forming the first surface and the chamfer;
a second ply forming the second surface and at least a portion of the edge; and
a plurality of additional plies located between the first ply and the second ply, respective ones of the additional plies being laterally staggered relative to one or more successively-layered ones of the additional plies.