Composite stringer end cap
View Patent ↗An aircraft panel assembly including a panel, a number of open-ended composite stringers, and a number of stringer end caps. Each stringer end cap covers an open end of one of the stringers and includes a base, a vertically extending wall, and an overlap section. The base is bonded to the panel near the open end of the stringer. The vertically extending wall is angled upward from the base and includes an upper periphery. The overlap section extends horizontally from the upper periphery and is bonded to the stringer near the open end of the stringer.
1. A stringer end cap for at least partially covering an open end of a stringer of a panel, the stringer end cap comprising:
a vertically extending wall having an upper periphery and a lower end;
an overlap section extending horizontally from the upper periphery of the vertically extending wall, the overlap section being configured to extend over a portion of the stringer near the open end; and
a base extending horizontally from the lower end of the vertically extending wall, the base including two end tabs extending laterally from the lower ends of the overlap section and an intermediate section extending laterally between the two end tabs along the lower end of the vertically extending wall, the base being configured to be adjacent and bonded to the panel near the open end of the stringer,
the overlap section being configured to be bonded to the stringer near the open end.
2. The stringer end cap of claim 1 , wherein the vertically extending wall is angled in a direction of the overlap section.
3. The stringer end cap of claim 1 , wherein the overlap section has a constant width.
4. The stringer end cap of claim 1 , wherein the base has a chamfered edge.
5. The stringer end cap of claim 1 , wherein the vertically extending wall has a vertical profile corresponding to a shape of the stringer.
6. The stringer end cap of claim 5 , wherein the upper periphery of the vertically extending wall and the overlap section include a middle convex portion and left and right concave portions.
7. The stringer end cap of claim 1 , wherein the stringer end cap is configured to be co-cured onto the panel via discrete plies of thermoset composite material.
8. The stringer of claim 1 , wherein the stringer end cap is formed of a material selected from the group consisting of a thermoset material, a thermoplastic composite material, and a metallic material.
9. An aircraft panel assembly comprising:
a composite panel;
an open-ended stringer formed on the composite panel and filled with a core material; and
a stringer end cap at least partially covering the open end of the stringer, the stringer end cap comprising:
a vertically extending wall having an upper periphery and a lower end;
an overlap section extending horizontally from the upper periphery of the vertically extending wall, the overlap section being configured to extend over the stringer near the open end; and
a base extending horizontally from the lower end of the vertically extending wall, the base including two end tabs extending laterally from the lower ends of the overlap section and an intermediate section extending laterally between the two end tabs along the lower end of the vertically extending wall, the base being configured to be adjacent and bonded to the panel near the open end of the stringer,
the overlap section being configured to be bonded to the stringer near the open end.
10. The aircraft panel assembly of claim 9 , wherein the vertically extending wall is angled in a direction of the overlap section.
11. The aircraft panel assembly of claim 9 , wherein the overlap section has a constant width.
12. The aircraft panel assembly of claim 9 , wherein the base has a chamfered edge.
13. The aircraft panel assembly of claim 9 , wherein the vertically extending wall has a vertical profile corresponding to a shape of the stringer.
14. The aircraft panel assembly of claim 13 , wherein the upper periphery of the vertically extending wall and the overlap section include a middle convex portion and left and right concave portions.
15. The aircraft panel assembly of claim 9 , wherein the stringer end cap is co-cured onto the panel via discrete plies of thermoset composite material.
16. A stringer end cap for at least partially covering an open end of a stringer of a panel, the stringer end cap comprising:
a vertically extending wall having an upper periphery; and
an overlap section extending horizontally from the upper periphery of the vertically extending wall, the overlap section being configured to extend over a portion of the stringer near the open end,
the stringer end cap being configured to be co-cured onto the panel via discrete plies of thermoset composite material.