Method for forming a composite structure
Methods and systems are provided for fabricating a composite structure. In one example, the composite structure may include a honeycomb core sandwiched between face sheets. An edge of the honeycomb core may be abraded and a top face sheet may be perforated. As such, a likelihood of delamination of the composite structure during a curing step may be reduced.
1. A method for forming a composite structure for an aircraft, comprising:
abrading an upper edge of a honeycomb core to form a rough, uneven edge of the honeycomb core;
coupling the honeycomb core to a top face sheet and a bottom face sheet to form a sandwich structure, wherein coupling the honeycomb core to the top face sheet includes forming pathways between the upper edge and the top face sheet allowing air to flow between cells of the honeycomb core; and
processing the sandwich structure to form a bonded structure.
2. The method of claim 1 , wherein abrading the upper edge of the honeycomb core includes one of abrading the upper edge with a sanding tool coupled to a 3-axis CNC and abrading the upper edge manually with sand paper.
3. The method of claim 1 , wherein processing the sandwich structure includes perforating the top face sheet with a puncturing tool.
4. The method of claim 1 , further comprising forming and maintaining a reduced pressure in the honeycomb core during the processing.
5. A method for forming a composite structure for an aircraft, comprising:
abrading an upper edge of a honeycomb core to form an uneven surface;
coupling the honeycomb core to a top face sheet and a bottom face sheet to form a sandwich structure;
perforating the top face sheet to fluidically couple air inside the sandwich structure to air outside of the sandwich structure; and
processing the sandwich structure to form a bonded structure, wherein processing the sandwich structure includes placing the sandwich structure under vacuum and heating the sandwich structure.
6. The method of claim 5 , wherein the vacuum is applied before the heating.
7. The method of claim 5 , wherein the honeycomb core has an untreated bottom edge.
8. The method of claim 5 , wherein placing the sandwich structure under vacuum and heating the sandwich structure includes placing the sandwich structure in an oven to cure resin in the top and bottom face sheets.
9. The method of claim 5 , wherein perforating the top face sheet includes positioning at least one perforation of a plurality of perforations directly above each cell of the honeycomb core.
10. The method of claim 5 , wherein perforating the top face sheet includes puncturing the top sheet using a puncturing tool and wherein the puncturing tool includes pins of a length sufficient to puncture entirely through a thickness of the top face sheet and a thickness of an adhesive coupling the honeycomb core to the top face sheet.
11. The method of claim 5 , wherein perforating the top face sheet further includes adjusting an amount of air aspirated from the honeycomb core by varying a number of perforations formed in the top face sheet.
12. The method of claim 5 , wherein perforating the top face sheet further includes perforating the top face sheet in a low pressure environment prior to placing the sandwich structure under vacuum.
13. The method of claim 5 , wherein abrading the upper edge of the honeycomb core includes treating the upper edge with one of machine sanding and manual sanding.
14. A method for forming a composite structure for an airplane fuselage, comprising:
abrading an upper edge of a honeycomb core to form an uneven surface;
coupling the upper edge of the honeycomb core to a top face sheet to form pathways between the uneven surface of the upper edge of the honeycomb core and the top face sheet;
coupling a bottom sheet to the honeycomb core to form a sandwich structure;
exposing the sandwich structure to a vacuum where air flows along the pathways reducing the internal pressure of the honeycomb core; and
heating the sandwich structure while maintaining a low internal pressure in the honeycomb core.
15. The method of claim 14 , further comprising applying an adhesive between the honeycomb core and the top face sheet and bottom face sheet.
16. The method of claim 14 , wherein a first portion of the upper edge of the honeycomb core is reduced by at least 0.015 inches from a second portion of the upper edge of the honeycomb core.
17. The method of claim 14 , further comprising perforating the top face sheet prior to the heating.
18. The method of claim 14 , further comprising sealing the sandwich structure.