System for curing a patch
A method for curing a patch. The method includes generating the patch according to a negative of a scan of a scarf in a composite material. The method also includes pre-curing the patch.
1. A system comprising:
a computer configured to receive, from a rework facility, shape data from a scan of a scarf in an object comprising a composite material located at the rework facility; and
a lathe tool located at a patch generation facility remote from the rework facility, the late tool in communication with the computer, wherein the lathe tool and the computer are configured to:
create a mandrel based on the shape data, the mandrel comprising a mandrel shape that is a negative of the shape data.
2. The system of claim 1 , further comprising:
a layup tool disposed at the patch generation facility, the layup tool configured to place a composite layup on the mandrel; and
a heater disposed at the patch generation facility, the heater configured to form a pre-cured composite patch by heat-curing the composite layup.
3. The system of claim 2 , further comprising:
a vacuum bag disposed at the patch generation facility, the vacuum bag configured to be placed over the composite layup during heat-curing of the composite layup.
4. The system of claim 2 , further comprising:
a transport system configured to transport the pre-cured composite patch to the rework facility.
5. The system of claim 1 , further comprising:
a scanning tool, located at the rework facility, and configured to scan the scarf, the scanning tool further configured to generate the shape data.
6. The system of claim 1 , further comprising:
a scarf tool, located at the rework facility, and configured to prepare the scarf at an inconsistency on a composite surface of an aircraft.
7. The system of claim 6 , further comprising:
a metrology tool, located at the rework facility, and configured to establish, as part of preparing the scarf, a metrology point with respect to the scarf.
8. The system of claim 7 , further comprising:
a scanning tool, located at the rework facility, and configured to scan the scarf, the scanning tool further configured to generate the shape data.
9. The system of claim 8 , further comprising:
a communication device, located at the rework facility, and configured to transmit the shape data to the patch generation facility.
10. The system of claim 9 , further comprising:
a patch generation tool, located at the patch generation facility, configured to generate a composite patch according to the shape data.
11. The system of claim 10 , further comprising:
wherein the patch generation tool is further configured to generate a counter metrology point on the composite patch.
12. The system of claim 11 , further comprising:
a curing tool, located at the patch generation facility, and configured to pre-cure the composite patch at a first temperature to form a pre-cured composite patch.
13. The system of claim 12 , wherein pre-curing comprises fully curing the composite patch.
14. The system of claim 13 , further comprising:
a transport system configured to transport the pre-cured composite patch to the rework facility.
15. The system of claim 14 , further comprising:
an adhesive application tool configured to apply an adhesive to the scarf.
16. The system of claim 15 , further comprising:
a patch application tool configured to apply the pre-cured composite patch to the adhesive on the scarf, including matching the counter metrology point to the metrology point.
17. The system of claim 16 , further comprising:
a curing tool configured to cure, after applying the pre-cured composite patch to the adhesive, the pre-cured composite patch at a second temperature sufficient to cure the adhesive.
18. The system of claim 17 , wherein the second temperature is less than the first temperature.
19. The system of claim 17 , further comprising:
wherein the first temperature comprises above about 350 degrees Fahrenheit and the second temperature comprises below about 250 degrees Fahrenheit.
20. The system of claim 1 , wherein the mandrel comprises a carbon foam material, and wherein the system further comprises:
a sealing tool configured to seal a surface of the carbon foam material.