Method for curing a patch

1. A method comprising:

preparing, at a first facility, a scarf at an inconsistency on a composite surface of an aircraft, wherein preparing includes establishing a metrology point with respect to the scarf;

scanning, at the first facility, the scarf and the metrology point to generate shape data of a shape of the scarf and of a location of the metrology point;

transmitting the shape data to a second facility remote from the first facility;

generating, at the second facility, a composite patch according to a negative of the shape of the scarf, wherein generating further comprises generating a counter metrology point on the composite patch;

pre-curing, at the second facility, the composite patch at a first temperature to form a pre-cured composite patch, wherein pre-curing the composite patch comprises fully curing the composite patch;

transporting the pre-cured composite patch to the first facility;

applying an adhesive to the scarf;

applying the pre-cured composite patch to the adhesive on the scarf, including matching the counter metrology point to the metrology point; and

curing, thereafter, the pre-cured composite patch at a second temperature sufficient to cure the adhesive, wherein the second temperature is less than the first temperature.

2. The method of claim 1 , wherein the first facility comprises a rework facility and the second facility comprises a patch generation facility.

3. The method of claim 1 , wherein the first temperature comprises above about 350 degrees Fahrenheit and the second temperature comprises below about 250 degrees Fahrenheit.

4. The method of claim 1 , wherein pre-curing the composite patch comprises vacuum bagging the composite patch and heating the composite patch while inside a vacuum bag.

5. The method of claim 1 , wherein the counter metrology point comprises a plurality of counter metrology points.

6. The method of claim 1 , further comprising:

machining, prior to pre-curing the composite patch, a carbon foam material to form a mandrel having a shape conforming to the negative of the shape data.

7. The method of claim 6 , further comprising:

sealing, after machining, a surface of the carbon foam material.

8. The method of claim 6 , further comprising:

laying up, prior to pre-curing the composite patch, at least one composite ply on the mandrel,

wherein pre-curing comprises pre-curing the at least one composite ply, and wherein the at least one composite ply is the composite patch.

9. The method of claim 1 , wherein generating comprises generating a size and dimensions of the composite patch to a size and dimensions of the scarf.

10. The method of claim 1 , wherein transmitting the shape data comprises transmitting the shape data to a computer, and wherein the method further comprises:

controlling, using the computer, a lathe tool to generate the composite patch.

11. The method of claim 10 , wherein the lathe tool cuts a block of carbon foam into a negative of the shape data to generate a shaped carbon foam as part of generating the composite patch.

12. The method of claim 11 , wherein a layup tool lays up a plurality of composite plies onto the shaped carbon foam as part of generating the composite patch.

13. The method of claim 12 , further comprising:

trimming the plurality of composite plies to generate the composite patch, wherein trimming comprises leaving excess composite ply material on the composite patch, and

wherein generating the counter metrology point comprises applying the counter metrology point to the excess composite ply material.

14. A method comprising:

preparing, at a rework facility, a scarf at an inconsistency on a composite surface of an aircraft, wherein preparing includes establishing a metrology point with respect to the scarf;

scanning, at the rework facility, the scarf and the metrology point to generate shape data of a shape of the scarf and of a location of the metrology point;

transmitting, from the rework facility, the shape data to a patch generation facility remote from the rework facility;

receiving, at the rework facility from the patch generation facility, a pre-cured composite patch generated according to a negative of the scan, wherein the pre-cured composite patch comprises a counter metrology point;

applying an adhesive to the scarf;

applying the pre-cured composite patch to the adhesive on the scarf, including matching the counter metrology point to the metrology point; and

curing, thereafter, the pre-cured composite patch at a second temperature sufficient to cure the adhesive, wherein the second temperature is less than a first temperature used to cure the pre-cured composite patch.

15. The method of claim 14 , wherein preparing comprises removing composite material in an area of the inconsistency.

16. The method of claim 14 , wherein:

the first temperature comprises above about 350 degrees Fahrenheit; and

the second temperature comprises above about 250 degrees Fahrenheit.

17. The method of claim 14 , further comprising:

applying, before applying the pre-cured composite patch to the scarf, a scrim between the adhesive and the pre-cured composite patch.

18. The method of claim 14 , wherein generating the shape data comprises:

data describing three-dimensional properties of the scarf.

19. The method of claim 18 , wherein the three-dimensional properties comprises a topology of the scarf, distance measurements of the scarf, and composition measurements of the scarf.

20. The method of claim 19 , wherein the shape data further comprises a picture of the scarf.