Surface area of fixtures

1. A system, configured to mill an aircraft body part, such that the system comprises:

a forming fixture configured to form the aircraft body part: and

a milling fixture that comprises:

a first portion, such that the first portion comprises a first surface that comprises:

a shape configured as a receptacle to contact a complementary shape of a first portion of a contoured surface of the aircraft body part and support the aircraft body part in a milling operation, such that the first surface comprises a number of through-holes through which the milling operation may be performed on a side, that faces the milling fixture, of the aircraft body part within the milling fixture; and

a vacuum port configured to secure the aircraft body part to the first surface; and

a second portion of the milling fixture, such that the second portion comprises:

a perimeter that lies within a perimeter of the first portion;

a second surface configured to be recessed away from contact with a second portion of the contoured surface of the aircraft body part during the milling operation; and

a hollow portion.

2. The system of claim 1 , wherein the milling fixture further comprises:

a number of vacuum ports disposed within the first surface of the milling fixture, wherein the second portion of the milling fixture does not include any vacuum ports.

3. The system of claim 2 , wherein the milling fixture further comprises:

a vacuum generator connected to the number of vacuum ports disposed within the first surface of the milling fixture, wherein the vacuum generator is configured to apply a vacuum to the number of vacuum ports and hold the first portion of the contoured surface of the aircraft body part against the first surface of the milling fixture.

4. The system of claim 2 , wherein

the contoured surface of the aircraft body part comprises a form complementary to a forming surface of the forming fixture.

5. The system of claim 1 , wherein the second surface of the contoured surface is recessed from designed parameters of the aircraft body part by a value greater than a tolerance for a manufacturing process utilized to manufacture the aircraft body part, such that the second portion of the aircraft body part does not contact the second surface of the milling fixture during the milling operation.

6. The system of claim 4 , wherein:

the forming fixture comprises the forming surface configured to contact the aircraft body part during a forming operation, wherein the forming surface defines an outer mold line for the aircraft body part; and

wherein a first surface area of the first surface of the milling fixture comprises a value less than a second surface area of the forming surface of the forming fixture.

7. The system of claim 6 , wherein a curvature of the first surface of the milling fixture is substantially the same as a respective curvature of a corresponding first portion of the forming surface of the forming fixture.

8. The system of claim 7 , wherein the second surface of the milling fixture differs from a respective second portion of the forming surface of the forming fixture.

9. The system of claim 8 , wherein a difference between the second surface of the milling fixture and the respective second portion of the forming surface comprises a value greater than a tolerance for a manufacturing process utilized to manufacture the aircraft body part, such that the second portion of the aircraft body part does not contact the second surface of the milling fixture during the milling operation.

10. The system of claim 1 , wherein the second surface of the milling fixture differs from a forming surface of the forming fixture, for the aircraft body part, by at least one of: a recessed portion of the second surface, or the hollow portion.

11. The system of claim 1 , wherein a surface area of the milling fixture is sufficient to maintain structural stability of the milling fixture.

12. The system of claim 1 , wherein the first surface of the milling fixture is sufficient to support the aircraft body part without undesirable vibration during the milling operation.

13. The system of claim 1 , wherein support of the aircraft body part by the second surface is not required for milling operation.

14. A milling system that comprises:

a forming fixture for an aircraft body part; and

a milling fixture that comprises:

a tool that comprises:

a support surface configured as a receptacle to conform to and support the aircraft body part during a milling operation on the aircraft body part;

a recessed surface that comprises a hollow portion and a perimeter that lies within a perimeter of the support surface;

a number of through-holes, disposed within the support surface, configured to provide alignment and access for the milling operation on a side, that faces the milling fixture, of the aircraft body part within the milling fixture; and

a number of vacuum ports disposed within the support surface and configured to contact and secure the aircraft body part to the support surface.

15. The milling system of claim 14 , wherein the milling fixture further comprises:

a vacuum generator connected to the number of vacuum ports disposed within the support surface; and

the vacuum generator configured to apply a vacuum to the number of vacuum ports and hold a first portion of the aircraft body part against the support surface of the tool.

16. The milling system of claim 15 , wherein the recessed surface is recessed from a second portion of the aircraft body part a value greater than a maximum growth of the aircraft body part.

17. The milling system of claim 14 , wherein the milling fixture further comprises a surface area sufficient to maintain structural stability of the milling fixture.

18. The milling system of claim 14 , wherein the milling fixture further comprises the support surface configured to support the aircraft body part without undesirable vibration during the milling operation.

19. A milling system that comprises:

a forming fixture that comprises a forming surface for an aircraft body part;

a milling fixture that comprises:

a surface configured as a receptacle that conforms to and supports the aircraft body part during a milling operation, such that the surface comprises:

a number of through-holes configured to provide alignment and access for the milling operation on a side, that faces the milling fixture, of the aircraft body part, such that the surface differs from the forming surface, of the forming fixture for the aircraft body part, by at least one of: a recessed portion that comprises a perimeter that lies within a perimeter of the forming surface, or a hollow portion, configured to allow access to the side, facing the milling fixture, of the aircraft body part within the milling fixture; and

a vacuum port configured to secure the aircraft body part to the surface.

20. The milling system of claim 19 , wherein the surface is sufficient to support the aircraft body part without inconsistencies forming in the aircraft body part during the milling operation.

21. The milling system of claim 19 , wherein a mass of the milling fixture is sufficient to maintain structural stability of the milling fixture.