Nacelle inlet lip skin with pad-up defining a developable surface having parallel ruling lines

1. A nacelle inlet for a turbo-fan engine for an aircraft, the nacelle inlet comprising:

a lip skin comprising

a first pad-up having a first mating surface, wherein the first pad-up is defined by an area of increased thickness of the lip skin relative to thicknesses of adjacent areas of the lip skin;

a second pad-up defining a fourth mating surface, said fourth mating surface machined as a developable surface;

an inner barrel including a forward flange having a second mating surface;

a bulkhead comprising

a third mating surface disposed opposite the first and second mating surfaces, the lip skin and the inner barrel attached to one another using the bulkhead;

a spanning member; and

an angle flange having a fifth mating surface substantially linear at all points around the bulkhead to interface with the fourth mating surface, said angle flange having a first leg;

wherein the first, second and third mating surfaces are each machined to be approximate developable surfaces with the first and second mating surface having parallel ruling lines with the third mating surface, said angle flange adapted for mating of the fourth and fifth mating surfaces prior to engagement between the first leg of the angle flange and the spanning member by a plurality of fasteners,

wherein sliding engagement of the first, second and third mating surfaces positions the spanning member, and

wherein sliding engagement of the fourth and fifth mating surfaces joins the first leg and the spanning member with greater or lesser overlap of the first leg and the spanning member determined by position of the first and third mating surfaces.

2. The nacelle inlet of claim 1 , further comprising one or more shims between the first and third mating surfaces and/or between the second and third mating surfaces, each shim having a constant thickness.

3. The nacelle inlet of claim 1 , wherein the fourth mating surface of the second pad-up is a ruled surface, the lip skin having a contoured exterior surface opposite the fourth mating surface.

4. The nacelle inlet of claim 1 , wherein the lip skin and bulkhead are slideable relative to one another along a forward-aft direction without distortion of an outer contour of the lip skin.

5. The nacelle inlet of claim 1 , wherein the lip skin and/or the inner barrel comprise a plurality of separably connected circumferential segments.

6. The nacelle inlet of claim 1 , wherein the lip skin further comprises at least one circumferential stiffener.

7. The nacelle inlet of claim 1 , wherein the lip skin and/or at least a portion of the bulkhead is formed of aluminum or titanium, and the inner barrel is formed of aluminum or composite materials.

8. A nacelle inlet for an aircraft engine, the nacelle inlet comprising:

a lip skin comprising

a contoured outer surface;

a first pad-up having a first mating surface machined as a first ruled surface, wherein the first pad-up is defined by an area of increased thickness of the lip skin relative to the thicknesses of adjacent areas of the lip skin; and

a second pad-up defining a fourth mating surface, said fourth mating surface machined as a developable surface;

an inner barrel including a first flange having a second mating surface machined as a second ruled surface;

a bulkhead comprising

a spanning member;

an angle flange having a fifth mating surface substantially linear at all points around the bulkhead to interface with the fourth mating surface, said angle flange having a first leg connected to the spanning member said angle flange having a second leg connected to the second pad-up; and

a second flange having a third mating surface machined as a third ruled surface, the third ruled surface extending over at least a portion of the ruled surfaces of the first ruled surface and the second ruled surface, the second flange joining the lip skin to the inner barrel wherein the first and second mating surfaces are machined to have parallel ruling lines with the third mating surface;

wherein said angle flange is adapted for mating of the fourth and the fifth mating surfaces prior to engagement between the first leg of the angle flange and the spanning member by a plurality of fasteners,

wherein sliding engagement of the first, second and third mating surfaces positions the spanning member, and

wherein sliding engagement of the fourth and fifth mating surfaces joins the first leg and the spanning member with greater or lesser overlap of the first leg and the spanning member determined by position of the first and third mating surfaces.

9. The nacelle inlet of claim 8 , wherein each of the ruled surfaces defines a cylindroid.

10. The nacelle inlet of claim 8 , wherein the second flange is free of joggles between the first pad-up and the first flange.

11. The nacelle inlet of claim 8 , wherein the lip skin further comprises at least one circumferential stiffener.

12. The nacelle inlet of claim 8 , wherein the lip skin and/ or at least a portion of the bulkhead is formed of aluminum or titanium, and the inner barrel is formed of aluminum or composite materials.

13. The nacelle inlet of claim 8 , wherein the bulkhead is pre-strained to act as a spring against the lip skin and/or the inner barrel.

14. The nacelle inlet of claim 8 , wherein a rearward end of the lip skin is proximate to a forward end of the second flange of the bulkhead.

15. An aircraft comprising:

an engine; and

a nacelle inlet for directing air into the engine, the nacelle inlet comprising

a lip skin including a first pad-up and a second pad-up, wherein each pad-up is defined by an area of increased thickness of the lip skin relative to the thicknesses of adjacent areas of the lip skin, said first pad-up having a first mating surface,

an inner barrel including a forward flange having a second mating surface, and

a bulkhead having a third mating surface disposed opposite the first and second mating surfaces, the first, second and third mating surfaces each machined to be approximate developable surfaces with the first and second mating surface having parallel ruling lines with the third mating surface, the lip skin and inner barrel attached to one another using the bulkhead, and

the bulkhead further comprising

a spanning member and

an angle flange connectable to the spanning member, the second pad-up having a fourth mating surface machined as a developable surface and the angle flange having a fifth mating surface substantially linear at all points around the bulkhead to interface with the fourth mating surface, said angle flange adapted for mating of the fourth and fifth mating surfaces prior to engagement between a first leg of the angle flange and the spanning member by fasteners whereby sliding engagement of the first, second and third mating surfaces positions the spanning member and sliding engagement of the fourth and fifth mating surfaces joins the first leg and spanning member with greater or lesser overlap of the first leg and spanning member determined by position of the first and third mating surfaces.

16. The aircraft of claim 15 , wherein the lip skin has a contoured exterior surface opposite the fourth mating surface.