Method for forming and installing stringers

1. A method of fabricating and installing a composite stringer on a skin, comprising:

using a tool assembly to form a composite charge into a preformed stringer;

placing the preformed stringer on the skin using the tool assembly;

displacing a first portion of the tool assembly toward the skin while holding a second portion of the tool assembly substantially stationary;

placing a mandrel in the preformed stringer; and

holding the mandrel in the preformed stringer while the tool assembly is moved into proximity with the skin.

2. The method of claim 1 , wherein using the tool assembly to form the composite charge into the preformed stringer includes pressing a composite charge between first and second tools.

3. The method of claim 1 , wherein placing the preformed stringer on the skin using the tool assembly includes:

holding the preformed stringer in a substantially fixed position on the tool assembly, and

moving the tool assembly having the preformed stringer thereon into proximity with the skin.

4. The method of claim 3 , further comprising:

compacting the preformed stringer by using a portion of the tool assembly to force the preformed stringer against the skin.

5. The method of claim 3 , further comprising:

compacting the preformed stringer;

releasing the preformed stringer from the tool assembly after the preformed stringer has been compacted; and,

moving the tool assembly away from the preformed stringer after the preformed stringer has been released.

6. The method of claim 3 , wherein holding the preformed stringer in a substantially fixed position on the tool assembly includes installing a stringer hold down on the tool assembly before the tool assembly is moved into proximity with the skin, and the method further comprises:

removing the stringer hold down after the preformed stringer has been placed on the skin.

7. The method of claim 1 , further comprising

compacting the preformed stringer against the skin;

vacuum bagging the skin and the preformed, compacted stringer; and,

co-curing the skin and the preformed, compacted stringer.

8. A method of fabricating and installing a composite stringer on a skin of an aircraft, comprising:

placing a composite charge on a tool assembly;

using the tool assembly to form the charge into a preformed stringer;

placing a mandrel in the preformed stringer;

using the tool assembly to position the preformed stringer on the skin;

holding the mandrel in the preformed stringer while the tool assembly is moved into proximity with the skin;

using the tool assembly to compact the preformed stringer against the skin;

displacing a first portion of the tool assembly toward the skin while holding a second portion of the tool assembly substantially stationary;

separating the tool assembly from the compacted stringer;

vacuum bagging the compacted stringer and the skin; and,

co-curing the stringer and the skin.

9. The method of claim 8 , wherein using the tool assembly to form the charge includes compressing the charge between male and female tools.

10. The method of claim 8 , further comprising:

holding the preformed stringer in a fixed position on the tool assembly; and,

moving the tool assembly having the preformed stringer held thereon into proximity with the skin.

11. The method of claim 10 , wherein holding the preformed stringer on the tool assembly includes wrapping straps around the preformed stringer and the tool assembly, and the method further comprises:

removing the straps after the preformed stringer has been positioned on the skin.

12. The method of claim 8 , wherein displacing the first portion of the tool assembly includes expanding a bladder to react against the first and second portions of the tool assembly.

13. The method of claim 8 , wherein using the tool assembly to position the preformed stringer on the skin includes:

forcing the preformed stringer into contact with the skin by displacing tools on the tool assembly and allowing the displaced tools to conform to the shape of the skin.

14. A method of fabricating and installing a composite stringer on a skin of an aircraft, comprising:

placing a flat composite charge on a tool assembly;

moving the tool assembly to a forming station;

shaping the flat charge into a preformed stringer at the forming station by compressing the flat charge between the tool assembly and a tool at the forming station;

clamping the preformed stringer on the tool assembly; moving the tool assembly and preformed stringer into proximity with the skin;

using the tool assembly to place the preformed stringer onto the skin;

compacting the preformed stringer against the skin by displacing the tool assembly toward the skin;

displacing a first portion of the tool assembly toward the skin while holding a second portion of the tool assembly substantially stationary, the displacing including expanding a bladder between the first and second portions of the tool assembly to react against the first and second portions of the tool assembly to contour the first portion to the skin via the bladder;

removing the tool assembly from the compacted stringer;

vacuum bagging the compacted stringer and the skin; and

co-curing the compacted stringer and the skin.

15. A method of fabricating and installing a composite stringer on a skin, comprising:

using a tool assembly to form a composite charge into a preformed stringer;

placing the preformed stringer on the skin using the tool assembly; and

displacing a first portion of the tool assembly toward the skin while holding a second portion of the tool assembly substantially stationary, the displacing including expanding a bladder between the first and second portions of the tool assembly to react against the first and second portions of the tool assembly to contour the first portion to the skin via the bladder.