| 摘要 |
An aircraft stringer lay-up assembly 10 is provided comprising a first mandrel element 12 having a first mandrel material 48 with a first mandrel coefficient of thermal expansion (COE) 50. A composite ply assembly 40 is laid up onto the first mandrel element 12 to generate a primary lay-up surface 42. The composite ply assembly 40 comprises a first primary fold-over portion 44 folded onto to the first mandrel right end surface 32. A second primary fold over portion 46 folds over to the first mandrel left end surface 36. The first mandrel coefficient of thermal expansion (COE) 50 is adapted such that the first mandrel 48 is movable between a first mandrel normal condition and a first mandrel heated condition where the first mandrel right end surface 32 and the first mandrel left end surface 36 move away from each other. The first primary fold-over portion 44 and the secondary primary fold over portion 46 are thereby moved such that wrinkles are pulled out of said primary lay-up surface 42. Element 12 has upper and lower surfaces 26, 28, side surfaces 30, and first mandrel right and left ends 34, 38. Portions 44, 46 may be affixed to the ends 34, 38. Vacuum bag assembly (70) (figure 3 - not shown) presses ply assembly 40 against element 12 during curing. Rigidity reducing slots (18) (figure 4 - not shown) allow mandrel element 12 to conform to a contoured curing block 24. Second mandrel element 16 has a coefficient of thermal expansion equal to that of first mandrel. |
