| 摘要 |
A system and method for assembling a 360-degree section of an aircraft fuselage or nacelle by properly positioning a plurality of assembly panels relative to a machine datum representing an assembly-level datum schema, drilling full-sized holes proximate to a second skin edge of the panels with the machine, net-trimming a second edge of the panels with the machine, then using the full-sized holes proximate to the second skin edges as alignment features to properly orient and attach pairs of the panels together proximate to first skin edges, opposite of the second skin edges with an auxiliary machine, forming panel pairs. Control systems may be installed into the panel pairs separately and independently, then the panel pairs may be joined together, aligning the full-sized holes proximate to the second edges, and inserting fasteners through the aligned full-sized holes proximate to the second skin edges. |
