| 摘要 |
The method involves defining machining windows (8) on a metallic fuselage skin panel (1). A convex upper side (1b) of the panel is maintained in position at the right side of each window, without introducing static indeterminacy for positioning. Real shape of the upper side is measured. Machining is performed on a concave inner side (1a) by taking the measured side as reference and the side (1b) is released. An independent claim is also included for a device to implement a fuselage skin panel machining method. |
