| 摘要 |
PROBLEM TO BE SOLVED: To provide an assembling method of an aircraft wing which does not require a large amount of tooling, can cope with an increase in tolerance due to application of composite materials, and is adaptable to horizontal assembling.SOLUTION: Tooling components 11, 12 include: spars 2, 3 comprising rib posts 5, 6 including first alignment mechanisms 7, 8; a rib 4 including first tooling mechanisms 9; second tooling mechanisms 13, 16; second alignment mechanisms 14, 17; and drill bushings 15. The tooling components 11, 12 are mounted on the rib 4 by positioning the first and second tooling mechanisms 9, 13, 16. The rib 4 and the spars 2, 3 are positioned by positioning the first and second alignment mechanisms 7, 8, 14, 17. Fastening holes are drilled in the rib 4 and rib posts 5, 6 with the drill bushings 15 of the tooling components 11, 12. The tooling components 11, 12 are removed from the rib 4. The rib 4 is fastened to the rib posts 5, 6 to form a rib-spar joint part. |
