| 摘要 |
A lower skin portion structure (20) is integrally molded by employing a front spar (23) and a rear spar (22) having rib posts (22c, 23c), lower stringers (24), a lower skin prepreg, and lower rib chord prepregs (25'). Then an upper skin portion structure (30) is integrally molded by employing upper stringers (34) an upper skin prepreg, and upper rib chord prepregs; then, ribs (40) are fastened to the rib posts (22c, 23c) and the lower rib chords (25) of the lower skin portion structure (20) by a mechanical fastening device. Thereafter, the lower skin portion structure (20) and the upper skin portion structure (30) are coupled by fastening the upper skin portion structure (30) to the front spar (23) and the rear spar (22) by fasteners, and then fastening upper rib chords (35) of the upper skin portion structure (30) to the ribs by the mechanical fastening device, whereby a composite material wing is manufactured. <IMAGE> |
