GB577716A - Method of and apparatus for adhesively assembling structural components - Google Patents

Abstract

577,716. Compound fabrics. FORD MOTOR CO., Ltd., (Ford Motor Co.). April 11, 1944, No. 6681. [Class 140] [Also in Groups XXIII and XXXIII] Structural components, particularly for aircraft wings, comprising a skin secured on continuous linear areas to a base support and presenting a sharply rounded surface and a relatively flat surface, are assembled by applying adhesive to the supports and skin along the linear areas and appling pressure successively to the rounded portion and to the remainder of the structure and then applying heat to the linear areas to cure the adhesive. Fig. 1 shows a fixture for assembling the leading edge component of an airplane wing and comprising an extended worktable 15, which corresponds to one of the spars of the completed wing and along which the component slides to enable successive sections to be completed; a press 16 associated with the table includes a supporting frame 17 to which are hinged at 20 pressure strips 18, controlled by links 22 and toggle levers 23 and which are spaced to conform to the rib, former and bulkhead spacing of the wing and have inner faces curved to that of the wing and containing in an inner groove an expansible tube for applying pressure; steam is supplied through tubes 34 and is removed through exhaust tubes 35. A nose pressure strip acting downwardly and pivotally mounted by links 25 is adapted to move upwardly and rearwardly to clear the work area; base pressure strips 27 corresponding to spar location are hinged to brackets 21 and move laterally to clear the table. An overall fixture for making structures which are not uniform in section is shown in Fig. 2 and includes upper and lower surface wing presses 36 and 37 (which may be arranged with the nose press 38 acting horizontally instead of as shown); there are included individual pressure strips 39 for nose ribs, 40 for spars, and 41 for wing ribs. The work in position is a portion of the leading edge structure 9 including the skin 10, a rib 11 and a bulkhead 12; notches 13 in longitudinal stiffening members 14 attached to the skin receive formers (not shown); an assembly of both edge and wing is made in the fixture of Fig. 2.