COMPOSITE STRUCTURAL PANELS AND AIRCRAFT FUSELAGES Structural panel assemblies (10) include first and second composite panels (12, 14) positioned in edgewise alignment, with at least one tab (20) extending from a mating edge (16) of the first panel (12) and including an exterior surface (24) in facing registration with a corresponding portion (34) of an interior surface (32) of the second composite panel (14). The corresponding portion (34) includes a recessed area (36) to interfit with the tab (20) or is otherwise configured to receive the tab (20). The exterior surface of the tab (20) is spaced from the corresponding portion (34), to receive a bonding material (40) therebetween for bonding the composite panels (12, 14). 10 2 42 26 _J~--44 -20 28 2 44 22 20 30 50-- 402 18 34 36 42 124 1 16 Fig.1 g114 74 1 170 142 1416 172 176 142 14 162 170 174 16 Fig. 2
Composite structural panels and aircraft fuselages
2016-12-08
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / F16B DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES , Vorrichtungen zum Befestigen oder Sichern von Konstruktionselementen oder Maschinenteilen, z.B. Nägel, Bolzen, Schrauben, Sprengringe, Klemmen, Klammern oder Keile |