AIRCRAFT WING WITH TUBULAR FUEL TANKS
AIRCRAFT WING WITH TUBULAR FUEL TANKS
An aircraft wing (fig.3,3) has a spanwise direction extending between a root (fig.3,16) and a tip end (fig.3,15), and a chordwise direction extending between a leading edge (fig.3,13) and a trailing edge (fig.3,14). A tubular fuel tank 12a-c is located between upper and lower wing covers 10,11, with a longitudinal axis extending in the spanwise direction. The fuel tank and each cover are integrally formed using composite material, such as carbon fibre reinforced or laminate materials. Preferably, pairs of fuel tanks are integrally formed, adjacent in the chordwise direction. Each tank may have a vertical wall extending between the covers forming a spar-like structure for the wing. Preferably, the tank cross-section is a rounded square or squircle, with a noodle or filler 78 used between rounded exterior corners of adjacent tanks. Each tank may have a port (fig.4a,81) for coupling to a fuel line, and be load bearing and safe-life for the aircraft wing. A method of manufacturing an aircraft wing by laying up composites and co-bonding the fuel tank to the covers is also claimed.
Dokumentinformationen
AIRCRAFT WING WITH TUBULAR FUEL TANKS
2021-04-14
Patent
Elektronische Ressource
Englisch
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