Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat (400) for use with an aircraft includes a single-piece nose skin (402) defining upper (412) and lower (414) external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar (508) coupled to an inner surface of the single-piece nose skin. The box spar (508) includes lateral walls (520) extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment (528) of the box spar.
CONTINUOUS SKIN LEADING EDGE SLATS
VORDERKANTENLEISTEN MIT KONTINUIERLICHER HAUT
BECS DE BORD D'ATTAQUE À REVÊTEMENT EN CONTINU
2024-04-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
ACTUATING MECHANISM FOR TRAILING EDGE FLAPS AND LEADING EDGE SLATS
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