An aircraft stabilizer (15, 17) with an enlarged area of laminar flow is provided. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).
AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE
FLUGZEUGSTABILISATORVORDERKANTENINTEGRATION MIT EINEM TORSIONSKASTEN UND RUMPF
STABILISATEUR D'AÉRONEF AVEC INTÉGRATION DE BORD D'ATTAQUE ET FUSELAGE À CAISSON DE TORSION
2019-10-30
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE
European Patent Office | 2018
|Fuselage Torsion of a CT4 Aircraft
NTIS | 1983
|