An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. 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
2018-06-07
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE
Europäisches Patentamt | 2019
|Fuselage Torsion of a CT4 Aircraft
NTIS | 1983
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