AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE

AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE

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...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: CEBOLLA GARROFE, Pablo, MARTINO GONZÁLEZ, Esteban, ARANA HIDALGO, Alberto, VÁZQUEZ CASTRO, Jesús Javier
Format: Patent
Sprache:eng
Schlagworte:
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Beschreibung
Zusammenfassung: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).