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...

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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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creator	CEBOLLA GARROFE, Pablo MARTINO GONZÁLEZ, Esteban ARANA HIDALGO, Alberto VÁZQUEZ CASTRO, Jesús Javier
description	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).
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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).</abstract><oa>free_for_read</oa></addata></record>
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subjects	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
title	AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE
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