STIFFENING ELEMENT RUN-OUT

The invention regards a torsion-box type airfoil composite structure comprising a skin component (6, 206) and at least a first and a second stiffening element (8, 8', 208', 8'', 208'') arranged adjacent to each other longitudinally along the skin component (6, 206), whe...

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Bibliographische Detailangaben
1. Verfasser:	GUSTAVSSON, STEFAN
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AEROPLANES AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING AIRCRAFT AVIATION CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COSMONAUTICS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HELICOPTERS PERFORMING OPERATIONS PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	The invention regards a torsion-box type airfoil composite structure comprising a skin component (6, 206) and at least a first and a second stiffening element (8, 8', 208', 8'', 208'') arranged adjacent to each other longitudinally along the skin component (6, 206), wherein the at least first and second stiffening element (8, 8', 208', 8'', 208'') each comprise a flange member (14', 214', 14'', 214'') arranged in parallel with and bonded to the skin component (6, 206), wherein the second stiffening element (8, 8'', 208'') comprises a run-out area (10, 210). The flange member (14', 214') of the first stiffening element (8, 8', 208') and the flange member (14'', 214'') of the second stiffening element (8, 8'', 208'') are joined at the run-out area (10, 210). L'invention concerne une structure composite de profil aérodynamique de type caisson de torsion comprenant un composant de peau (6, 206) et au moins des premier et second éléments de raidissement (8, 8', 208', 8'', 208'') disposés l'un à côté de l'autre longitudinalement le long du composant de peau (6, 206), les au moins premier et second éléments de raidissement (8, 8', 208', 8'', 208'') comprenant chacun un élément de rebord (14', 214', 14'', 214'') disposé en parallèle avec le composant de peau (6, 206) et lié à celui-ci, le second élément de raidissement (8, 8'', 208'') comprenant une zone d'excentricité (10, 210). L'élément de rebord (14', 214') du premier élément de raidissement (8, 8', 208') et l'élément de rebord (14'', 214'') du second élément de raidissement (8, 8'', 208'') sont joints au niveau de la zone d'excentricité (10, 210).