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1. WO2014175798 - EXCENTRICITÉ D'ÉLÉMENT DE RAIDISSEMENT

Numéro de publication WO/2014/175798
Date de publication 30.10.2014
N° de la demande internationale PCT/SE2013/050462
Date du dépôt international 25.04.2013
Demande présentée en vertu du Chapitre 2 07.11.2014
CIB
B64C 3/26 2006.01
BTECHNIQUES INDUSTRIELLES; TRANSPORTS
64AÉRONAUTIQUE; AVIATION; ASTRONAUTIQUE
CAÉROPLANES; HÉLICOPTÈRES
3Voilures
26Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
B64C 1/06 2006.01
BTECHNIQUES INDUSTRIELLES; TRANSPORTS
64AÉRONAUTIQUE; AVIATION; ASTRONAUTIQUE
CAÉROPLANES; HÉLICOPTÈRES
1Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
06Cadres; Lisses; Longerons
B64C 1/12 2006.01
BTECHNIQUES INDUSTRIELLES; TRANSPORTS
64AÉRONAUTIQUE; AVIATION; ASTRONAUTIQUE
CAÉROPLANES; HÉLICOPTÈRES
1Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
06Cadres; Lisses; Longerons
12Structure ou fixation de panneaux de revêtement
B64C 3/18 2006.01
BTECHNIQUES INDUSTRIELLES; TRANSPORTS
64AÉRONAUTIQUE; AVIATION; ASTRONAUTIQUE
CAÉROPLANES; HÉLICOPTÈRES
3Voilures
18Longerons; Nervures; Lisses
CPC
B29C 70/44
BPERFORMING OPERATIONS; TRANSPORTING
29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
70Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
04comprising reinforcements only, e.g. self-reinforcing plastics
28Shaping operations therefor
40Shaping or impregnating by compression
42for producing articles of definite length, i.e. discrete articles
44using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/443
BPERFORMING OPERATIONS; TRANSPORTING
29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
70Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
04comprising reinforcements only, e.g. self-reinforcing plastics
28Shaping operations therefor
40Shaping or impregnating by compression
42for producing articles of definite length, i.e. discrete articles
44using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
443and impregnating by vacuum or injection
B29D 99/0014
BPERFORMING OPERATIONS; TRANSPORTING
29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
DPRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
99Subject matter not provided for in other groups of this subclass
001Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
0014provided with ridges or ribs, e.g. joined ribs
B64C 3/18
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
3Wings
18Spars; Ribs; Stringers
B64C 3/20
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
3Wings
20Integral or sandwich constructions
B64C 3/26
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
3Wings
26Construction, shape, or attachment of separate skins, e.g. panels
Déposants
  • SAAB AB [SE]/[SE]
Inventeurs
  • GUSTAVSSON, Stefan
Mandataires
  • ZACCO SWEDEN AB
Données relatives à la priorité
Langue de publication anglais (EN)
Langue de dépôt anglais (EN)
États désignés
Titre
(EN) STIFFENING ELEMENT RUN-OUT
(FR) EXCENTRICITÉ D'ÉLÉMENT DE RAIDISSEMENT
Abrégé
(EN)
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).
(FR)
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).
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