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1. WO1999026781 - COMPOSITE MATERIAL PANEL WITH SHOCK-PROTECTED EDGES

Publication Number WO/1999/026781
Publication Date 03.06.1999
International Application No. PCT/FR1998/002464
International Filing Date 18.11.1998
IPC
B29C 70/86 2006.1
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
68by incorporating or moulding on preformed parts, e.g. inserts or layers
86Incorporating in coherent impregnated reinforcing layers
B29C 70/88 2006.1
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
88characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B32B 3/02 2006.1
BPERFORMING OPERATIONS; TRANSPORTING
32LAYERED PRODUCTS
BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
3Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form
02characterised by features of form at particular places, e.g. in edge regions
B64C 1/12 2006.1
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
1Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
06Frames; Stringers; Longerons
12Construction or attachment of skin panels
B64D 29/00 2006.1
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
29Power-plant nacelles, fairings, or cowlings
CPC
B29C 70/86
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
68by incorporating or moulding on preformed parts, e.g. inserts or layers ; , e.g. foam blocks
86Incorporated in coherent impregnated reinforcing layers, ; e.g. by winding
B29C 70/885
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
88characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
882partly or totally electrically conductive, e.g. for EMI shielding
885with incorporated metallic wires, nets, films or plates
B32B 2260/021
BPERFORMING OPERATIONS; TRANSPORTING
32LAYERED PRODUCTS
BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
2260Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
02Composition of the impregnated, bonded or embedded layer
021Fibrous or filamentary layer
B32B 2260/046
BPERFORMING OPERATIONS; TRANSPORTING
32LAYERED PRODUCTS
BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
2260Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
04Impregnation, embedding, or binder material
046Synthetic resin
B32B 2262/103
BPERFORMING OPERATIONS; TRANSPORTING
32LAYERED PRODUCTS
BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
2262Composition of fibres which form a fibrous or filamentary layer or are present as additives
10Inorganic fibres
103Metal fibres
B32B 2307/558
BPERFORMING OPERATIONS; TRANSPORTING
32LAYERED PRODUCTS
BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
2307Properties of the layers or laminate
50having particular mechanical properties
558Impact strength, toughness
Applicants
  • AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE [FR]/[FR] (AllExceptUS)
  • PORTE, Alain [FR]/[FR] (UsOnly)
  • ANDRE, Robert [BE]/[FR] (UsOnly)
Inventors
  • PORTE, Alain
  • ANDRE, Robert
Agents
  • THEBAULT, Jean-Louis
Priority Data
97/1486821.11.1997FR
Publication Language French (fr)
Filing Language French (FR)
Designated States
Title
(EN) COMPOSITE MATERIAL PANEL WITH SHOCK-PROTECTED EDGES
(FR) PANNEAU EN MATERIAU COMPOSITE A BORDURES PROTEGEES DES CHOCS
Abstract
(EN) The invention concerns a panel made of composite material, in particular with thermosetting or thermoplastic matrix, with edges and/or external surface protected against shocks or erosion, for any shroud elements of aircraft engine airframes or pods. The invention is characterised in that it comprises, over all or part of its edges (6, 8), a coating which forms an edge overlapping the pane two opposite faces (4, 5) consisting of a metallic fabric (3, 3') linked to the panel structure (2, 2') by means of an adhesive agent diffused through said fabric. The invention is applicable to aircraft.
(FR) L'objet de l'invention est un panneau en matériau composite, en particulier à matrice thermodurcissable ou thermoplastique, à bordures et/ou surface extérieure protégées des chocs ou de l'érosion, pour tout élément de carénage de cellules ou de nacelles de moteurs d'aéronefs, caractérisé en ce qu'il comporte, sur tout ou partie de ses bordures (6, 8), un revêtement qui forme une bordure chevauchant les deux faces opposées (4, 5) du panneau, constitué d'un tissu métallique (3, 3') lié à la structure (2, 2') du panneau par l'intermédiaire d'un agent d'adhésion diffusé au travers dudit tissu. Application notamment aux aéronefs.
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