Saab Ab

Björn Weidmann

Mikael Petersson

Per Hallander

Max Krogager

Tommy Grankäll

Pontus Nordin

Göte Strindberg

Anders Westerdahl

Ingemar Turesson

Claes Rudqvist

Jan Vaara

Jan Andersson

Jan-Erik Lindbäck

Jonny Gustavsson

Rustan Önnefors

Anders Lundberg

Tonny Nyman

Stefan Gustavsson

Rustan ÖNnefors

Tommy GRANKÄLL

A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.

Smooth surface forming tool and manufacture thereof

An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein.

A composite article having a longitudinal direction and a transversal direction. The article includes a stack of plies wherein one ply is a bottom ply and one ply is a top ply. Most or all of the plies include fibers. A plurality of plies have fibers substantially in an orthogonal direction and substantially in a same direction as the longitudinally direction of the article. The bottom ply and the top ply have fibers in a substantially orthogonal direction to the longitudinal direction of the article. At least one ply has the fibers substantially in the same direction as the longitudinal direction of the article. At least one of the plies having fibers substantially in the longitudinal direction includes particles selected from the group of thermoplastic tougheners, nano particles, micro particles, elastic particles, elastomer particles and polymer particles or a combination. Also a method of forming an article on a tool.

Composite article comprising particles and a method of forming a composite article

A structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure arranged within the composite joint. A method of producing a structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure and an aircraft structure comprising such structural composite parts.

Structural longitudinal composite joint for aircraft structure

A method for producing an object of composite material comprising the steps of:

Manufacturing method for trumpet spar and other curved objects

A method of attaching a first portion and a second portion to each other. An adhesive is exposed to a low temperature in order to obtain a non-tacky adhesive. The non-tacky adhesive is arranged between the two portions. The adhesive is cured. Use of adhesive according to the method.

Method of attaching elements by bonding

A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.

Article with de-icing/anti-icing function

The present invention relates to a method for the manufacture of a composite article comprising a composite plate () and at least one fitting (). The method is characterized by the steps of arranging at least one former on said composite plate (), arranging at least one fitting () on said composite plate (), producing a lay-up by applying a composite material layer () least partly covering an external surface of the former and of the fitting, and curing the layup in a curing process. After curing, said composite material layer () forms the walls of a stiffener and at least partly encloses the fitting so as to support it in a predetermined position.

Method for the manufacture of a composite article

A device for shaping of an article of composite material. The device includes a tool including a top surface and side surface for shaping at least one blank of composite material into an article having a predetermined profile; and a air-tight foil. The device further includes at least one support arranged to be in supporting contact with the underside of the protruding part of the blank.

Method and device for shaping of composite material

A method for manufacturing a contoured composite article. A separation distance of dividing elements of a dividing unit configured to divide a tape comprising fiber is adjusted. The tape is fed through the dividing unit to divide the tape into a plurality of inter-connected or separate, substantially longitudinal strips. The tape is laid onto a surface with an automatic tape laying apparatus.

Automatic tape laying apparatus and method

A curved beam of fiber composite material. The beam includes a first flange curved in a longitudinal direction, a second flange curved in a longitudinal direction and having a greater longitudinal extent than the first flange, and a web curved in a longitudinal direction and extending between the first flange and the second flange. The beam includes a fiber composite laminate including layers of fibers having different fiber directions, wherein a fiber density per unit of area of the second flange is lower than a fiber density per unit of area of the first flange, and wherein the first flange, the second flange and the web are seamless, continuous, and unfolded in a longitudinal direction.

Curved beam of fiber composite material

A method for manufacturing an elongate stiffening element and a rigid shell structure integrated with at least one elongate stiffening element. The method includes providing a preformed, form-stable reinforcement member, which has a hat profile with two inwardly directed, opposing flange portions, covering the reinforcement member with a curable composite material to form an external hat profile having outwardly directed flanges, and integrating this assembly with either a curable or preformed shell structure of composite material.

Method of manufacturing an elongate structural element configured for stiffening a shell structure, and a method for manufacturing a rigid shell structure integrated with at least one elongate stiffening element

A method and device for shaping of an article of composite material. The method includes arranging a blank of composite material on a top surface of a forming tool. A portion of the blank is arranged to protrude outside the top surface of the tool. At least one support is arranged in contact with an underside of the protruding portion of the blank. An air-tight foil is arranged over the arrangement. The air-tight foil is forced towards the blank. The support is lowered until the blank is shaped over the tool. The support is stopped and/or removed. The device includes a tool including a top surface and side surface for shaping at least one blank of composite material into an article having a predetermined profile; and a air-tight foil. The device further includes at least one support arranged to be in supporting contact with the underside of the protruding part of the blank.

A tool assembly including a male tool including an inner shape tool including a bag having a connection connectable to a depressurization source for providing a vacuum in the bag such that beads therein form a body of firm cohesion providing the inner shape tool rigid. The male tool further includes a flexible, hollow curing support arranged around the rigid inner shape tool, the inner shape tool is arranged to be removable from the flexible, hollow curing support by rupturing the vacuum.

Method and apparatus for manufacturing of an article including an empty space

A method of manufacturing a composite structure including a plurality of sheets and a radius filler. The radius filler is adapted to fill a gap at least partially formed by the sheets of the composite structure. The radius filler includes a plastic material with a first curing temperature. The sheets include a plastic material with a second curing temperature. The method includes arranging the sheets in a desired shape, applying the radius filler material into the gap, exposing the sheets and the radius filler material to the first temperature, whereby the material of the radius filler cures, and exposing the sheets and the radius filler to the second temperature, which exceeds the first temperature, whereby the material of the sheets cures. A radius filler for filling gaps between sheets of a composite structure. The material of the radius filler has a curing temperature which is below the curing temperature of the sheets of the composite structure.

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Borensberg, Sweden

Björn Weidmann