Saab Ab

Saab Ericsson Space Ab

Mikael Petersson

Björn Weidmann

Per Hallander

Max Krogager

Tommy Grankäll

Pontus Nordin

Göte Strindberg

Anders Westerdahl

Ingemar Turesson

Jan Andersson

Claes Rudqvist

Jan Vaara

Jan-Erik Lindbäck

Jonny Gustavsson

Per Ingvarson

Rustan Önnefors

Anders Lundberg

Tonny Nyman

Jan Waara

Stefan Gustavsson

Peter Johansson

Anders Larsson

Stefan HALLSTRÖM

Rustan ÖNnefors

Tommy GRANKÄLL

Torbjörn Alenby

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

A stiffening element including at least a first stiffening profile and at least a second stiffening profile. The first stiffening profile includes a profile member. At least one structural flange is connected to the profile member. A through-passage extends through the profile member. At least one support flange is connected to the profile member. The second stiffening profile includes a bottom portion and at least one support side portion connected to the bottom portion. A method for manufacturing a stiffening element. A method for manufacturing a reinforced structure, where the reinforced structure includes at least one structural element and at least one stiffening element.

Stiffening element and reinforced structure

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

An apparatus and a method of conforming a blank onto forming surface sections of a forming tool by drawing a first vacuum against an elastic forming medium for transmitting forming forces from the elastic forming medium to the blank. The elastic forming medium is evacuated with the first vacuum for allowing the elastic forming medium to stretch and conform the blank to the forming surface sections. The elastic forming medium includes at least one void. A second vacuum is applied to the void for achieving a stiffened section of the elastic forming medium corresponding with the location of the void and corresponding with, when the elastic forming medium after the completion lies against the forming tool having the blank in between, a forming surface section of the forming tool where the blank requires a forming force being larger than that of surrounding sections of the elastic forming medium.

Hot drape forming by means of a stiffness controlled vacuum bag

A thermoforming apparatus for forming a blank into a composite article. The thermoforming apparatus includes a forming tool. A forming member forms the blank over the forming tool. A first chamber is arranged for containing the blank. A second chamber is separated from the first chamber by the forming member. A first air circulator is configured to circulate air in the first chamber for achieving a heat distribution to the blank. The first air circulator includes a controllable valve member. The apparatus also includes a second air circulator. A method for forming a blank during circulation of air in a first chamber.

Thermoforming apparatus

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 reflector including a reflector dish and a backing structure. The reflector dish has a reflecting surface and a back surface. The backing structure is arranged in a pattern on the back surface of the reflector dish for supporting and stiffening the reflector dish. The backing structure includes a first backing structure skin and a second backing structure skin and a backing structure core there between. The core is substantially thicker than each skin. The backing structure is arranged such that the first backing structure skin is faced against the back surface of the reflector dish. Also, a method of manufacturing a reflector.

Reflector

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

Growing community of inventors

Linköping, Sweden

Mikael Petersson