Airbus Operations Gmbh

Patria Aerostructures Oy

Risto Kallinen

Simon W Topping

Nils Haack

Martin Edwards

Christopher Payne

Antti Aho-Mantila

Pentti Ahtonen

Jussi Linjama

Jani Korpimäki

A method of manufacturing a panel, the panel comprising a composite skin and at least one composite stiffener, the method comprising: positioning first and second mandrels on opposite sides of the stiffener; positioning first and second compaction tools on opposite sides of the skin; and compacting the skin between the first and second compaction tools by moving one or both of the compaction tools, wherein the movement of the compaction tool(s) causes the first and second mandrels to move towards the stiffener along inclined paths so as to compact the stiffener between the mandrels.

Composite manufacturing method

A method of manufacturing a composite element. A stack of plies is assembled on a lay-up table, each ply comprising a plurality of reinforcement elements such as dry-fibers. A first part of the stack of plies is bound to form a partially bound stack of plies, a second part of the stack of plies remaining unbound. The partially bound stack of plies is press-formed in a mold cavity between a pair of mold tools to form a shaped pre-form, plies in the second part of the stack sliding against each other during the press-forming. A liquid matrix material is injected into the shaped pre-form in the mold cavity and subsequently cured.

Apparatus for manufacturing a composite element

Method of manufacturing a composite element

A fitting for joining a first component to a second component, the fitting comprising a composite part and a reinforcement element. The composite part is formed from a composite material and comprises: a base; an end wall meeting the base at a first corner; and a side wall meeting the end wall at a second corner and the base at a third corner. The reinforcement element is shaped such that it can be fitted to the composite part and engage the end wall of the composite part, the first corner of the composite part; and the second corner of the composite part.

Fitting

A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece () is arranged as a part of the frame structure of the panel (). The support piece has an extension portion () to which an actuator connection fitting () of an actuator () can be fastened. The extension portion () distributes the forces to the structures of the panel ().

Pivoting panel for aircraft, and composite support piece

Growing community of inventors

Bristol, United Kingdom

Risto Kallinen