Abstract: A rotation apparatus for a boom of a mining vehicle includes a rotation device having an axial central axis. The rotation device has a housing and an inner manifold having a tube-like structure with a space within, wherein the inner manifold is arranged concentrically inside the housing. The housing is arranged to rotate around the axial central axis and the housing includes a housing channel. The inner manifold has a fluid channel having a fluid inlet for receiving fluid from the boom, and the fluid channel is connected to the housing channel for forming a fluid conduit through the rotation device.

Abstract: A feed beam, a rock drilling unit and to a method of manufacturing a feed beam is provided. The feed beam includes a basic profile element, which has two or more superimposed material layers. At least one of the material layers may be made of a composite material.

Abstract: A feed beam, a rock drilling unit and to a method of manufacturing a feed beam is provided. The feed beam includes a basic profile element, which has two or more superimposed material layers. At least one of the material layers may be made of a composite material.

Abstract: 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.

Abstract: 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.

Abstract: 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-fibres. 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 mould cavity between a pair of mould 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 mould cavity and subsequently cured.

Abstract: 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.

Abstract: 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.

Abstract: A cutting tool has: a rotatable hollow tube with an inlet at a distal end of the tube and a cutting edge at the perimeter of the inlet, the tube being arranged so as to rotate when in use so as to cut a work piece with the cutting edge; and an auger housed within the hollow tube, the auger being arranged so as to rotate when in use so as to feed cut material from the inlet along the hollow tube, wherein a distal end of the auger is set back from the cutting edge of the tube.

Abstract: 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.

Abstract: 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.

Abstract: 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-fibres. 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 mould cavity between a pair of mould 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 mould cavity and subsequently cured.

Abstract: 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.

Abstract: A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened. The extension portion (23) distributes the forces to the structures of the panel (3).

Abstract: A cutting tool comprising: a rotatable hollow tube with an inlet at a distal end of the tube and a cutting edge at the perimeter of the inlet, the tube being arranged so as to rotate when in use so as to cut a work piece with the cutting edge; and an auger housed within the hollow tube, the auger being arranged so as to rotate when in use so as to feed cut material from the inlet along the hollow tube, wherein a distal end of the auger is set back from the cutting edge of the tube. A method of drilling a hole in a dry fibre assembly, the method comprising engaging the dry fibre assembly with a cutting tool comprising a hollow tube with an inlet at a distal end of the tube and a cutting edge at the perimeter of the inlet; and rotating the hollow tube so as to cut the dry fibre assembly with the cutting edge.

Abstract: 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.

Abstract: A pivoting panel for an aircraft and to a composite support piece for this kind panel. The support piece (17) is arranged as a part of the frame structure of the panel (3). The support piece has an extension portion (23) to which an actuator connection fitting (7) of an actuator (4) can be fastened. The extension portion (23) distributes the forces to the structures of the panel (3).

Abstract: A spoiler and wing of an aircraft. A bottom surface of the spoiler has several longitudinal, elongated grooves. At least some of the grooves are equipped with one or more vortex generators. Further, the invention relates to a wing having in its back part at least one flap and having at least one spoiler of the invention arranged on the section between the wing and flap. The invention also relates to a method and control surface for generating vortexes.

Abstract: A spoiler and wing of an aircraft. A bottom surface of the spoiler has several longitudinal, elongated grooves. At least some of the grooves are equipped with one or more vortex generators. Further, the invention relates to a wing having in its back part at least one flap and having at least one spoiler of the invention arranged on the section between the wing and flap. The invention also relates to a method and control surface for generating vortexes.

Abstract: An arrangement for fastening stringers of an aircraft wing to a transverse wing rib in the wing. An elongated fastening element is arranged to the side of the wing rib comprising a plate-like flexible portion close to the wing rib, and the first longitudinal edge of the flexible portion is fastened to the side of the wing rib and the second free longitudinal edge comprises a stiffening portion. The ends of the stiffening portion also comprise fastening portions, from where the fastening element is fastened to the stringers. The flexible portion in the fastening element is formed to be flexible in the longitudinal direction of the wing rib, and by bending the flexible portion in the longitudinal direction of the wing rib the stiffening portion can if necessary be transferred during the assembly of the wing. The stiffening portion is in turn dimensioned to carry vertical loads.