A three dimensional printer which prints at using at least one composite material having an inherently abrasive filler or fiber material has a Mohs hardness greater than substantially 1, or a Knoop/Vickers hardness greater than substantially 300 kg/mm.sup.2, or a Rockwell C hardness at least C30, and where a nozzle tip may contact a top surface of a previously deposited line of material may have a nozzle body includes a material having a thermal conductivity at least 35 w/M-K to conduct heat to the nozzle, and a nozzle throat and/or nozzle tip each include a material having a Rockwell C hardness at least C40, to resist wear from sliding contact of the nozzle tip with the previously deposited lines of the material being printed or another previously deposited material, or from the material being printed as it is printed through the nozzle throat.

A three dimensional printer which prints at using at least one composite material having an inherently abrasive filler or fiber material has a Mohs hardness greater than substantially 1, or a Knoop/Vickers hardness greater than substantially 300 kg/mm.sup.2, or a Rockwell C hardness at least C30, and where a nozzle tip may contact a top surface of a previously deposited line of material may have a nozzle body includes a material having a thermal conductivity at least 35 w/M-K to conduct heat to the nozzle, and a nozzle throat and/or nozzle tip each include a material having a Rockwell C hardness at least C40, to resist wear from sliding contact of the nozzle tip with the previously deposited lines of the material being printed or another previously deposited material, or from the material being printed as it is printed through the nozzle throat.

Devices and methods for handling uncured radius fillers are disclosed. The devices, i.e., radius filler transport tools, generally are configured to load a radius filler from above, to index the radius filler to a desired location (e.g., a cavity), and to downwardly unload (e.g., drop) the radius filler at the desired location. Radius filler transport tools comprise at least two trough portions, coupled together to form a trough to carry the radius filler, and a plurality of hanger assemblies configured to transversely span the trough. The radius filler transport tool may have a transport state, where the trough and the hanger assemblies are in closed states, a load state, where the trough is in the closed state and at least one hanger assembly is in an open state, and an unload state, where the trough is in an open state and the hanger assemblies are in closed states.

Chopped fiber composite systems and methods are disclosed. Sorting systems include a conveyor, an imager, a plurality of receptacles, a pneumatic device, and controller. Molding systems include a conveyor, an imager, a mold, a pneumatic device, and a controller. The controller directs the pneumatic device to alter the freefall of chopped fiber composite pieces based on characteristics of the chopped fiber composite pieces as they drop from the conveyor and into a receptacle or a mold. Sorting and molding methods include dropping chopped fiber composite pieces, detecting characteristics of the dropping pieces, and directing the pieces based on the detected characteristics.

A method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system with an end effector and a control, wherein at least one metal layer and at least one unhardened fiber layer are being stacked onto each other in a mould in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer or a fiber layer from a supply stack according to the stacking sequence, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface. After being picked up from the supply stack and before being deposited onto the deposition surface the layer to be stacked can be deformed by the end effector as to adapt the form of the layer to the form of the deposition surface.

A method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system with an end effector and a control, wherein at least one metal layer and at least one unhardened fiber layer are being stacked onto each other in a mould in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer or a fiber layer from a supply stack according to the stacking sequence, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface. After being picked up from the supply stack and before being deposited onto the deposition surface the layer to be stacked can be deformed by the end effector as to adapt the form of the layer to the form of the deposition surface.

Method and device for the transport of foil in a transport direction, in particular, for an stretching plant, wherein at least one upper moving rope and at least one lower moving rope are guided, and the at least one upper moving rope and the at least one lower moving rope clamp the foil at its lateral edge at least in places and take it along.

Methods for manufacturing a turbomachine composite part, such as a fan blade, are provided. The composite part has a fibrous structure with a three-dimensional fibrous preform coated with a surface fibrous web, and which is embedded in a polymer matrix The methods include: forming the surface web in a cavity of a mold in order to shape it, wetting and forming the preform on the surface web in order to shape it, and closing the mold, drying the fibrous structure, and injecting thermosetting resin into the mold in order to form said polymer matrix. The surface web is wetted before and/or during the forming thereof.

An optical printing positioning system is set forth. The system includes a cavity for retaining an optical surface having an inner surface dimensioned and configured to maintain and to constrain an optical surface disposed therein when the optical surface undergoes a printing process.

A large scale composite structure is fabricated by forming a plurality of composite laminate modules and joining the modules together along their edges using scarf joints.