A method of removing a vacuum bag from a composite mold. Removable strips are placed around the perimeter of the component parts and across the parts to create natural break points in the consumable materials used during manufacture of a composite product, e.g. wind turbine blade. The vacuum bag, and other consumable layers, are placed over the removable strip such that when the strips are pulled, the strip tears, in a controlled and complete manner, through each layer of consumables. This eliminates the need to use a knife/scissor to remove the finished product, thereby avoiding risk of injury.

A method and system for manufacturing composite parts free of wrinkles and mark-offs from bagging compression. The method can include placing composite material around a rigid mandrel and sealing opposing end of an elastomeric hollow membrane within a rigid external vessel. Then the method can include inflating the hollow membrane from a natural state to an inflated state. In the natural state, the hollow membrane can have a cross-section smaller than the cross section of the rigid mandrel with the composite material thereon. The method can then include inserting the rigid mandrel and the composite material into the membrane while it is in the inflated state, followed by releasing the membrane from the inflated state to naturally contract toward its natural state. Then the method can include heating the composite material to a cure temperature while the composite material is compressed by the membrane.

A method and system for manufacturing composite parts free of wrinkles and mark-offs from bagging compression. The method can include placing composite material around a rigid mandrel and sealing opposing end of an elastomeric hollow membrane within a rigid external vessel. Then the method can include inflating the hollow membrane from a natural state to an inflated state. In the natural state, the hollow membrane can have a cross-section smaller than the cross section of the rigid mandrel with the composite material thereon. The method can then include inserting the rigid mandrel and the composite material into the membrane while it is in the inflated state, followed by releasing the membrane from the inflated state to naturally contract toward its natural state. Then the method can include heating the composite material to a cure temperature while the composite material is compressed by the membrane.

Grid structure, such as a lattice or grid-stiffened structure and a process of manufacturing such a grid structure. Fiber material is laid up on a base tool to form intersecting ribs defining a grid with a plurality of cavities. In the same step fiber material is laid to form one or more; local substructures. Blocks are placed, at the positions of the cavities. The fiber material of the ribs and. the local substructures is impregnated with a resin. Optionally, one or more layers of fiber material are placed on the base tool and/or over the ribs and the blocks to form an outer skin. The ribs, the local substructure and optionally the outer skin jointly consolidated to form, the grid, structure.

A method for manufacturing a centre wing box which includes inner stiffeners, at least one of which has at least one through-hole is described. For each stiffener having at least one through-hole and having a first leg of a first U-shaped and C-shaped profile and a second leg of a second U-shaped and C-shaped profile, the method includes, for each through-hole, the steps of producing a first section of the through-hole in the first U-shaped or C-shaped profile and of producing a second section of the through-hole in the second U-shaped or C-shaped profile before the first and second U-shaped or C-shaped profiles are positioned on the mould.

A resin impregnation measurement system includes first electrodes, second electrodes, a measurement controller, and an impregnation ratio deriving unit. The first electrodes extend in parallel. The second electrodes are disposed so as to oppose to the first electrodes across a container and extend in a direction intersecting the first electrodes. The container is configured to be filled with a resin. The measurement controller is configured to sequentially switch between the first electrodes and the second electrodes and measure electrostatic capacities of measurement regions where the first electrodes are opposite to the second electrodes. The impregnation ratio deriving unit is configured to derive an impregnation ratio of the resin to the fiber base material in the container on a basis of a distribution of the electrostatic capacities of the measurement regions.

A composite part layup is compacted and cured on a mandrel using one or more cauls that are sealed together and to the mandrel, creating a vacuum tight enclosure over the composite part layup.

An apparatus for processing a composite structure includes a mandrel that includes a tooling surface and vacuum bagging that includes an elastomeric membrane and a bagging surface. The apparatus also includes a surface interface formed between the mandrel and the elastomeric membrane. The surface interface includes a suction channel formed in at least one of the tooling surface of the mandrel and the bagging surface of the elastomeric membrane. The elastomeric membrane is configured to be sealed to the mandrel along the suction channel in response to a vacuum applied to the suction channel.

A covering device for a component space in a tool for producing fiber composite components is a multi-layer pre-fabricated material cloth provided with a gas-permeable, matrix material-impermeable membrane. A gas-impermeable, matrix material-impermeable film is provided. Membrane and film are connected at their circumferential rims to delimit an evacuation space with a flow aid and closed by a matrix material-tight connection. Gas having passed from the component space through the membrane into the evacuation space is evacuated through an opening of the film away from the component space. A contact element arranged at a side of the film facing away from the evacuation space surrounds the opening of the film. It is connected matrix material-tightly to the film. The contact element has a contact surface at a side facing away from the film for attaching the covering device to an inner side of a tool wall delimiting the component space.

A covering device for a component space in a tool for producing fiber composite components is a multi-layer pre-fabricated material cloth provided with a gas-permeable, matrix material-impermeable membrane. A gas-impermeable, matrix material-impermeable film is provided. Membrane and film are connected at their circumferential rims to delimit an evacuation space with a flow aid and closed by a matrix material-tight connection. Gas having passed from the component space through the membrane into the evacuation space is evacuated through an opening of the film away from the component space. A contact element arranged at a side of the film facing away from the evacuation space surrounds the opening of the film. It is connected matrix material-tightly to the film. The contact element has a contact surface at a side facing away from the film for attaching the covering device to an inner side of a tool wall delimiting the component space.