Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.

Abstract: To improve the complicated painting process of large three-dimensionally shaped components, preferably aircraft components, the masking step is automated. This is achieved by printing a masking medium onto the component with an inkjet method, the masking medium forming a masking film. The masking film masks the desired surface area and can be pulled off following the end of the painting. Preferably, spray films, functional printing inks or mold release agents are used as the masking medium.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.

Abstract: To improve the complicated painting process of large three-dimensionally shaped components, preferably aircraft components, the masking step is automated. This is achieved by printing a masking medium onto the component with an inkjet method, the masking medium forming a masking film The masking film masks the desired surface area and can be pulled off following the end of the painting. Preferably, spray films, functional printing inks or mold release agents are used as the masking medium.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.

Abstract: A forming tool for forming a semi-finished product comprising reinforcement fibers and being conveyed to the forming tool in a continuous process. The forming tool comprises at least one pressure bag configured to be pressurized during a forming step of the semi-finished product, during which the semi-finished product is sandwiched between a forming surface of a forming element and the at least one pressurized pressure bag, such that the semi-finished product substantially takes on the shape of the forming surface. Further, a forming apparatus and a forming method for forming a semi-finished product comprising reinforcement fibers are provided.

Abstract: An arrangement for producing a composite material component comprises a bagging configured to seal a receiving space for a semi-finished part against the ambient atmosphere. The bagging is a thermoformed bagging having a shape which, at least in sections, corresponds to a shape of the semi-finished part and which comprises an air-tight outer layer and an inner separation layer. The inner separation layer is configured to allow the bagging to be separated from the composite material component made from the semi-finished part. The arrangement further comprises a vacuum source connected to the receiving space and configured to generate a reduced pressure within the receiving space. The arrangement also comprises a curing apparatus configured to cure a thermoset plastic material either contained in at least one element of the semi-finished part or injected into the receiving space when the semi-finished part is sealed within the receiving space via the bagging.

Abstract: A setup device for manufacturing a fuselage barrel, made of a fiber composite material, for an aircraft is provided. The setup device for the purpose of reinforcement includes several stringers arranged so as to be spaced apart from each other. The stringers include a base structure to form a load-bearing rigid substructure that is connected to an outwardly curved supporting surface that can be adjusted by means of actuators for the positive setup of the fuselage barrel to be manufactured with the help of form channels for accommodating the stringers. The actuators, designed as pressure-means cylinders, move one or several form channels in radial direction. The form channels are interconnected longitudinally by means of a flexible intermediate element for forming a ring-shaped supporting surface that is closed in a vacuum-tight manner and that overall is able to adjust itself in radial direction.

Abstract: A method for manufacturing an aircraft structure component of fiber composite material, wherein a semifinished first part made of a dry fiber preform is provided, a semifinished second part made of either a dry fiber preform or a hardened fiber matrix composite is provided, a semifinished aircraft structure component is prepared by placing the semifinished first part against the semifinished second part, such that a first connection surface rests against a second connection surface, matrix material is infused through the semifinished aircraft structure component, and the semifinished aircraft structure component is cured. Before infusing matrix material through the semifinished aircraft structure component, an intermediate layer for assisting adhesion is applied between the first connection surface and the second connection surface.

Abstract: The invention relates to a rod-shaped base body with at least one bearing surface which can be brought to bear against at least one counter-bearing surface of a bearing device for fastening to a further rod-shaped base body and/or a functional component for forming a framework. The rod-shaped base body can be a fiber-composite material, particularly carbon-fiber-reinforced plastic, and the rod-shaped base body has a recess as positioning mark determining the position of the further base body and/or the functional component in relation to the rod-shaped base body in the framework by the positive engagement due to the at least one bearing surface and at least one counter-bearing surface bearing against one another. The invention also includes a framework system having a rod-shaped base body of this type. The object of the invention is additionally achieved by a method for producing a rod-shaped base body of this type.

Abstract: An arrangement for producing a composite material component comprises a bagging configured to seal a receiving space for a semi-finished part against the ambient atmosphere. The bagging is a thermoformed bagging having a shape which, at least in sections, corresponds to a shape of the semi-finished part and which comprises an air-tight outer layer and an inner separation layer. The inner separation layer is configured to allow the bagging to be separated from the composite material component made from the semi-finished part. The arrangement further comprises a vacuum source connected to the receiving space and configured to generate a reduced pressure within the receiving space. The arrangement also comprises a curing apparatus configured to cure a thermoset plastic material either contained in at least one element of the semi-finished part or injected into the receiving space when the semi-finished part is sealed within the receiving space via the bagging.

Abstract: A device for automatically laying and draping a plurality of web-form portions of a dry sheet-like formation, in particular of a multiaxial laid fiber fabric and/or a woven reinforcing fabric to create a profiled preform on a core by repeated laying and draping of the portions in order to produce a reinforcing profile with a composite material. Accordingly at least one portion, is kept in at least one cassette between two roller conveyors ready for laying on the core. As a result of the preferably simultaneous laying of preferably more than one prefabricated portion of the sheet-like formation on the core by means of at least one cassette of the cassette arrangement a profiled preform can be fully automatically laid and draped quickly and with great dimensional accuracy and at the same time with good reproducibility for the production of CRP profiles.

Abstract: A forming tool for forming a semi-finished product comprising reinforcement fibers and being conveyed to the forming tool in a continuous process. The forming tool comprises at least one pressure bag configured to be pressurized during a forming step of the semi-finished product, during which the semi-finished product is sandwiched between a forming surface of a forming element and the at least one pressurized pressure bag, such that the semi-finished product substantially takes on the shape of the forming surface. Further, a forming apparatus and a forming method for forming a semi-finished product comprising reinforcement fibers are provided.

Abstract: An arrangement for reinforcing a fiber composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry are provided. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, together with the pressure element fastened thereto, is then applied in a reproducible manner to the fiber composite component cured to connect the reinforcing element to the fiber composite component. The reversible fastening device and the pressure element are then removed from the reinforced fiber composite component.

Abstract: The invention pertains to a method for manufacturing a FRC/FRP-component component from rovings by means of a molding tool with a mold surface, featuring the steps of: applying rovings formed of dry fibers onto the mold surface by depositing the rovings under tension with predetermined orientations between deflection devices by means of an application device, applying binder material onto the tensioned rovings; consolidating the arrangement of fiber strands and binder material by applying heat and pressure in order to produce a preform for the component to be manufactured; separating the preform from the deflection devices and removing the preform from the molding tool; and carrying out an injection process or infusion process in order to manufacture the component after separating the preform from the deflection devices; as well as to a molding tool and a device for implementing the method.

Abstract: A device and a method for manufacturing a fiber-reinforced fuselage shell for an aircraft, which fuselage shell for the purpose of reinforcement comprises several stringers that are spaced apart from each other, wherein the device includes a base frame comprising several supporting walls of different lengths for forming a curved mounting surface for the fuselage shell to be manufactured, wherein several actuators that extend radially outwards and that are longitudinally adjustable are affixed to the mounting surface, at the distal ends of which actuators in each case mold channels for receiving the stringers are attached, which mold channels are interconnected by means of flexible intermediate elements and/or further mold channels for forming a vacuum-tight closed mold surface.

Abstract: A process for producing fiber preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fiber rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fiber preforms are produced straight from the dry fiber rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fiber strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fiber webs. The described process can also readily be scaled since the number of dry fiber rovings arranged next to one another make it possible to vary the area which can be covered.

Abstract: An apparatus for the production of a fuselage shell for an aircraft made of fiber composite, which is to be equipped with a plurality of stringers disposed spaced apart for reinforcement, comprising a main frame to form a supporting substructure having an outwardly curved mounting surface for positive mounting, having longitudinal mounting grooves for receiving of formed parts for deformably positioning the stringers relative to the mounting surface, wherein a plurality of short formed parts spaced apart from each other are disposed in each mounting groove, and which are adjustable relative to the corresponding mounting groove in the transverse direction (Y) by means of adjusters, and which can be raised in the vertical direction (Z) by means of lifters for guiding the stringers in the direction of a laminating adhesive bonding unit brought over the mounting surface.

Abstract: The present invention provides a method and a device for treating a surface of a fiber composite material which contains fibers of a specific hardness, the surface of the fiber composite material being removed abrasively by an abrasion means, the hardness of which is less than the hardness of the fibers contained in the fiber composite material and is greater than the hardness of a plastics material in which the fibers of the fiber composite material are embedded.

Abstract: A setup device for manufacturing a fuselage barrel, made of a fiber composite material, for an aircraft is provided. The setup device for the purpose of reinforcement includes several stringers arranged so as to be spaced apart from each other. The stringers include a base structure to form a load-bearing rigid substructure that is connected to an outwardly curved supporting surface that can be adjusted by means of actuators for the positive setup of the fuselage barrel to be manufactured with the help of form channels for accommodating the stringers. The actuators, designed as pressure-means cylinders, move one or several form channels in radial direction. The form channels are interconnected longitudinally by means of a flexible intermediate element for forming a ring-shaped supporting surface that is closed in a vacuum-tight manner and that overall is able to adjust itself in radial direction.