Abstract: A method for the preparation of a dry textile preform for a large surface area fiber-reinforced composite component, in which resin-free textile material layers for purposes of manufacturing the preform are tensioned in each case in a tensioning frame, and in the stretched state are laid down on a moulding body by means of a linear relative movement between the tensioning frame and the moulding body. Also disclosed is a device for the execution of a method of this type with a tensioning frame for purposes of tensioning the material layers, and with a clamping unit for purposes of fixing the laid-down material layers on a moulding body.

Abstract: The present invention provides a method as well as a tool (1, 48) for producing a T-stringer, in particular in the aircraft and spacecraft sector. The method is characterized by two lay-up strips (3, 4) being arranged on top of one another, wherein areas (5, 6) of the lay-up strips (3, 4) corresponding to the stringer foot (60) that is to be formed, are spaced apart from one another by means of separation films (7, 8) and areas (14, 15) of the lay-up strips (5, 6) corresponding to a stringer web (61) come into direct contact with one another, in particular, forming a material bond. In a further method step, the lay-up strips (3, 4) are clamped at the areas (14, 15) corresponding to the stringer web (61) that is to be formed.

Abstract: A method for the preparation of a dry textile preform for a large surface area fibre-reinforced composite component, in which resin-free textile material layers for purposes of manufacturing the preform are tensioned in each case in a tensioning frame, and in the stretched state are laid down on a moulding body by means of a linear relative movement between the tensioning frame and the moulding body. Also disclosed is a device for the execution of a method of this type with a tensioning frame for purposes of tensioning the material layers, and with a clamping unit for purposes of fixing the laid-down material layers on a moulding body.

Abstract: In a method for reinforcing a fibre composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fibre composite component to be reinforced to form a mould portion and at least the formed mould portion is cured to connect the at least one reinforcing element to the fibre composite component. The vacuum mat is then removed from the reinforced fibre composite component so that the vacuum mat can be reused.

Abstract: In a method for reinforcing a fiber composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fiber composite component to be reinforced to form a mold portion and at least the formed mold portion is cured to connect the at least one reinforcing element to the fiber composite component. The vacuum mat is then removed from the reinforced fiber composite component so that the vacuum mat can be reused.

Abstract: Disclosed is a method for producing a profiled semifinished fiber composite (FC) product from a semifinished product (2) that is made of dry fiber or prepreg material and is moved through a shaping device (1) in the longitudinal direction (L) of the semifinished product (2). The semi-finished product (2) is moved through the shaping device (1) on a support film in the longitudinal direction (L) of the shaping device (1), between the facing shaping contours of tool parts (11a, 12a). The shaping contours of the cross-sections of the tool parts (11a, 12a) continuously change from a cross-sectional contour in the feeding zone to a shaping contour in the discharge zone. Furthermore, the support piece in the drawing-in zone of the shaping device (2) is made to oscillate such that the semifinished product is transformed into a shapeable state as a result of the frictional heat generated between the support piece and the semifinished product.

Abstract: In a method for reinforcing a fibre composite component for aviation and space flight, a vacuum mat is configured with at least one receiving portion for reproducibly receiving at least one reinforcing element. The at least one reinforcing element is introduced into the at least one receiving portion of the vacuum mat. The vacuum mat with at least one introduced reinforcing element is applied reproducibly in a sealed manner to the fibre composite component to be reinforced to form a mould portion and at least the formed mould portion is cured to connect the at least one reinforcing element to the fibre composite component. The vacuum mat is then removed from the reinforced fibre composite component so that the vacuum mat can be reused.

Abstract: The present invention provides a method as well as a tool (1, 48) for producing a T-stringer, in particular in the aircraft and spacecraft sector. The method is characterized by two lay-up strips (3, 4) being arranged on top of one another, wherein areas (5, 6) of the lay-up strips (3, 4) corresponding to the stringer foot (60) that is to be formed, are spaced apart from one another by means of separation films (7, 8) and areas (14, 15) of the lay-up strips (5, 6) corresponding to a stringer web (61) come into direct contact with one another, in particular, forming a material bond. In a further method step, the lay-up strips (3, 4) are clamped at the areas (14, 15) corresponding to the stringer web (61) that is to be formed.