The invention relates to a molding device (1) and a method for the manufacture of structured or semistructured composite components comprising a polymer resin (50) and a fibrous substrate (51). According to the invention, the device comprises a mold (2) comprising a bottom and a lateral surface, a part (10) that is movable along the lateral surface of the mold, comprising a compression surface (14) forming a cavity (7) with the bottom and the lateral surface (5) of said mold (2), characterized in that the movable part (10) comprises a vacuum-drawing channel (13, 23) opening into a chamber (25, 42) located above the cavity and communicating with said cavity (7).

A vertical injection molding machine has a rotary table rotatably in an axial direction as a vertical direction, lower molds on an upper surface of the rotary table, and an upper mold for opening and closing the lower molds, and opening and closing mold in a vertical direction. The vertical injection molding machine has a robot mounted on the lower molds on the plane surface part of the fiber resin base material and a heater for heating the fiber resin base material mounted on the lower molds, and when the plane surface part of the fiber resin base material facing the lower molds is defined as a lower surface, and an opposite surface being defined as an upper surface, an upper and a lower directions of the fiber resin base material is matched to a mold opening and closing direction of the upper mold and the lower molds.

A modular tooling arrangement includes a base member comprising a planar working surface, a frame circumscribing a first cavity at least partially defined by the planar working surface, and a plurality of plates configured to be received in the first cavity for forming a second cavity of a desired shape and size. The plurality of plates at least partially define the second cavity configured to receive a work piece. The plurality of plates may be replaced with plates of various sizes to vary at least one of the size and shape of the second cavity.

A modular tooling arrangement includes a base member comprising a planar working surface, a frame circumscribing a first cavity at least partially defined by the planar working surface, and a plurality of plates configured to be received in the first cavity for forming a second cavity of a desired shape and size. The plurality of plates at least partially define the second cavity configured to receive a work piece. The plurality of plates may be replaced with plates of various sizes to vary at least one of the size and shape of the second cavity.

A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.

A connection (110) between a rim portion (102) and a face portion (104) of a composite wheel (100). The rim portion (102) comprises a first set of fibers (122). The face portion (104) comprises a second set of fibers (124). The connection (110) comprises a transition zone (120) in which the first set of fibers (122) and the second set of fibers (124) are arranged in a layered structure. Each layer (125A, 125B, 125C) of the layer structure includes a first section (127) including an arrangement of the first set of fibers (122), and a first connection end (128), and a second section (129) including an arrangement of the second set of fibers (124), and a second connection end (130). The first connection end (128) is arranged adjacent to or abutting the second connection end (130) forming a layer joint (132A, 132B, 132C). The layer joint (132A, 32B, 132C) of each adjoining layer (125A, 125B, 125C) is spaced apart in a stepped configuration.

A connection (110) between a rim portion (102) and a face portion (104) of a composite wheel (100). The rim portion (102) comprises a first set of fibers (122). The face portion (104) comprises a second set of fibers (124). The connection (110) comprises a transition zone (120) in which the first set of fibers (122) and the second set of fibers (124) are arranged in a layered structure. Each layer (125A, 125B, 125C) of the layer structure includes a first section (127) including an arrangement of the first set of fibers (122), and a first connection end (128), and a second section (129) including an arrangement of the second set of fibers (124), and a second connection end (130). The first connection end (128) is arranged adjacent to or abutting the second connection end (130) forming a layer joint (132A, 132B, 132C). The layer joint (132A, 32B, 132C) of each adjoining layer (125A, 125B, 125C) is spaced apart in a stepped configuration.

A composite material blade molding method is for molding a composite material blade by curing a prepreg. The composite material blade has a back-side blade member and a belly-side blade member which are superposed and joined. The composite material blade molding method includes: a lamination step for forming a back-side laminate in a back-side molding die and forming a belly-side laminate in a belly-side molding die; an inner surface cowl plate disposition step for disposing an inner surface cowl plate for maintaining an inner space formed by the back-side laminate and the belly-side laminate; a die mating step for die-mating the back-side molding die and the belly-side molding die and disposing a foaming agent in the inner space maintained by the inner surface cowl plate; and a curing step for heating and expanding the foaming agent and heat-curing the back-side laminate and the belly-side laminate.

A composite material blade molding method is for molding a composite material blade by curing a prepreg. The composite material blade has a back-side blade member and a belly-side blade member which are superposed and joined. The composite material blade molding method includes: a lamination step for forming a back-side laminate in a back-side molding die and forming a belly-side laminate in a belly-side molding die; an inner surface cowl plate disposition step for disposing an inner surface cowl plate for maintaining an inner space formed by the back-side laminate and the belly-side laminate; a die mating step for die-mating the back-side molding die and the belly-side molding die and disposing a foaming agent in the inner space maintained by the inner surface cowl plate; and a curing step for heating and expanding the foaming agent and heat-curing the back-side laminate and the belly-side laminate.

The invention relates to a method for producing a fibre composite moulded part. The method includes the steps of i) applying a gelatine-containing matrix material onto a fibre material, ii) deforming the fibre material provided with matrix material, and iii) curing the fibre material provided with matrix material.