A guide wheel (26) for fitting a layer of carbon armor wires around a tubular core (24). The guide wheel (26) has a central cavity (32), an internal circular edge (34), and a peripheral circular edge (38) that extends coaxially at a distance from said internal circular edge (34), the guide wheel (26) includes a plurality of guiding devices (46), each of which is capable of guiding in translation a plurality of carbon armor wires, the guiding devices being mounted around said central cavity (32). The guiding device (46) includes a peripheral redirecting member (50) in order to be able to guide the carbon armor wires to the internal circular edge (34), and a central redirecting member (52) in order to be able to guide said carbon armor wires through a second curved passageway.

A filament winding system includes a storage unit that stores in advance a reference shape of a winding object, and winding conditions including a winding position and a winding angle at which a fiber is wound around the winding object having the reference shape, a guide that is movable relative to the winding object, and feeds the fiber onto the winding object, a rotating device that rotates the winding object, such that the fiber fed from the guide is wound around the winding object, a measuring unit that measures a shape of the winding object, and a controller. When there is a difference between the reference shape stored in the storage unit, and the measured shape of the winding object, the controller corrects the winding conditions so as to reduce or eliminate the difference, and controls the guide according to the corrected conditions.

A machine for filament winding, in particular on a liner for the manufacture of tanks, comprising a displacement system able to drive a body in rotation around its longitudinal axis (A) and to effect a relative displacement of the body with respect to winding means. The winding means comprise a rotating support, mounted so as to rotate around a rotation axis (B), on which are mounted at least two winding systems, each winding system comprising a winding head associated with storage means, so that, by rotation of said rotating support around its rotation axis (B), each winding system can be displaced into an active position for winding fiber via its winding head, and an inactive position in which an operator can perform maintenance operations.

A fiber composite component has two inner elements arranged at a distance from one another, around which inner elements a fiber-reinforced plastics band is wrapped. In order to simplify the production of the fiber composite component, a first fiber-reinforced plastics band is wrapped around a first inner element, and a second fiber-reinforced plastics band is wrapped around a second inner element. The first and the second fiber-reinforced plastics band are wrapped alternately around the first and the second inner element in such a manner that the distance between the inner elements is bridged by the first and the second fiber-reinforced plastics band.

A multi-arm forming device for space on-orbit composite braiding is provided. Through the rotary movement of a combination of circularly arranged mechanical arm-type laying apparatuses relative to a mold, a plurality of hot press laying heads are controlled together to implement high-efficiency and high-freedom winding and braiding formation of a composite member. The retraction and expansion deformation of the gasbag mold is achieved by inflating and deflating based on design, and the overall device is lightened by switching its structural volume in an operating/non-operating state, thereby achieving the purpose of facilitating the lift-off of rockets and the demolding, repair and weight reduction of winding and braiding structural members for operation in space. Additionally, gas in a gasbag can be used as emergency kinetic energy for the movement and attitude adjustment of the overall device in space. High-quality and efficient winding and braiding formation of composites in space are achieved ultimately.

An apparatus and a method for attaching functional elements, e.g. composed of metal, to a component, in particular to a component comprising fiber-reinforced plastic, while using a setting head, wherein the functional element has a contact surface provided with adhesive and wherein the adhesive can be supplied to the setting head in individual depots adapted to the functional elements on a carrier band is characterized in that the functional elements are taken over by a guide device and are each pressable to an adhesive depot and are subsequently guidable with the adhering adhesive depots and separately from the carrier band in the setting head to the setting position in front of a setting die.

A device for holding a fiber texture on an impregnation mandrel of a winding machine, the device including a cross-member forming a support having each of its ends for fastening on one of cheekplates of the mandrel, a central pad carrier mounted on the cross-member and including a pad for pressing against a fiber texture layer wound on the mandrel, two lateral pad carriers mounted on the cross-member and each including a main pad for pressing against the fiber texture layer wound on the mandrel and a lateral pad for pressing against a lateral margin of the fiber texture layer wound on the mandrel, and a mechanism exerting a clamping force urging the pads against the fiber texture layer wound on the mandrel.

A method for producing a structural component part (1) from a fiber-reinforced plastic according to a three-dimensional winding process. Threadlike or strand-shaped fiber material (12) supplied on at least one bobbin (18) is wound around at least one filament carrier (11) in at least one winding pattern by at least one computer-controlled winding device (10). The fiber material (12) is laid down on the filament carrier (11) with a filament tensile force (F.sub.ZN) that is preadjusted by a control device (14). The filament tensile force (F.sub.Zist) is controlled depending on location and/or depending on path in order to take into account specific lay-down locations (29) on the filament carrier (11) in which a lay-down path (28) predefined by the winding pattern is departed from owing to the local geometry at preadjusted filament tensile force (F.sub.ZN).

A multi-arm forming device for space on-orbit composite braiding is provided. Through the rotary movement of a combination of circularly arranged mechanical arm-type laying apparatuses relative to a mold, a plurality of hot press laying heads are controlled together to implement high-efficiency and high-freedom winding and braiding formation of a composite member. The retraction and expansion deformation of the gasbag mold is achieved by inflating and deflating based on design, and the overall device is lightened by switching its structural volume in an operating/non-operating state, thereby achieving the purpose of facilitating the lift-off of rockets and the demolding, repair and weight reduction of winding and braiding structural members for operation in space. Additionally, gas in a gasbag can be used as emergency kinetic energy for the movement and attitude adjustment of the overall device in space. High-quality and efficient winding and braiding formation of composites in space are achieved ultimately.

A filament winding device (100) comprising a liner support device (42) supporting a liner (1), and a hoop winding device (43) that winds a fiber bundle (F) on to the outer peripheral surface (1S) of the liner (1) by rotating centered around the liner (1). The filament winding device (100) is characterized by being capable of simultaneously transporting the liner (1) and the hoop winding device (43), by having the liner support device (42) and the hoop winding device (43) arranged upon a trolley (40A), and moving the trolley (40A).