Abstract: A module element for driving and retaining braiding bobbin carriers on a predetermined bobbin path has at least one base element that can rotate about an axis of rotation, and at least one retaining element that is formed integrally with the base element. The retaining element is configured to releasably hold at least one braiding bobbin carrier offset from the rotary axis.

Abstract: A module element for driving and retaining braiding bobbin carriers on a predetermined bobbin path has at least one base element that can rotate about an axis of rotation, and at least one retaining element that is formed integrally with the base element. The retaining element is configured to releasably hold at least one braiding bobbin carrier offset from the rotary axis.

Abstract: In the method provided herein, quantities of fuel are determined during a direct injection of a motor vehicle. In this connection, within one work cycle, test injections are carried out in two cylinders of an internal combustion engine of the motor vehicle during overrun phases, speed oscillations of moved masses of the cylinders are measured and a relative difference in quantity of the fuel quantity of the test injections within one work cycle is determined from the speed oscillations. By evaluating a relative signal between the test injections within one work cycle in the two cylinders, an intrinsic dependence of the drive train of the quantity of fuel signal is compensated.

Abstract: A module element for driving and retaining braiding bobbin carriers on a predetermined bobbin path has at least one base element that can rotate about an axis of rotation, and at least one retaining element that is formed integrally with the base element. The retaining element is configured to releasably hold at least one braiding bobbin carrier offset from the rotary axis.

Abstract: In the method provided herein, quantities of fuel are determined during a direct injection of a motor vehicle. In this connection, within one work cycle, test injections are carried out in two cylinders of an internal combustion engine of the motor vehicle during overrun phases, speed oscillations of moved masses of the cylinders are measured and a relative difference in quantity of the fuel quantity of the test injections within one work cycle is determined from the speed oscillations. By evaluating a relative signal between the test injections within one work cycle in the two cylinders, an intrinsic dependence of the drive train of the quantity of fuel signal is compensated.

Abstract: A method for production of fiber composite components, particularly suitable for the production of profiles of complicated shape with varying profile cross-section and/or with at least parts with curved lines, such as used for the production of aircraft, for example. The method (a) produces plural core components, (b) separates application of a first fiber material to each of the core components, (c) assembles the core components provided with the first fiber material to form a sequence of core components, (d) applies a second fiber material common to the core component sequence along at least one side of the core component sequence, provided with the first fiber material, (e) impregnates and hardens the first and second fiber materials to form a fiber-reinforced component body, and (f) separates the component body into plural sections as represented by the fiber composite components.

Abstract: In a method, multilayer tailored fiber placement (TFP) preforms of any desired thickness may be easily produced without fixing threads or intermediate layers interfering. Reinforcing fibers are sewn onto a substrate using a chemically or thermally meltable fixing thread thus resulting in the formation of a reinforcing fiber structure. The fixing thread firstly serves to fix the reinforcing fibers on the substrate and is subsequently melted so that the fixing thread disintegrates while pre-fixing the reinforcing fibers and may not influence the mechanical properties of the reinforcing fiber structure.

Abstract: The invention relates to a process and a device for manufacturing a perform (42) for a load path aligned fiber composite structure. The process includes cutting off relatively short fiber band pieces (40, 40?, 40?) from a spread fiber band (14), placing the fiber band pieces (40, 40?, 40?) at a predetermined position and fixing them at this position by means of a binder material (38).

Abstract: A method for production of fiber composite components, particularly suitable for the production of profiles of complicated shape with varying profile cross-section and/or with at least parts with curved lines, such as used for the production of aircraft, for example. The method (a) produces plural core components, (b) separates application of a first fiber material to each of the core components, (c) assembles the core components provided with the first fiber material to form a sequence of core components, (d) applies a second fiber material common to the core component sequence along at least one side of the core component sequence, provided with the first fiber material, (e) impregnates and hardens the first and second fiber materials to form a fiber-reinforced component body, and (f) separates the component body into plural sections as represented by the fiber composite components.

Abstract: Method of producing fiber composite semifinished products by means of a circular braiding technique, a braiding core being braided with braiding threads which are unwound by means of bobbins circling concentrically about the braiding core in different directions, characterized in that the bobbins of one circling direction are fitted with reinforcing threads and the bobbins of the opposite circling direction are at least partially fitted with supporting threads, the supporting threads at least partially consisting of thermoplastic threads.

Abstract: Method of producing fiber composite semifinished products by means of a circular braiding technique, a braiding core being braided with braiding threads which are unwound by means of bobbins circling concentrically about the braiding core in different directions, characterized in that the bobbins of one circling direction are fitted with reinforcing threads and the bobbins of the opposite circling direction are at least partially fitted with supporting threads, the supporting threads at least partially consisting of thermoplastic threads.

Abstract: A fiber composite structural component such as a fitting, bracket, mounting or the like is produced by applying fiber material such as fiber threads or fiber yarns in an automatic circular weaving operation to a core that has at least two sections, to form a fiber material body (6). One core section is removed from the fiber material body when the weaving is completed. The body is then deformed in a mold that has the contour of the finished structural component with at least one mold core section still in the fiber material body. The deformed configuration of the structural component is then impregnated in an RTM device with a resin and hardener followed by curing. Reinforcements may be inserted or secured to the fiber material body prior to the impregnated and curing step.

Abstract: An aerodynamic profile has an adjustable flap, which has a forward profile area as well as a rearward profile area situated in the downward current, bounded by a pressure-side covering skin as well as a suction-side covering skin. The pressure-side and suction-side covering skins converge in the rearward profile area at a trailing profile edge. In the rearward profile area on the underside of the pressure-side covering skin, a flap is swivellably disposed such that, in the inoperative condition, the flap, pointing in the flow direction, rests against the contour of the pressure-side covering skin and, in the deflected condition, the flap encloses an angle with the pressure-side covering skin. An airtight hinge connection is integrated in the flap so that, on the side of the flap protected from the wind, a turbulence system which improves the flow conditions is formed.

Abstract: A method is described whereby multilayer tailored fiber placement (TFP) preforms of any desired thickness may be easily produced without fixing threads or intermediate layers interfering. To this end, the invention provides that reinforcing fibers (1) are sewn onto a substrate (2) using a chemically or thermally meltable fixing thread (3) thus resulting in the formation of a reinforcing fiber structure (5a). The fixing thread (3) firstly serves to fix the reinforcing fibers (1) on the substrate (2) and is subsequently melted so that the fixing thread (3) disintegrates while pre-fixing the reinforcing fibers (1) and does not influence the mechanical properties of the reinforcing fiber structure (5a).

Abstract: A fiber composite structural component such as a fitting, bracket, mounting or the like is produced by applying fiber material such as fiber threads or fiber yarns in an automatic circular weaving operation to a core that has at least two sections, to form a fiber material body (6). One core section is removed from the fiber material body when the weaving is completed. The body is then deformed in a mold that has the contour of the finished structural component with at least one mold core section still in the fiber material body. The deformed configuration of the structural component is then impregnated in an RTM device with a resin and hardener followed by curing. Reinforcements may be inserted or secured to the fiber material body prior to the impregnated and curing step.

Abstract: An aerodynamic profile has an adjustable flap, which has a forward profile area as well as a rearward profile area situated in the downward current, bounded by a pressure-side covering skin as well as a suction-side covering skin. The pressure-side and suction-side covering skins converge in the rearward profile area at a trailing profile edge. In the rearward profile area on the underside of the pressure-side covering skin, a flap is swivellably disposed such that, in the inoperative condition, the flap, pointing in the flow direction, rests against the contour of the pressure-side covering skin and, in the deflected condition, the flap encloses an angle with the pressure-side covering skin. An airtight hinge connection is integrated in the flap so that, on the side of the flap protected from the wind, a turbulence system which improves the flow conditions is formed.