Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.

Abstract: A leading edge structure for an aerodynamic surface of an aircraft with an outer wall part curved in a streamlined manner around an interior compartment and having an inner surface pointing toward the interior compartment and an outer surface provided for contact with the external surrounding flow. The outer wall part has a first outer wall section extending from a leading edge point in an incident flow direction in a convexly curved manner in the direction of a first side. The outer wall part has a second outer wall section which extends from the leading edge point in the incident flow direction in a convexly curved in the direction of a second side. An inner wall part is arranged in the interior compartment opposite the inner surface of the outer wall part and extends from the first outer wall section to the second outer wall section.

Abstract: Method for producing composite components having an undevelopable surface. To be able to maintain the tolerances when manufacturing especially large components in the case of composite components with undevelopable surfaces, it is proposed according to the invention to drape a cut-to-size blank on a molding tool and to determine the deviation of the cut-to-size blank edge from the setpoint cut-to-size edge. Then, on the basis of the deviation, a new cut-to-size blank edge is calculated, and a new cut-to-size blank is created and re-draped for examination purposes. The method is repeated until the deviations are below a tolerable threshold value. The method is furthermore carried out for each textile ply of the composite component.

Abstract: An aerostructure assembly of an aircraft is disclosed having a first aerostructure portion extending in a direction between a first position and a second position and including structurally of at least one rib or spar portion at least partially enclosed by a cover portion; a corresponding second aerostructure portion connected to the first aerostructure portion and extending continuously in the direction from the first aerostructure portion between the second position and a third position and including structurally of at least one further rib or further spar portion at least partially enclosed by a further cover portion. The first aerostructure portion has a first aerodynamic planform area (SI) and the corresponding second aerostructure portion has a corresponding second aerodynamic planform area (S2).

Abstract: A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

Abstract: A leading edge structure for an aerodynamic surface of an aircraft with an outer wall part curved in a streamlined manner around an interior compartment and having an inner surface pointing toward the interior compartment and an outer surface provided for contact with the external surrounding flow. The outer wall part has a first outer wall section extending from a leading edge point in an incident flow direction in a convexly curved manner in the direction of a first side. The outer wall part has a second outer wall section which extends from the leading edge point in the incident flow direction in a convexly curved in the direction of a second side. An inner wall part is arranged in the interior compartment opposite the inner surface of the outer wall part and extends from the first outer wall section to the second outer wall section.

Abstract: Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.

Abstract: In a manufacturing method for a component, a clamping force is applied perpendicular to a surface of a first portion of a semifinished product containing reinforcing fibers via opposing first clamping surfaces of a first clamping tool. A clamping force is applied perpendicular to a surface of a second portion of the semifinished product via mutually opposing first clamping surfaces of a second clamping tool, spaced a first distance from the first clamping tool. A shaping device deforms a third portion of the semifinished product lying between the first and the second portions to form a first subportion and an opposite second subportion. The first distance is reduced to a second distance. A clamping force is applied perpendicular to the surfaces of the first and second subportions via a second clamping surface of the first clamping tool and an opposite second clamping surface of the second clamping tool.

Abstract: The present invention relates to a method of stabilizing a gluten network in a food product. The present invention further provides a dough improver and a method of making said dough improver. Further aspects relate to the use of the dough improver, compositions comprising the dough improver, uses of such compositions, and to food products comprising the dough improver.

Abstract: In a manufacturing method for a component, a clamping force is applied perpendicular to a surface of a first portion of a semifinished product containing reinforcing fibers via opposing first clamping surfaces of a first clamping tool. A clamping force is applied perpendicular to a surface of a second portion of the semifinished product via mutually opposing first clamping surfaces of a second clamping tool, spaced a first distance from the first clamping tool. A shaping device deforms a third portion of the semifinished product lying between the first and the second portions to form a first subportion and an opposite second subportion. The first distance is reduced to a second distance. A clamping force is applied perpendicular to the surfaces of the first and second subportions via a second clamping surface of the first clamping tool and an opposite second clamping surface of the second clamping tool.

Abstract: The present invention provides a method for producing a profile from composite fiber material, in particular in the aviation and aerospace field, having the following steps: A preliminary fabric, particularly made of pre-impregnated fiber material, is first packed in a vacuum bag. Then support elements are laid on the packed preliminary fabric to support the latter. The vacuum bag is then supplied with a vacuum. Next, the preliminary fabric is hardened to the profile under the action of heat, in particularly in an autoclave. With the claimed method the support elements can be formed advantageously from favorable material, in particular aluminum, instead of highly expensive nickel-36 steel, since the support elements are uncoupled mechanically from the preliminary fabric in a longitudinal direction by means of the vacuum bag, enabling movement of the support elements in the longitudinal direction relative to the preliminary fabric.

Abstract: The present invention provides a method for producing a profile from composite fiber material, in particular in the aviation and aerospace field, having the following steps: A preliminary fabric, particularly made of pre-impregnated fiber material, is first packed in a vacuum bag. Then support elements are laid on the packed preliminary fabric to support the latter. The vacuum bag is then supplied with a vacuum. Next, the preliminary fabric is hardened to the profile under the action of heat, in particularly in an autoclave. With the claimed method the support elements can be formed advantageously from favorable material, in particular aluminum, instead of highly expensive nickel-36 steel, since the support elements are uncoupled mechanically from the preliminary fabric in a longitudinal direction by means of the vacuum bag, enabling movement of the support elements in the longitudinal direction relative to the preliminary fabric.