An optical analysis device for determining particulate matter includes three light sources having different wavelengths, an apparatus for combining the three transmitted light beams on a common optical path, a measurement volume, an optical axis in the forward scattering direction that defines the scattering angle 0°, a light absorption apparatus at 0° that absorbs unscattered light, and six detectors arranged at different specified angles which are as close as possible to 0° directly next to the light absorption apparatus, at a second scattering angle between 7° and 40°, at a third scattering angle between 41° and 70°, at a fourth scattering angle between 71° and 115°, at a fifth scattering angle between 116° and 145°, at a sixth scattering angle between 146° and 180°. A control and evaluation unit controls the light sources such that the scattered light is detected in a wavelength selective manner by the detectors.

A load structure may include a panel, a layer of fibrous material, and/or an over mold coating. The panel may include a core. The layer of fibrous material may be disposed on a first side of the panel and an edge of the panel. The over mold coating may be disposed on a second side of the panel.

A manufacturing system (1) for manufacturing shaped laminates including: forming tools (2.1, 2.2) extending along a longitudinal direction X, located parallel to one another and configured to receive a laminate (4) between the forming tools; a shaping tool (3) extending along the longitudinal direction X and along a transversal direction Z, and configured to receive the laminate (4) on an external surface of the shaping tool, wherein the forming tools (2.1, 2.2) or the shaping tool (3) are movable in the longitudinal direction X and in the transversal direction Z, relative to the at least one of the shaping tool (3) and the two forming tools (2.1, 2.2).

A manufacturing system (1) for manufacturing shaped laminates including: forming tools (2.1, 2.2) extending along a longitudinal direction X, located parallel to one another and configured to receive a laminate (4) between the forming tools; a shaping tool (3) extending along the longitudinal direction X and along a transversal direction Z, and configured to receive the laminate (4) on an external surface of the shaping tool, wherein the forming tools (2.1, 2.2) or the shaping tool (3) are movable in the longitudinal direction X and in the transversal direction Z, relative to the at least one of the shaping tool (3) and the two forming tools (2.1, 2.2).

The present invention relates to a method and a mould system (66) for manufacturing at least two preforms for moulding a wind turbine blade. The preforms include at least one preform of a first shape and at least one preform of a second shape. The preform mould structure (68) has a moulding surface (70) of variable shape such that the shape of the moulding surface (70) can be varied at least between a first and a second configuration by using actuators.

A three-dimensional component is produced in a simplified molding operation. Expandable substrates, which are referred to as blanks, are created by compressing thermobonded nonwovens after heating the binder material above its melting temperature, and then cooling the compressed nonwovens so that the binder material hardens and holds the fibers of the nonwoven together in a compressed configuration with stored kinetic energy. Boards can be formed by laminating two or more blanks together and/or by laminating the blanks with other materials, including non-expendable materials. A mold for the component to be manufactured can be partially filled with a number of boards (or blanks) in a stacked, vertically, adjacent or even random orientation. In addition, the boards or blanks may be cut to create desired shapes of parts that can be placed in the mold.

A control surface for an aircraft may comprise an outer skin and a core coupled to the outer skin. The core may include a plurality of corrugations. A height of the core may decrease in a direction extending from a leading edge of the control surface to a trailing edge of the control surface.

A control surface for an aircraft may comprise an outer skin and a core coupled to the outer skin. The core may include a plurality of corrugations. A height of the core may decrease in a direction extending from a leading edge of the control surface to a trailing edge of the control surface.

The present disclosure generally relates to systems and methods for composites, including short-fiber films and other composites. In certain aspects, composites comprising a plurality of aligned fibers are provided. The fibers may be substantially aligned, and may be present at relatively high densities within the composite. For example, the composite may include substantially aligned carbon fibers embedded within a thermoplastic substrate. The composites may be prepared, in some aspects, by dispersing fibers by neutralizing the electrostatic interactions between the fibers, for example using aqueous liquids containing the fibers that are able to neutralize the electrostatic interactions that typically occur between the fibers. The liquids may be applied to a substrate, and the fibers may be aligned using techniques such as shear flow and/or magnetism. Other aspects are generally directed to methods of using such composites, kits including such composites, or the like.

The present disclosure generally relates to systems and methods for composites, including short-fiber films and other composites. In certain aspects, composites comprising a plurality of aligned fibers are provided. The fibers may be substantially aligned, and may be present at relatively high densities within the composite. For example, the composite may include substantially aligned carbon fibers embedded within a thermoplastic substrate. The composites may be prepared, in some aspects, by dispersing fibers by neutralizing the electrostatic interactions between the fibers, for example using aqueous liquids containing the fibers that are able to neutralize the electrostatic interactions that typically occur between the fibers. The liquids may be applied to a substrate, and the fibers may be aligned using techniques such as shear flow and/or magnetism. Other aspects are generally directed to methods of using such composites, kits including such composites, or the like.