The present invention relates to a reinforcing structure, such as a reinforcing structure for reinforcing a wind turbine blade, comprising: a first composite element layer comprising at least two carbon fibre reinforced composite elements; a second composite element layer comprising one or more carbon fibre reinforced composite elements; an interlayer sandwiched at least partly between the first and the second composite element layer, the interlayer comprising an electrically conductive portion and a non-conductive portion surrounding the conductive portion, the conductive portion abutting exactly two of the carbon fibre reinforced composite elements comprised in the first composite element layer. A method for manufacturing such a structure is also provided.

Square symmetric composite laminate structures, and sub-modules thereof, are provided, along with methods of forming the same. The square symmetric laminate structures include two or more sub-laminate modules, each comprising: a first ply set consisting of a first ply layer oriented at a first angle and a second ply layer oriented at a second angle, a first sum of the first and second angles being ninety degrees; and a second ply set consisting of a third ply layer oriented at a third angle and a fourth ply layer oriented at a fourth angle, a second sum of the third and fourth angles being ninety degrees; wherein the second ply layer is positioned adjacent the third ply layer and the second and third ply layers are both positioned intermediate the first and fourth ply layers, thereby defining a double-double helix arrangement of the respective ply layers. Associated methods are also provided.

A deployable Kiriform flexure includes first and second sections. The first section of the Kiriform flexure includes a plurality of curved fins arranged about a central axis. The second section of the Kiriform flexure includes a plurality of curved fins arranged about a central axis. Each fin of the second section is joined with a fin of the first section such that the first and second sections share a common central axis in a configuration that produces out-of-plane elastic buckling of the fins to actuate the Kiriform flexure from a substantially flat structure that extends substantially only in two dimensions orthogonal to the central axis to an expanded structure extending substantially in a third dimension parallel to the central axis when at least one of the first and second sections is rotated relative to the other section.

This specification presents sheets including graphitic materials, including sandwich structures, thermoformed or wet-formed single layer or multilayer structures of graphitic materials, and methods of forming a layer of graphitic material. In accordance with one aspect, the specification presents a multi-layer structure comprising a core layer having a core density between 0.01 and 1 g/cm.sup.3; and a skin layer covering the core layer, the skin layer having at least 10% by weight of a graphitic material, the graphitic material having one or more of graphene oxide, reduced graphene oxide, graphene, graphite oxide, reduced graphite oxide and graphite, the skin layer having a skin density of between 0.5 and 2 g/cm.sup.3 , a thickness ratio of the skin layer to the core layer being of between 1:1000 and 1:1.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an acoustic panel and a mount. The acoustic panel includes a perforated face skin, a back skin, a perforated intermediate layer, a first cellular core and a second cellular core. The first cellular core includes a first section and a second section. The first section is between and is connected to the perforated face skin and the perforated intermediate layer. The second section is between and is connected to the perforated face skin and the back skin. The second cellular core is between and is connected to the perforated intermediate layer and the back skin. The mount is attached to the back skin along the second section.

A stacked lamination endplate for a rotor that includes a number of adjacent laminations, stacked one on top of another, wherein each lamination has an identical shape, the shape having a central region, symmetric about a center axis, and a number of spokes, each spoke emanating radially outward from the central region, where each spoke includes a through-hole at its distal end, and wherein the laminations are stacked one on top of another and aligned, enabling, for each spoke, a bolt to be inserted through a corresponding through-hole of each lamination.

The invention relates to a method for manufacture of a product or in completion of a product. A flexible mat (20) is manufactured from an incompletely cured thermo-setting plastic, wherein the mat comprises an article (10) of electrically conductive material. The incompletely cured mat (20) including the article (10) is then formed as a function of a forming tool or to lie against or for contact with a product, whereafter final curing of the mat (20) is executed by supplying electric power to the article (10) or by external heat application or ultraviolet light. The invention also relates to an arrangement and uses.

A unidirectional laminate comprising a fiber reinforced composite material having a main relaxation temperature (Tα) in a range between about 110° C. and 140° C. The composite comprises a plurality of unidirectional reinforcement fibers coated with a sizing composition and a matrix resin. The unidirectional laminate has a tensile modulus of at least 45 GPa at a fiber volume fraction greater than or equal to 50% and fatigue mechanical performance of at least 450 MPa at 1 MM cycles, measured according to ASTM E 739-91.

A wind turbine component, the wind turbine component comprising a laminate of layers with an outer side and an inner side, wherein the outer side faces an exterior of the wind turbine component and the inner side faces an interior of the wind turbine component, the laminate of layers being configured to reflect a radar wave impinging the outer side of the laminate of layers, wherein a reflection loss of the reflected radar wave is below a threshold at a frequency, the laminate of layers comprising: an attenuating layer comprising reinforcing fiberglass or reinforcing carbon fibers, a polymer matrix, and radar absorbing particles; a reflective layer arranged on the inner side of the attenuating layer, the reflective layer being configured to reflect a transmitted portion of the radar wave, the transmitted portion of the radar wave being a portion of the radar wave that has passed through the attenuating layer.

The present invention relates to a wind turbine blade with a blade structure comprising a surface and a load-carrying spar supporting a shell structure, wherein the blade structure comprises functionalized graphene-containing material. The present invention relates to a wind turbine concrete tower comprising a load-carrying structure extending vertically to a height, comprising functionalized graphene-containing material. The invention further relates to use of functionalized graphene-containing material in wind turbine parts. The invention further relates to a method for retrofitting a blade structure and the use of functionalized graphene-containing material in a repair system for wind turbine tower foundations. Furthermore the invention relates to use of at least one sensor containing graphene.