Abstract: A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.

Abstract: The present invention regards an article (5) comprising at least one composite material, comprising matrix material (19) and at least one micro-sized reinforcement element distributions (23), arranged in plies (13) positioned on top of each other. The nano-sized reinforcement elements (17, 17?, 17?, 17??) are arranged in between and/or inside the micro-sized reinforcement element distributions (23), the nano-sized reinforcement elements (17, 17?, 17?, 17??) having matrix material accumulation properties so as to provide a tailored increased reinforcement volume of said one or more distributions (23). The present invention regards a method for manufacture of a composite article (5) and use of the article (5).

Abstract: An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

Abstract: An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system.

Abstract: The present invention regards an article (5) comprising at least one composite material, comprising matrix material (19) and at least one micro-sized reinforcement element distributions (23), arranged in plies (13) positioned on top of each other. The nano-sized reinforcement elements (17, 17?, 17?, 17??) are arranged in between and/or inside the micro-sized reinforcement element distributions (23), the nano-sized reinforcement elements (17, 17?, 17?, 17??) having matrix material accumulation properties so as to provide a tailored increased reinforcement volume of said one or more distributions (23). The present invention regards a method for manufacture of a composite article (5) and use of the article (5).

Abstract: An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein.

Abstract: An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system.

Abstract: An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

Abstract: A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.

Abstract: The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano-engineered composite material layer (5) comprising a set of electrodes arranged (7?, 7?) in at least an upper (P1) and a lower (P2) plane extending parallel with the aerodynamic surface (3); the electrodes (7?, 7?) comprising nano filaments (9); the electrodes (7?) of the upper plane (P1) are arranged in the aerodynamic surface (3) such that they define a smooth and hard aerodynamic surface (3); conductors (11, 11?) of nano filaments (9?) arranged for electrical communication between a control unit (13) and each of the electrodes (7?, 7?), wherein the control unit (13) is adapted to address current between cooperating electrodes (7?, 7?) of the upper and lower plane (P1, P2) from a current supply depending upon air flow characteristic signals fed from air flow sensor means (19).

Abstract: A de-icing/anti-icing system including at least two conductive structures embedded in an article that includes an outer surface designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. A first of the conductive structures includes a first conductive nano structure and a second of the conductive structures includes a second conductive nano structure. A conductive property of the first of the conductive structures differs from a conductive property of the second of the conductive structures. The first conductive nano structure serves as a heating conductor and the second conductive nano structure serves as a heating element. The first and second conductive nano structures are embedded in a common plane of a resin layer forming the outer surface.

Abstract: A structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure arranged within the composite joint. A method of producing a structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure and an aircraft structure comprising such structural composite parts.

Abstract: A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.

Abstract: The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano-engineered composite material layer(5) comprising a set of electrodes arranged (7?, 7?) in at least an upper (P1) and a lower (P2) plane extending parallel with the aerodynamic surface (3); the electrodes (7?, 7?) comprising nano filaments (9); the electrodes (7?) of the upper plane (P1) are arranged in the aerodynamic surface (3) such that they define a smooth and hard aerodynamic surface (3);conductors (11, 11?) of nano filaments (9?) arranged for electrical communication between a control unit (13) and each of the electrodes (7?, 7?), wherein the control unit (13) is adapted to address current between cooperating electrodes (7?, 7?) of the upper and lower plane (P1, P2) from a current supply depending upon air flow characteristic signals fed from air flow sensor means (19).

Abstract: An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein.

Abstract: A de-icing/anti-icing system including at least two conductive structures embedded in an article that includes an outer surface designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. A first of the conductive structures includes a first conductive nano structure and a second of the conductive structures includes a second conductive nano structure. A conductive property of the first of the conductive structures differs from a conductive property of the second of the conductive structures. The first conductive nano structure serves as a heating conductor and the second conductive nano structure serves as a heating element. The first and second conductive nano structures are embedded in a common plane of a resin layer forming the outer surface.

Abstract: A wind turbine blade including an outer surface that serves as an aerodynamic surface when the blade is subjected for an air stream. A resin matrix made of a laminate of at least one ply includes the outer surface. The outer ply includes a nano structure embedded therein such that the filaments of the nano structure in the ply have essentially the same angular orientation relative a plane of the outer surface.

Abstract: A de-icing/anti-icing system including at least two conductive structures embedded in a wind turbine blade. An outer surface is designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. One conductive structure includes a first conductive nano structure. A conductive property of the conductive structure differs from a conductive property of the other conductive structure including a second conductive nano structure, for achieving different degrees of heat depending on the needed mode of the system.

Abstract: An article including an outer surface that serves as an aerodynamic surface when the article is subjected for an air stream. A resin matrix made of a polymeric composite laminate of at least one ply includes the outer surface. The at least one ply includes a nano structure embedded therein such that nano filaments of the nano structure in the ply essentially have the same angular orientation relative the plane of the outer surface. The outer ply is a ply of a laminate including at least two plies. Each ply includes large fibers having an orientation different from or identical to the orientation of large fibers of an adjacent ply.

Abstract: A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.