Abstract:
The present invention regards an aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) by means of a bonding material (15). It also regards a method of manufacture of the aircraft structure. The bonding material (15) comprises a non-structural fiber reinforced resin system, wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15), due to settlement of resin of the non-structural fiber reinforced resin system in said interior face filling volume (21) during the viscous phase of the curing of the non-structural fiber reinforced resin system.
Abstract:
The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 80 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most of or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 and the stack further comprises a plurality of plies having fibres substantially in the same direction 811 as the longitudinally direction L of the article 801 and / or a plurality of plies having fibres in the diagonal direction (812, 813, 815, 816, 817, 818) of the longitudinal direction (L) of the article (801), wherein at least one of the ply / plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 comprise fibres that are stiffer than the fibres in the other plies which have less stiff fibres. The present invention also relates to a method of forming an article on a tool, the tool having one longitudinal direction L and one transversal direction T.
Abstract:
The present invention regards an aircraft article composite forming tool (3) and a method for producing the tool (3), the aircraft article (2) to be formed comprises a composite material including an outer surface (9), the aircraft 5 article composite forming tool (3) comprises a matrix laminate (11) made of at least an upper ply (P1) including a forming surface (7) for forming said aircraft article (2) and outer surface (9). The upper ply (P1) comprises a nano filament structure (15) embedded 10 therein.
Abstract:
The present invention relates to a composite radius filler for use in an aircraft structure (2), which comprises structural composite parts (7) assembled together to form the aircraft structure (2). The composite radius filler (3) is arranged between rounded sections (5', 5") of the structural composite parts (7) for filling a gap (4) formed between the structural composite parts (7). The composite radius filler (3) is made structural by a nanostructure (23) arranged within the composite radius filler (3) for the reinforcement of the interface between the radius filler (3) and the structural composite part (7). The invention also relates to a method for producing an aircraft structure comprising said nano-reinforced radius filler.
Abstract:
The present invention relates to a reinforced structure (1) and a method for manufacturing a reinforced structure (1) of composite material. The reinforced structure (1) comprises a stiffening element (2) which is attached to the concave surface (37) of a shell element (3). The stiffening element (2) comprises a first profile (5A) and a second profile (5B) connected to each other and forming a web (9). The stiffening element (2) further comprises a reinforcing element (7) of composite material having at least one forming bulge (21) on each of its respective sides (31and 33). The forming bulges (21) extend from an outer edge (27) of the reinforcing element (7) to an inner edge (29) of reinforcing element (7). The height of the at least two forming bulges (21) is highest at the outer edge (27), tapers towards the inner edge (29) and is levelled out at the inner edge (29). The reinforcing element (7) is positioned between the first profile (5A) and the second profile (5B) and forms the web (9) of the stiffening element (2).
Abstract:
The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 801 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 and substantially in the same direction 811 as the longitudinally direction L of the article 801, wherein the bottom ply and the top ply have fibres in a substantially orthogonal direction 810 to the longitudinal L direction of the article 801, at least one ply has the fibres substantially in the same direction 811 as the longitudinal direction L of the article 801, wherein at least one of the ply/plies having fibres substantially in the longitudinal direction L comprise/s particles selected from the group of thermoplastic tougheners, nano particles, micro particles, elastic particles, elastomer particles and polymer particles or a combination of them. The present invention also relates to an method of forming an article on a tool.
Abstract:
The present invention regards a structural article comprising an outer surface (5), which serves as an aerodynamic surface when the structural article (1) is subjected for an air stream, the structural article (1 ) comprises a resin matrix laminate (7) including an upper ply (P1 ) and a bottom ply (P3, P4, P6)$ a heating element (13) is arranged in contact with the bottom ply (P3, P4, P6) and coupled to a power supply unit (45) in purpose to de-ice/anti-ice the outer surface (5). Each ply (P1, P2.... P6) comprises a thermally conductive filament structure (9) having a filament orientation such that the prolongation of the filaments (11 ) has an extension essentially perpendicular to the extension of the laminate (7).
Abstract:
The present invention regards a method of producing a forming tool and the forming tool for forming an article, the forming tool (1) comprises a composite face sheet (7) having a forming surface (29) and an inner surface (17) opposite the forming surface (29), and further comprises a support structure being attached to the inner surface (17) of the composite face sheet (7). The support structure comprises a support shell (9, 9', 9") of composite having a first surface (27) facing the inner surface (17) of the composite face sheet (7) and having a second surface (28) opposite the first surface (27), the support structure further comprises distance members (11, 31), and the support shell (9, 9', 9") is fixed at a distance from the composite face (7) sheet by means of the distance members (11, 31).
Abstract:
The present invention regards a structural composite part made of pre-impregnated fibre plies (5). The edges (7) of two adjacent fibre plies (5) are connected via a longitudinal composite joint (9) made structural by a nanostructure (41) arranged within the composite joint (9). The invention concerns also a method of producing a structural composite part (11) made of pre-impregnated fibre plies wherein the edges (7) of two adjacent fibre plies (5) are connected via a longitudinal composite joint (9) made structural by a nanostructure (41) and an aircraft structure, such as a wing, comprising such structural composite parts (11).
Abstract:
The present invention regards an aircraft structure comprising structural composite parts (5) assembled together to form said aircraft structure (3); said aircraft structure (3) further comprises a bonding interlayer material provided (17) to bond said structural composite parts (5) to each other. The bonding interlayer material (17) comprises a nanostructure enhanced material (20, 21). The invention also regards a method of producing an aircraft structure of assembled structural composite parts (5), being cured or semi-cured before said assembly.