Abstract: A fitting for transporting an industrial part, the fitting including: a first fitting member comprising a first surface, and a second fitting member including a second surface, wherein the first surface of the first fitting member includes a protuberance and the second surface of the second fitting member includes a recess, wherein the protuberance and the recess are configured such that the protuberance is insertable in the recess when the protuberance is inserted along the recess the first fitting member and the second fitting member are slidable one on another along at least a first direction.

Abstract: Method of manufacture of one or more pairs of components in composite material (11, 13; 11?, 13?) intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10°, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (11, 13; 11?, 13?), the components of each pair being arranged adjacently and the first components (11, 11?) and the second components (13, 13?) of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.

Abstract: Joining arrangement for the lateral boxes (11, 11?) of a horizontal tail stabilizer with a central tubular box and manufacturing method for said box. The boxes (11, 11?) are joined using an intermediate joining part (31) that comprises a central box (33, 63, 73), upper (35, 35?) and lower (37, 37?) lateral flaps, fitting plates (A) for the trimming device and fitting plates (B) for the pivoting device, the join being made with rivets between the skins (15, 15?; 17, 17?) of the lateral boxes (11, 11?) and said flaps (35; 35?; 37; 37?). The method for manufacturing the intermediate joining part (31) comprises steps to: a) Provide preforms suitable for forming said part (31); b) Form and cure the part (31) made from said preforms using an RTM method.

Abstract: Computer assisted method for the advanced design of bent parts of composite material using a computer assisted CAD system comprising the following stages: a) Supplying the 2D mesh model (11) of the part; b) Generating the 3D outer surface (19) of the part; c) Obtaining the 3D mesh model (51) by adapting the 2D mesh model (11) to the geometry of the 3D outer surface (19) by bending the contour lines (17) of the patterns (13) of the 2D model (11) with respect to some bending lines (23) set up in relation to a bending surface (31) similar to that of the tool provided for bending the part; d) Generating the solid model (53) of the bent part. The invention also relates to a computer program that when it is executed on a computer together with a CAD system it causes the execution of the method.

Abstract: A riveted union arrangement between parts of composite material in which, in the area of the union, at least one of the parts (11) is a strengthened directionally part whose lay-up comprises ply packets (13, 13?, 13?) with the optimum direction for carrying out the load transmission in the union inserted between at least one continuous ply (15) along said union area, where each of those ply packets (13, 13?, 13?) has a different length, so that said directionally strengthened part (11) be structured in the area of the union in stretches (17, 17?, 17?) with a different number of ply packets (13, 13?, 13?).

Abstract: Joining arrangement for the lateral boxes (11, 11?) of a horizontal tail stabiliser with a central tubular box and manufacturing method for said box. The boxes (11, 11?) are joined using an intermediate joining part (31) that comprises a central box (33, 63, 73), upper (35, 35?) and lower (37, 37?) lateral flaps, fitting plates (A) for the trimming device and fitting plates (B) for the pivoting device, the join being made with rivets between the skins (15, 15?; 17, 17?) of the lateral boxes (11, 11?) and said flaps (35; 35?; 37; 37?). The method for manufacturing the intermediate joining part (31) comprises steps to: a) Provide preforms suitable for forming said part (31); b) Form and cure the part (31) made from said preforms using an RTM method.

Abstract: Joining arrangement for two boxes (11, 11?) of composite material with an intermediate part (31) and method for manufacturing said intermediate part (31). The joint is effected using rivets between the skins (15, 15?; 17, 17?) of said boxes (11, 11?) and the upper and lower flanges (33, 35) of said T-shaped part (31). The manufacturing method includes the following steps: a) Providing two C-shaped preforms (41, 41?), configured such that their central sections (43, 43?) are parallel with one another and their upper and lower flanges (55, 55?; 57, 57?) are approximately parallel to the end zones of said skins (15, 15?; 17?, 15?); b) Providing two flat preforms (45, 47) to reinforce the flanges (35, 37); c) Forming and curing the part (31) made from said preforms (41, 41?, 45, 47) using an RTM method.

Abstract: The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas (11, 15) of different thickness and a transition area (13) between both configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics (21, 21?; 29, 29?) extending along the three mentioned areas (11, 13, 15); a second section formed by one or more symmetrical and balanced fabric packets (23) ending in the transition area (13) placed among one or more continuous fabrics (25); a third section formed by a symmetrical and balanced fabric packet (27) extending along the three mentioned areas (11, 13, 15) placed among one or more continuous fabrics (25).

Abstract: Computer assisted method for the advanced design of bent parts of composite material using a computer assisted CAD system comprising the following stages: a) Supplying the 2D mesh model (11) of the part; b) Generating the 3D outer surface (19) of the part; c) Obtaining the 3D mesh model (51) by adapting the 2D mesh model (11) to the geometry of the 3D outer surface (19) by bending the contour lines (17) of the patterns (13) of the 2D model (11) with respect to some bending lines (23) set up in relation to a bending surface (31) similar to that of the tool provided for bending the part; d) Generating the solid model (53) of the bent part. The invention also relates to a computer program that when it is executed on a computer together with a CAD system it causes the execution of the method.

Abstract: Method of manufacture of one or more pairs of components in composite material (11, 13; 11?, 13?) intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10°, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (11, 13; 11?, 13?), the components of each pair being arranged adjacently and the first components (11, 11?) and the second components (13, 13?) of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.

Abstract: The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas (11, 15) of different thickness and a transition area (13) between both configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics (21, 21?; 29, 29?) extending along the three mentioned areas (11, 13, 15); a second section formed by one or more symmetrical and balanced fabric packets (23) ending in the transition area (13) placed among one or more continuous fabrics (25); a third section formed by a symmetrical and balanced fabric packet (27) extending along the three mentioned areas (11, 13, 15) placed among one or more continuous fabrics (25).