A composite material laying structure, a composite material vehicle body, and a composite material laying method, the composite material laying structure comprising a profile provided with multiple quadrilateral cavities reinforced by lap joints after butt joint connection, the quadrilateral cavities comprising square cavities and profile cavities, and the square shape of the square cavities transitioning along the profile into the trapezoidal shape of the profile cavities. The present composite material laying structure employs the laying structure of the composite material profile and a butt joint lap-joint form.

A mold assembly for manufacturing a composite part with a stiffener, the mold assembly includes a bottom mold configured to form a first surface of the composite part, wherein the bottom mold has at least one elongated recess configured to form a stiffener in the composite part; a feeder unit having a shape corresponding to the at least one elongated recess, wherein the feeder unit is configured to fit at least partially into the at least one elongated recess; and a top mold configured to form a second surface of the composite part opposite to the first surface. Also a method of manufacturing a composite part using such a mold assembly, which includes draping a flat laminate over the bottom mold and pushing portions of the laminate into the at least one elongated recess.

In a method of producing symmetrical carbon fiber reinforced composite parts, a plurality of sheets of fibrous material configured as a single structure are positioned on a tool surface where the single structure is comprised of a first composite part joined to a symmetric, second composite part. The single structure is infused with resin and cured on the tool surface, producing a single cured structure comprised of a first cured composite part joined to a second cured composite part. The single cured structure is then divided along a dividing plane, producing the symmetric first cured composite part and second cured composite part.

A preform for forming a composite structure, such as, but not limited to a panel for a building, house or the like includes a body substantially formed of a reinforcing material. The reinforcing material defines one or more compartments or sections. The compartments are fillable with a granular filler material through which settable liquid matrix material is impregnatable to form the composite structure. There is also disclosed a composite structure, a panel and related methods of forming the preform, the composite structure and the panel.

Freeform, additive manufacturing equipment, processes and products, including residential, commercial and other buildings. A movable extruder places extrudate that solidifies in open space to create scaffolding or skeletons of buildings and other products. Elongated extrudate elements are fused to each other or connected by other means to form a cellular structure. Filler material such as polymeric insulating foam may simultaneously or thereafter be placed within the cellular structure to contribute desired strength, rigidity, insulative, barrier or other properties. Finish materials may also be applied.

This shaping structure (1) comprises two shaping sheets (5, 7) facing each other at a distance from one another. According to the invention, the shaping structure (1) further comprises a macroporous spacer sheet (9), the spacer sheet (9) being arranged between the two shaping sheets (5, 7) and being corrugated in such a way as to form a series of alternating even peaks (18) and odd peaks (20) distributed in a first direction (D1) of the shaping structure, at least one of the even peaks (18) being attached to the first shaping sheet (5), at least one of the odd peaks (20) being attached to the second shaping sheet (7), each peak (18, 20) attached in this way defining an attachment surface (22, 26) for attachment to the shaping sheet (5, 7) to which this peak (18, 20) is attached.

According to one implementation, a composite material molding jig 3 includes a tubular member 5 and at least one rigid plate member 6 (6A, 6B) so that a composite material structure O (O1, O2) having a hollow structure can be formed easily. The tubular member 5 has flexibility. The at least one rigid plate member 6 (6A, 6B) reinforces strength of the tubular member 5 partially. The tube is used in a state where air is introduced inside the tube. Further, according to one implementation, a composite material molding method includes using the above-mentioned composite material molding jig 3 in order to produce a composite material structure O (O1, O2) so that the composite material structure O (O1, O2) having a hollow structure can be formed easily.

In a method of producing symmetrical carbon fiber reinforced composite parts, a plurality of sheets of fibrous material configured as a single structure are positioned on a tool surface where the single structure is comprised of a first composite part joined to a symmetric, second composite part. The single structure is infused with resin and cured on the tool surface, producing a single cured structure comprised of a first cured composite part joined to a second cured composite part. The single cured structure is then divided along a dividing plane, producing the symmetric first cured composite part and second cured composite part.

A plugged stringer on a surface of a part, and a method and assembly for production of the plugged stringer. The plug has opposite first and second axial end faces. The plug also has a radially outer margin defined by a radially outer bottom face, radially outer first and second opposite side faces, and a radially outer top face. The plugged stringer also includes a covering overlaying the radially outer top face and the first and second opposite side faces of the plug and extending away from the plug along an axis to form a stringer having first and second segments delineated by the plug. The radially outer margin of the plug is at least partly covered by an adhesive. The radially outer bottom face is adhered to the surface of the part, and the covering is adhered to the radially outer first and second opposite side faces and the radially outer top face. The first and second segments of the stringer respectively define first and second fluid passages separated by the plug. The first fluid passage is fluidly isolated from the second fluid passage by the plug.

A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.