A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

In an aspect, the present disclosure is directed to a composite structure. The composite structure includes a three-dimensional (3-D) grid structure and at least one monolithic skin layer at least partially enveloping and securing the grid structure. As such, the grid structure is configured to stabilize the composite structure under at least one of: static local buckling and dynamic global buckling.

A flexible coupling for transmitting torque between parts of a transmission shaft system comprises a tubular section of continuous-fibre-reinforced composite material which has been modified to form a living hinge section with reduced bending stiffness to allow flexion of the tubular section. The tubular section may be modified through the provision of a pattern of formations within the living hinge section. The formations may be in the form of apertures and/or recesses in the continuous-fibre-reinforced composite material to create a plurality of living hinges in the material between, in particular slots and/or grooves.

A flexible coupling for transmitting torque between parts of a transmission shaft system comprises a tubular section of continuous-fibre-reinforced composite material which has been modified to form a living hinge section with reduced bending stiffness to allow flexion of the tubular section. The tubular section may be modified through the provision of a pattern of formations within the living hinge section. The formations may be in the form of apertures and/or recesses in the continuous-fibre-reinforced composite material to create a plurality of living hinges in the material between, in particular slots and/or grooves.

A joint structure includes a reinforcement portion that is formed by joining a composite material and a reinforcing material through an adhesive. The composite material includes a plate portion that is formed by laminating a plurality of fiber sheets, and a raised portion that is formed by laminating a plurality of fiber sheets in addition to the plurality of fiber sheets of the plate portion, and surfaces of the plate portion and the raised portion are covered with a single fiber sheet. The reinforcement portion includes the raised portion and the reinforcing material that is bonded to the raised portion through an adhesive. A first boundary between the plate portion and the raised portion and a second boundary between the raised portion and the reinforcing material are located at different positions in an in-plane direction of a laminated interface between the fiber sheets that are laminated.

A joint structure includes a reinforcement portion that is formed by joining a composite material and a reinforcing material through an adhesive. The composite material includes a plate portion that is formed by laminating a plurality of fiber sheets, and a raised portion that is formed by laminating a plurality of fiber sheets in addition to the plurality of fiber sheets of the plate portion, and surfaces of the plate portion and the raised portion are covered with a single fiber sheet. The reinforcement portion includes the raised portion and the reinforcing material that is bonded to the raised portion through an adhesive. A first boundary between the plate portion and the raised portion and a second boundary between the raised portion and the reinforcing material are located at different positions in an in-plane direction of a laminated interface between the fiber sheets that are laminated.

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.

Methods, systems, and apparatuses are disclosed for the manufacture of composite components having incorporated reinforcing structures machined into composite material substrates, and composite components manufactured according to disclosed methods, and assemblies and larger structures comprising the composite material components.

A method, apparatus, system, and computer program product for designing a composite hollow body. A computer system selects ply layers for the hollow composite body. The ply layers comprise courses having course edges. The computer system positions the course edges between the ply layers throughout the hollow composite body to create a staggering of the course edges between the ply layers for a design of the hollow composite body.