Abstract: A method of forming a weld joint is provided. A first component having a base portion and a flange extending from the base portion is provided. A second component is provided. The second component and the flange are brought into abutment and a load is applied to the flange via the second component. The flange is biased against the second component by a reaction of the first component to the load. One of the first and the second components is vibrated to form a weld joint between at least a part of the second component and at least a part of the flange.

Abstract: During a formation method, a first component and a second component are provided. The first component is configured from or otherwise includes a first fiber-reinforced thermoplastic composite. The first component also includes a base and a material buildup on a portion of the base. The second component is configured from or otherwise includes a second fiber-reinforced thermoplastic composite. The second component is arranged with the first component. The second component abuts the material buildup. The second component is vibration welded to the first component to provide a weld joint between the first component and the second component. At least a portion of the material buildup is displaced during the vibration welding.

Abstract: A base assembly for an aircraft seat is disclosed. The base assembly may include one or more leg sub-assemblies. Each leg sub-assembly may include a front leg, a rear leg, and a link beam configured to couple the front leg to a portion of the rear leg. At least one of the front leg or the rear leg being at least partially formed of a hybrid composite structure. The link beam being at least partially formed of the hybrid composite structure. The hybrid composite structure formed of at least a first material and a second material, where the first material is different from the second material, the first material including a thermoplastic material configured to provide ductility for the base assembly, the second material being a composite material configured to provide strength for the base assembly.

Abstract: A structural assembly of an aircraft has a fastener extending into first and second structural members. A washer is disposed between the fastener and one of the structural members to electrically insulate the fastener and the structural members. The washer has a core of reinforcement fibers supported in a thermoplastic matrix material. Electrically-insulating outer layers of glass fibers overlay the core.

Abstract: A system may include a fastener strap, a first component, and a second component. The fastener strap may include a strap section, at least one first stiffening rib section, and at least one second stiffening rib section. The first component may include a first strap section channel and at least one first stiffening rib section channel positioned along the first strap section channel. The second component may include a second strap section channel and at least one second stiffening rib section channel positioned along the second strap section channel. When the fastener strap is installed in the first strap section channel, the at least one first stiffening rib section channel, the second strap section channel, and the at least one second stiffening rib section channel, a load-bearing connection may be formed between the first component and the second component.

Abstract: A head-pan diaphragm structure attachable to or an integral part of a seat back structure, the head-pan diaphragm structure including high-performance fibers and the head-pan diaphragm structure positionable in a head strike target area of the seat back structure. A seat back assembly including a seat back frame member including spaced portions, a torsion bar attached between the spaced portions, a head-pan diaphragm structure positioned in a framed opening formed by the torsion bar and a portion of the seat back frame member, the head-pan diaphragm structure positioned in a head strike target area, and the head-pan diaphragm member including integrated high-performance fibers.

Abstract: Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.

Abstract: A head-pan diaphragm structure attachable to or an integral part of a seat back structure, the head-pan diaphragm structure including high-performance fibers and the head-pan diaphragm structure positionable in a head strike target area of the seat back structure. A seat back assembly including a seat back frame member including spaced portions, a torsion bar attached between the spaced portions, a head-pan diaphragm structure positioned in a framed opening formed by the torsion bar and a portion of the seat back frame member, the head-pan diaphragm structure positioned in a head strike target area, and the head-pan diaphragm member including integrated high-performance fibers.

Abstract: A structural assembly of an aircraft has a fastener extending into first and second structural members. A washer is disposed between the fastener and one of the structural members to electrically insulate the fastener and the structural members. The washer has a core of reinforcement fibers supported in a thermoplastic matrix material. Electrically-insulating outer layers of glass fibers overlay the core.

Abstract: A system may include a fastener strap, a first component, and a second component. The fastener strap may include a strap section, at least one first stiffening rib section, and at least one second stiffening rib section. The first component may include a first strap section channel and at least one first stiffening rib section channel positioned along the first strap section channel. The second component may include a second strap section channel and at least one second stiffening rib section channel positioned along the second strap section channel. When the fastener strap is installed in the first strap section channel, the at least one first stiffening rib section channel, the second strap section channel, and the at least one second stiffening rib section channel, a load-bearing connection may be formed between the first component and the second component.

Abstract: Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.

Abstract: An electrical protector with a central axis includes a cap defining a top and a downwardly extending cap wall, and insert defining a ring and an upwardly extending insert wall, at least three protrusions extending inwardly from an interior surface of the insert wall toward the central axis, and a sealant disposed at least within the cap. The cap wall engages the insert wall, thereby establishing a connection between the cap and the insert. The protrusions are adapted to engage a structure, thereby securing the electrical protector onto the structure.

Abstract: An electrical protector with a central axis includes a cap defining a top and a downwardly extending cap wall, and insert defining a ring and an upwardly extending insert wall, at least three protrusions extending inwardly from an interior surface of the insert wall toward the central axis, and a sealant disposed at least within the cap. The cap wall engages the insert wall, thereby establishing a connection between the cap and the insert. The protrusions are adapted to engage a structure, thereby securing the electrical protector onto the structure.

Abstract: A method of forming a nanocomposite material that includes nanoparticles includes disposing in a forming apparatus a fiber material, a carrier material with nanoparticles dispersed therein, the carrier material having a releasing trigger to release the nanoparticles, the releasing trigger being at least one of a releasing temperature and a releasing pressure, and a resin having an infusion temperature, increasing the temperature within the forming apparatus to a temperature at least equal to the infusion temperature of the resin to allow the resin to impregnate the fiber material without triggering the releasing trigger of the carrier material, and triggering the releasing trigger of the carrier material in the forming apparatus by increasing at least one of the temperature and the pressure within the forming apparatus to cause dispersion of the nanoparticles.

Abstract: A propeller propulsion unit for aircrafts in general including a rotation shaft driven by a motor, the unit including a single-blade propeller and a counterweight that are connected to the shaft, the counterweight being arranged in a substantially diametrical position with respect to the single blade in order to balance the moment generated by centrifugal force and being variably offset with respect to the axis of the blade in order to balance the moment generated by the traction force of the single-blade propeller.