Short Brothers Plc

B/e Aerospace, Inc.

Rockwell Collins, Inc.

Rohr, Inc.

University of Surrey

Paolo Ballocchi

Damian Christie

Nigel McKibbin

Michael Van Tooren

Daniel O Ursenbach

Sarah Lohman

Ravi Silva

Ryan M Robinson

Shyan Bob Shen

Deepa Jose

Ian Hamerton

Thomas Pozegic

Lynsey Rebbeck

Andrew W Blackwood

Peter Quigley

Sam Wilson

Philip Jenkins

Robert Walsh

Nigel Donaldson

James Alan Phillips

Nigel J Mckibbin

Nigel Mckibbin

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.

Vibration welding fiber-reinforced composite aircraft structures

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.

Aircraft seat base assembly

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.

Aircraft electrical isolation component and method of manufacturing electrical isolation component

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.

Load-transferring connection between structurally loaded components

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.

Composite seat assemblies including high performance fibers

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 10nanostructures per cmof 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.

Fibre-reinforced components including nanostructures

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.

Electrical protector

Growing community of inventors

Dundrum, United Kingdom

Paolo Ballocchi