An aircraft device, in particular an aircraft seat device, comprises at least one load-bearing constructional unit, which in at least one outer subregion of the constructional unit consists of a plastic reinforced with reinforcing fibers wherein the reinforcing fibers are distributed at least substantially homogeneously over the entire outer subregion and/or the outer subregion has essential load-bearing properties.

Described herein is a seat back for an aircraft seat, the seat back comprising a body, wherein the body comprises a support wall for supporting a passenger leaning against the seat back, a first side wall, a second side wall and a cross brace, wherein the cross brace connects the first side wall and the second side wall at a position between a lower end and an upper end of each of the side walls, and wherein the support wall, the first side wall, the second side wall and the cross brace are integrally formed. Also described is a seat comprising the seat back and a row of seats.

A failure module includes a support element. A reinforcing element is disposed on the support element. The support element is chemically compatible with the reinforcing element. A homogeneous chemical bond is formed between the support element and the reinforcing element.

Lightweight passenger seats that are especially adapted for use in aircraft cabins. The seats will include a seat back and a seat bottom having a basin which defines a recessed central interior space, a plurality of straps having opposed ends connected to respective upper edge regions of the basin so as to be positioned under tension over the recessed central interior space; and a cover cushion covering the straps and connected to the basin. The seat back may be connected at opposed sides thereof to upright support members adjacent a lumbar region thereof so as to establish an upper region of the seat back above the lumbar region which is capable of being resiliently flexed between upright and rearwardly inclined positions.

In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

Seats and seat assemblies, such as for installation into aircraft, are described herein. In some embodiments, a seat assembly can include a framework configured to be mounted within an aircraft and a plurality of seats coupled to the framework. Each seat can include (a) a seat pan slidably coupled to the framework and (b) a seat back pivotally coupled to the framework and rotatable between an upright position and a reclined position. In some embodiments, the seat back is operably coupled to the seat pan such that movement of the seat back from the upright position to the reclined position moves the seat pan away from seat back to increase the effective recline of the seat.

Described are seat backs (102) for aircraft passenger seats (100). Such a seat back (102) can include a unitary structural core (112) formed as a single piece that includes a body (138) and a flange (140). The body (138) and the flange (140) can each include carbon fiber composite material. The flange (140) can include portions extending from the rearward-facing side (132) of the body respectively along a left lateral side edge, a top (134) side edge, and a right lateral side edge of the unitary structural core (112). The flange (140) can be non-tubular.

A cushion assembly such as an aircraft passenger seat cushion assembly including a solid foam component and an elastomeric lattice insert disposed in a void in the solid foam component, the elastomeric lattice insert having a compression profile that mimics a predetermined compression profile of a solid foam. The elastomeric lattice insert including repeating like cuboid structures such as interconnected repeating face-centered cube structures, interconnected repeating body-centered cube structures, or interconnected repeating kagome structures. The elastomeric lattice insert may be in thermal communication with an air conditioning system for delivering conditioned air through the elastomeric lattice insert.

In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

An airplane seat device has a seat base module, comprising at least one main body which is at least substantially implemented from a rigid foam, at least one comfort element disposed on an upper side of the main body, at least one accommodating region for attaching to a tubular support, and at least one fastening element for attaching to the tubular support, wherein the main body has at least two coupling regions, via which the at least one fastening element can be selectively attached to the main body.