An assembly for an energy attenuation system is described. The assembly offers a lower profile configuration that fits better into tight spaces that exist in the compact seats that are required for military helicopters. The assembly includes a cable that is oriented and positioned to work with the profile. The assembly includes an actuator which ejecting the pins in a multi-stage sequence. The design of the assembly also ensures the pins cannot back drive when the pins are in the ejected position. Additionally, the pins may have part commonality reducing a unique part of the assembly.

A bulkhead-mounted aircraft seat assembly configured for independent vertical and horizontal adjustment includes an aircraft seat (seatback and seat frame/cushion) for supporting a pilot, passenger, or other occupant. Parallel rails attach to the bulkhead and extend along the bulkhead (vertically or near vertically) with opposing slots set into each rail. A sled translates along the rails via paired sliding members set into the slots, each pair of sliding members connected to an axle extending through the sled. A four-bar linkage attached to the sled and to the aircraft seat; the four-bar linkage extends from a default position to allow the aircraft seat to translate along a horizontal linear rail under the seat while maintaining a stable vertical reference point above the cabin floor. The seat is independently configured for substantially vertical adjustment via a metering plate attached to the bulkhead.

A seat base assembly for an aircraft seat includes parallel rails attached to an aircraft bulkhead, each rail including a slot extending vertically within the rail. The seat (e.g., seatback and seat frame) is attached to a sled capable of vertical translation relative to the bulkhead via slidable members that translate along the slots. The sled includes a hole for accommodating a locking pin controllable by the seat occupant. A metering plate attached to the seat base behind the sled is folded over a lateral axis into a forward and rear layer, the forward layer including holes for the locking pin wherein each hole corresponds to a desired seat height to which the seat may be adjusted by securing the locking pin through the sled hole and metering hole. In response to an impact event, the metering plate deforms to absorb impact energy and control downward deceleration of the seat.

A damping member (1) which has at least two engagement points (2), wherein the damping member (1) has an absorption means, wherein fastening elements (3) are arranged on the damping member (1), and wherein an additional absorption means (4) is provided which brings about shock absorption together with the absorption means.

A collapsible structure is provided and includes a hub, an exterior skin surrounding the hub and a plurality of spokes extending outwardly from the hub to the exterior skin. Each spoke is tapered along a length thereby providing varying stiffness based energy attenuation capabilities

There is disclosed an energy absorption device comprising a plurality of pillars mountable to a ceiling of a hull, each pillar having a fixed portion and a movable portion, the movable portion slidable relative to the fixed portion; a deformable material disposed between the fixed portion and movable portion such that the deformable material resist the sliding movement of the movable portion in one direction; the deformable material further adapted to permanently deform when a blast energy is directed towards the ceiling; and a seat assembly attached to the movable portion, the seat assembly adapted for an occupant.

An aircraft seat assembly including stanchions defining elongated guide channels and elongated motion sleds nested in the guide channels and affixed to a seat bucket. An energy absorber implemented as a wire bender assembly is coupled between the stanchions and the motion sled. In use, the elongated guide channels guide motion of the motion sleds and the wire bender assemblies attenuate energy during a dynamic event exceeding a predetermined threshold load value. The elongated interface between the guide channels and motion sleds serve to transfer excessive loading to the seat frame thereby protecting the seat assembly from damage and the occupant from excessive lumbar spinal loads.

A singular energy absorber and an offset pilot seat including the same. The pilot seat includes a seat base, a seat bucket positioned laterally offset relative to a centerline of the seat base, a singular motion controller movably coupling the seat bucket to the seat base, wherein the singular motion controller is centered relative to the seat bucket and laterally offset relative to the seat base, and the singular energy absorber associated with the singular motion controller, the singular energy absorber operative to maintain relative positions of components of the singular motion controller during normal use of the rotorcraft pilot seat and allow relative motion between the components of the singular motion controller during a dynamic event.

In one aspect, the present disclosure provides a rotorcraft pilot seat including a seat base attachable to floor tracks, a seat bucket positioned laterally offset relative to a centerline of the seat base, and a singular motion controller movably coupling the seat bucket to the seat base, wherein the singular motion controller is centered relative to the seat bucket and laterally offset relative to the seat base. In another aspect, the present disclosure provides a rotorcraft cockpit configuration including a floor defining a well configured to receive retracted landing gear, a pilot seat positioned to one lateral side of the well, and a copilot seat positioned to an opposing lateral side of the well, each seat including an offset configuration.

A mount assembly for mounting a cabin attendant seat to a support structure may comprise a first strap configured to plastically deform in response to a deflection of the support structure. The first strap may comprise a first perforation, a second perforation, and a third perforation located between the first perforation and the second perforation. The perforations may be configured to allow the strap to plastically deform.