Abstract: A seat and an energy absorbing system for a seat including sequentially activated first and second energy absorbing devices. The first device is resiliently deformable and activates to accommodate less severe dynamic events whereas the second device plastically deforms to accommodate severe dynamic events such as a crash. In use, when a first predetermined load value is exceeded the first device activates until a compressive limit of the first device is reached, after which exceeding a second predetermined load value transfers remaining energy to the second device. In embodiments, the first device operates to permit a limited amount of seat bucket stroking followed by recovery to an original state, and the second device operates to permit continued stroking without recovery to an original state.

Abstract: An aircraft seat may include an integrated tracking system. The tracking system may include at least one track foot and one or more roller bearings. The track foot may include one or more axles and be able to interface with a portion of an aircraft seat track. The one or more roller bearings may be coupled to the one or more axles of the track foot and interface with a top surface of the aircraft seat track to aid in the translation of the aircraft seat.

Abstract: Disclosed are methods and apparatus for disinfecting an interior space in a vehicle such as an aircraft. A method includes determining critical levels of heated air in the interior space of the vehicle required to neutralize effects of at least one predetermined pathogen, providing an apparatus for supplying heated air and positioning the apparatus in the interior space, activating the apparatus to supply the heated air to achieve the determined critical levels of the heated air in the interior space of the vehicle, maintaining the achieved critical levels of the heated air in the interior space for a determined critical time period, and optionally cooling the interior space following completion of the disinfecting process. A disinfecting apparatus may include a heated air generator, blower, controller and optional humidity generator, and may be implemented as a cart for traversing an aisle.

Abstract: 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.

Abstract: A double-shear secured vehicle seating assembly includes an operator seat (e.g., for a pilot or operator of a rotorcraft or like vehicle) and a seat frame structure via which the operator seat is secured to floor tracks in the cabin floor. Floor track grippers attached to the underside of the seat frame structure “grip” the floor tracks by extending down and around an upper portion of the floor track. The floor track grippers are further united with the floor tracks by locking pins that extend through holes in the grippers as well as the floor track itself, which includes a rail and a plurality of evenly spaced holes extending through the rail. The locking pin fully pierces the floor track gripper on a first side, fully piercing the aligned hole in the rail, and at least partially piercing the floor track gripper on the opposing side, creating the double-shear condition.

Abstract: A seat frame structure for a rotorcraft or other vehicle operator seat is convertible between non-breakover and breakover configurations. The structure includes fixed frame members mounted to the cabin floor (e.g., via floor tracks) and pivoting frame members for supporting the operator seat, the pivoting and fixed frame members connected by a bushing assembly. The seat frame structure includes a tilt controller with coupling pins extending into the fixed frame members, locking the structure into the non-breakover configuration. A control lever mounted to the seat frame structure controls the coupling pins via connecting cables; the occupant of the seat may, via the control lever, transition the seat frame structure to the breakover configuration by retracting the coupling pins into the pivoting frame members, enabling rearward rotation of the pivoting frame members (e.g., at least 80 degrees, or contact with the cabin floor).

Abstract: 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.

Abstract: An aircraft seat assembly including first and second stanchions forming interior spaces open through forward slots. A seat pan is pivotally attached to the stanchions and includes rearward extensions that extend through the forward slots and are received in the interior spaces. First and second spring mechanisms reside in the respective first and second interior spaces and are attached at opposing ends to their respective stanchion and to the seat pan. In use, rotating the seat pan toward a deployed position elongates the first and second elongation springs thereby energizing a return force of the spring mechanisms.

Abstract: Seat mounted inboard flight controllers for aircraft pilot seats cause the flight controllers to move with the pilot and copilot seats as the seats are adjusted forward and aft. The flight controllers are tied to the seats and move with the seats via the extenders and flight controller mounting brackets. The two flight controllers are coupled together using a linear bearing. One half of the linear bearing is attached to the inboard side of the flight controller. The other half of the linear bearing attaches to the inboard side of the copilot cyclic flight controller. The flight controllers attach to a mounting bracket that extends down to the extenders that attach to the seats. A complete load path is formed between the pilot and copilot seats that support the flight controllers without mounting anything to the cockpit center column.

Abstract: 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.

Abstract: An aircraft seating system may include an integrated track locking system. The track locking system may include a track lock. The track lock may include a base fitting, securing the seat to the seat track when the seat track feet are between a metered position. The track lock may also include a shaft, a locking hole, and a confinement hole. The track locking system may include a through hole, where the shaft of the track lock is able to fit within the through hole. The track locking system may include a locking cavity. The track locking system may include one or more recesses on at least one face of the locking cavity. The track locking system may include a locking member secured by the one or more recesses and the locking hole. The track locking system may include a confinement member secured by the confinement hole via the through hole.

Abstract: A cabin attendant seat is disclosed. The seat may include a seat pan and a seatback. The seat may include a device holder coupled to the seat pan. The device holder may include a main body including a plurality of main body walls that define a main body cavity and a cover including a plurality of cover walls that define a cover cavity. The main body cavity and the cover cavity may form a device holder cavity configured to stow a mobile device. The device holder may include an opening configured to receive the mobile device. The device holder may include a device securing assembly configured to rotate between a first and second position, when in the first position the securing assembly configured to secure the mobile device within the cavity, when in the second position the mobile device configured to be removed from the device holder cavity.

Abstract: A flight controller ingress and egress system is implemented using an assembly. The assembly pivots an outboard flight controller. The pivoting of the outboard flight controller creates a space for the pilot to ingress and egress through the aircraft door more easily. The assembly improves pilot safety and convenience when during ingress and egress from the aircraft. The assembly includes a seat bracket, a pivot bracket, a carriage, and a link.

Abstract: 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.

Abstract: 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.

Abstract: A leg rest assembly is disclosed. The assembly may include a support sub-assembly configured to provide at least one of leg support or foot support. The support sub-assembly may include a panel and a support cushion. The support cushion may include a cavity defined by one or more surfaces of the support cushion. The assembly may include a translation sub-assembly configured to translate the support sub-assembly. The translation sub-assembly may include one or more translation arms. The translation sub-assembly may include one or more guide rails. The translation sub-assembly may include one or more linear bearings configured to engage with the one or more guide rails, the one or more linear bears slideable along a length of the one or more guide rails. The translation sub-assembly may include one or more translation devices configured to translate the support sub-assembly between a first position and one or more additional positions.

Abstract: A cabin attendant seat is disclosed. The seat may include a seat pan and a seatback. The seat may include a device holder coupled to the seat pan. The device holder may include a main body including a plurality of main body walls that define a main body cavity and a cover including a plurality of cover walls that define a cover cavity. The main body cavity and the cover cavity may form a device holder cavity configured to stow a mobile device. The device holder may include an opening configured to receive the mobile device. The device holder may include a device securing assembly configured to rotate between a first and second position, when in the first position the securing assembly configured to secure the mobile device within the cavity, when in the second position the mobile device configured to be removed from the device holder cavity.

Abstract: 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.

Abstract: A shaft locking mechanism includes a rack disposed on a translating shaft and a toothed locking lever disposed on a corresponding translation post. The toothed locking lever engages the rack in a locked orientation to prevent the shaft translating within the translation post. The toothed locking lever is disengaged during translation and the shaft may be translated and locked in place with very granular adjustability. A control rod release mechanism may be biased to maintain the toothed locking lever in the locked orientation. A cam feature on the toothed locking lever engages the body of the control rod which defines a recessed portion that coincides with the cam while in an unlocked orientation.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes an input device configured to receive user input. The system further includes a controller coupled to the ejection system and to the input device and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the user input.