Abstract: Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

Abstract: The energy absorbing assembly may include a seat frame having a base, a seat pan coupled to the seat frame, and a deformable member disposed substantially between the seat pan and the base of the seat frame. In various embodiments, the seat pan is configured to support a passenger in a seated position and the deformable member is configured to undergo plastic deformation in response to a first compressive load on the deformable member.

Abstract: The present disclosure provides a brake assembly for aircraft cabin fixtures. A brake assembly includes a carriage, a lever having a ramp, a shaft, and a pivot, wherein the lever is coupled to the pivot, wherein the shaft is coupled to the lever, and wherein the carriage is configured to ride along the ramp. A brake assembly may comprise a spring in communication with the lever. The shaft may comprise a first end and a brake plate coupled at the first end. The ramp may comprise a slot. A brake assembly may comprise an actuation lever coupled to the carriage.

Abstract: A modular monocoque backrest is provided. The modular monocoque backrest may comprise a front shroud, a back shroud, and an at least one back spar. The front shroud may be coupled to the back shroud, and the back spar may be configured as a mounting point, enabling the modular monocoque backrest to mount to an aircraft floor. The front shroud and the back shroud may comprise a carbon fiber composite material, allowing the modular monocoque backrest to be modular in nature. The carbon fiber composite material may enable the modular monocoque backrest to have a lightweight design while also maintaining resistance to dynamic crash loads.

Abstract: A seat actuation control system is disclosed. The seat actuation control system may permit multiple functions to be controlled by a single actuator. For example, a seat floor tracking function, and a seat pan track and swivel function may be individually controlled by a single actuator, such as a rotary actuator.

Abstract: A contoured stowable seat is provided. The contoured stowable seat may comprise a housing, a seat pan, a contoured backrest, and a deployment lever. The contoured stowable seat may be configured to be in a stowed position and a deployed position. In response to the seat pan being in the deployed position, the deployment lever may contact the contoured backrest, causing the contoured backrest to deploy and form into a contoured shape. The contoured stowable seat may also further comprise a tension cord and a headrest. The contoured backrest may also further comprise a cushion located on the outer surface of the contoured backrest.

Abstract: A modular monocoque backrest is provided. The modular monocoque backrest may comprise a front shroud, a back shroud, and an at least one back spar. The front shroud may be coupled to the back shroud, and the back spar may be configured as a mounting point, enabling the modular monocoque backrest to mount to an aircraft floor. The front shroud and the back shroud may comprise a carbon fiber composite material, allowing the modular monocoque backrest to be modular in nature. The carbon fiber composite material may enable the modular monocoque backrest to have a lightweight design while also maintaining resistance to dynamic crash loads.

Abstract: Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

Abstract: A contoured stowable seat is provided. The contoured stowable seat may comprise a housing, a seat pan, a contoured backrest, and a deployment lever. The contoured stowable seat may be configured to be in a stowed position and a deployed position. In response to the seat pan being in the deployed position, the deployment lever may contact the contoured backrest, causing the contoured backrest to deploy and form into a contoured shape. The contoured stowable seat may also further comprise a tension cord and a headrest. The contoured backrest may also further comprise a cushion located on the outer surface of the contoured backrest.

Abstract: A modular monocoque backrest is provided. The modular monocoque backrest may comprise a front shroud, a back shroud, and an at least one back spar. The front shroud may be coupled to the back shroud, and the back spar may be configured as a mounting point, enabling the modular monocoque backrest to mount to an aircraft floor. The front shroud and the back shroud may comprise a carbon fiber composite material, allowing the modular monocoque backrest to be modular in nature. The carbon fiber composite material may enable the modular monocoque backrest to have a lightweight design while also maintaining resistance to dynamic crash loads.

Abstract: The present disclosure provides a brake assembly for aircraft cabin fixtures. A brake assembly includes a carriage, a lever having a ramp, a shaft, and a pivot, wherein the lever is coupled to the pivot, wherein the shaft is coupled to the lever, and wherein the carriage is configured to ride along the ramp. A brake assembly may comprise a spring in communication with the lever. The shaft may comprise a first end and a brake plate coupled at the first end. The ramp may comprise a slot. A brake assembly may comprise an actuation lever coupled to the carriage.

Abstract: The present disclosure provides a swivel stop comprising a rotating member, a first boss coupled to the rotating member and a second boss coupled to the rotating member, and a second plate having a first interference surface and a second interference surface. An interference between the first boss and the first interference surface and the second boss and the second interference surface tends to limit the rotation of the rotating member with respect to the second plate. The swivel stop may further comprise a rail wherein the second plate is configured to translate along the rail.

Abstract: A seat actuation control system is disclosed. The seat actuation control system may permit multiple functions to be controlled by a single actuator. For example, a seat floor tracking function, and a seat pan track and swivel function may be individually controlled by a single actuator, such as a rotary actuator.

Abstract: In various embodiments, a drive system with a motor rotary actuator driven linkage and an override system is provided. The override system may be a manually actuated override system that, in response to a power loss or outage, is configured to disengage one or more links of drive system 100 from the electric motor rotary actuator, allowing the disengaged link to be moved and/or repositioned. Moreover, drive system 100 and, more specifically, the override system may be configured to restore normal operation to the disengaged link in response to power being restored (i.e., by reengaging the link).

Abstract: A seat actuation control system is disclosed. The seat actuation control system may permit multiple functions to be controlled by a single actuator. For example, a seat floor tracking function, and a seat pan track and swivel function may be individually controlled by a single actuator, such as a rotary actuator.

Abstract: Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

Abstract: An aircraft seat assembly includes a foot assembly, a seat, and a track lock assembly. The foot assembly is received within a track assembly disposed on an aircraft floor. The seat is connected to the foot assembly. The track lock assembly moves between a lock position and an unlock position. The track lock assembly includes a clamping shaft having a base member and a shaft. The base member is received within the track assembly. The shaft extends from the base member and extends through the foot assembly.

Abstract: Systems and methods are disclosed herein for reclining seats. A seat may have a seat back, a seat bottom, and a spine within the seat back and seat bottom. The seat bottom may be coupled to a base. The seat bottom may translate relative to the base. The seat may include a guide ramp coupled to the base. A portion of the spine may be located within the guide ramp. In response to translation of the seat bottom, the guide ramp may apply a torque on the spine, causing the seat back to recline.

Abstract: Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

Abstract: A bi-directional linear clutch lock is provided that may selectively restrain a rack from translating. A bi-directional rotary clutch lock is provided that may selectively restrain a rotary rack from rotating.