A lift assist system for an aircraft seat is disclosed. The lift assist system may include one or more pivoting lift rails configured to couple to one or more fixed seat pan rails of a seat pan frame. The lift assist system may include an actuator sub-system. The actuator sub-system may include an actuator configured to actuate the seat pan frame between one or more positions by actuating the one or more pivoting lift rails a predetermined distance.

An aircraft seat pod with a reclining seat includes a controller interface that extends around a surface of the pod, include a surface obscured by the seat when in an upright position. The controller tracks the position and orientation of the seat and displays seat controls on the interface at a convenient location. More than one interface may be disposed at different locations to conveniently accommodate passengers of different size or in different orientations. Vision sensors may track the position and orientation of a passenger and preemptively display controls at a convenient location.

A powered seat-base release system includes a rod rotatably mounted in a bucket assembly of an aircraft seat and a motor mechanically coupled to the rod. The motor is configured for rotating the rod from a locked position to a released position. A locking mechanism is configured for preventing motion of the bucket assembly. A cable has a first end and a second end, the first end being mechanically coupled to the rod, and the second end being mechanically coupled to the locking mechanism. A user interface is configured to activate the motor for rotating the rod to the released position such that the rod pulls the cable thereby releasing the locking mechanism to enable motion of the bucket assembly. Upon deactivation of the motor, a biasing mechanism is configured to counter rotate the rod from the released position to the locked position thereby back driving the motor.

A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

An aircraft seat includes an actuator and a movement transmission device. The transmission device includes a frame provided with an immobilizing portion and a drive shaft. The transmission device further includes a gear wheel provided with coupling teeth having inclined side walls and a sleeve with an immobilizing portion complementary to the immobilizing portion of the frame, and coupling teeth having inclined side walls. The transmission device also has an elastic member configured to push the sleeve. The stiffness of the elastic member and the inclination of the side walls of the coupling teeth of the gear wheel and sleeve are chosen such that, when a torque greater than a threshold torque is applied to the gear wheel, the sleeve slides on the drive shaft from a position of coupling the sleeve to the gear wheel to a position of immobilizing the sleeve relative to the frame.

A seat drivetrain assembly for an aircraft seat is disclosed. The assembly may include a seatback drivetrain sub-assembly configured to actuate a seatback frame of a seat frame of the aircraft seat between a first position and at least a second position. The assembly may include a seat pan drivetrain sub-assembly configured to actuate a seat pan frame of the seat frame of the aircraft seat between a first position and at least a second position. The assembly may include an actuator sub-assembly configured to cause one of the seatback drivetrain sub-assembly or the seat pan drivetrain sub-assembly to actuate one of the seatback frame or the seat pan frame of the aircraft seat between the first position and the at least second position.

Example lie-flat passenger seat configurations for transportation are described. A non-elevated passenger seat includes a seat base and a seatback pivotably connected to the sliding bar. The seat base may be opened upwardly or downwardly. The seatback may be opened sideway such that a space originally used for seat base and seatback is converted to a passage accessible by the passenger. An elevated-height passenger seat also includes a seat base, a seatback pivotably connected to the seat base, and a hinge at an upper portion of the seatback. The elevated-height passenger seat may rotate upwardly around the hinge. When the elevated-height passenger seat rotates upwardly, the elevated-height passenger seat transitions from a seating position to an elevated position with the seat base and the seatback forming a flat bed such that the passenger can lie flat on the flat bed formed by the seat base and the seatback.

A powered seat-base release system includes a rod rotatably mounted in a bucket assembly of an aircraft seat and a motor mechanically coupled to the rod. The motor is configured for rotating the rod from a locked position to a released position. A locking mechanism is configured for preventing motion of the bucket assembly. A cable has a first end and a second end, the first end being mechanically coupled to the rod, and the second end being mechanically coupled to the locking mechanism. A user interface is configured to activate the motor for rotating the rod to the released position such that the rod pulls the cable thereby releasing the locking mechanism to enable motion of the bucket assembly. Upon deactivation of the motor, a biasing mechanism is configured to counter rotate the rod from the released position to the locked position thereby back driving the motor.

In embodiments, an aircraft passenger seat assembly includes a seatback assembly including one or more lateral seatback sections. In embodiments, at least one lateral seatback section includes a base seatback panel coupled to a seatback frame, a first set of segmented seatback panels coupled to the base seatback panel, and a second set of segmented seatback panels coupled to the first set of segmented seatback panels. In embodiments, the aircraft passenger seat assembly further includes a plurality of actuatable assemblies, wherein the plurality of actuatable assemblies include a first set of actuatable assemblies configured to selectively actuate the first set of segmented seatback panels relative to the base seatback panel, and a second set of actuatable assemblies configured to selectively actuate the second set of segmented seatback panels relative to the first set of segmented seatback panels.

An aircraft armrest lifting mechanism generally biases the aircraft armrest toward a raised configuration. A linear actuator applies tension to a cable connected to a portion of an armrest hub connected to an armrest shaft. The portion of the armrest hub extends some distance from the armrest shaft so that the linear actuator applies a moment between an attachment point on the armrest and the armrest shaft that tends to rotate the armrest toward a raised configuration.