Abstract: A transformable canopy assembly includes one or more canopy mounts configured to couple the transformable canopy to a frame of a seat. The transformable canopy includes a canopy sub-assembly configured to rotate between a stowed and a deployed position. The canopy sub-assembly includes a canopy configured to provide lighting or sound mitigation when in the deployed position. The canopy sub-assembly includes one or more canopy support members coupled to the canopy. The transformable canopy includes a canopy frame lock configured to couple the canopy sub-assembly to the frame. When in the stowed position, the canopy sub-assembly is secured to the frame via the canopy frame lock, where the canopy frame lock prevents the canopy sub-assembly from rotating to the deployed position. When in the deployed position, the canopy sub-assembly forms an arcuate-shaped cover over at least a portion of one of a seatback or a seat pan of the seat.

Abstract: An armored seating assembly for a rotorcraft or other aircraft (e.g., for a pilot or operator) includes a wing armor panel capable of rotational and vertical movement relative to the seat base when adjusted by the operator. For example, a carriage attached to the armor panel translates along a carriage slot in the seat base, stabilized in the carriage slot by orthogonal sets of bearings (e.g., lateral bearings and longitudinal bearings) and allowing the wing armor panel to be vertically adjusted relative to the seat base (e.g., to accommodate pilots of varying heights). The armor panel is coupled to the carriage by hinges allowing the panel to pivot or rotate away from the seat base, in order to facilitate entry to and egress from the seat.

Abstract: Drogue parachute systems include an ejection seat, an elastic riser operably connected to the ejection seat at a first end and a riser connection is arranged at a second end of the elastic riser, a set of suspension lines operably connected to the riser connection, and a drogue canopy attached to the set of suspension lines opposite the riser connection.

Abstract: An adjustable armrest assembly for a seat such as a pilot seat. In embodiments, the armrest assembly includes an armrest frame, a leadscrew rotatably mounted in the armrest frame, a control wheel mounted to the leadscrew, an armpad subassembly pivotally attached to the armrest frame, and a tilt link subassembly coupled between the armrest frame and the armpad subassembly. In use, rotating the leadscrew synchronizes rotational motion of the armrest frame relative to the seat, and armpad subassembly motion relative to the armrest frame. In embodiments, the adjustment capability of the armrest assembly facilitates use with a flight controller positioned forward of the armrest.

Abstract: A seat assembly includes a seat pan that is tilted automatically by way of a seat bucket moving up and down relative to a base structure. The seat bucket is pivotably coupled to a carrier. The carrier and the seat bucket each follow respective channels of a base structure. The movement of the seat bucket along the channel of the base structure causes the pivoting of the seat bucket relative to the carrier. The channels are shaped with an angular orientation resulting in the seat pan angle changing as the seat bucket moves up and down.

Abstract: A floor seal assembly for use with furniture configured to be mounted spaced above a movable floor. In embodiments, the floor seal assembly includes a seal carrier that is elongated in a longitudinal direction, defines a clearance at each opposing longitudinal end configured to be positioned in surrounding relation and out of contact with mounting hardware, and includes an upstanding peripheral rim supporting a lateral side of a foam seal mounted to the bottom of the seal carrier. In use, the floor seal assembly closes off a gap formed between the mounted furniture and the floor to prevent food, waste, and other debris from migrating and accumulating under the furniture. In embodiments, the furniture is a cabin attendant seat in an aircraft.

Abstract: An air conditioning system for a seat, comprising an arm rest (4a, 4b) of the seat, the arm rest having a top side, an inner wall, an outer wall, a front end, and a back end defining a hollow interior between them, means for providing air conditioned to a desired temperature, from an air source to the hollow interior of the arm rest, and a plurality of nozzles formed through the inner wall, defined between a nozzle inlet on an inner surface of the inner wall facing into the hollow interior and a nozzle outlet on an outer surface of the inner wall facing towards a seating area of a person when sitting in the seat, the nozzles providing a path through which air flows from the hollow interior, into the nozzle inlet and out of the nozzle outlet.

Abstract: An aircraft seat may include an integrated motion control system. The motion control system may include one or more user controlled sub-systems. Each sub-system may include at least one of a user control device, a lever arm, and a metering pin assembly. The lever arm may couple to the user control device and synchronously transmit a force to one or more cables in response to an actuation of the user control device. The metering pin assembly may include a metering pin which may be configured to attach to an end portion of the one or more cables and receive a force from the one or more cables causing the respective control sub-system to execute an adjustment control operation. The adjustment control operation may include a vertical position adjustment, a swivel position adjustment, or a track position adjustment.

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 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: A locking mechanism to prevent back-drive includes a locking shaft with guide grooves. Locking shaft guides engage the guide grooves to constrain lateral motion of the locking shaft. A nut includes corresponding grooves to the locking shaft, and engages the locking shaft to prevent linear translation. The locking mechanism may be incorporated into a aircraft seat armrest to create a positive lock in the armrest position.

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.