Abstract: A seating assembly for a pilot or operator of a rotorcraft, aircraft, or other vehicle includes a seat base comprising base side panels, each panel having a cam surface on its forward face capable of accepting a cam follower. A seat bucket translates relative to the seat base, adjustably up or down through a tracking region and down through a stroking region in response to an impact event; the cam surfaces likewise include an upper portion corresponding to the tracking region and a lower portion corresponding to the stroking region. The seating assembly includes hip armor panels connected to the seat bucket and coplanar with the base side panels, each armor panel including a cam follower translatable along the cam surface such that when the seat bucket tracks through the stroking region the cam followers translate through the lower portion of the cam surface, pivoting the hip armor panels upward.

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: 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: 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: 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 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 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 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 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: 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 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: 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 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: 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: 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.