AMI Industries

An aircraft seat assembly (100) including stanchions (112) defining elongated guide channels (120) and elongated motion sleds (116) nested in the guide channels and affixed to a seat bucket (104). An energy absorber (124) 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.

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A seat base assembly for an aircraft seat includes parallel rails (104) 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 (302) capable of vertical translation relative to the bulkhead via slidable members that translate along the slots. The sled (302) includes a hole for accommodating a locking pin controllable by the seat occupant. A metering plate (108) attached to the seat base (106) behind the sled (302) 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 (308) and metering hole. In response to an impact event, the metering plate (108) deforms to absorb impact energy and control downward deceleration of the seat.

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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 (110) that is oriented and positioned to work with the profile. The assembly includes an actuator which ejecting the pins (106) 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.

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An aircraft seat (100) includes infinitely adjustable, lateral tilt control within a specified range. The aircraft seat includes a stationary support (102), a tilting frame (104) rotatably or translatably attached to the stationary base, and a tilt control mechanism to adjust the tilt within the defined range and positively lock the frame without back-driving. The tilt control mechanism may include a plurality of linkages (204, 206) connected to the stationary support (102) and the tilting frame (104), and to each other via a threaded block (208); a threaded shaft adjusts the linkages and thereby adjust the tilt. Alternatively, the tilt control mechanism comprises a curved rack (304) and a pinion (306). The threaded block (208) and threaded shaft, or the rack (304) and pinion (306) define ACME threads to prevent back-driving.

A console mounted armrest includes an adjustable post (104; 204; 304; 404; 504) to raise and lower the armrest, and a linkage (106; 206; 306; 406; 506). The linkage (106; 206; 306; 406; 506) defines the tilt of the armrest with respect to the post (104; 204; 304; 404; 504). A single control mechanism (110; 210; 310; 410) controls the motion of the post (104; 204; 304; 404; 504), and thereby also controls the tilt of the armrest to maintain a desirable orientation with respect to the sidestick. The control mechanism (110; 210; 310; 410) defines multiple positive lock-out positions with respect to the post (104; 204; 304; 404; 504) such that the control mechanism (110; 210; 310; 410) will always engage one of the positive lock-out positions.