AMI Industries Patente

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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Zusammenfassung wird geladen …

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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Zusammenfassung wird geladen …

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.

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.

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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.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An adjustable armrest assembly (110) for a seat such as a pilot seat (100). In embodiments, the armrest assembly includes an armrest frame (120), a leadscrew (122) rotatably mounted in the armrest frame, a control wheel (114) mounted to the leadscrew, an armpad subassembly (126) pivotally attached to the armrest frame, and a tilt link subassembly (132) 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.

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Zusammenfassung wird geladen …

A bulkhead-mounted aircraft seat assembly (100) configured for independent vertical and horizontal adjustment includes an aircraft seat (102) (seatback and seat frame/cushion) for supporting a pilot, passenger, or other occupant. Parallel rails (104) attach to the bulkhead (110) and extend along the bulkhead (110) (vertically or near vertically) with opposing slots (104a) set into each rail (104). A sled (202) translates along the rails (104) via paired sliding members (112) set into the slots (104a), each pair of sliding members (112) connected to an axle extending through the sled (202). A four-bar linkage attached to the sled (202) and to the aircraft seat (102); the four-bar linkage extends from a default position to allow the aircraft seat (102) to translate along a horizontal linear rail under the seat while maintaining a stable vertical reference point above the cabin floor. The seat (102) is independently configured for substantially vertical adjustment via a metering plate (106) attached to the bulkhead (110).

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An armrest is disclosed that includes an armrest subframe (128) configured to couple to an arm of the seat that includes a slot (132) within a face of the armrest subframe configured to receive a stop pin (136). The armrest further includes an arm pad (124) translatably coupled to the armrest subframe and includes a plurality of grooves (140) formed on one edge of the armrest subframe. The arm pad further includes the stop pin that restricts the translation of the arm pad and a spring anchor. The armrest further includes a lever (144) rotationally coupled to the armrest that includes a locking pin configured to engage one or more grooves of the plurality of grooves, and an actuating end (156), wherein a movement of the actuating end at least one of engages or disengages the locking pin from the one or more grooves of the plurality of grooves. The armrest further includes a biasing spring (160).

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Zusammenfassung wird geladen …

A suspension line assembly for a parachute assembly, comprising a plurality of suspension lines bound together at a confluence, a first riser (120) extending between the confluence and a first attachment location disposed on a first strap, a second riser (124) extending between the confluence and a second attachment location disposed on a second strap and a cradle (150) disposed between the first riser and the second riser.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes a sensor configured to detect weight data corresponding to a weight of a user of the ejection system. The system further includes a controller coupled to the ejection system and to the sensor and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the weight data.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A system may include a vehicular seat assembly including first and second seat support beams (106), a seat pan (108), a bar (110), a fabric seat back (112), and at least one detachable attachment means (126). The fabric seat back (112) may have a first end and a second end. The fabric seat back (112) may be secured at the first end to the bar (110). The fabric seat (112) back may have an expandable seat back section (114) secured at the second end to the seat pan (108). Each detachable attachment means (126) may be secured at a first detachable attachment means end to the seat pan (108) and may be secured at a second detachable attachment means end to a portion of the fabric seat back (112) located between the first end and the second detachable attachment means end. When all detachable attachment means (126) are in the detached state, an effective length of the fabric seat back (112) may extend.

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A floor mounted aircraft seat seal frame includes a frame (200), displacing elements (202, 204) connecting the frame to the posterior of the seat, and fabric tensioning elements (210, 212, 214, 216) that keep a gap covering fabric connected to the posterior surface of the seat in tension around the frame. The frame displacing elements, which may be leaf springs, coil springs, or manually adjustable element, allow the frame to conform to a wall behind the seat, regardless of the tapering of the wall.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An aircraft armrest lifting mechanism generally biases the aircraft armrest (100) toward a raised configuration. A linear actuator (102) applies tension to a cable (105) connected to a portion of an armrest hub (110) connected to an armrest shaft (116). The portion of the armrest hub (110) extends some distance from the armrest shaft (116) so that the linear actuator (102) applies a moment between an attachment point on the armrest (100) and the armrest shaft (116) that tends to rotate the armrest (100) toward a raised configuration.

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A singular energy absorber (236) and an offset pilot seat (202) including the same. The pilot seat includes a seat base (208), a seat bucket (212) positioned laterally offset relative to a centerline of the seat base, a singular motion controller (230) 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.