Patent Description:
Aircraft seats, for example pilot or crew seats in a rotorcraft cockpit, may attach directly to a rear wall of bulkhead rather than to the cabin floor. Such seats may be capable of at least a limited amount of vertical adjustment, or adjustment of the seat height relative to the cabin floor. While vertical adjustment may help the aircraft seat accommodate a broader range of taller or shorter pilots, for example, there is as yet no corresponding capacity for horizontal adjustment of the seat.

<CIT> discloses a combination of a seat, a support, a track and a slide movable in the track.

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

In some embodiments, the sled includes an upper pair and a lower pair of sliding members, each pair of sliding members (e.g., left-side and right-side) connected to an upper or lower axle extending through the sled and translating through left-side and right-side slots respectively.

In some embodiments, the aircraft seat assembly includes a linear lock for securing the aircraft seat in the desired horizontal position along the linear rail (e.g., relative to the bulkhead).

In some embodiments, the metering plate is configured for energy attenuation via controlled deformation to control downward deceleration of the aircraft seat in response to an impact event.

In some embodiments, the aircraft seat is held at a desired height by a spring-loaded locking pin which extends through a hole in the sled and a second hole in the metering plate, the metering plate including a substantially vertical sequence of holes where each hole corresponds to a desired height of the seat. For example, an occupant of the seat may release the locking pin via a handle to articulate the aircraft seat to a higher or lower desired height, releasing the handle to restore the locking pin through the sled hole and higher or lower metering hole and securing the aircraft seat to the new desired height.

Broadly speaking, embodiments of the inventive concepts disclosed herein are directed to a seat assembly for a rotorcraft or other aircraft that attaches directly to a rear bulkhead, e.g., of a rotorcraft cockpit. While the aircraft seat is capable of vertical adjustment, e.g., height adjustment of the aircraft seat relative to the cabin floor, the aircraft seat is also capable of horizontal adjustment. For example, the aircraft seat may be adjusted forward or backward relative to the bulkhead, e.g., along an x-axis. Further, the horizontal adjustment mechanism maintains the vertical seat position (e.g., the height of the seat relative to the floor) within a narrow tolerance during horizontal adjustment.

Referring now to <FIG>, an aircraft seat assembly <NUM> is shown. The aircraft seat assembly may include an aircraft seat <NUM>, seat base rails <NUM>, metering plate <NUM>, and linkage <NUM>.

In embodiments, the aircraft seat assembly <NUM> may attach directly to a rear bulkhead <NUM>, e.g., within a rotorcraft cockpit or like aircraft interior space, rather than to a cabin floor. For example, two parallel seat base rails <NUM> may be rigidly attached to the bulkhead <NUM>, e.g., a left-side rail and a right-side rail in a spaced apart relationship. The aircraft seat <NUM> may include a seatback 102a and a seat frame/seat cushion 102b collectively capable of supporting an occupant of the seat; for example, the seatback and seat frame/seat cushion may be two separate components or may be combined into a single component.

In embodiments, the aircraft seat <NUM> may attach to the bulkhead <NUM> via a sled (not shown), the sled capable of translation along the left-side and right-side seat base rails <NUM> via sliding members <NUM> (e.g., rolling members). For example, each seat base rail <NUM> may include a slot 104a extending substantially the length of the base rail, the sliding member <NUM> capable of translating through the slot.

In embodiments, the aircraft seat <NUM> may be spring-loaded to a default height above the cabin floor and secured to the default height via a locking pin (<NUM>, <FIG>; e.g., "pop pin") inserted through a hole <NUM> in the metering plate <NUM>. For example, the metering plate <NUM> may include a substantially vertical array of holes <NUM>, each hole corresponding to a height to which the aircraft seat <NUM> may be secured. Vertical adjustment (<NUM>; e.g., height adjustment) of the aircraft seat <NUM> by the occupant of the aircraft seat <NUM> may be achieved by releasing the locking pin from the metering plate <NUM>, allowing the aircraft seat to translate freely along the seat base rails <NUM>. In some embodiments, the occupant may raise or lower the aircraft seat <NUM> to a new desired height by shifting their weight in the aircraft seat, e.g., pushing the seat downward or allowing the seat to rise toward the default height, and secure the aircraft seat to the new desired height by reinserting the locking pin in the appropriate hole <NUM> in the metering plate.

Referring also to <FIG>, in embodiments, the aircraft seat <NUM> may be capable of horizontal adjustment (<NUM>), as well as vertical adjustment (<NUM>), relative to the bulkhead <NUM>. For example, the linkage <NUM> may operate as a four-bar linkage, including an upper portion 108a and a lower portion 108b attached to the aircraft seat <NUM> and to the sled <NUM>, the linkage pivotable at both ends. For example, the sled <NUM> (e.g., to which the aircraft seat <NUM> may be fixed) may translate relative to the seat base rails <NUM> via pairs of sliding members <NUM>, each pair of sliding members including a left-side sliding member capable of translation along the slot of the left-side seat base rail and a right-side sliding member capable of translation along the slot of the right-side seat base rail. In embodiments, each opposing pair of sliding members (e.g., left and right) may be joined to an axle <NUM> extending through the sled <NUM>. For example, the upper portion 108a of the linkage <NUM> may be connected to an upper axle <NUM> and may pivot relative to the upper axle; similarly, the lower portion 108b of the linkage may be connected, and may pivot relative to, a lower axle. In embodiments, the linkage <NUM> may pivot to allow the occupant to articulate the aircraft seat <NUM> along the horizontal axis <NUM>, e.g., forward or backward relative to the bulkhead <NUM> (and allowing the aircraft seat <NUM> to accommodate a broader range of pilot sizes).

In some embodiments, the metering plate <NUM> may be configured for energy attenuation (EA). For example, in response to a crash event associated with a downward load (e.g., a rapid downward deceleration) on the aircraft seat <NUM> and its occupant, the aircraft seat may stroke downward (<NUM>) along the seat base rails <NUM>, the metering plate <NUM> deforming to absorb at least a portion of the load as it deforms, slowing the deceleration of the aircraft seat (as disclosed by <CIT>).

Referring now to <FIG>, the aircraft seat assembly <NUM> is shown.

In embodiments, the aircraft seat assembly <NUM> may include a linear lock assembly <NUM> comprising a linear track <NUM> and a sliding carriage <NUM> capable of horizontal translation along the linear track. For example, the linear track <NUM> may attach to the sled <NUM> and project forward therefrom, defining a substantially horizontal axis (<NUM>). In embodiments, the sliding carriage <NUM> may secure to the linear track <NUM> to lock the aircraft seat <NUM> in a desired horizontal position relative to the bulkhead (<NUM>, <FIG>).

In embodiments, the occupant of the aircraft seat <NUM> may vertically adjust (<NUM>) the aircraft seat by releasing the locking pin <NUM> and actuating the aircraft seat to a new desired height as described above. For example, the locking pin <NUM> may be spring-loaded to a default configuration wherein the locking pin is inserted through a hole <NUM> extending through the sled <NUM> and through a hole <NUM> in the metering plate <NUM>. In embodiments, when the aircraft seat <NUM> has reached the new desired height, the occupant may re-insert the locking pin <NUM> into the hole <NUM> and into the hole <NUM> in the metering plate <NUM> corresponding to the new desired height.

In embodiments, the occupant may horizontally articulate the aircraft seat <NUM> by releasing the sliding carriage <NUM> from the linear track <NUM> and actuating the aircraft seat along the horizontal axis <NUM> to the new desired position. For example, the linkage <NUM> may pivot between the aircraft seat <NUM> and the sled <NUM>, allowing the aircraft seat to translate forward or backward along the linear track. When the new desired position on the linear track <NUM> is reached, the occupant may lock the aircraft seat <NUM> to the new desired position via the sliding carriage.

Referring now to <FIG> and <FIG>, the aircraft seat assembly <NUM> is shown.

In embodiments, horizontal adjustment <NUM> of the aircraft seat <NUM> relative to the bulkhead <NUM> may be achieved independently of vertical adjustment <NUM> of the aircraft seat, and vice versa. For example, the aircraft seat <NUM> is shown by <FIG> at a default horizontal position, e.g., wherein the aircraft seat <NUM> is closest to the bulkhead <NUM>, and by <FIG> at a maximum horizontal distance from the bulkhead (e.g., as allowed by the placement of other fixtures or objects within a cockpit <NUM> or control area wherein the aircraft seat assembly <NUM> is situated, where continued horizontal adjustment of the aircraft seat may collide or interfere with said other fixtures or objects). In embodiments, full horizontal adjustment of the aircraft seat <NUM> may be possible at any selected height of the aircraft seat, and full vertical adjustment of the aircraft seat may be possible at any position of the aircraft seat along the linear track (<NUM>, <FIG>).

In embodiments, the upper and lower linkages 108a, 108b may be sized to provide adjustment <NUM> of the aircraft seat <NUM> along the linear track while maintaining the vertical seat reference point <NUM> (VSRP) within a minimal tolerance. For example, given a bulkhead <NUM> at an angle of <NUM> degrees from vertical and a desired range of horizontal adjustment (e.g., <NUM> inches), the upper and lower linkages 108a, 108b may be sized (e.g., bar length) so as to provide sufficient rotational radius <NUM> that the aircraft seat <NUM> may be horizontally adjusted with minimal variation in VSRP <NUM>. In embodiments, the achievable VSRP tolerance may vary according to the length of the upper and lower linkages 108a, 108b and the desired range of horizontal adjustment. For example, shorter upper and lower linkages 108a, 108b and/or greater desired ranges of horizontal adjustment may both increase the achievable VSRP tolerance.

Claim 1:
An aircraft seat assembly (<NUM>), comprising:
an aircraft seat (<NUM>) capable of supporting an occupant;
two parallel rails (<NUM>) attachable to a bulkhead (<NUM>) of an aircraft, each rail including a slot (104a) set thereinto and extending along the rail (<NUM>);
a sled (<NUM>) disposed between the two rails (<NUM>) and slidably attached to each rail via at least two pairs of sliding members (<NUM>), each pair including a left-side sliding member configured for translation along a left-side slot and a right-side sliding member configured to translation along a right-side slot, the sled including at least one first hole set thereinto;
a four-bar linkage pivotably attached to the sled (<NUM>) and to the aircraft seat (<NUM>), the linkage including at least an upper portion (108a) and a lower portion (108b);
a metering plate (<NUM>) disposed between the two parallel rails (<NUM>) behind the sled (<NUM>), the metering plate (<NUM>) including a substantially vertical array of second holes set thereinto, each second hole associated with a height of the aircraft seat;
and
a locking pin controllable by the occupant;
wherein the locking pin (<NUM>) is configured for insertion through the first hole and a second hole of the array to secure the aircraft seat (<NUM>) at a height associated with the second hole;
and
wherein the four-bar linkage is configured for horizontal articulation of the aircraft seat (<NUM>) relative to the bulkhead (<NUM>).