Patent Description:
<CIT> discloses a moveable seat comprising a seat frame assembly and a tapered swivel assembly as well as a tracking assembly.

A vertical adjustment system for an aircraft seat is disclosed, in accordance with one or more embodiments of the disclosure. The system includes a swivel assembly. The swivel assembly includes a swivel plate including integrally-formed connecting members, the integrally-formed connecting members configured to couple to a portion of the aircraft seat; and a swivel mechanism configured to rotate the aircraft seat about a central axis of the aircraft seat. The system includes a tracking assembly. The tracking assembly includes a plurality of slide tubes configured to slide the aircraft seat one of side-to-side or fore-and-aft; a plurality of slide bearings configured to receive a portion of the plurality of slide tubes; and a tracking plate coupled to the plurality of slide bushings. The system includes an actuation assembly. The actuation assembly includes an actuator configured to provide a vertical height adjustment for the aircraft seat. The actuator is configured to arrest relative motion between a base assembly of the aircraft seat and an upper portion of the aircraft seat. The actuation assembly includes a release mechanism configured to couple to a rotatory portion of the swivel plate and configured to release the actuator. The actuation assembly includes a plurality of vertical stabilizer rods coupled to a portion of the tracking plate. The actuation assembly includes a pillow block assembly. The pillow block assembly including a plurality of pillow blocks coupled to a portion of the swivel plate. The pillow block assembly includes a plurality of rollers coupled to a portion of the plurality of pillow blocks, the plurality of rollers configured to receive a portion of the plurality of stabilizer rods, the plurality of rollers configured to provide stability along the vertical stabilizer rods when the actuator provides the vertical height adjustment.

In some embodiments, the swivel mechanism may include a first inner ring; an additional inner ring, the swivel plate positioned between the first inner ring and the additional inner ring; one or more ball bearings, the one or more ball bearings positioned between the swivel plate and at least one of the first inner ring or the additional inner ring; and a locking ring, the locking ring include one more teeth to arrest the relative motion between the swivel plate and at least one of the first inner ring or the additional inner ring.

In some embodiments, the swivel mechanism may include a helix swivel mechanism and a locking mechanism configured to engage the helix swivel mechanism to lock the aircraft seat in a select position. The helix swivel mechanism may include a shaft. The shaft may include one or more helical protrusions.

In some embodiments, the release mechanism may include a pull lever coupled to a portion of the swivel plate and one or more pull cables coupled to a portion of the pull lever, the one or more pull cables configured to pull the pull lever to release the actuator.

In some embodiments, the integrally-formed connecting members may be configured to couple to a portion of seat frame of the aircraft seat.

In some embodiments, the tracking assembly may be configured to couple to a portion of the base assembly of the aircraft seat.

In some embodiments, the integrally-formed connecting members may be configured to couple to a portion of base assembly of the aircraft seat.

The appearances of the phrase "in some embodiments" in various places in the specification are not necessarily all referring to the same embodiment, and embodiments may include one or more of the features expressly described or inherently present herein, or any combination of or sub-combination of two or more such features, along with any other features which may not necessarily be expressly described or inherently present in the instant disclosure.

<FIG> in general illustrate a vertical adjustment system for an aircraft seat, in accordance with one or more embodiments of the disclosure.

Often it is desirable to have an aircraft seat configured with one or more comfort features for a passenger to adjust as necessary. For example, it is often desirable to have an aircraft seat with the ability to swivel the aircraft seat, slide side-to-side, and slide the aircraft seat fore and aft. Further, it is often desirable to have an aircraft seat with the ability to adjust a vertical height with the aircraft. However, the vertical height adjustment feature is lacking in conventional aircraft seats.

Accordingly, embodiments of the present disclosure are directed to curing one or more of the shortfalls of previous approaches identified above. Broadly, embodiments of the present disclosure are directed to a vertical adjustment system for an aircraft seat to adjust a vertical height of the aircraft seat. More particularly, embodiments of the present disclosure are directed to a vertical adjustment system for an aircraft seat including a swivel mechanism and a tracking mechanism. In this regard, the vertical adjustment system may be configured to allow for motion of the aircraft seat up and down, side-to-side, fore and aft, and to rotate (swivel).

It is noted herein that the vertical adjustment system may be implemented in any environment or number of environments. For example, the environment may include any type of vehicle known in the art. For instance, the vehicle may be any air, land, or water-based personal equipment or vehicle; any air, land, or water-based commercial equipment or vehicle; any air, land, or water-based military equipment or vehicle known in the art. By way of another example, the environment may include a commercial or industrial establishment (e.g., a home or a business).

Where the environment may be an aviation environment, the aircraft cabin designs need to be certified in accordance with aviation guidelines and standards, while being designed so as not to lose the intended functionality of the structures and/or monuments in the aircraft cabin. For example, the structures and/or monuments in the aircraft cabin may need to be configured in accordance with aviation guidelines and/or standards put forth by, but not limited to, the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA) or any other flight certification agency or organization; the American National Standards Institute (ANSI), Aeronautical Radio, Incorporated (ARINC), or any other standards setting organization or company; the Radio Technical Commission for Aeronautics (RTCA) or any other guidelines agency or organization; or the like.

<FIG> illustrates an aircraft cabin <NUM> including an aircraft seat <NUM>, in accordance with one or more embodiments of the disclosure.

The aircraft seat <NUM> may include a seat back <NUM>. The aircraft seat <NUM> may include a seat pan <NUM>. The aircraft seat <NUM> may include one or more arms <NUM>. The aircraft seat <NUM> may be coupled to a base <NUM>. The base <NUM> may be covered by a shroud <NUM>. For example, the shroud <NUM> may include one or more sections configured to cover at least a portion of the aircraft seat <NUM>. For instance, the shroud <NUM> may include a bucket shroud section and a base shroud section. It is noted herein, however, that the shroud <NUM> may be formed from one piece (e.g., includes a single section).

The aircraft seat <NUM> may include a vertical adjustment system <NUM>. It is noted that the vertical adjustment system <NUM> may be adapted and mounted in any orientation to cater to various aircraft seat base designs and requirements. For example, as shown in <FIG>, the vertical adjustment system <NUM> may be mounted in an upright orientation of the aircraft seat <NUM>. By way of another example, as shown in <FIG>, the vertical adjustment system <NUM> may be mounted in an upside down orientation of the aircraft seat <NUM>.

The aircraft seat <NUM> may include a seat back frame <NUM>. The aircraft seat <NUM> may include a seat frame <NUM>. The aircraft seat <NUM> may include a seat pan frame <NUM>. The seat frame <NUM> may include one or more components <NUM> and/or one or more components <NUM>. For example, the one or more components <NUM>, <NUM> may be configured to allow and/or assist the aircraft seat <NUM> to recline and/or return to an upright position.

One or more of the seat back frame <NUM> and/or the seat pan frame <NUM> may be directly coupled, or indirectly coupled via one or more interconnecting components, to the one or more of the components <NUM>, <NUM> of the seat frame <NUM>. At least a portion of the shroud <NUM> (e.g., the bucket shroud section of the shroud <NUM>) may be configured to cover the seat frame <NUM> and/or the seat pan <NUM>.

Referring to <FIG>, the aircraft seat <NUM> (e.g., the base <NUM>, as illustrated in <FIG>) may include a base assembly <NUM>. The base assembly <NUM> may include one or more base rails <NUM> (e.g., tubes, bars, or the like). For example, the one or more base rails <NUM> may be positioned relative to a particular direction of travel of the aircraft seat <NUM> including, but not limited to, perpendicular (e.g., cross-wise), parallel (e.g., cross-wise), or the like. For instance, the one or more base rails <NUM> may be positioned relative to a same or a different direction of travel of the aircraft seat <NUM>.

The base assembly <NUM> may include one or more base brackets <NUM>. For example, the one or more base rails <NUM> may be coupled together via the one or more base brackets <NUM>. For example, a base bracket <NUM> may couple together an adjacent base rail <NUM> and base rail <NUM> at any angle, such that the base assembly <NUM> may include an outline of any geometric shape known in the art. For instance, the outline may be rectangular or substantially rectangular. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The one or more base brackets <NUM> may be coupled to a set of floor tracks <NUM> of the aircraft cabin <NUM> (e.g., as illustrated in <FIG>) via one or more floor fittings <NUM>. At least a portion of the shroud <NUM> (e.g., the base shroud section of the shroud <NUM>) may be configured to cover the base assembly <NUM>.

Referring to <FIG>, the aircraft seat <NUM> (e.g., the base <NUM>, as illustrated in <FIG>) may include a base assembly <NUM>. The base assembly <NUM> may include one or more fixed base rails <NUM>. The one or more fixed base rails <NUM> may be coupled to a set of floor tracks of the aircraft cabin <NUM> (e.g., as illustrated in <FIG>) via one or more floor fittings <NUM>. At least a portion of the shroud <NUM> (e.g., the base shroud section of the shroud <NUM>) may be configured to cover the base assembly.

Referring generally to <FIG>, the seat <NUM> and the base <NUM> (e.g., as illustrated in <FIG>) may be coupled together via the vertical adjustment system <NUM>. For example, the seat frame <NUM> of the seat <NUM> (e.g., as illustrated in <FIG>) and the base assembly <NUM>, <NUM> of the base <NUM> (e.g., as illustrated in <FIG>) may be coupled together via the vertical adjustment system <NUM>. For example, as shown in <FIG>, the vertical adjustment system <NUM> may include a swivel assembly <NUM> attached to the aircraft seat <NUM> and a tracking assembly <NUM> attached to the base <NUM>, wherein the swivel assembly and tracking assembly may be attached via an actuation assembly. By way of another example, as shown in <FIG>, the vertical adjustment system <NUM> may include a swivel assembly <NUM> attached to the base and a tracking assembly <NUM> attached to the aircraft seat <NUM>, wherein the swivel assembly and tracking assembly may be attached via an actuation assembly.

The vertical adjustment system <NUM> includes a swivel assembly <NUM> configured to rotate (e.g., swivel) the aircraft seat <NUM> relative to the tracking assembly about an axis through the vertical adjustment system.

Referring to <FIG>, the swivel assembly <NUM> includes a swivel mechanism <NUM> and a traversely-extending spar <NUM>. The swivel mechanism is preferably integrally-formed with and forms the spar (e.g., a "sparvel" mechanism).

The swivel mechanism includes a swivel plate <NUM> (e.g., an outer ring). The swivel plate includes integrally-formed connecting members <NUM>. The integrally-formed connecting members is configured to mount to a portion of the aircraft seat <NUM>. For example, as shown in <FIG>, the integrally-formed connecting members <NUM> may be configured to mount to the seat frame <NUM> of the aircraft seat <NUM>. For instance, the integrally-formed connecting members <NUM> may include one or more bolt holes positioned to align with one or more bolts holes of the seat frame. In this regard, the swivel assembly thus becomes the spar, mounting the seat frame and the attached seat back to the base rails without adding height to the seat. By way of another example, as shown in <FIG>, the integrally-formed connecting members may be configured to mount to the one or more fixed base rails <NUM> of the base assembly <NUM>. For instance, the integrally-formed connecting members may include one or more bolt holes positioned to align with one or more bolt holes of the one or more fixed base rails <NUM>. In this regard, the swivel assembly thus becomes the spar, mounting the base rails to the seat frame and the attached seat back without adding height to the seat.

Referring to <FIG>, the swivel mechanism may include one or more inner rings. For example, the swivel mechanism may include a first inner ring <NUM>. By way of another example, the swivel mechanism may include an additional inner ring <NUM>. The outer ring <NUM> (swivel plate <NUM>) may be positioned between the first inner ring <NUM> and the additional inner ring <NUM>. When the outer ring <NUM> is fixed to the seat <NUM>, the one or more inner rings <NUM>, <NUM> may be configured to rotate. When the one or more inner rings <NUM>, <NUM> are held steady, the outer ring <NUM> may be configured to rotate.

The swivel mechanism may include one or more ball bearings <NUM>. For example, the swivel mechanism may include a first ball bearing <NUM> positioned between the outer <NUM> (swivel plate <NUM>) and the first inner ring <NUM>. By way of another example, the swivel mechanism may include an additional ball bearing <NUM> positioned between the outer <NUM> (swivel plate <NUM>) and the additional inner ring <NUM>.

The swivel mechanism may include a toothed ring <NUM> configured to arrest the relative motion between the inner rings and the outer ring as required in the upright or upside down configuration.

The swivel mechanism may include one or more fasteners <NUM> configured to couple the one or more swivel mechanism components to each other. For example, the first inner ring <NUM> may include one or more fastener holes configured to receive a portion of the one or more fasteners <NUM>.

The vertical adjustment system includes a tracking assembly <NUM> configured to allow the aircraft seat <NUM> to move side-to-side and fore-and-aft within a select range of motion.

Referring to <FIG>, the swivel assembly <NUM> includes a plurality of pillow block assemblies <NUM>. For example, the swivel plate may be configured to couple to four or more pillow block assemblies <NUM>. For instance, each pillow block assembly <NUM> may be configured to couple to the outer ring <NUM>.

Each pillow block assembly <NUM> includes a pillow block <NUM> and a plurality of rollers <NUM>. For example, each pillow block assembly <NUM> may include a pillow block <NUM> and four or more rollers <NUM>. The plurality of rollers <NUM> may be configured to provide stable vertical movement along the vertical stabilizer rods <NUM> of the tracking assembly <NUM>.

Referring to <FIG>, the tracking assembly <NUM> includes a plurality of slide tubes <NUM>. For example, the tracking assembly <NUM> may include one or more slide tubes <NUM> for side-to-side translating movement. By way of another example, the tracking assembly <NUM> may include one or more slide tubes <NUM> for fore-and-aft translating movement. In this regard, the seat frame and the attached seat back may be permitted to slide side-to-side and fore-and-aft within the range of motion providing by the length of the slide tubes. The plurality of slide tubes <NUM> may be locked via a tube locking mechanism <NUM>. For example, the locking mechanism <NUM> may be configured to engage the plurality of slide tubes <NUM> to cause the plurality of slide tubes <NUM> to lock in a select position. This permits a seated passenger a wide range of seat adjustment during travel, as well as the ability to slide the aircraft seat <NUM> away from the fuselage and aft while swiveling via the swiveling assembly to comfortably stand up and leave the aircraft seat.

The tracking assembly includes a plurality of slide bearings <NUM> configured to receive a portion of the plurality of slide tubes <NUM>. For example, the tracking assembly <NUM> may include one or more slide bearings <NUM> for side-to-side translating movement. For instance, the one or more slide bearings <NUM> for side-to-side translating may be configured to receive one or more slide tubes <NUM> for side-to-side translating. In this regard, the slide tube may slide/translate a select distance based on the length of the slide tube. By way of another example, the tracking assembly <NUM> may include one or more slide bearings <NUM> for fore-and-aft translating movement. For instance, the one or more slide bearings <NUM> for fore-and-aft translating movement may be configured to receive one or more slide tubes <NUM> for fore-and-aft translating movement. In this regard, the slide tube may slide/translate a select distance based on the length of the slide tube.

The tracking assembly <NUM> includes a tracking plate <NUM>. The tracking plate <NUM> may include a plurality stabilizer rods <NUM>. The plurality stabilizer rods <NUM> may be configured to couple to the swivel assembly <NUM> via the pillow block assemblies <NUM>. For example, the swivel assembly <NUM> including the pillow block assemblies <NUM> may be configured to couple to the tracking assembly <NUM> via the four or more vertical stabilizer rods <NUM>. In this regard, the pillow block assemblies <NUM> may be configured to provide stable vertical movement via the plurality of vertical stabilizer rods <NUM> and the plurality of rollers <NUM>.

Referring to <FIG>, the tracking assembly <NUM> may couple to the swivel assembly <NUM> via the one or more stabilizer rods <NUM> and plurality of vertical rollers <NUM> It is noted that the tracking assembly <NUM> and the swivel assembly <NUM> may be adapted and mounted in any orientation to cater to various aircraft seat base designs and requirements. For example, as shown in <FIG>, the tracking assembly <NUM> and the swivel assembly <NUM> may be mounted in an upright orientation of the aircraft seat <NUM>. For instance, the swivel assembly <NUM> may be mounted to the seat frame and the tracking assembly <NUM> may be mounted to the base assembly. By way of another example, as shown in <FIG>, the tracking assembly <NUM> and the swivel assembly <NUM> may be mounted in an upside down orientation of the aircraft seat <NUM>. For instance, the swivel assembly <NUM> may be mounted to the base assembly and the tracking assembly <NUM> may be mounted to the seat frame.

Referring to <FIG>, the vertical adjustment system <NUM> includes an actuation assembly <NUM> configured to adjust a vertical height of the aircraft seat <NUM>. For example, the actuation assembly <NUM> may be configured to provide at least approximately <NUM> inches of vertical adjustment, with infinite positions between the lowest and highest positions. In this regard, the actuation assembly <NUM> may be configured to allow the aircraft seat <NUM> to raise vertically between <NUM>-<NUM> (<NUM>-<NUM> inches), with infinite positions between <NUM>-<NUM> (<NUM>-<NUM> inches).

The actuation assembly <NUM> includes an actuator <NUM> configured to adjust a vertical height of the aircraft seat <NUM>. The actuation assembly <NUM> may include any type of actuator including, but not limited to, a gas spring actuator, hydraulic actuator, coil spring-damper actuation system, a rotary actuator, or the like.

The actuation assembly <NUM> includes a release mechanism <NUM> configured to couple to a rotary portion of the sparvel. In this regard, the release mechanism <NUM> will rotate along with the seat's swivel, thus there is no need to have slack.

The release mechanism <NUM> may include a pull lever <NUM> and a conduit <NUM> to release the actuator <NUM>. For example, the conduit <NUM> may be pulled up to pivot the pull lever <NUM> down to release the actuator <NUM>.

The release mechanism <NUM> may include one or more brackets <NUM> configured to hold one or more components of the release mechanism. For example, the release mechanism may include a bracket <NUM> configured to hold the pull lever <NUM>. For instance, the bracket <NUM> may couple to one or more portions of the swivel mechanism to secure the pull lever <NUM>. By way of another example, the release mechanism <NUM> may include a bracket <NUM> configured to hold the cable conduit <NUM>. For instance, the bracket <NUM> may couple to one or more portions of the swivel mechanism to secure the cable conduit <NUM>.

The aircraft seat <NUM> may be adjusted electrically. For example, the aircraft seat <NUM> may include a control panel for adjusting the aircraft seat <NUM>. The control panel may be coupled to an aircraft controller. For example, the conduit <NUM> may directly run into the a control panel coupled to the arms <NUM> of the aircraft seat <NUM>. In this regard, a passenger may electrically adjust one of swivel, tracking, or vertical height via the control panel.

<FIG> in general illustrate a helix vertical adjustment system <NUM> for an aircraft seat <NUM>, in accordance with one or more embodiments of the disclosure. It is noted that the description of the various embodiments, components, and operations described previously herein with respect to the aircraft seat <NUM> should be interpreted to extend to the system <NUM>, and vice versa. Further, is noted that the description of the various embodiments, components, and operations described previously herein with respect to the system <NUM> should be interpreted to extend to the system <NUM>, and vice versa, unless otherwise noted herein.

The aircraft seat <NUM> may include a helix vertical adjustment system <NUM>. It is noted that the vertical adjustment system <NUM> may be adapted and mounted in any orientation to cater to various aircraft seat base designs and requirements. For example, the helix vertical adjustment system <NUM> may be mounted in an upright orientation of the aircraft seat <NUM>. For instance, a portion of the helix adjustment system <NUM> may be hard mounted to a portion of the tracking plate. By way of another example, the helix vertical adjustment system <NUM> may be mounted in an upside down orientation of the aircraft seat <NUM>.

The helix vertical adjustment system <NUM> may include a swivel plate <NUM> including integral-connecting members <NUM> and a traversely-extending spar (e.g., a sparvel) and the tracking assembly <NUM>.

The helix vertical adjustment system <NUM> may include a helix swivel mechanism <NUM> configured to allow the aircraft seat <NUM> to rotate (e.g., swivel) about a central axis. For example, the helix swivel mechanism <NUM> may include a shaft <NUM> including one or more helical protrusions <NUM> (e.g., protrusions in a helical configuration). The shaft <NUM> may be mounted to a portion of the swivel plate <NUM>. It is noted that the helix swivel mechanism <NUM> may be configured to provide rigidity for the adjustment system <NUM>.

The helix vertical adjustment system <NUM> may include an actuator <NUM> configured to adjust a vertical height of the aircraft seat <NUM>. The adjustment system <NUM> may include any type of actuator including, but not limited to, a gas spring actuator, hydraulic actuator, coil spring-damper actuation system, a rotary actuator, or the like. For example, as shown in <FIG>, the actuator <NUM> may include a gas spring configured to be mounted within the shaft <NUM> of the helix mechanism <NUM> to adjust a vertical height of the aircraft seat <NUM>. In this regard, the shaft <NUM> may include an internal cavity to house the actuator <NUM>.

The helix vertical adjustment system <NUM> may include a locking mechanism <NUM> configured to lock the aircraft seat <NUM> in a select position. For example, the helix vertical adjustment system <NUM> may include a ring brake locking mechanism <NUM>.

The helix vertical adjustment system <NUM> may include one or more stabilizer rods <NUM>. For example, the helix vertical adjustment system <NUM> may include one or more vertical stabilizer rods <NUM> configured to couple to a portion of the base assembly (e.g., fixed base rails) and a portion of the locking mechanism <NUM>. It is noted that the one or more stabilizer rods <NUM> may be configured to provide additional rigidity for the adjustment system <NUM>.

Claim 1:
A vertical adjustment system (<NUM>) for an aircraft seat, comprising:
a swivel assembly (<NUM>), the swivel assembly (<NUM>) comprising:
a swivel plate (<NUM>) including integrally-formed connecting members (<NUM>), the integrally-formed connecting members configured to couple to a portion of the aircraft seat; and
a swivel mechanism (<NUM>) configured to rotate the aircraft seat about a central axis of the aircraft seat;
a tracking assembly (<NUM>), the tracking assembly (<NUM>) comprising:
a plurality of slide tubes (<NUM>) configured to slide the aircraft seat one of side-to-side or fore-and-aft;
a plurality of slide bearings (<NUM>) configured to receive a portion of the plurality of slide tubes; and
a tracking plate (<NUM>) coupled to the plurality of slide bearings (<NUM>); and
an actuation assembly (<NUM>), the actuation assembly comprising:
an actuator (<NUM>) configured to provide a vertical height adjustment for the aircraft seat, the actuator configured to arrest relative motion between a base assembly (<NUM>, <NUM>) of the aircraft seat and an upper portion of the aircraft seat;
a release mechanism (<NUM>), the release mechanism (<NUM>) configured to couple to a rotatory portion of the swivel plate, the release mechanism (<NUM>) configured to release the actuator;
a plurality of vertical stabilizer rods (<NUM>) coupled to a portion of the tracking plate; and
a pillow block assembly (<NUM>), the pillow block assembly comprising:
a plurality of pillow blocks (<NUM>) coupled to a portion of the swivel plate; and
a plurality of rollers (<NUM>) coupled to a portion of the plurality of pillow blocks, the plurality of rollers (<NUM>) configured to receive a portion of the plurality of stabilizer rods, the plurality of rollers (<NUM>) configured to provide stability along the vertical stabilizer rods when the actuator provides the vertical height adjustment.