Patent ID: 12240606

DETAILED DESCRIPTION OF THE INVENTION

Reference will now be made in detail to the subject matter disclosed, which is illustrated in the accompanying drawings.

Before explaining one or more embodiments of the disclosure in detail, it is to be understood the embodiments are not limited in their application to the details of construction and the arrangement of the components or steps or methodologies set forth in the following description or illustrated in the drawings. In the following detailed description of embodiments, numerous specific details may be set forth in order to provide a more thorough understanding of the disclosure. However, it will be apparent to one of ordinary skill in the art having the benefit of the instant disclosure the embodiments disclosed herein may be practiced without some of these specific details. In other instances, well-known features may not be described in detail to avoid unnecessarily complicating the instant disclosure.

As used herein a letter following a reference numeral is intended to reference an embodiment of the feature or element that may be similar, but not necessarily identical, to a previously described element or feature bearing the same reference numeral (e.g.,1,1a,1b). Such shorthand notations are used for purposes of convenience only and should not be construed to limit the disclosure in any way unless expressly stated to the contrary.

Further, unless expressly stated to the contrary, “or” refers to an inclusive or and not to an exclusive or. For example, a condition A or B is satisfied by any one of the following: A is true (or present) and B is false (or not present), A is false (or not present) and B is true (or present), and both A and B are true (or present).

In addition, use of “a” or “an” may be employed to describe elements and components of embodiments disclosed herein. This is done merely for convenience and “a” and “an” are intended to include “one,” “one or more,” or “at least one,” and the singular also includes the plural unless it is obvious that it is meant otherwise.

Finally, as used herein any reference to “one embodiment” or “some embodiments” means that a particular element, feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment disclosed herein. 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.

FIGS.1-5Ein general illustrate a monitor stop device, in accordance with one or more embodiments of the disclosure.

Aircraft seats often contain in-flight entertainment (IFE) devices installed within the seatback of the aircraft seat. During a head injury criterion (HIC) event, it is possible for an aircraft training device (ATD) to be trapped underneath the top-mounted back-seat monitor. More particularly, a head of a passenger may become trapped underneath a back-seat monitor, where the monitor is a top-mounted monitor that hinges from the top. Head entrapment is a major safety concern, as it would not allow a passenger to exit their row easily and may also prevent other passengers from exiting the row.

Conventional devices often include components (e.g., support pins, brackets, etc.) that are apart of the monitor assembly (e.g., coupled to the monitor itself). Such components add to the weight of the monitor assembly and increase the mass that a passenger's head is hitting, thereby increasing the HIC score. Further, in the event of a false deployment, it may be difficult to reset the device. Additionally, conventional devices are often one-time use devices.

In addition, in select industries the build of the seat (and any included components within the build) may be required to meet guidelines and/or standards. For example, aircraft seats may be required to meet aviation guidelines and/or standards. For instance, the select aircraft seats 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.

As such, it would be desirable to provide a monitor stop device for a top-mounted tilt monitor (i.e., a monitor that rotates about the top axis of the monitor). The monitor stop device should prevent a head of a passenger from becoming trapped by the back of the top-mounted tilt monitor. For example, the monitor stop device should prevent the top-mounted tilt monitor from deploying when load is applied to the monitor, such that the head of the passenger does not become entrapped. The monitor stop device should be a multi-use device that may be reset after the HIC event. The monitor stop device should not be visible to a passenger prior to an HIC event. The monitor stop device should not add additional weight to the monitor itself, such that the mass hitting a passenger's head is not increased. The monitor stop device should be configured in accordance with aviation guidelines and/or standards.

Referring in general toFIGS.1-5E, one or more monitor stop devices may be integrated within an aircraft seat100installed within an aircraft cabin. For example, the aircraft seat100may include, but is not limited to, a business class or first-class passenger seat, an economy-class passenger seat, a crew member seat, or the like. It is noted the terms “aircraft seats” and “passenger seats” may be considered equivalent, for purposes of the disclosure.

The aircraft seat100may be rotatable about an axis (e.g., swivelable). The aircraft seat100may be fully positionable between the outer limits of motion as defined by the moveable components of the aircraft seat100. Where the aircraft seat100is installed within a passenger compartment, the aircraft seat100may be fully positionable between the outer limits of motion as defined by one or more passenger compartment monuments of the passenger compartment. It is noted an upright or raised position may be considered a taxi, takeoff, or landing (TTL) position during select stages of flight (though the upright or raised position is not limited to use during the select stages of flight as the TTL position, but also may be used at any point during the flight), for purposes of the present disclosure. In addition, it is noted that any position that does not meet the above-defined requirements of the TTL position may be considered a non-TTL position, for purposes of the present disclosure. Further, it is noted the aircraft seat100may be actuatable (e.g., translatable and/or rotatable) from the TTL position to a non-TTL position, and/or vice versa. Further, it is noted the aircraft seat100may be capable of a fully upright or raised position, and that the TTL position may have a more reclined seatback cushion and a more angled upward seat pan cushion as compared to the fully upright or raised position. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

In general, an aircraft seat100may be translatable (e.g., trackable or slidable). The aircraft seat100may be rotatable about an axis cross-wise through the aircraft seat100into a position including, but not limited to, the upright or raised position, one or more lounge or reclined positions, and a lie-flat or bed position. For example, the aircraft seat100may transition directly between the upright or raised position and the lie-flat or bed position. By way of another example, it is noted the aircraft seat100may transition through one or more lounge or reclined positions between the upright or raised position and the lie-flat or bed position. By way of another example, the aircraft seat100may transition into one or more lounge or reclined positions in a motion separate from the transition between the upright or raised position and the lie-flat or bed position. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

The aircraft seat100may include a seat pan102and a seatback104. The aircraft seat100may further include one or more arms. The aircraft seat100may be coupled to a base. The base may be couplable to a floor of an aircraft cabin.

The seatback104may include a headrest. For example, the headrest may be integrated within the seatback104. By way of another example, the headrest may be a separate component coupled to (or inserted into) the seatback104. For instance, the headrest may be movable relative to the seatback frame of the aircraft seat100(e.g., adjustable, removable, or the like).

The seatback102may include a seatback bezel106configured to couple to a portion of a seatback frame. The seatback bezel106may include, but is not required to include, a cavity for storing a food tray, a storage compartment, a charging port, a headphone jack, and the like. The cavity may be defined by one or more surfaces of the seatback bezel106. For example, the cavity may be configured to store a food tray during TTL or non-TTL stages of flight. For instance, the seatback bezel106may include a latch configured to securely store the food tray in the stowed position within the cavity during TTL or non-TTL stages of flight.

The seatback bezel106may further include an in-flight entertainment (IFE) device108coupled to a surface of the seatback bezel106(e.g., in an actuatable position). For example, the seatback bezel106may include a top-tilting IFE device configured to rotate/actuate about a top axis, as will be discussed further herein.

The seatback bezel106may further include one or more monitor stop devices110. For example, the one or more monitor stop devices110may be coupled to the seatback bezel106and arranged proximate to a portion of the IFE device108, such that the one or more monitor stop devices110may capture at least portion of the IFE device108during deployment to prevent possible head entrapment, as will be discussed further herein.

FIG.2illustrates an exploded view of the monitor stop device110, in accordance with one or more embodiments of the present disclosure.FIGS.3A-3Cillustrate simplified schematics of the monitor stop device110coupled to the seatback bezel106, in accordance with one or more embodiments of the present disclosure.

Referring toFIG.2, the monitor stop device110may include a spring-loaded pin assembly200. The spring-loaded pin assembly200may include, but is not limited to, a pin202, a spring204, a bushing206(or sleeve bearing), a washer208, a retaining clip210, and the like.

The spring204of the spring-loaded pin assembly200may be configured to couple to a shaft of the pin202via at least one of the bushing206, the washer208, or the retaining clip210. For example, as shown inFIG.3C, the bushing206may be configured to secure a first end of the spring204to a first end of the shaft of the pin202and the washer208and retaining clip210may secure a second send of the spring204to a second end of the shift of the pin202. In this regard, the spring204may be configured to compress along a horizontal axis of the pin shaft between the first end and the second end, and vice versa, when a force is applied to the pin202.

The monitor stop device110may include a housing212configured to house (or surround) one or more components of the spring-loaded pin assembly200. For example, as shown inFIGS.3A-3C, the housing212may be configured to house (or surround) at least a portion of the pin202and the spring204.

The housing212may be formed of a single piece or a plurality of pieces coupled together. For example, as shown inFIG.2, the housing212may include a first portion213coupled to a second portion215via a fastener217.

The housing212may be formed of any flexible material suitable for housing/surrounding one or more components of the spring-loaded pin assembly200without adding too much weight to the aircraft seat100. For example, the housing212may be formed of sheet metal. By way of another example, the housing212may be formed of an injection molded material. For instance, the housing212may be formed of plastic.

The housing212may include one or more pin openings214configured to receive a least portion of a shaft of the pin202. For example, the pin202may translate through the one or more pin openings214of the housing212. For instance, the spring204may be configured to compress when a force is applied to the monitor to cause the pin202to translate through the one or more pin openings214of the housing212.

Referring toFIGS.3A-3C, the housing212may be configured to couple to the seatback bezel106via one or more fasteners. For example, the housing212may be configured to couple the spring-loaded pin assembly200to the seatback bezel106. For instance, as shown inFIG.3A, the housing212and the spring-loaded pin assembly200may be configured to couple to the seatback bezel106at a center axis of the monitor, such that the lever of the spring-loaded pin assembly200is shorter to allow the spring-loaded pin assembly200to deploy quickly to capture the monitor and prevent head entrapment.

The IFE device108may include a monitor shroud300configured to couple a monitor301to the seatback bezel106of the seatback104.

The monitor301may include a top-tilting monitor301configured to rotate/tilt about a top axis of the monitor. It is noted that the monitor stop device110may be used with any suitable top-tilting monitor301.FIGS.3A-3Care provided merely for illustrative purposes and shall not be construed as limiting the scope of the present disclosure.

Referring toFIG.3C, the monitor shroud300may include a tab302. The tab302may be configured to translate to allow the pin202of the spring-loaded pin assembly200to translate through an opening304in the seatback bezel106. For instance, when force is applied to the monitor301, the force may cause the tab302to translate towards the seatback104(in the same direction as the applied force) such that the pin202may deploy through the opening304and capture the monitor301when the monitor301swings out towards the passenger (in the opposite direction of the applied force).

It is noted thatFIGS.2-3Care provided merely for illustrative purposes and shall not be construed as limiting the scope of the present disclosure. The spring-loaded pin assembly200may include any type of spring, pin, and/or fastener/bearing suitable for preventing the monitor from deploying. The housing212may be any shape, size, or configuration suitable for surrounding the spring-loaded pin assembly200and coupling the spring-loaded pin assembly200to the seatback bezel106of the aircraft seat100.

FIG.4illustrates a flowchart depicting a method of process400for deployment of the pin202of the monitor stop device110after a load has been applied to the aircraft seat100, in accordance with one or more embodiments of the present disclosure.FIGS.5A-5Eillustrate a conceptual flow diagram of the method or process400for deployment of the pin202of the monitor stop device110, in accordance with one or more embodiments of the present disclosure.

In a step402, the monitor stop device110may be installed within a seatback bezel106of the aircraft seat100and positioned proximate to a top-tilting monitor301. When installed, the monitor stop device110may be hidden from the passenger, as shown inFIG.5A.

In a step404, during an HIC event, force may applied to the monitor. For example, as shown inFIGS.5B-5D, a head of a user may push in the monitor301(towards the monitor shroud300) during an HIC event. For instance, as shown inFIGS.5B-5D, during an HIC event, the head of the user may propel in the fore direction and may push the monitor301in the fore direction (towards the monitor shroud300).

In a step406, the monitor301may translate the monitor shroud300(or monitor closeout shroud300) to cause the tab302of the monitor shroud300to translate to allow the pin202to deploy. For example, as shown inFIGS.5C-5D, the tab302may be configured to translate to allow the pin202of the spring-loaded pin assembly200to translate through an opening304in the seatback bezel106. For instance, when force is applied to the monitor301, the force may cause the tab302to translate towards the seatback104(in the same direction as the applied force) such that the pin202may deploy through the opening304.

In a step408, the pin202may capture at least a portion of the monitor301to prevent the monitor301from fully deploying. For example, as shown inFIG.5E, once the pin202is deployed (in step406), the pin202may be configured to capture the monitor301when the monitor301swings out towards the passenger (in the opposite direction of the applied force) to prevent the monitor301from fully deploying and causing head entrapment.

It is noted the method or process400is not limited to the steps and/or sub-steps provided. The method or process400may include more or fewer steps and/or sub-steps. In addition, the method or process400may perform the steps and/or sub-steps simultaneously. Further, the method or process400may perform the steps and/or sub-steps sequentially, including in the order provided or an order other than provided. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

It is noted the monitor stop device110may be configured to work with any aircraft seat100and/or any set of components in the aircraft seat100. For example, the monitor stop device110may be configured to take into account any changes in shape/size of the components of the aircraft seat100(e.g., monitor, seatback bezel, and the like).

Although embodiments of the disclosure illustrate the monitor stop device110integrated within the aircraft seat100, it is noted, however, that the monitor stop device110and/or components of the monitor stop device110are not limited to the aviation environment and/or the aircraft components within the aviation environment. For example, the monitor stop device110and/or components of the monitor stop device110may be configured for any type of vehicle known in the art. For instance, the vehicle may be any air, space, land, or water-based personal equipment or vehicle; any air, space, land, or water-based commercial equipment or vehicle; any air, space, land, or water-based military equipment or vehicle known in the art. By way of another example, the monitor stop device110and/or components of the monitor stop device110may be configured for commercial or industrial use in either a home or a business. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Although the disclosure has been described with reference to the embodiments illustrated in the attached drawing figures, equivalents may be employed and substitutions made herein without departing from the scope of the claims. Components illustrated and described herein are merely examples of a system/device and components that may be used to implement embodiments of the disclosure and may be replaced with other devices and components without departing from the scope of the claims. Furthermore, any dimensions, degrees, and/or numerical ranges provided herein are to be understood as non-limiting examples unless otherwise specified in the claims.