阅读说明：本技术 带有可配置的分隔件系统的航空器 (Aircraft with configurable spacer system ) 是由 I·G·斯科利 G·诺达 M·罗梅罗 于 2020-09-17 设计创作，主要内容包括：一种航空器,包括本体,本体限定机舱内部并包括外表面和内表面,所述内表面包括地板,并且航空器至少包括第一分隔件构件,第一分隔件构件具有底部,所述底部上包括分隔件安装部件的集合。所述地板上包括本体安装部件的集合。分隔件安装部件的集合可移除地安装到本体安装部件的集合,并且第一分隔件定位成使得其将机舱内部分隔成乘客区段和飞行员区段。(An aircraft includes a body defining a cabin interior and including an exterior surface and an interior surface, the interior surface including a floor, and at least a first divider member having a bottom including a collection of divider mounting components thereon. The floor includes a collection of body mount components thereon. A set of divider mounting components is removably mounted to the set of body mounting components, and a first divider is positioned such that it divides the cabin interior into a passenger section and a pilot section.)

1. An aircraft, comprising:

a body defining a nacelle interior, wherein the body comprises an exterior surface and an interior surface, wherein the interior surface comprises a floor,

at least a first divider member having a bottom including a set of divider mounting components thereon, wherein the floor includes a set of body mounting components thereon, wherein the set of divider mounting components are removably mounted to the set of body mounting components, wherein the first divider is positioned such that it divides a cabin interior into a passenger section and a pilot section.

2. The aircraft of claim 1, wherein the first divider member includes at least one functional component on a front portion thereof, wherein the functional component is at least one of an entertainment system, a cup holder, a charging port, a storage pocket, a handle, a tie anchor, or a lighting device.

3. An aircraft according to claim 1, wherein the first divider member comprises a deposit extending into the pilot section.

4. An aircraft according to claim 3, wherein the storage section defines a storage area accessible through a door of the aircraft.

5. The aircraft of claim 1, wherein the body comprises a composite monocoque structure.

6. An aircraft according to claim 1, wherein the aircraft is a vertical take-off and landing aircraft.

7. The aircraft of claim 1, further comprising at least a first panel member having a front and a rear, wherein the rear includes a set of panel-mounted components thereon, wherein the inner surface of the body includes a second set of body-mounted components thereon, wherein the set of panel-mounted components is removably mounted to the second set of body-mounted components.

8. A method implemented on an aircraft, the aircraft comprising a body defining a cabin interior, wherein the body comprises an exterior surface and an interior surface, the interior surface comprising a floor, and the aircraft comprising at least a first divider member having a bottom, wherein the bottom of the first divider member comprises a first set of divider mounting components thereon, wherein the floor comprises at least a first set of body mounting components thereon, wherein the first set of divider mounting components are removably mounted to the first set of body mounting components, and wherein the first divider is positioned such that it divides the cabin interior into a passenger section and a pilot section, the method comprising the steps of:

disconnecting the first set of spacer mounting members from the first set of body mounting members,

obtaining a second spacer member having a bottom including a second set of spacer mounting components thereon, wherein the second spacer member has a different shape than the first spacer member, an

Removably mounting the second set of spacer mounting members with the second set of body mounting members.

9. The method of claim 8, wherein the first set of body mount components includes a plurality of members, wherein the second set of body mount components includes a plurality of members, and wherein some members of the first set of body mount components are identical to some members of the second set of body mount components.

10. The method of claim 8, further comprising front and rear seats positioned in a cabin interior, wherein a first foot space region is defined between the front seat and a first divider member, wherein a second foot space region is defined between the front seat and a second divider member, and wherein one of the first and second foot space regions is larger than the other of the first and second foot space regions.

11. An aircraft, comprising:

a body defining a nacelle interior, wherein the body comprises a composite monocoque structure, wherein the body comprises an outer surface and an inner surface, and wherein the inner surface comprises a floor,

at least a first divider member having a bottom including a set of divider mounting components thereon, wherein the floor includes a set of body mounting components thereon, wherein the set of divider mounting components are removably mounted to the set of body mounting components, wherein the first divider is positioned such that it divides the cabin interior into a passenger section and a pilot section, wherein the first divider member includes a functional component on a front portion thereof, wherein the functional component is at least one of an entertainment system, a cup holder, a charging port, a storage pocket, a handle, a tie-down anchor, or a lighting device, and wherein the aircraft is a take-off and landing aircraft.

12. An aircraft according to claim 11, wherein the first divider member includes a deposit that extends into the pilot section.

13. An aircraft according to claim 12, wherein the storage section defines a storage area accessible through a door of the aircraft.

Technical Field

The present invention relates generally to aircraft dividers, and more particularly to VTOL aircraft with configurable aircraft divider systems.

Background

With the increasing popularity of ride sharing (edge sharing), small aircraft are being conceived that can accommodate a small number of passengers traveling relatively short distances (e.g., urban) are being conceived. However, current smaller aircraft such as helicopters, light civilian/VIP aircraft, and other aircraft with similarly sized interiors are too bulky, expensive, and low-volume to meet the demands for new Vertical Take Off and Landing (VTOL) and powered VTOL (known as eVTOL) aircraft.

Some of the challenges in developing these aircraft are cost and weight. The manufacturing costs and weight of prior art helicopters and light aircraft are cost prohibitive in trying to lower the final price point for passengers in a VTOL aircraft. Prior art aircraft typically cost millions of dollars per rack, while VTOL aircraft cost targets in the range of hundreds of thousands of dollars per rack. Thus, limiting the number of components on an aircraft may reduce both weight and cost.

Disclosure of Invention

According to a first aspect of the invention, an aircraft is provided, comprising a body defining a cabin interior and comprising an outer surface and an inner surface, and comprising at least a first panel member having a front portion and a rear portion. The rear portion includes a set of panel mounting members thereon and the body includes a set of body mounting members on an inner surface thereof. The set of panel mounting components is removably mounted to the set of body mounting components (to form a panel system). In a preferred embodiment, the inner surface of the body includes at least a first panel recess defined therein, and the second set of mounting components are located in the first panel recess.

In a preferred embodiment, the aircraft includes front and rear rows of seats positioned in the cabin interior. The body includes a door positioned adjacent the front seat, the set of body mount components are located on the door, and the first panel is secured to the door. Preferably, the first panel member includes at least one functional component on a front portion thereof, such as at least one of an armrest, a cup holder, a charging port, a storage bag, a handle, a tie down anchor (tie down anchor), or a lighting device. Preferably, the body is a composite monocoque structure/composite load bearing structure and the aircraft is a vertical take-off and landing aircraft. In a preferred embodiment, the first panel member is in electrical communication with the body. This may be achieved by electrically connecting at least one of the panel mounting members with at least one of the body mounting members. In a preferred embodiment, the aircraft with the panel system further comprises a spacer system.

According to another aspect of the invention, a method implemented on or in an aircraft is provided, the aircraft including a body defining a cabin interior. The body includes an outer surface and an inner surface, and includes at least first and second panel members each having a front portion and a rear portion. The first panel member includes a first set of panel mounting components on a rear portion thereof and the second panel member includes a second set of panel mounting components on a rear portion thereof. At least first and second sets of body mount components are included on the inner surface of the body. The first set of panel mounting components is removably mounted to the first set of body mounting components, and the second set of panel mounting components is removably mounted to the second set of body mounting components. The method comprises the following steps: disconnecting the first set of panel mounting components from the first set of body mounting components; obtaining a third panel member having a front and a rear, the rear including a third set of panel mount components thereon; and removably mounting the third set of panel mounting components with the first set of body mounting components.

In a preferred embodiment, the method includes disconnecting the second set of panel mounting components from the second set of body mounting components. The second panel member may be replaced with a fourth panel member or the second set of body mounted components may be left unoccupied for the next use of the aircraft. In a preferred embodiment, the first functional component requires no power and the second functional component requires power (e.g., when upgrading from a base-type internal to a VIP-type internal).

According to another aspect of the invention, there is provided an aircraft comprising a body defining a cabin interior and comprising an exterior surface and an interior surface with a floor, and at least a first divider member having a bottom including a collection of divider mounting members thereon. The floor includes a collection of body mount components thereon. The set of divider mounting components is removably mounted to the set of body mounting components, and a first divider is positioned such that the first divider divides the interior cabin portion into a passenger section and a pilot section. In a preferred embodiment, the first divider member includes at least one functional component on a front thereof, wherein the functional component is at least one of an entertainment system, a cup holder, a charging port, a storage pocket, a handle, a tie-down anchor, or a lighting device.

In a preferred embodiment, the first divider member includes a storage portion that extends into the pilot section. The storage portion defines a storage area accessible through a door of the aircraft.

According to another aspect of the invention, a method is provided for implementation on an aircraft, the aircraft comprising a body defining a cabin interior and exterior surface and an interior surface comprising a floor, and the aircraft comprising at least a first divider member having a bottom. The first spacer member includes a first set of spacer mounting features on a bottom portion thereof. The floor includes at least a first set of body mount components thereon. The first set of divider mounting components are removably mounted to the first set of body mounting components, and the first divider is positioned such that the first divider divides the under-cabin portion into a passenger section and a pilot section. The method comprises the following steps: disconnecting the first set of spacer mounting members from the first set of body mounting members; obtaining a second spacer member having a bottom portion including a second set of spacer mounting components thereon and having a different shape than the first spacer member; and removably mounting the second set of divider mounting members with the second set of body mounting members.

In a preferred embodiment, the first set of body mount components includes a plurality of members, the second set of body mount components includes a plurality of members, and some of the members of the first set of body mount components are identical to some of the members of the second set of body mount components. Preferably, the aircraft includes front and rear rows of seats positioned in the cabin interior. A first footspace region is defined between the front seat and the first divider member, a second footspace region is defined between the front seat and the second divider member, and one of the first and second footspace regions is larger than the other of the first and second footspace regions. It will be appreciated that in embodiments having both a panel system and a divider system, the body mount components may be the same for the panel and divider, or they may be different.

The present invention provides a solution that addresses new needs for eVTOL and VTOL aircraft (collectively referred to herein as VTOL aircraft) due to deficiencies in the state of the art. Products within the current state of the art (such as helicopters, light civil/VIP aircraft with similarly sized interiors) are too bulky, expensive and low-volume to meet the demands for new types of eVTOL and VTOL aircraft. The present invention relates to a new interior product which in a preferred embodiment is specifically designed for use in VTOL aircraft.

The present invention includes integration and installation of panels with the primary structure and includes a new method of installing interior panels into the primary structure of a VTOL aircraft and may include, but is not limited to, interior panels for doors, ceilings, Personal Service Units (PSU) and cargo holds. The design feature achieved is that the primary structure acts as a decorative surface visible to the passenger, with inset (instet) locations for the interior panels to be inserted or installed therein. It will be appreciated by those of ordinary skill in the art that the present invention may provide weight savings and cost effectiveness or cost reduction when compared to the prior art, and may also provide opportunities for custom branding on panels.

In a preferred embodiment, the panel may be installed and removed with a quick release system such that the panel is installed temporarily and not permanently. Thus, the panels may be altered as desired.

In a preferred embodiment, the panel may also be modular and include one or more features integrated therewith or thereon. Such features may include an armrest, a handle, a cup holder, a storage portion, a power portion (e.g., a USB charging port), a lighting device, and so forth. Preferably, the panels also provide sound and vibration damping.

In a preferred embodiment, the body of the aircraft comprises a composite monocoque structure comprising an a-side (exterior) and a B-side (interior). Preferably, at least a portion of the interior of the body is visible to a passenger in use. The inside includes the system of plugging and playing the panel in the key area. The panels may be of different shapes for different areas but include a common quick release fastening system. Preferably, the panels help to insulate sound and vibration, but also to assist in contouring the interior of the vehicle. This platform approach allows panel system manufacturers to use the same system across multiple OEMs. In other words, the present invention includes a common fastener that allows for standardization across multiple OEMs for installation, the common feature providing the benefit of platform commonality rather than providing different attachment methods for each different VTOL manufacturer or OEM.

In a preferred embodiment, the panels may be reinforced with features that may be used on the interior of the aircraft. The panel itself provides a baseline product that can be enhanced by providing selectable options of functionality, such as handrails. For example, the "New York taxi" version may simply include the plastic panel interior side only, while the VIP version of the panel may include a padded leather covering, with a cup holder built into it, and a USB charger.

VTOL aircraft may also be used for cargo consignment. In some scenarios, the same aircraft may be used for passenger transport at times and freight transport at other times. In this case, it is crucial that the removal and replacement of the panels is quick. Thus, the panels may include provisions (provisions) or features related to the consignment of goods, such as loops, hooks, or other fastening portions for the attachment of straps. The aircraft may also be used for emergency evacuation and the panels may be functionally equipped as required. Thus, the system enables a user to quickly remove and replace panels to adequately aesthetically replace passenger vehicles with cargo vehicles in a minimum amount of time.

The present invention relates to systems that allow one or more aircraft dividers or partitions to be configured for different uses and interior arrangements that may be provided for stowage, additional front leg room, nacelle consolidation, asymmetric nacelle configuration (or symmetric nacelle configuration), and the like.

This platform approach allows a divider member system manufacturer to use the same system across multiple OEMs. In other words, the present invention includes a common attachment system that allows for standardization of installation across multiple OEMs that provides the benefit of platform commonality rather than providing different attachment methods for each different VTOL manufacturer or OEM.

The present invention allows the divider member to be easily removed and replaced with a divider member having a different configuration. This allows for a fast reconfiguration of the interior of the aircraft. Furthermore, the spacer member may comprise different built-in functions or components, depending on the intended use of the aircraft. For example, a simple divider member without a functional component thereon may be used for a cargo aircraft, while a divider member including functional components such as storage pockets, cup holders, charging ports, televisions, etc., and other components associated with passenger use may be included. For example, the base divider member may simply be a composite panel, and the VIP version may include a leather-covered composite panel with recessed lighting and cup holders.

It will be understood that both the removable panel system and the removable divider system may be used separately or together in a single aircraft.

The present invention may be used in conjunction with other concepts associated with VTOL aircraft such as the inventions and concepts taught in U.S. application No. 16/566,652, which is incorporated herein by reference in its entirety. The common quick release system and concept may be similar to the systems described in U.S. patent nos. 9,527,591 and 9,562,549, which are incorporated herein by reference in their entirety.

Drawings

The invention may be more readily understood by reference to the accompanying drawings in which:

fig. 1 is a plan view of a VTOL aerial vehicle including a panel system and a spacer system therein according to a preferred embodiment of the invention;

FIG. 2 is an elevational view of a portion of an aircraft showing a panel secured to the interior of the body of the aircraft;

FIG. 3 is an exploded perspective view of the panel member assembly;

FIG. 4 is an elevational cross-sectional view showing the panel member secured to the interior of the aircraft body;

FIG. 5 is an exploded perspective view showing a plurality of different panel members with functional components thereon;

fig. 6 is a plan view of a VTOL aerial vehicle including a spacer system therein in accordance with a preferred embodiment of the present invention;

fig. 7 is a plan view of a VTOL aerial vehicle having a different panel between the pilot section and the passenger section than in fig. 6;

FIG. 8 is an exploded perspective view of two different panels;

FIG. 9 is another exploded perspective view of two different panels; and

fig. 10 is a plan view of a VTOL aerial vehicle having different panels between the passenger and pilot sections and the cargo area than in fig. 6.

Like reference numerals refer to like parts throughout the several views of the drawings.

Detailed Description

The following description and drawings are illustrative and are not to be construed as limiting. Numerous specific details are described to provide a thorough understanding of the present disclosure. However, in certain instances, well-known or conventional details are not described in order to avoid obscuring the description. References to one embodiment or an embodiment in this disclosure may be, but are not necessarily, references to the same embodiment; and, such references mean at least one of the embodiments.

Reference in the specification to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the disclosure. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments necessarily mutually exclusive of other embodiments. Furthermore, various features are described which may be shown by some embodiments and not by others. Similarly, various requirements are described which may be requirements for some embodiments but not other embodiments.

The terms used in this specification generally have their ordinary meanings in the art, in the context of the present disclosure, and in the specific context in which each term is used. Certain terms used to describe the present disclosure are discussed below or elsewhere in this specification to provide additional guidance to the practitioner regarding the description of the present disclosure. For simplicity, certain terms will be highlighted, such as with italics and/or quotation marks: the use of highlighting has no effect on the scope and meaning of the term; the scope and meaning of a term are the same whether or not it is highlighted in the same context.

It will be understood that the same thing may be said in more than one way. Thus, alternative languages and synonyms may be used for any one or more of the terms discussed herein. It is not intended that a term be interpreted as specifically recited or discussed herein. Synonyms for certain terms are provided. The recitation of one or more synonyms does not exclude the use of other synonyms. The use of examples anywhere in this specification, including the use of examples of any term discussed herein, is illustrative only and is not intended to further limit the scope and meaning of the disclosure or any illustrative terms. Similarly, the present disclosure is not limited to the various embodiments presented in this specification.

Without intending to further limit the scope of the present disclosure, examples of instruments, devices, methods and their related results according to embodiments of the present disclosure are given below. Note that for the convenience of the reader, titles or subtitles may be used in the examples, which shall in no way limit the scope of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs. In case of conflict, the present document, including definitions, will control.

It will be understood that terms such as "forward", "rearward", "top", "bottom", "side", "short", "long", "up", "down", "aft", "forward", "inboard", "outboard" and "below" are used herein for ease of description only and refer to the orientation of the components as shown in the drawings. It should be understood that any orientation of the components described herein is within the scope of the present invention.

Referring now to the drawings wherein the showings are for the purpose of illustrating the invention and not for the purpose of limiting the same, fig. 1-5 show a VTOL aerial vehicle 10 including a modifiable panel system 12 therein. Fig. 1 shows a plan view of an aircraft 10 including a body 14 defining a cabin interior 16 and a plurality of panel members 18 secured to an interior surface 14a of the body 14. The panel members 18 each include a front portion 18a and a rear portion 18 b. The rear portion 18b includes a first or set of panel mounting members 20 thereon that are compatible with a second or set of body mounting members 22 on the inner surface 14a of the body 14. A set of panel mounting members 20 are removably mounted to a set of body mounting members 22. In general, this means that the set of panel mount components 20 can be easily and quickly removed from or disconnected from the set of body mount components 22, as discussed above. For example, as shown in fig. 3-4, the panel mounting members 20 may be posts, protrusions, or other male members that snap fit, press fit, or otherwise are received and retained into female receptacles (body mounting members) in the walls of the body 14. Fig. 3-4 show the ridge 21 on the male part received in the annular groove in the female part. However, this is merely exemplary and any complementary set of first and second mounting components that allow for quick release of the panel member from the body is within the scope of the invention. The male and female parts may be reversed such that the male part is on the wall and the female part is on the panel member.

As shown in fig. 2-4, in a preferred embodiment, the body 14 includes a plurality of panel recesses 24 that receive at least a portion of the panel members 18. The body mounting member 22 is positioned in the panel recess 24. This allows the panel member 18 to be inserted into the wall or body of the aircraft. The panel member 18 may be shaped such that a portion of the panel member is received in the panel recess 24 and inset therein, and the outer edges and/or surfaces may be flush with the inner surface 14a of the body 14. This may provide a relatively seamless appearance to the wall. Fig. 2 shows the first panel member 18 received in the forwardmost panel recess 24 and two further panel recesses 24 in which no panel member is received. Fig. 2 also shows a long panel member connected to the ceiling of the body 14. It will be appreciated that the panel member 18 may be of different sizes and may be attached to any interior surface within the interior of the nacelle. Additionally, the panel member 18 may be received in a panel recess or may be connected to an area of the body that is free of a panel recess.

As shown in fig. 5, in a preferred embodiment, the panel member 18 may include one or more features on its front that would be usable by a passenger or for other purposes. For example, the panel members may include a handrail 26, a cup holder 28, a charging port 30, a storage bag 32, a handle 34, tie-down anchors 36 (loops, hooks, etc. for connecting straps or cords to tie down goods), lighting, branding, openings for door latch mechanisms, and the like. In embodiments of the invention, the male and female mounting components may include electrical connection capabilities (at least one of the sets may include electrical connection capabilities). Thus, if the functional component requires power (e.g., lighting, charging port), power or electricity may be provided.

As shown in fig. 1, in a preferred embodiment, the aircraft 10 includes front and rear rows of seats 38, 38 positioned in the cabin interior. The seat 38 includes one or more doors 40 adjacent thereto for ingress and egress. The door may include a panel member 24 connected thereto.

Fig. 1 and 6-10 show a VTOL aerial vehicle 10 including a modifiable spacer system 50 therein. The system allows different dividers or partitions to be used with different OEM bodies or allows different dividers to be altered or replaced in different scenarios or arrangements within the same body.

Fig. 6, 7 and 10 show differently shaped forms of the divider 52 positioned between the pilot and passenger compartments. Similar to the panel system discussed above, the divider system 50 includes a first or set of dividers of mounting members 54 positioned on or associated with the dividers 52 and includes a second or set of bodies of mounting members 56 positioned on or associated with the walls, floors or ceilings of the bodies 14.

Fig. 8 shows a plurality of male parts representing a collection of spacer mounting parts 54 extending from the spacer 52 and shows a plurality of female parts on the floor or body 14 representing a collection of body mounting parts 56. All of the above discussion relating to the collection of mounting components on the panel system is relevant to the spacer system. Fig. 8 shows a collection of spacers 52 and body mounting members 56 associated therewith in different shapes. Thus, a first set of spacer mounting members 56 would be usable with one spacer, and a second set of spacer mounting members 56 would be usable with a different spacer.

Fig. 9 shows dividers similar to those in fig. 8, but with tracks or channels on the floor as a collection of body mount components 56 and footings on the divider 52 as a collection of divider mount components 54. The tracks or channels may be identical, used to mount the seat, or the tracks or channels may be separate.

As discussed above, an advantage of differently shaped dividers is the ability to provide space in different areas. For example, as shown in fig. 6, the storage spaces 60 may be disposed on both sides of the pilot seat. As shown in fig. 7, a foot space 62 may be provided for passengers in the front row. As shown in fig. 10, both the storage space 60 and the foot space 62 may be provided by the dividers shown therein. The storage space 60 may simply be a space within the interior of the aircraft, as represented by the phantom lines in fig. 6, or the storage space may be defined by a structure, as shown in fig. 10. Fig. 9 shows a storage portion 64 that is part of and/or connected to the partition 52. The storage portion 64 may include thereon a first set of mounting features 54 that are secured when the divider 52 is installed.

In a preferred embodiment, the divider 52 includes functional components thereon, similar to the panel system discussed above (any of the functional components discussed above may be included on the divider). For example, FIG. 8 shows tie-down anchors 36 and entertainment system 66 (e.g., TV) on the divider.

Throughout this specification and claims, the words "comprise", "comprising", and the like, are to be construed in an inclusive sense as opposed to an exclusive or exhaustive sense, unless the context clearly requires otherwise; that is, it is to be read in the sense of "including, but not limited to". As used herein, the terms "connected," "coupled," or any variant thereof, means any connection or coupling, either direct or indirect, between two or more elements; the coupling of the connections between the elements may be physical, logical, or a combination thereof. Additionally, the words "herein," "above," "below," and words of similar import, when used in this application, shall refer to this application as a whole and not to any particular portions of this application. Words using the singular or plural number in the above detailed description may also include the plural or singular number, respectively, where the context permits. In a reference to a list of two or more items, the word "or" encompasses all of the following interpretations of the word: any item in the list, all items in the list, and any combination of items in the list.

The above detailed description of embodiments of the disclosure is not intended to be exhaustive or to limit the teachings to the precise form disclosed above. While examples and specific embodiments for the disclosure have been described above for illustrative purposes, various equivalent modifications are possible within the scope of the disclosure, as those skilled in the relevant art will recognize. Additionally, any specific numbers mentioned herein are merely examples; alternate embodiments may use different values, measurements, or ranges.

The teachings of the present disclosure provided herein are applicable to other systems, not necessarily the systems described above. The elements and acts of the various embodiments described above can be combined to provide further embodiments. Any measurements described or used herein are exemplary only and are not limiting of the present invention. Other metrics may also be used. In addition, any particular materials mentioned herein are merely examples; alternate embodiments may use dissimilar materials.

The entire contents of any patents and applications and other references mentioned above, including any references that may be listed in the attached application documents, are incorporated herein by reference. Aspects of the disclosure can be modified, if necessary, to utilize the systems, functions, and concepts of the various references described above to provide yet another embodiment of the disclosure.

These and other changes can be made to the disclosure in light of the above detailed description. While the above description describes certain embodiments of the disclosure, and describes the best mode contemplated, no matter how detailed the above appears in text, the teachings can be practiced in many ways. The details of the system may vary widely in the details of its implementation while still being encompassed by the subject matter disclosed herein. As noted above, particular terminology used when describing certain features or aspects of the disclosure should not be taken to imply that the terminology is being redefined herein to be restricted to any specific characteristics, features, or aspects of the disclosure with which that terminology is associated. In general, unless the above detailed description section explicitly defines such terms, the terms used in the appended claims should not be construed to limit the disclosure to the specific embodiments disclosed in the specification. Accordingly, the actual scope of the disclosure encompasses not only the disclosed embodiments, but also all equivalent ways of practicing or implementing the disclosure according to the claims.

Thus, while exemplary embodiments of the invention have been illustrated and described, it is to be understood that all terms used herein are intended to be illustrative and not restrictive, and that various changes, modifications and substitutions may be made by one having ordinary skill in the art without departing from the spirit and scope of the invention.