Patent Publication Number: US-2022219821-A1

Title: Inflatable Aerodynamic Cargo Container

Description:
TECHNICAL FIELD 
     The present disclosure is directed to an aerodynamic cargo container for an aircraft and, more particularly, to an inflatable aerodynamic cargo container for an aircraft. 
     BACKGROUND OF THE INVENTION 
     Aircraft, including vertical takeoff and landing (VTOL) aircraft such as helicopters, tiltrotor aircraft, and tiltwing aircraft, are commonly used to transport cargo from one geographical location to another. In some instances, cargo may be loaded into a pod assembly which is selectively attachable to an exterior of the aircraft, such as an underside of a helicopter, to facilitate transportation of the cargo via the aircraft. 
     BRIEF SUMMARY OF THE INVENTION 
     In a first aspect, the present disclosure is directed to an inflatable pod assembly for an aircraft. The inflatable pod assembly includes (a) an expandable exoskeleton, wherein the expandable exoskeleton defines a leading edge and a trailing edge of the inflatable pod assembly, wherein the expandable exoskeleton includes first and second portions selectively attachable to each other; (b) an internal cargo area configured to receive cargo, wherein the first and second portions are configured to selectively enclose the internal cargo area when the first and second portions are attached to each other; and (c) an internal inflation chamber configured to selectively receive an inflation fluid for expanding the exoskeleton to thereby transition the inflatable pod assembly from a deflated state to an inflated state. In some embodiments, the internal inflation chamber is defined by the internal cargo area. In other embodiments, the internal inflation chamber is defined by a pocket fluidly isolated from the internal cargo area. 
     In some embodiments, the inflatable pod assembly further includes at least one coupling mechanism configured to selectively attach the first and second portions of the expandable exoskeleton to each other to thereby enclose the internal cargo area. The at least one coupling mechanism may be configured to provide a fluid-tight seal between the first and second portions of the expandable exoskeleton when the first and second portions are attached to each other. In addition or alternatively, the at least one coupling mechanism may include a zipper. In some embodiments, the expandable exoskeleton includes a flexible material. For example, the flexible material may include nylon. In some embodiments, the inflatable pod assembly further includes at least one partition positioned in the internal cargo area and selectively attachable to the expandable exoskeleton for dividing the internal cargo area into a plurality of cargo area compartments. In addition or alternatively, the inflatable pod assembly may further include at least one attachment device configured to couple to a receiving assembly of the aircraft. 
     In some embodiments, the first portion includes a forward exoskeleton portion, and the second portion includes an aft exoskeleton portion separable from the forward exoskeleton portion. In this regard, the inflatable pod assembly may further include an intermediate frame portion, wherein the at least one coupling mechanism includes a forward coupling mechanism and an aft coupling mechanism configured to selectively attach the forward and aft exoskeleton portions to the intermediate frame portion, respectively, for operatively attaching the forward and aft exoskeleton portions to each other. For example, the intermediate frame portion may include a rigid material. In other embodiments, the trailing edge is bifurcated, wherein the first portion includes an upper trailing edge portion, wherein the second portion includes a lower trailing edge portion. In this regard, the expandable exoskeleton may include a forward exoskeleton portion and an aft exoskeleton portion integrally formed together as a unitary piece. 
     In a second aspect, the present disclosure is directed to an aircraft including (a) an aircraft body; and (b) an inflatable pod assembly selectively attached to the aircraft body, wherein the inflatable pod assembly includes: (i) an expandable exoskeleton, and (ii) an internal cargo area defined within the expandable exoskeleton, wherein the internal cargo area is configured to receive cargo. In some embodiments, the inflatable pod assembly further includes an internal inflation chamber configured to selectively receive an inflation fluid for expanding the exoskeleton to thereby transition the inflatable pod assembly from a deflated state to an inflated state. In addition or alternatively, the inflatable pod assembly may be selectively attached to an exterior of the aircraft body. 
     In a third aspect, the present disclosure is directed to a method of transporting cargo. The method includes (a) loading the cargo into an internal cargo area of an inflatable pod assembly; (b) directing an inflation fluid into an internal inflation chamber of the inflatable pod assembly to transition the inflatable pod assembly from a deflated state to an inflated state; (c) selectively attaching the inflatable pod assembly to an aircraft body of an aircraft; and (d) conducting a flight operation via the aircraft while the inflatable pod assembly is selectively attached to the aircraft body and in the inflated state. In some embodiments, the method further includes (a) jettisoning the inflatable pod assembly from the aircraft body over a body of water; and (b) floating the inflatable pod assembly atop the body of water via the inflation fluid within the internal inflation chamber of the inflatable pod assembly. 
     The foregoing has outlined rather broadly the features and technical advantages of the present invention in order that the detailed description of the invention that follows may be better understood. Additional features and advantages of the invention will be described hereinafter which form the subject of the claims of the invention. It should be appreciated by those skilled in the art that the conception and specific embodiment disclosed may be readily utilized as a basis for modifying or designing other structures for carrying out the same purposes of the present invention. It should also be realized by those skilled in the art that such equivalent constructions do not depart from the spirit and scope of the invention as set forth in the appended claims. The novel features which are believed to be characteristic of the invention, both as to its organization and method of operation, together with further objects and advantages will be better understood from the following description when considered in connection with the accompanying figures. It is to be expressly understood, however, that each of the figures is provided for the purpose of illustration and description only and is not intended as a definition of the limits of the present invention. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       For a more complete understanding of the present invention, reference is now made to the following descriptions taken in conjunction with the accompanying drawings, in which: 
         FIG. 1  is a perspective view of an aircraft including an exemplary pod assembly, showing the pod assembly in an inflated state; 
         FIG. 2  is a perspective view of the pod assembly of  FIG. 1 ; 
         FIG. 3  is a cross-sectional view of the pod assembly of  FIG. 1 , taken along section line  3 - 3  in  FIG. 2 ; 
         FIG. 4  is a cross-sectional view of another exemplary pod assembly, showing the pod assembly in an inflated state; 
         FIG. 5  is a flowchart of an exemplary method of transporting cargo; and 
         FIG. 6  is a flowchart of an exemplary method of manufacturing a pod assembly. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring now to  FIG. 1 , an aircraft  10  having a versatile propulsion system is depicted. In the illustrated embodiment, aircraft  10  includes an airframe  12  having wings  14 ,  16  each having an airfoil cross-section that generates lift responsive to the forward airspeed of aircraft  10 . Extending generally perpendicularly between wings  14 ,  16  are truss structures depicted as pylons  18 ,  20 . In the illustrated embodiment, the versatile propulsion system includes a plurality of independently operating propulsion assemblies  26  that are independently attachable to and detachable from airframe  12 . As shown, each propulsion assembly  26  includes a nacelle  28  that houses a power source, an engine or motor, a drive system, a rotor hub, actuators and an electronics node including, for example, controllers, sensors and communications elements as well as other components suitable for use in the operation of a propulsion assembly. Each propulsion assembly  26  also includes a tail assembly  46  having an active aerosurface  48 . In addition, each propulsion assembly  26  has a rotor assembly including the rotor hub having a plurality of grips such as spindle grips and a proprotor  38  depicted as having three rotor blades each of which is coupled to one of the spindle grips of the respective rotor hub such that the rotor blades are operable to rotate with the spindle grips about respective pitch change axes. These and various other components of aircraft  10  may be configured in accordance with at least some of the teachings of U.S. Pat. No. 10,618,646, entitled “Rotor Assembly Having A Ball Joint For Thrust Vectoring Capabilities,” issued Apr. 14, 2020, the disclosure of which is incorporated by reference herein. 
     Aircraft  10  includes a pod assembly, illustrated as cargo pod assembly  50 , that is selectively attachable to and detachable from airframe  12  between pylons  18 ,  20 . In the illustrated embodiment, wings  14 ,  16  each include a receiving assembly  51  for coupling with pod assembly  50 . The connection between wings  14 ,  16  and pod assembly  50  may be a fixed connection that secures pod assembly  50  in a single location relative to airframe  12 . Alternatively, pod assembly  50  may be allowed to rotate and/or translate relative to airframe  12  during ground and/or flight operations. Such a configuration may be provided in accordance with at least some of the teachings of U.S. Pat. No. 10,618,646. In any event, pod assembly  50  may be selectively coupled to and decoupled from airframe  12  to enable sequential pickup, transportation and delivery of one or more pod assemblies  50 . 
     Referring now to  FIGS. 2 and 3 , pod assembly  50  includes a generally bulbous forward exoskeleton portion  52  and a generally tapered aft exoskeleton portion  54  operatively coupled to each other via an intermediate frame portion  56  to collectively define an internal cargo area  58 . When coupled to each other in this manner, forward and aft exoskeleton portions  52 ,  54  provide pod assembly  50  with an aerodynamic exterior shape and define leading and trailing edges  60 ,  62 , respectively, of pod assembly  50 . In some versions, pod assembly  50  may have a length of between approximately 3 ft and approximately 4 ft, a height of approximately 1½ ft to approximately 2 ft, and a width of approximately 3 ft. However, it will be appreciated that pod assembly  50  may have any suitable dimensions based on various parameters such as the amount of cargo to be transported and the load capacity of aircraft  10 , for example. 
     As shown, an aft face of forward exoskeleton portion  52  is selectively attachable to and detachable from a forward face of intermediate frame portion  56  by a forward coupling mechanism in the form of a forward zipper  64 , and a forward face of aft exoskeleton portion  54  is likewise selectively attachable to and detachable from an aft face of intermediate frame portion  56  by an aft coupling mechanism in the form of an aft zipper  66 . Thus, forward and aft zippers  64 ,  66  may permit selective attaching of each exoskeleton portion  52 ,  54  to intermediate frame portion  56  to enclose internal cargo area  58 , as well as selective detaching (e.g., full or partial detaching) of one or both exoskeleton portions  52 ,  54  from intermediate frame portion  56  to permit access to internal cargo area  58 , such as for loading cargo thereinto or unloading cargo therefrom. 
     In some versions, forward and aft zippers  64 ,  66  may be configured to provide a fluid-tight (e.g., airtight and/or watertight) seal between intermediate frame portion  56  and the respective exoskeleton portions  52 ,  54  such that internal cargo area  58  may be fluidly isolated from an external environment surrounding pod assembly  50  when exoskeleton portions  52 ,  54  are each attached to intermediate frame portion  56 . Thus, forward and aft zippers  64 ,  66  may provide both a coupling function and a sealing function. While forward and aft zippers  64 ,  66  are shown in the present version, it will be appreciated that any other suitable types of coupling mechanisms may be used to selectively attach exoskeleton portions  52 ,  54  to intermediate frame portion  56 , such as a hook-and-loop fastener (e.g., Velcro). In addition or alternatively, any other suitable types of sealing mechanisms may be used to provide a fluid-tight seal between exoskeleton portions  52 ,  54  and intermediate frame portion  56 . 
     In some versions, pod assembly  50  may be at least partially inflatable. In this regard, forward and aft exoskeleton portions  52 ,  54  may each be constructed of a flexible, semi-rigid material having durable and UV resistant properties, such as any material known for forming emergency helicopter floats. For example, forward and aft exoskeleton portions  52 ,  54  may each be constructed of a synthetic polymeric textile, such as a nylon textile. Such a construction may enable forward and aft exoskeleton portions  52 ,  54  to selectively expand and contract. In the present version, forward and aft exoskeleton portions  52 ,  54  may expand and contract when coupled to intermediate frame portion  56  in response to an inflation fluid such as air or nitrogen being introduced to and removed from internal cargo area  58 , respectively. For example, fluid may be introduced to internal cargo area  58  to expand forward and aft exoskeleton portions  52 ,  54  to define the illustrated inflated state of pod assembly  50 , and fluid may be removed from internal cargo area  58  to contract forward and aft exoskeleton portions  52 ,  54  to define a deflated state (not shown) of pod assembly  50 . In some versions, at least one fluid port (not shown) may extend through at least one of forward exoskeleton portion  52 , aft exoskeleton portion  54 , and/or intermediate frame portion  56  to facilitate transfer of fluid into and out of internal cargo area  58 . Thus, in addition to containing cargo, internal cargo area  58  may define an internal inflation chamber of pod assembly  50 . 
     As shown, one or both exoskeleton portions  52 ,  54  may also include at least one internal pocket  68 ,  69 , respectively, fluidly isolated from internal cargo area  58  for receiving an inflation fluid such as air or nitrogen to expand exoskeleton portions  52 ,  54  irrespective of whether exoskeleton portions  52 ,  54  are coupled to each other. For example, one or both exoskeleton portions  52 ,  54  may include a pair of panels spaced apart from each other to define a pocket  68 ,  69  therebetween. In such cases, the pockets  68 ,  69  of exoskeleton portion(s)  52 ,  54  may be filled with fluid in addition to or instead of internal cargo area  58  to thereby inflate a periphery of pod assembly  50 . Thus, pockets  68 ,  69  may each define an internal inflation chamber of pod assembly  50 . Such pockets  68 ,  69  may be provided in any suitable number and arrangement. In some versions, filling such pockets  68 ,  69  of exoskeleton portion(s)  52 ,  54  may assist with avoiding deflation of pod assembly  50  when either exoskeleton portion  52 ,  54  is fully or partially uncoupled from intermediate frame portion  56  (e.g., to access internal cargo area  58  for loading or unloading cargo), thereby placing internal cargo area  58  in fluid communication with the external environment. Alternatively, pockets  68 ,  69  may be omitted (e.g., exoskeleton portions  52 ,  54  may each be formed as a singular panel), such that internal cargo area  58  may provide the sole internal inflation chamber of pod assembly  50 . 
     In the embodiment shown, pod assembly  50  further includes at least one partition  70  for dividing internal cargo area  58  into a forward cargo area compartment  58   a  and an aft cargo area compartment  58   b . As shown, an outer periphery of partition  70  is selectively attachable to and detachable from an inner periphery of forward exoskeleton portion  52  by a partition coupling mechanism in the form of a partition zipper  72 . Partition zipper  72  may be configured to provide a fluid-tight seal between partition  70  and forward exoskeleton portion  52  such that forward cargo area compartment  58   a  may be fluidly isolated from aft cargo area compartment  58   b  when partition  70  is attached to forward exoskeleton portion  52 . Partition  70  may include a flat panel of the same material as forward and aft exoskeleton portions  52 ,  54 . In some versions, partition  70  may include a pocket defining an internal inflation chamber (not shown) for receiving an inflation fluid such as air or nitrogen to enable partition  70  to transition between inflated and deflated states. Such a configuration may assist with providing structural stability to pod assembly  50 . In any event, partition  70  may allow cargo to be organized in a desired manner among forward and aft cargo area compartments  58   a ,  58   b , such as for positioning a center of gravity of the cargo at a desired location within internal cargo area  58 . While a single partition  70  is shown attached to forward exoskeleton portion  52 , it will be appreciated that any suitable number of partitions  70  may be attached to any one or more of forward exoskeleton portion  52 , aft exoskeleton portion  54 , and/or intermediate frame portion  56 . Such partitions  70  may each be selectively attachable and detachable to enable customizable reconfiguring of the number, size, shape, and/or position of cargo area compartments  58   a ,  58   b . While partition zipper  72  is shown in the present version, it will be appreciated that any other suitable types of coupling mechanisms may be used to selectively attach partition  70  to any of exoskeleton portions  52 ,  54  or intermediate frame portion  56 , such as a hook-and-loop fastener (e.g., Velcro). 
     As shown, intermediate frame portion  56  includes an opposed pair of attachment devices in the form of hooks or eyelets  74  for selectively engaging respective receiving assemblies  51  of wings  14 ,  16  to thereby removably couple pod assembly  50  to airframe  12 . In this regard, eyelets  74  of the present version are arranged on opposed upper and lower surfaces of intermediate frame portion  56 . Alternatively, eyelets  74  may be arranged on opposed lateral side surfaces of intermediate frame portion  56 , such as for selectively engaging respective receiving assemblies (not shown) of pylons  18 ,  20 , or may be arranged in any other suitable manner for securing pod assembly  50  to airframe  12 . In some versions, intermediate frame portion  56  may be constructed of a substantially rigid material, such as metal, such that intermediate frame portion  56  is relatively rigid compared to forward and aft exoskeleton portions  52 ,  54 . For example, intermediate frame portion  56  may neither expand nor contract during inflation or deflation of pod assembly  50 . In this manner, intermediate frame portion  56  may assist with providing structural stability to pod assembly  50 . More particularly, intermediate frame portion  56  may provide improved stability to pod assembly  50  at and/or near eyelets  74  for assisting with transferring load from pod assembly  50  to airframe  12 . 
     Inflation of pod assembly  50  may be performed at any suitable time, such as during assembly of pod assembly  50 , prior to loading cargo into pod assembly  50 , and/or after loading cargo into pod assembly  50 . In some versions, forward and aft exoskeleton portions  52 ,  54  may be sufficiently rigid to substantially retain their expanded states once inflated such that subsequent full or partial uncoupling of either exoskeleton portion  52 ,  54  from intermediate frame portion  56  may be performed (e.g., to access internal cargo area  58  for loading or unloading cargo), thereby placing internal cargo area  58  in fluid communication with the external environment, without causing deflation of pod assembly  50 . 
     In addition to providing internal cargo area  58  for facilitating transportation of cargo, pod assembly  50  may serve as an aerodynamic fairing for aircraft  10  via its aerodynamic exterior shape. In some versions, pod assembly  50  may also provide aircraft  10  with impact protection by acting as a buffer between airframe  12  and surrounding objects. Pod assembly  50  may also provide the cargo contained therein with impact protection by acting as a buffer between such cargo and surrounding objects (e.g., airframe  12 , ground, a body of water, etc.). Moreover, pod assembly  50  may operate as a flotation device for aircraft  10  and/or for cargo contained within pod assembly  50 . In this regard, pod assembly  50  may be capable of floating atop water while containing cargo, at least when pod assembly  50  is in the inflated state. Thus, pod assembly  50  may be loaded with cargo and subsequently jettisoned from aircraft  10  during a flight operation over a body of water and, rather than sinking down into the body of water, pod assembly  50  may float atop the body of water to allow relatively simple retrieval of both the pod assembly  50  and the cargo contained therein from the body of water. 
     Referring now to  FIG. 4 , an alternative pod assembly  150  similar to pod assembly  50  except as otherwise described herein includes a generally bulbous forward exoskeleton portion  152  and a generally tapered aft exoskeleton portion  154  integrally formed together as a unitary piece to define an internal cargo area  158 . As shown, forward and aft exoskeleton portions  152 ,  154  provide pod assembly  150  with an aerodynamic exterior shape and define leading and trailing edges  160 ,  162  respectively, of pod assembly  150 . In the present version, trailing edge  162  is bifurcated such that trailing edge  162  includes upper and lower trailing edge portions  162   a ,  162   b  selectively attachable to and detachable from each other by a trailing edge coupling mechanism in the form of a trailing edge zipper  163 . Thus, trailing edge zipper  163  may permit selective attaching of trailing edge portions  162   a ,  162   b  to each other to enclose internal cargo area  158 , as well as selective detaching (e.g., full or partial detaching) of trailing edge portions  162   a ,  162   b  from each other to permit access to internal cargo area  158 , such as for loading cargo thereinto or unloading cargo therefrom. In some versions, trailing edge zipper  163  may be configured to provide a fluid-tight (e.g., airtight and/or watertight) seal between trailing edge portions  162   a ,  162   b  such that internal cargo area  158  may be fluidly isolated from an external environment surrounding pod assembly  150  when trailing edge portions are attached to each other. While trailing edge zipper  163  is shown in the present version, it will be appreciated that any other suitable types of coupling mechanisms may be used to selectively attach upper and lower trailing edge portions  162   a ,  162   b  to each other, such as a hook-and-loop fastener (e.g., Velcro). 
     In some versions, pod assembly  150  may be inflatable in a manner similar to that described above with respect to pod assembly  50  to enable forward and aft exoskeleton portions  152 ,  154  to transition between expanded and contracted states in response to fluid such as air or nitrogen being introduced to or removed from internal cargo area  158 . For example, fluid may be introduced to internal cargo area  158  to expand forward and aft exoskeleton portions  152 ,  154  to define the illustrated inflated state of pod assembly  150 , and fluid may be removed from internal cargo area  158  to contract forward and aft exoskeleton portions  152 ,  154  to define a deflated state (not shown) of pod assembly  150 . In some versions, at least one fluid port (not shown) may extend through at least one of forward exoskeleton portion  152  and/or aft exoskeleton portion  154  to facilitate transfer of fluid into and out of internal cargo area  158 . In addition or alternatively, one or both exoskeleton portions  152 ,  154  may include at least one pocket defining an internal inflation chamber (not shown) fluidly isolated from internal cargo area  158 . While not shown, pod assembly  150  may further include at least one partition  70  for dividing internal cargo area  158  into a plurality of cargo area compartments. 
     As shown, forward exoskeleton portion  152  includes an opposed pair of attachment devices in the form of hooks or eyelets  174  for selectively engaging respective receiving assemblies  51  of wings  14 ,  16  to thereby removably couple pod assembly  150  to airframe  12 . In this regard, eyelets  174  of the present version are arranged on opposed upper and lower surfaces of forward exoskeleton portion  152 . Alternatively, eyelets  174  may be arranged on opposed lateral side surfaces of forward exoskeleton portion  152 , such as for selectively engaging respective receiving assemblies (not shown) of pylons  18 ,  20 , or may be arranged in any other suitable manner for securing pod assembly  150  to airframe  12 . In some versions, eyelets  174  may be constructed of a plastic material, and may be molded into forward exoskeleton portion  152  such that eyelets  174  are directly embedded therein. 
     Referring now to  FIG. 5 , a method  200  of transporting cargo begins with step  202 , at which cargo is loaded into an internal cargo area  58 ,  158  of an inflatable pod assembly, such as either pod assembly  50 ,  150 . After step  202 , method  200  proceeds to step  204 , at which an inflation fluid is directed into at least one internal inflation chamber  58 ,  68 ,  69 ,  158  of pod assembly  50 ,  150  to transition pod assembly  50 ,  150  from a deflated state to an inflated state. In some versions, step  204  may be performed during or prior to step  202 . In any event, method  200  then proceeds to step  206 , at which pod assembly  50 ,  150  is attached to an aircraft body of an aircraft, such as aircraft  10 . In some versions, step  206  may be performed during or prior to one or both of steps  202 ,  204 . In any event, method  200  then proceeds to step  208 , at which a flight operation is conducted via the aircraft  10  while the inflatable pod assembly  50 ,  150  is attached to the aircraft body and in the inflated state. In the illustrated version, method  200  then proceeds to step  210 , at which the inflatable pod assembly  50 ,  150  is jettisoned from the aircraft body over a body of water, and further proceeds to step  212 , at which the inflatable pod assembly  50 ,  150  is floated atop the body of water via the inflation fluid within the internal inflation chamber  58 ,  68 ,  69 ,  158  of the inflatable pod assembly  50 ,  150 . 
     Referring now to  FIG. 6 , a method  300  of manufacturing an inflatable pod assembly  50 ,  150  begins with step  302 , at which an expandable exoskeleton is formed, which may include forming exoskeleton portions  52 ,  54  separately from a flexible, semi-rigid material or forming exoskeleton portions  152 ,  154  together from a flexible, semi-rigid material. Method  300  proceeds from step  302  to step  304 , at which portions of the expandable exoskeleton are selectively coupled to each other, such as to enclose an internal cargo area  58 ,  158 , which may include operatively coupling exoskeleton portions  52 ,  54  to each other via intermediate frame portion  56 , or attaching trailing edge portions  162   a ,  162   b  to each other. In any event, method  300  proceeds to step  306 , at which at least one inflation chamber  58 ,  68 ,  69 ,  158  is provided within the exoskeleton, which may include providing internal cargo area  58 ,  158  and/or pockets  68 ,  69 . In some versions, step  306  may be performed during or prior to one or both of steps  302 ,  304 . In the illustrated version, method  300  then proceeds to step  308 , at which an inflation fluid is directed into at least one internal inflation chamber  58 ,  68 ,  69 ,  158  of pod assembly  50 ,  150  to transition pod assembly  50 ,  150  from a deflated state to an inflated state. 
     While pod assemblies  50 ,  150  have been described for use with aircraft  10 , it will be appreciated that pod assemblies  50 ,  150  may be used with any suitable type of aircraft, such as a helicopter. For example, pod assemblies  50 ,  150  may be selectively attachable to corresponding receiving assemblies provided on an underside of such a helicopter via eyelets  74 ,  174  or any other suitable attachment devices. 
     Although the present invention and its advantages have been described in detail, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims. Moreover, the scope of the present application is not intended to be limited to the particular embodiments of the process, machine, manufacture, composition of matter, means, methods and steps described in the specification. As one of ordinary skill in the art will readily appreciate from the disclosure of the present invention, processes, machines, manufacture, compositions of matter, means, methods, or steps, presently existing or later to be developed that perform substantially the same function or achieve substantially the same result as the corresponding embodiments described herein may be utilized according to the present invention. Accordingly, the appended claims are intended to include within their scope such processes, machines, manufacture, compositions of matter, means, methods, or steps.