Patent Publication Number: US-2023159169-A1

Title: Onboard workstations for aircraft

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims priority to, and the benefit of, India Provisional Patent Application No. 202141053469, filed Nov. 20, 2021 (DAS Code F2A4) and titled “ONBOARD WORKSTATIONS FOR AIRCRAFT,” which is incorporated by reference herein in its entirety for all purpose. 
     FIELD 
     The present disclosure generally relates to the field of aircraft and, more particularly, to workstations on aircraft. 
     BACKGROUND 
     Aircraft will typically include a tray table that is disposed on the back side of a passenger seat. A passenger may place food and/or drink on such a tray table. Although these tray tables are oftentimes used as a working surface, including where a laptop or the like may be positioned on the tray table, these tray tables are less than optimal as working surfaces. For instance, these tray tables may be somewhat unstable when used as a working surface for a laptop or the like. 
     SUMMARY 
     An aircraft workstation is presented herein. Both the configuration of such an aircraft workstation and the operational characteristics/operation/use of such an aircraft workstation are within the scope of this Summary. 
     The aircraft workstation includes a table that is movable between a stowed position and a deployed position. In one aspect, the aircraft workstation is incorporated within an exit row or aisle of any appropriate aircraft, and as such the table will extend into the exit row when in its deployed position. In another aspect, the aircraft workstation includes at least one latch that is disposable in each of a locked configuration (e.g., where the table is in its stowed position) and an unlocked configuration (e.g., where the table is in its deployed position). Access to an unlocking functionality for the aircraft workstation may be controlled/established in any appropriate manner, for instance by a carrier that operates an aircraft that incorporates the aircraft workstation. A carrier may elect to have only aircraft personnel be able to dispose the latch in its unlocked configuration. However, a carrier may allow an aircraft passenger (or any other individual) to be able to dispose the latch in its unlocked configuration as well. 
     In another aspect, the table is disposed within a recess of a wall when in its stowed position. At least one power socket, at least one power switch, at least one wire holder (e.g., for wire management), or any combination thereof, may also be disposed in this recess. In another aspect, the table blocks access to at least one power socket of the aircraft workstation when the table is in its stowed position. In another aspect, at least two different pivot pins and at least one torque hinge are used to movably interconnect the table with an aircraft wall, for instance so that the table pivots (e.g., about a single axis) in moving between its stowed and deployed positions. 
     Each of the above-noted aspects may be used individually and in any combination. 
     Various aspects of the present disclosure are also addressed by the following examples and in the noted combinations:
     1. An aircraft comprising:   

     a plurality of passenger seat rows; 
     a first exit row; 
     a first border wall assembly for said first exit row; and 
     a table movably interconnected with said first border wall assembly, wherein said table is movable between a deployed position where said table extends into said first exit row and a stowed position.
     2. The aircraft of example 1, wherein said first border wall assembly comprises a pocket, and wherein said table is disposed within said pocket when said table is in said stowed position.   3. The aircraft of example 2, wherein said first border wall assembly comprises a first power socket disposed within said pocket.   4. The aircraft of any of examples 2-3, wherein said first border wall assembly comprises at least one wire holder disposed within said pocket.   5. The aircraft of any of examples 1-2, wherein said first border wall assembly comprises a first power socket, wherein said table is disposed over said first power socket when said table is in said stowed position.   6. The aircraft of any of examples 1-2 and 5, wherein said first border wall assembly comprises at least one wire holder.   7. The aircraft of any of examples 1-5, further comprising a latch disposable in each of a locked configuration and an unlocked configuration, said latch requiring at least one of a key and an unlocking signal to change said latch from said locked configuration to said unlocked configuration, wherein said table is movable from said stowed position to said deployed position when said latch is in said unlocked configuration.   8. The aircraft of any of examples 1-7, further comprising:   

     a stand movably interconnected with said table, wherein said stand is movable from a first stowed position to a first deployed position, wherein said stand is at least substantially coplanar with an upper table surface of said table when in said first stowed position and is disposed at an angle relative to said upper table surface when in said first deployed position.
     9. The aircraft of any of examples 1-8 further comprising at least one of:   

     a cupholder movably connected with said table; 
     a mouse extender movably connected with said table; and 
     a table extender movably connected with said table.
     10. The aircraft of any of examples 1-7, further comprising:   

     first and second wall mounts that are spaced in a first dimension and that are fixed relative to said first border wall assembly; 
     first, second, and third table recesses on an upper table surface of said table that are spaced in said first dimension, wherein said first wall mount is disposed in said first table recess and said second wall mount is disposed in said second table recess; 
     a first pivot pin that extends in said first dimension through said first wall mount and through portions of said table on each side of said first table recess; 
     a second pivot pin that extends in said first dimension through said second wall mount and through portions of said table on each side of said second table recess; 
     a first torque hinge comprising a first wall anchor section interconnected with said first border wall assembly and a first table anchor section disposed in said third table recess, wherein said first torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a first fastener that extends through said first table anchor section and into said table.
     11. The aircraft of example 10, further comprising:   

     a fourth table recess on said upper table surface, wherein said fourth table recess is spaced from each of said first table recess, said second table recess, and said third table recess in said first dimension; 
     a second torque hinge comprising a second wall anchor section interconnected with said first border wall assembly and a second table anchor section disposed in said fourth table recess, wherein said second torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a second fastener that extends through said first table anchor section and into said table.
     12. The aircraft of any of examples 1-9, wherein said table comprises first and second supports that are spaced in a first dimension, wherein said first support extends through a first aperture in said first border wall assembly and said second support extends through a second aperture in said first border wall assembly, wherein said aircraft further comprises:   

     a first set pin that is positioned on an opposite side of said first border wall assembly compared to said table, wherein said first set pin engages an upper surface of said first support when said table is in said deployed position; and 
     a second set pin that is positioned on an opposite side of said first border wall assembly compared to said table, wherein said second set pin engages an upper surface of said second support when said table is in said deployed position.
     13. An aircraft comprising:   

     a plurality of passenger seat rows; 
     a first wall assembly; 
     first and second wall mounts that are spaced in a first dimension and that are fixed relative to said first wall assembly; 
     a table movably interconnected with said first wall assembly, wherein said table is movable between a stowed position and a deployed position; 
     first, second, and third table recesses on an upper table surface of said table that are spaced in said first dimension, wherein said first wall mount is disposed in said first table recess and said second wall mount is disposed in said second table recess; 
     a first pivot pin that extends in said first dimension through said first wall mount and through portions of said table on each side of said first table recess; 
     a second pivot pin that extends in said first dimension through said second wall mount and through portions of said table on each side of said second table recess; 
     a first torque hinge comprising a first wall anchor section interconnected with said first wall assembly and a first table anchor section disposed in said third table recess, wherein said first torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a first fastener that extends through said first table anchor section and into said table.
     14. The aircraft of example 13, further comprising:   

     a fourth table recess on said upper table surface, wherein said fourth table recess is spaced from each of said first table recess, said second table recess, and said third table recess in said first dimension; 
     a second torque hinge comprising a second wall anchor section interconnected with said first wall assembly and a second table anchor section disposed in said fourth table recess, wherein said second torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a second fastener that extends through said first table anchor section and into said table.
     15. The aircraft of any of examples 13-14, wherein said first wall assembly comprises a pocket, and wherein said table is disposed within said pocket when said table is in said stowed position.   16. The aircraft of example 15, wherein said first wall assembly comprises a first power socket disposed within said pocket.   17. The aircraft of any of examples 15-16, wherein said first wall assembly comprises at least one wire holder disposed within said pocket.   18. The aircraft of any of examples 13-14, wherein said first wall assembly comprises a first power socket, wherein said table is disposed over said first power socket when said table is in said stowed position.   19. The aircraft of any of examples 13-14, and 18, wherein said first wall assembly comprises at least one wire holder.   20. The aircraft of any of examples 13-19, further comprising a latch disposable in each of a locked configuration and an unlocked configuration, said latch requiring at least one of a key and an unlocking signal to change said latch from said locked configuration to said unlocked configuration, wherein said table is movable from said stowed position to said deployed position when said latch is in said unlocked configuration.   21. The aircraft of any of examples 13-20, further comprising:   

     a stand movably interconnected with said table, wherein said stand is movable from a first stowed position to a first deployed position, wherein said stand is at least substantially coplanar with said upper table surface when in said first stowed position and disposed at an angle relative to said upper table surface when in said first deployed position.
     22. The aircraft of any of examples 13-21, further comprising at least one of:   

     a cupholder movably connected with said table; 
     a mouse extender movably connected with said table; and 
     a table extender movably connected with said table.
     23. The aircraft of any of examples 13-22, wherein said table comprises first and second supports that are spaced in said first dimension, wherein said first support extends through a first aperture in said first wall assembly and said second support extends through a second aperture in said first wall assembly, wherein said aircraft further comprises:   

     a first set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said first set pin engages an upper surface of said first support when said table is in said deployed position; and 
     a second set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said second set pin engages an upper surface of said second support when said table is in said deployed position.
     24. An aircraft comprising:   

     a plurality of passenger seat rows; 
     a first wall assembly; 
     a table movably interconnected with said first wall assembly, wherein said table is movable between a stowed position and a deployed position; and 
     a latch disposable in each of a locked configuration and an unlocked configuration, said latch requiring at least one of a key and an unlocking signal to change said latch from said locked configuration to said unlocked configuration, wherein said table is movable from said stowed position to said deployed position when said latch is in said unlocked configuration.
     25. The aircraft of example 24, wherein said first wall assembly comprises a pocket, and wherein said table is disposed within said pocket when said table is in said stowed position.   26. The aircraft of example 25, wherein said first wall assembly comprises a first power socket disposed within said pocket.   27. The aircraft of any of examples 25-26, wherein said first wall assembly comprises at least one wire holder disposed within said pocket.   28. The aircraft of example 24, wherein said first wall assembly comprises a first power socket, wherein said table is disposed over said first power socket when said table is in said stowed position.   29. The aircraft of any of examples 24 and 28, wherein said first wall assembly comprises at least one wire holder.   30. The aircraft of any of examples 24-29, further comprising:   

     a stand movably interconnected with said table, wherein said stand is movable from a first stowed position to a first deployed position, wherein said stand is at least substantially coplanar with an upper table surface of said table when in said first stowed position and is disposed at an angle relative to said upper table surface when in said first deployed position.
     31. The aircraft of any of examples 24-30 further comprising at least one of:   

     a cupholder movably connected with said table; 
     a mouse extender movably connected with said table; and 
     a table extender movably connected with said table.
     32. The aircraft of any of examples 24-31, further comprising:   

     first and second wall mounts that are spaced in a first dimension and that are fixed relative to said first wall assembly; 
     first, second, and third table recesses on an upper table surface of said table that are spaced in said first dimension, wherein said first wall mount is disposed in said first table recess and said second wall mount is disposed in said second table recess; 
     a first pivot pin that extends in said first dimension through said first wall mount and through portions of said table on each side of said first table recess; 
     a second pivot pin that extends in said first dimension through said second wall mount and through portions of said table on each side of said second table recess; 
     a first torque hinge comprising a first wall anchor section interconnected with said first wall assembly and a first table anchor section disposed in said third table recess, wherein said first torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a first fastener that extends through said first table anchor section and into said table.
     33. The aircraft of example 32, further comprising:   

     a fourth table recess on said upper table surface, wherein said fourth table recess is spaced from each of said first table recess, said second table recess, and said third table recess in said first dimension; 
     a second torque hinge comprising a second wall anchor section interconnected with said first wall assembly and a second table anchor section disposed in said fourth table recess, wherein said second torque hinge is located between said first wall mount and said second wall mount in said first dimension; and 
     a second fastener that extends through said first table anchor section and into said table.
     34. The aircraft of any of examples 32-33, wherein said table comprises first and second supports that are spaced in said first dimension, wherein said first support extends through a first aperture in said first wall assembly and said second support extends through a second aperture in said first wall assembly, wherein said aircraft further comprises:   

     a first set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said first set pin engages an upper surface of said first support when said table is in said deployed position; and 
     a second set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said second set pin engages an upper surface of said second support when said table is in said deployed position.
     35. The aircraft of any of examples 24-31, wherein said table comprises first and second supports that are spaced in a first dimension, wherein said first support extends through a first aperture in said first wall assembly and said second support extends through a second aperture in said first wall assembly, wherein said aircraft further comprises:   

     a first set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said first set pin engages an upper surface of said first support when said table is in said deployed position; and 
     a second set pin that is positioned on an opposite side of said first wall assembly compared to said table, wherein said second set pin engages an upper surface of said second support when said table is in said deployed position.
     36. A method of operating a workstation on an aircraft, comprising:   

     unlocking said workstation; 
     moving a table of said workstation from a stowed position to a deployed position after said unlocking; and 
     using said table in said deployed position as a working surface.
     37. The method of example 36, wherein said unlocking comprising using at least one of a key and an unlocking signal.   38. The method of any of examples 36-37, wherein said using comprises disposing a portable computer on said table.   39. The method of any of examples 36-38, wherein said moving comprises moving said table into an exit row of said aircraft.   40. The method of any of examples 36-39, wherein using comprises a user being in one of a sitting position or a standing position.   

    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. An understanding of the present disclosure may be further facilitated by referring to the following detailed description and claims in connection with the following drawings. While the drawings illustrate various embodiments employing the principles described herein, the drawings do not limit the scope of the claims. Reference to “in accordance with various embodiments” in this Brief Description of the Drawings also applies to the corresponding discussion in the Detailed Description. 
         FIG.  1    is a perspective view of a representative aircraft, in accordance with various embodiments; 
         FIG.  2    is a perspective view of one aircraft workstation having a table in a deployed position and another aircraft workstation with a table in a stowed position, in accordance with various embodiments; 
         FIG.  3 A  is an enlarged, perspective view of an aircraft workstation, in accordance with various embodiments; 
         FIG.  3 B  is a block diagram of a latching system that may be used by an aircraft workstation, in accordance with various embodiments; 
         FIG.  4 A  is an enlarged, perspective view of an interconnection between an aircraft wall and a table of an aircraft workstation that utilizes a pair of torque hinges (in exploded view), in accordance with various embodiments; 
         FIG.  4 B  is an enlarged, perspective view of an interconnection between an aircraft wall and a table of an aircraft workstation that utilizes a pair of pivot pins (in exploded view), in accordance with various embodiments; 
         FIG.  4 C  is an enlarged, perspective view of a rear portion of a table for an aircraft workstation that is interconnectable with an aircraft wall, in accordance with various embodiments; 
         FIG.  5    is a side view of an aircraft workstation with a table in a deployed position, in accordance with various embodiments; 
         FIG.  6 A  is a perspective view of an aircraft workstation having a cupholder in a stowed position, in accordance with various embodiments; 
         FIG.  6 B  is a perspective view of an aircraft workstation having a cupholder in a deployed position, in accordance with various embodiments; 
         FIG.  7 A  is a perspective view of an aircraft workstation having a stand and a table extender that are each in a stowed position, in accordance with various embodiments; 
         FIG.  7 B  is a perspective view of an aircraft workstation having a stand and a table extender that are each in a deployed position, in accordance with various embodiments; 
         FIG.  7 C  is a cutaway side view schematic showing the stand in its stowed position of  FIG.  7 A , in accordance with various embodiments; 
         FIG.  8 A  is a schematic (plan view) of an aircraft cabin having a plurality of exit rows, in accordance with various embodiments; 
         FIG.  8 B  is a schematic (side view) of an aircraft cabin with sit-down workstations in two different exit rows, in accordance with various embodiments; 
         FIG.  8 C  is a schematic (side view) of an aircraft cabin with stand-up workstations in two different exit rows, in accordance with various embodiments; and 
         FIG.  8 D  is a perspective view of an aircraft cabin with a pair of stand-up workstations in a front row of a passenger cabin, in accordance with various embodiments. 
     
    
    
     DETAILED DESCRIPTION 
     With reference to  FIG.  1   , there is illustrated an example aircraft  100  that may incorporate one or more workstations in accordance with this disclosure. The aircraft  100  includes a fuselage  110  and wings  115 . Each wing  115  has a corresponding leading edge  115   a  (e.g., a “leading” structure/surface of the corresponding wing  115  during movement of the aircraft  100  through the air). The fuselage  110  includes a cockpit  120  and a tailcone  130 , which can be substantially integral to the fuselage  110 . The aircraft  100  also includes engines  140  which can be affixed to the wings  115  and/or to the fuselage  110 , and that may be controlled in any appropriate manner (e.g., by one or more control systems, for example one or more engine control systems). As used herein, the term “engine” is to be understood as including the engines themselves and nacelles  150  which contain the engines. Although shown in  FIG.  1    generally as a turbofan aircraft in which the engines  140  are gas turbine engines, it should be noted that the aircraft  100  can be any suitable type of aircraft having any suitable number of engines of any suitable type. 
       FIG.  2    illustrates an aircraft workstation  200  that may be incorporated by any appropriate aircraft and including the aircraft  100  of  FIG.  1   . The aircraft workstation  200  includes a table  280  that is movably (e.g., pivotally) interconnected with a wall assembly  210  of the aircraft. As the wall assembly  210  may be adapted for the table  280 , the wall assembly  210  may also be characterized as being part of the workstation  200 . In any case one of the aircraft workstations  200  (the left workstation  200  in the view shown in  FIG.  2   ) is shown with its table  280  disposed in a deployed position and with a laptop  270  being positioned thereon. Any appropriate portable computer, tablet, other electronics (e.g., mobile phone), or other articles may be disposed on/supported by the table  280  when in its deployed position. The other of the aircraft workstations  200  (the right workstation  200  in the view shown in  FIG.  2   ) is shown with its table  280  disposed in a stowed position. The lower or bottom surface of the table  280  may be at least substantially flush with the wall  212  when the table  280  is in its stowed position. 
     The wall assembly  210  includes a wall  212  that is disposed within the cabin of an aircraft. This wall  212  could be a forward bulkhead, a rear bulkhead, a wall of a monument, or any other wall-type structure within the aircraft cabin. A pocket or recess  214  is formed in the wall  212  and includes a back panel  216 . A power switch  224 , one or more power sockets or electrical outlets  226 , and one or more wire holders  228  may be incorporated by the back panel  216 . The wire holder(s)  228  are for wire management and are of a configuration that encompasses clips (e.g., U-shaped; J-shaped), or any appropriate retention structure for retaining a cord, cable, or the like, such as a power cable for a laptop, a tablet, or the like. 
     The aircraft workstation  200  may include one or more latches  230  for locking the table  280  in its stowed position (e.g., the right workstation  200  in the view shown in  FIG.  2   ).  FIG.  3 A  illustrates an enlarged view of the latch  230 . The latch  230  may be characterized as a dual latch having a pair of separately actuatable prongs  232 . A forward end  288   a  of the table  280  may include a separate aperture  298  (e.g.,  FIG.  4 B ) for each of the prongs  232 . When the table  280  is disposed in its stowed position, each of the prongs  232  of the latch  230  may be extended for disposition within the corresponding aperture  298  on the forward end  288   a  of the table  280  to lock the table  280  and its stowed position (i.e., to dispose the latch  230  in a locked configuration). When the latch  230  is disposed in an unlocked configuration, a push pin  234  may at least initiate movement of the table  280  toward its deployed position. The push pin  234  may include a spring that biases the push pin  234  to exert a force on the table  280  that biases the same toward its deployed position. 
     The latch  230  may be configured such that only an authorized user may change the latch  230  from its locked configuration to its unlocked configuration.  FIG.  3 B  illustrates a number of options for changing the latch  230  from its locked configuration to its unlocked configuration. A latch system  360  is shown in  FIG.  3 B  and includes a latch  362  (e.g., latch  230 ) that is disposable in each of a locked configuration and an unlocked configuration. One option for disposing the latch  362  in its unlocked configuration is to use a physical key  364 . Aircraft personnel could retain possession of this key  364  to unlock the latch  362  such that the corresponding workstation could thereafter be used by a passenger that has paid an appropriate fee for use of the workstation (or aircraft personnel could provide a passenger with the key  364  upon payment of the relevant fee). Another option would be to include an input device  366  that is operatively interconnected with the latch  362  by an appropriate communication link  370 . A code could be entered through the input device  366  (e.g., a keypad) to dispose the latch  362  in its unlocked configuration (the code could be entered by aircraft personnel or by a passenger that has paid an appropriate fee for use of the workstation). The input device  366  could also be in the form of a credit card reader that an individual could use to dispose the latch  362  in its unlocked configuration for subsequent use of the corresponding workstation. Yet another option would be to operatively interconnect a remotely located actuator  372  with the latch  362  (e.g., via a communication link  374 ) such that aircraft personnel could actuate the actuator  372  at a remote location to dispose the latch  362  in its unlocked configuration for use of the corresponding workstation by an aircraft passenger that has paid an appropriate fee. 
       FIGS.  4 A,  4 B, and  4 C  illustrate an interconnection between the table  280  and the wall assembly  210  that allows the table  280  to move between the stowed position and the deployed position that are each shown in  FIG.  2   . The table  280  includes an upper surface  282 , the above-noted forward end  288   a , a rear end  288   b , a first side  284 , and a second side  286 . The first side  284  and the second side  286  that are spaced from one another in a first dimension  306  (e.g., a width dimension for the table  280 ), while the forward end  288   a  and rear end  288   b  are spaced in a dimension that is orthogonal to the first dimension  306  (e.g., a length dimension for the table  280 ). 
     The table  280  includes a pair of recesses  300   a ,  300   b  in its upper surface  282  that are located at/toward its rear end  288   b  and that are spaced in the first dimension  306 , along with a pair of recesses  302   a ,  302   b  in its upper surface  282  that are located at/toward its rear end  288   b  and that are also spaced in the first dimension  306 . Each of the recesses  302   a ,  302   b  is located between the pair of recesses  300   a ,  300   b  in the first dimension  306 . 
     The aircraft workstation  200  includes a pair of wall mounts  236   a ,  236   b  that may be attached to the back panel  216  of the wall assembly  210 , to a lower sidewall  220  that extends from the wall  212  to the back panel  216  (and that defines a depth of the pocket  214 , along with left and right sidewalls  215 ), or both. The wall mounts  236   a ,  236   b  are spaced in the first dimension  306 . A separate bore extends through each of the wall mounts  236   a ,  236   b . The wall mount  236   a  is disposed in the recess  300   a  of the table  280 , while the wall mount  236   b  is disposed in the recess  300   b  of the table  280 . One pivot pin  240  extends through the wall mount  236   a  and into a corresponding aperture in the table  280  on both sides of the wall mount  236   a . Similarly, the other pivot pin  240  extends through the wall mount  236   b  and into a corresponding aperture in the table  280  on both sides of the wall mount  236   b . The pivot pins  240  are aligned in the first dimension  306  and define an axis about which the table  280  pivots relative to the wall assembly  210 . 
     The aircraft workstation  200  further includes a pair of torque hinges  250   a ,  250   b  that further movably interconnect the table  280  with the wall assembly  210 . Each torque hinge  250   a ,  250   b  includes a first section  252  that is secured to the wall assembly  210  (the lower sidewall  220  in  FIGS.  4 A and  4 B ) by one or more fasteners  254 , along with a second section  256  that is secured to the table  280  by one or more fasteners  258 . The second section  256  is movable relative to its corresponding first section  252  for each of the torque hinges  250   a ,  250   b . The second section  256  of the torque hinge  250   a  is disposed within the recess  302   a  of the table  280 , while the second section  256  of the torque hinge  250   b  is disposed in the recess  302   b  of the table  280 . Each torque hinge  250   a ,  250   b  exerts a biasing force on its corresponding second section  256  to resist movement of the table  280  to its deployed position. That is, the torque hinges  250   a ,  250   b  may be used to pivot the table  280  to its deployed position at a controlled rate (e.g., at a rate that is slower than would be provided by gravitational forces alone). 
     A pair of rear legs or supports  304  extend from the rear end  288   b  of the table  280 . In this regard, a pair of apertures  218  extend through the back panel  216  of the wall assembly  210 . The lower sidewall  220  of the wall assembly  210  may also includes a corresponding recess that intersects a corresponding one of the apertures  218  to accommodate movement of the table  280  relative to the wall assembly  210 . In the deployed position for the table  280 , the rear legs  304  of the table  280  extend completely through the corresponding aperture  218  in the back panel  216 . 
     A back plate  260  may be attached to the backside of the back panel  216  ( FIG.  5   ). At least one support  262  is fixed relative to this back plate  260  at a location that is above the corresponding rear leg  304  of the table  280  when the table  280  is in its deployed position. A set pin  264  (e.g., a threaded fastener) may extend through a corresponding support  262  and engage the upper surface of the rear leg  304  when the table  280  is in its deployed position. This may be used to enhance the stability of the table  280  in its deployed position, as the set pins  264  exerts a downward force on the table  280  in its deployed (via engagement with the corresponding support  304 ) that generates a moment that is opposite to that of the moment exerted on the table  280  by the laptop  270  (or by a user “pushing down” on the table  280 )—the set pins  264  and the laptop  270  are on opposite sides of the pivotal axis for the table  280 . Moreover, the amount that the set pins  264  extend past their corresponding support  262  may be used to adjust the angle of the table  280  when in its deployed position. 
     The table  280  may include one or more features to enhance a workstation in accordance with this disclosure. The upper surface  282  of the table  280  may be textured (e.g., to provide anti-slip functionality) and may also include for magnetic charging of electronic devices (e.g., mobile phones). In this regard, the table  280  may be in the form of a frame with an insert disposed thereon and that includes the upper surface  282 . The table  280  may include a mouse extender  294  that is movably connected with the table  280  (e.g., slidably) and that may be moved from a stowed position ( FIGS.  2 ,  3 , and  4 B ) to a deployed position (e.g., where it extends beyond the first side  284  of the table  280 ). The mouse extender  294  may be used to accommodate use of a mouse or the like with the laptop  270 . A user may push on the mouse extender  294  to “unlock” the mouse extender  294  to change the same from its stowed position to its deployed position. Similarly, a user may push on the mouse extender  294  to move the mouse extender  294  from its deployed position back to its stowed position. 
       FIGS.  6 A and  6 B  illustrate that the table  280  may include a cupholder  292  that is movably connected with the table  280  (e.g., slidably) and that may be moved from a stowed position ( FIG.  6 A ) to a deployed position ( FIG.  6 B ; e.g., where it extends beyond the second side  286  of the table  280 ). A user may push on the cupholder  292  to “unlock” the cupholder  292  to change the same from its stowed position to its deployed position. Similarly, a user may push on the cupholder  292  to move the cupholder  292  from its deployed position back to its stowed position. 
       FIGS.  7 A,  7 B, and  7 C  illustrate that the table  280  may include a stand  290 , a table extender  296 , or both, where each would be movably connected with the table  280  and that each may be moved from a stowed position ( FIG.  7 A ) to a deployed position ( FIG.  7 B ). The stand  290  may be disposed at least substantially flush with the upper surface  282  of the table  280  when the stand  290  is in its stowed position ( FIGS.  7 A and  7 C ). The stand  290  may be disposed at an angle relative to the upper surface  282  of the table  280  when the stand  290  is in its deployed position ( FIG.  7 B ). The stand  290  could be pivotally interconnected with the table  280 , could be disposed in any number of different inclined positions relative to the table  280  for its deployed position, or both. A device  272  (e.g., a mobile phone, a tablet computer, or the like) could disposed “on edge” on the table  280  and could be supported in an inclined or upright position by the stand  290  when in its deployed position. The table extender  296  may be slidably interconnected with the table  280  for movement between its stowed position of  FIG.  7 A  to its deployed position of  FIG.  7 B  (e.g., where it extends beyond the first side  284  of the table  280 ). The table extender  296  may be of a size to increase the size of the working surface, and may be used in place of the above-described mouse extender  294 . A user may push on the table extender  296  to “unlock” the table extender  296  to change the same from its stowed position to its deployed position. Similarly, a user may push on the table extender  296  to move the table extender  296  from its deployed position back to its stowed position. 
     The aircraft workstations described herein may be disposed at a number of different locations within an aircraft.  FIG.  8 A  illustrates a schematic of at least a portion of an aircraft cabin  310  having a plurality of rows  312  of one or more passenger seats  314 . The aircraft cabin  310  includes four different exit rows  316  for exiting the aircraft—two on each side of the aircraft. The above-described workstations may be mounted to a wall that defines a boundary for an exit row  316  such that the table  280  will extend into the corresponding exit row  316  when in its deployed position. 
       FIG.  8 B  illustrates a schematic of at least a portion of an aircraft cabin  320  having a plurality of passenger seats  322 , with each passenger seat  322  that is illustrated in  FIG.  8 B  being disposed in a different row in the aircraft cabin  320 . A pair of first walls  330   a ,  330   b  are spaced from one another (e.g., along a length dimension of the aircraft cabin  320 ) and define a first exit row  332 . The first exit row  332  includes a first exit door  334  for exiting the aircraft cabin  320 . A workstation  350  in accordance with the foregoing is incorporated by one of the first walls  330   a ,  330   b , while a jump seat  354  is incorporated by the other of the first walls  330   a ,  330   b . The workstation  350  and the jump seat  354  within the first exit row  332  are each disposed in their respective deployed positions (the table  352  extending into the first exit row  332 ). The workstation  350  is incorporated so as to position its corresponding table  352  at a height to accommodate a seated user. As such, a user may utilize the workstation  350  while sitting in the jump seat  354 . 
       FIG.  8 B  also illustrates a pair of second walls  340   a ,  340   b  that are spaced from one another (e.g., along a length dimension of the aircraft cabin  320 ) and define a second exit row  342  (e.g., aft of the first exit row  332 ). The second exit row  342  includes a second exit door  344  for exiting the aircraft cabin  320 . A workstation  350  in accordance with the foregoing is incorporated by one of the second walls  340   a ,  340   b , while a jump seat  354  is incorporated by the other of the second walls  340   a ,  340   b . The workstation  350  and the jump seat  354  within the second exit row  342  are each disposed in their respective stowed positions. 
       FIG.  8 C  illustrates a schematic of a variation of the aircraft cabin  320  of  FIG.  8 B , and is thus identified as aircraft cabin  320 ′. The first exit row  332  in the case of the aircraft cabin  320 ′ ( FIG.  8 C ) may be larger than the first exit row  332  in the case of the aircraft cabin  320  ( FIG.  8 B ). The first exit door  334  in the case of the aircraft cabin  320 ′ ( FIG.  8 C ) may be larger than the first exit door  334  in the case of the cabin  320  ( FIG.  8 B ). In any case, a workstation  350  in accordance with the foregoing is incorporated by each of the first walls  330   a ,  330   b  in the first exit row  332  for the aircraft cabin  320 ′ of  FIG.  8 C  (the tables  352  each being in the deployed position and extending into the first exit row  332  of the aircraft cabin  320 ′). Moreover, the workstations  350  are incorporated by each of the first walls  330   a ,  330   b  in the first exit row  332  for the aircraft cabin  320 ′ of  FIG.  8 C  so as to position their corresponding table  352  at a height to accommodate a standing user. 
     Similarly and continue to refer to  FIG.  8 C , the second exit row  342  in the case of the aircraft cabin  320 ′ ( FIG.  8 C ) may be larger than the second exit row  342  in the case of the aircraft cabin  320  ( FIG.  8 B ). The second exit door  344  in the case of the aircraft cabin  320 ′ ( FIG.  8 C ) may be larger than the second exit door  344  in the case of the cabin  320  ( FIG.  8 B ). In any case, a workstation  350  in accordance with the foregoing is incorporated by each of the second walls  340   a ,  340   b  in the second exit row  342  for the aircraft cabin  320 ′ of  FIG.  8 C  (the tables  352  each being in their stowed position so as to not extend within second exit row  342  of the aircraft cabin  320 ′). Moreover, the workstations  350  are incorporated by each of the first walls  340   a ,  340   b  in the second exit row  342  for the aircraft cabin  320 ′ of  FIG.  8 C  so as to position their corresponding table  352  at a height to accommodate a standing user. 
       FIG.  8 D  illustrates another integration of the workstations addressed in this disclosure.  FIG.  8 D  illustrates a portion of an aircraft cabin  380  having a plurality of passenger seats  384  (two being illustrated in  FIG.  8 D ) disposed in a common seat row  382 . The seat row  382  may be the first row of a section of the aircraft cabin  380  (e.g., the first row of economy class). A wall  386  (e.g., bulkhead; wall of a monument) is spaced in front of the passenger seats  384  (e.g., along a length dimension of the aircraft cabin  320 ). A separate workstation  350  in accordance with the foregoing may be incorporated by the wall  386  for each of the passenger seats  384 . The workstations  350  disclosed in  FIG.  8 D  are in their corresponding stowed position and are positioned at a height to accommodate a standing user. 
     The workstations addressed in this disclosure may be incorporated by an aircraft to enhance the ability to do work on flights, particularly long haul flights. Moreover, the workstations may be implemented in a manner so as to control use of the same (e.g., by locking the same in the stowed position). A carrier could charge fees for use of such workstations, and as such workstations may be individually unlocked for subsequent use by an aircraft passenger or the like. 
     Any feature of any other various aspects addressed in this disclosure that is intended to be limited to a “singular” context or the like will be clearly set forth herein by terms such as “only,” “single,” “limited to,” or the like. Merely introducing a feature in accordance with commonly accepted antecedent basis practice does not limit the corresponding feature to the singular. Moreover, any failure to use phrases such as “at least one” also does not limit the corresponding feature to the singular. Use of the phrase “at least substantially,” “at least generally,” or the like in relation to a particular feature encompasses the corresponding characteristic and insubstantial variations thereof (e.g., indicating that a surface is at least substantially or at least generally flat encompasses the surface actually being flat and insubstantial variations thereof). Finally, a reference of a feature in conjunction with the phrase “in one embodiment” does not limit the use of the feature to a single embodiment. 
     The foregoing description has been presented for purposes of illustration and description. Furthermore, the description is not intended to limit the invention to the form disclosed herein. Consequently, variations and modifications commensurate with the above teachings, and skill and knowledge of the relevant art, are within the scope of the present disclosure. Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosure. The scope of the disclosure is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials. 
     Systems, methods and apparatus are provided herein. In the detailed description herein, references to “one embodiment,” “an embodiment,” “various embodiments,” etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments. 
     Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f) unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises,” “comprising,” or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Finally, it should be understood that any of the above described concepts can be used alone or in combination with any or all of the other above described concepts. Although various embodiments have been disclosed and described, one of ordinary skill in this art would recognize that certain modifications would come within the scope of this disclosure. Accordingly, the description is not intended to be exhaustive or to limit the principles described or illustrated herein to any precise form. Many modifications and variations are possible in light of the above teaching.