WO2019199174A1

WO2019199174A1 - Portable and foldable aeronautical workstation

Info

Publication number: WO2019199174A1
Application number: PCT/NO2019/050064
Authority: WO
Inventors: Frank Robin Danielsen; Bjørge JACOBSEN; Ulf Tolfsen; Kjetil Huuse
Original assignee: Norwegian Special Mission As
Priority date: 2018-04-13
Filing date: 2019-03-27
Publication date: 2019-10-17
Also published as: NO20180508A1; NO344012B1

Abstract

An aeronautical foldable workstation (1) comprising a base portion (2) with a left column (2L) and a right column (2R), wherein the columns are arranged for being mounted on left and right floor rails on an aircraft cabin floor and comprising left and right bearings (21L, 21R) for a rotatable horizontal cylindrical beam (2H) provided with a laterally translatable bracket and a rotation actuator for the cylindrical beam. The workstation further comprises a monitor unit (4) comprising at least a first monitor screen and arranged on the bracket, and wherein the monitor unit is rotatable with the horizontal cylindrical beam (2H) between an initial downfolded position between the columns, and an upright unfolded operating position above the horizontal beam and comprising at least a first monitor screen.

Description

Portable and foldable aeronautical workstation Field of the invention

[0001] The invention is a portable and foldable aeronautical workstation which may be mounted into an aircraft such as a small aircraft of the King Air 200, a helicopter, but alternatively also into a ground vehicle. The workstation is foldable and may be transferred between different aircraft or vehicles and in the aircraft it is mounted in standard seat rails in the aircraft floor.

Background art

[0002] Aeronautical workstations such as for inflight calibration of the airspace around an airfield require large monitor screens in order for the operator to handle large amounts of visual information in a safe and efficient way. Usually an aeronautical workstation has a bulky computer unit for communication of inflight signals and communication and processing and one or two large monitor screens for the visual information and control commands given via the monitor unit. However, space is confined in small aircraft such as a King Air 200; the rather low ceiling profile forbids the use of a large, high and wide screen.

Short summary of the invention

[0003] A main object of the present invention is to disclose an invention as defined in the attached independent claims.

[0004] The invention seeks to solve the problems discussed above and is an

aeronautical foldable workstation comprising a base portion with a left column and a right column, wherein the columns are arranged for being mounted on left and right floor rails on an aircraft cabin floor and comprising left and right bearings for a rotatable horizontal cylindrical beam provided with a laterally translatable bracket and a rotation actuator for the cylindrical beam. The workstation further comprises a monitor unit comprising at least a first monitor screen and arranged on the bracket, and wherein the monitor unit is rotatable with the horizontal cylindrical beam between an initial downfolded position between the columns, and an upright unfolded operating position above the horizontal beam and comprising at least a first monitor screen.

[0005] The present workstation may simply be fitted into the passenger cabin after removing a seat or a seat row from the floor rails and when the aircraft is used for passenger business, the computer modules may not be onboard or placed secured in another storage space onboard in the aircraft, and the monitor unit will be folded all the way down for a minimal space demand.

Figure captions

[0006] The attached figures illustrate some embodiments of the claimed invention.

[0007] Fig. 0 is a cross-section view of a passenger cabin portion of a King Air 200 aircraft with a rear elevation view of a workstation of the invention arranged in the standard chair rails (5) on the floor.

[0008] Fig. la illustrates a perspective front view of a portable aeronautical workstation. The directions "front" and "rear", "right" and "left" are relative to a user position, i.e. the front of the workstation is the direction facing the operator in his or her normal seated position before the folded-up, open monitor screen (and keyboard (6)), please see Fig.

Id top view. This must not be confused with the flight direction. If the operator shall sit facing other directions than the flight direction, such as sitting transversely oriented, the relative direction terms used herein shall still be used.

[0009] Figs la, b, etc. illustrate various views of the workstation according to the invention in an open position and being left laterally displaced, similar to the position used in Fig. 0. In this embodiment the monitor unit (4) has two screens, one main screen and hinged to the left side of the main screen a fold-out left monitor screen.

[0010] Fig. la is a perspective front view of an embodiment of the workstation according to the invention.

[0011] Fig. lb is a front elevation view of an embodiment of the workstation of the invention.

[0012] Fig. lc is a front left perspective view of the embodiment of the invention.

[0013] Fig. Id is a top view of the embodiment of the workstation of the invention. In this view, we have illustrated a section of the standard floor rails (5) onto which the workstation columns shall be mounted directly in the ordinary way used for passenger seats, or indirectly via a floor rail adapter piece if the column separation width does not fit with the particular floor rail non-standard distance of a deviating aircraft model. In practice, the present workstation may simply be fitted into the passenger cabin after removing a seat (7) or a seat row from the floor rails (5). Please observe that the left side fold-out screen will block the aisle if used as in Fig. 0, so the left fold-out screen must be folded in and the monitor unit (4) must be folded down forwardly before landing and before take-off. In an embodiment the computer unit (8) for the workstation may be attached in the same floor rails (5) and arranged at the rear side of the workstation (i.e. ahead in the aircraft) and the monitor unit folded down 90 degrees to rest on the computer unit (8) during take-off and landing. This will contribute to flight safety. Please notice that in Fig. Id the left fold-out screen is folded out to an angle of about 150 - 160 degrees from its folded-in position in order to better face the operator. A gas spring may be arranged to hold the left screen in this position relative to the main screen.

[0014] Fig. le is a rear left perspective view of the embodiment according to the invention. This view is seen from an aisle position looking back and starboard in the aircraft.

[0015] Fig. If is a rear elevation view of the embodiment of the invention.

[0016] Fig. lg is a left elevation view of the embodiment of the invention.

[0017] Fig. lh is a rear right perspective view of the embodiment of the invention.

[0018] Figs. 2a, b, etc. are illustrations of an embodiment of the invention in an upright position, wherein if the monitor screen has a double screen is folded in, i.e. not opened. Wherein the term "front" is the face of the workstation towards the operator, which is also "fore" and "rear" in the present description. "Front" is thus the direction rearward in the aircraft.

[0019] Fig. 2a is a front elevation view of an embodiment of the invention.

[0020] Fig. 2b is a right side elevation view of the embodiment of the invention.

[0021] Fig. 2c is a left side elevation view of the embodiment of the invention, i.e. as seen from the aisle.

[0022] Fig. 2d is a rear elevation view of the embodiment of the invention.

[0023] Fig. 2e is a rear left perspective view of the embodiment of the invention.

[0024] Fig. 2f is a front left perspective view of the embodiment of the invention. [0025] Fig. 2g is a rear right perspective view of the embodiment of the invention (as if seen through the main body wall of the aircraft).

[0026] Fig. 2h is a front right perspective view of the invention.

[0027] Figs. 3a, b, ... illustrate an embodiment of the workstation of the invention in an upright position, and in a central position before lateral translation, - i.e. folded-up and with the left screen folded out and with open, folded out keyboard (6). In most circumstances when used in a small aircraft this position would interfere with the right ceiling portion of the aircraft and is, in practice, more for illustration. In most

circumstances the leftward translation of the monitor unit must take place before the screen reaches its folded-up top position.

[0028] Fig. 3a is a front left perspective view of the embodiment of the invention.

[0029] Fig. 3b is a front elevation view of the embodiment of the invention.

[0030] Fig. 3c is a right elevation view of the embodiment of the invention.

[0031] Fig. 3d is a rear elevation view of the embodiment of the invention.

[0032] Fig. 3e is a left elevation view of the embodiment of the invention.

[0033] Figs. 4a, b, c, ... illustrate a down folded position of an embodiment of the workstation of the invention. This position may be used if the workstation shall remain in the aircraft cabin while temporarily not in use, i.e. during ordinary passenger flights between workstation operation flights. In this position it takes the space otherwise occupied by an ordinary seat (row) and has a slim space-efficient design but is otherwise not a disadvantage to the passengers or the cabin crew and does not hinder evacuation in an emergency situation.

[0034] Fig. 4a is a front elevation view of the embodiment of the invention.

[0035] Fig. 4b is a rear left perspective view of the embodiment of the invention.

[0036] Fig. 4c is a front left perspective view of the embodiment of the invention. [0037] Fig. 4d is a rear right perspective view of the embodiment of the invention.

[0038] Fig. 4e is a left elevation view of the invention. Please notice that in an embodiment of the invention the left column (2L) is placed half a rotation bearings (21L) length to the rear of the right column (2R) relative to a transverse line for two reasons: firstly, because in this embodiment the left bearing (21L) is placed on the upper front edge (relative to the user seat position) of the left column for enabling the monitor unit mounted with its operational rear lower edge on the bracket (3) to be generally enveloped by the two columns when folded down, and secondly in order to allow the user to have better access to and from his seat and also some legroom for his left foot.

[0039] Fig. 4f is a rear elevation view (with column top covers removed) of an embodiment of the invention. Please observe that here we have illustrated a portion of the aircraft floor and the seat rails (5) into which the columns (2R, 2L) are attached.

[0040] Fig. 4g is a top view and part horizontal section of the folded down monitor unit (4) arranged between the two columns (2L, 2R) wherein the cut-out in the right column gives a top view of the gas spring and moment arm (partly hidden by the horizontal beam (2H)), and a view of the bracket (3) attached to the monitor unit.

[0041] Figs. 5a, b, c, ... show an embodiment of the invention in a forward folded position such as for the monitor unit (4) being folded down lying on top of a stack of computer units (8), or the monitor unit (4) in an intermediate position between folded down and folded up positions. In this position, please see Fig. 5c, the monitor unit on the bracket (3) is enabled to start travelling leftwardly partly beyond the left column (2L) because it is now clear over the top of the left column. Further, in an embodiment of the invention there is a quarter bore in the bracket (3) and monitor unit (4) housing which allows both to pass leftward across the left bearing (21L), so the monitor unit (4) may start being raised from this position and upwardly. The leftward movement may be initiated by turn-releasing the L-shaped bracket lateral movement bolt lock on the bracket.

[0042] Fig. 5a is a front elevation view of an embodiment of the invention in this 90 degrees rearward directed position of the monitor unit (4).

[0043] Fig. 5b is a rear elevation view of the same. [0044] Fig. 5c is a left elevation view of the same, here with a computer unit

(8)arranged at the rear side of the columns (2L, 2R) and below the 90 degs. folded-down monitor unit (4), so as for allowing a safe position for take-off and landing of the aircraft with the units mounted on board.

[0045] Fig. 5d is a front right perspective view of the embodiment of the invention.

[0046] Fig. 5e is a left rear perspective view of the embodiment of the invention.

[0047] Fig. 5f is a front left perspective view of the embodiment of the invention. The maximum allowed left lateral translation distance (d) of the bracket (4) with the monitor unit (4) is indicated.

[0048] Fig. 5g is a right rear perspective view of the embodiment of the invention.

[0049] Figs. 6 a, b, c, ... are section view illustrations of the internal mechanism in the right column (2R).

[0050] Fig. 6a is a vertical section view and part right elevation view and shows the internal mechanism in the right column (2R). Here is shown the partially hidden down- folded monitor unit (4) which is held on the bracket (not shown) on the rotatable cylindrical beam (2H). Here the monitor unit (4) is held in its folded down position with gas spring (31P) holding moment arm (31M) of the transverse beam (2H) in a down locked position. In an embodiment of the invention the gas spring (31P) has a force of 700 N to 7000 N which will allow it to lift and raise the monitor unit (4) up in the rearward direction (see arrow) up to an elevated position, please see moment arm illustrated in a broken line with numeral (31M (upright)). There is space for the moment arm (31M) inside the rectangular horizontal section of the column to allow the rotation from downfolded to upright. However, this makes placing the right bearing (21R) on the right wall of the right column (2R) a good practical solution, please see the small near- cylindrical box on the right column (2R) in Fig. 4f and Fig. 4g.

[0051] Fig. 6b is a front perspective and section view of the embodiment of the invention.

[0052] Fig. 6C is a rear right perspective and section view of the same. [0053] Fig. 6d is a left part exploded perspective view of base portion (2) with right and left column (2R, 2L) and horizontal cylindrical beam (2H).

[0054] Fig. 6e is a rear left perspective and exploded view of an embodiment of the invention showing parts of the right bearing (21R) for the horizontal cylindrical beam (2H) and the left bearing (21L), the moment arm (31M) and the moment arm gas spring (31P). Further is shown the horizontal gas spring (32H) for the bracket (3) (not shown) and the rollers (2H) for guiding the slot of the bracket in the left lateral displacement (d).

[0055] Fig. 6f is a rear left perspective view of the above components but with the bracket (3) mounted on the horizontal beam (2H). Here the left bearing (21L) is attached such as by welding, to a quarter-circle cut-out corner portion of a rectangular adapter block for fitting into the top of the left column (2L), please also see the exploded view in Fig. 6e.

[0056] Fig. 6g is a left view section of bracket (3) and an elevation view of the partly hidden right column (2R) behind. Here is shown the horizontal beam (2H) in a horizontal bore (26B) of the bracket (3), a roller bearing (33H) mounted in bolts on the horizontal beam (2H), and the gas spring (32H) shown in cross section inside a slot (26H) along the bore (26B). Here it is apparent that rotating the horizontal beam (2H) will force rotation of the bracket (3) due to the roller bearings (33H).

[0057] Fig. 6h is a left front perspective view and vertical section view of bracket (3) and horizontal beam (2H), i.e. the same vertical section as shown in Fig. 6g.

[0058] Fig. 6i is a left rear perspective view and section view of bracket (3) and horizontal beam (2H), here in a near- vertical section through the horizontal beam (2H), illustrating the position of the horizontal actuator (32H) acting between the bracket (3) and the bolt (32B) fixing the piston to the horizontal beam (2H). This makes it apparent how the horizontal actuation works.

[0059] Fig. 6j is a left rear perspective view and horizontal section view of bracket (3) and rollers (33H) on horizontal beam (2H) running in slot (26H) in bracket (3). Here it is clear why the roller bearings (33H) guides the slot (26H) of the bracket (3) back and forth on the horizontal beam (2H). The roller bearings (33H) only need a very small clearance in the slot in order to allow rolling against the relevant wall of the slot.

[0060] Fig. 6k left rear perspective view and horizontal part transparent view of bracket (3) and gas spring (32H) and rollers (33H) on horizontal beam (2H) running in slot (26H) in bracket (3).

Embodiments of the invention

[0061] The invention will in the following be described and embodiments of the invention will be explained with reference to the accompanying drawings.

[0062] The invention seeks to solve the problems discussed above and is an

aeronautical foldable workstation (1) comprising a base portion (2) with a left column (2L) and a right column (2R), wherein the columns (2L, 2R) are arranged for being mounted on left and right floor rails (5) on an aircraft cabin floor and comprising left and right bearings (21L, 21R) for a rotatable horizontal cylindrical beam (2H) provided with a laterally translatable bracket (3) and a rotation actuator (31) for the cylindrical beam (2H). The workstation further comprises a monitor unit (4) comprising at least a first monitor screen (41) and arranged on the bracket (3), and wherein the monitor unit (4) is rotatable with the horizontal cylindrical beam (2H) between an initial downfolded position between the columns (2L, 2R), and an upright unfolded operating position above the horizontal beam (2H), and comprising at least a first monitor screen (41).

[0063] Left and right is seen from the operator and "Front" is defined as the direction towards the operator's side of the workstation, i.e. with an open monitor facing a seated operator, and the rear face of the monitor usually in the forward direction of the aircraft, the operator usually will sit facing forward. The right column will then be placed closest to the aircraft body and the left column by the aisle, and directly or indirectly attached to the existing seat rails (5) in the aircraft floor. The present workstation may simply be fitted into the passenger cabin after removing a seat or a seat row from the floor rails (5). The workstation according to the invention is a workstation for aeronautical computer systems for special missions, flight inspections and also in combination with existing data processing, surveillance and communication systems etc. for helicopters and aircrafts and special designed to fit into small aircrafts used in both special missions and passenger business and thus requires a flexible arrangement. Please see Fig.O. and Id. The workstation is arranged for use together with one or more separate computer modules (CM). They will generally be placed and fit under the monitor unit (4). Please see Fig. 5c which also illustrates a typical take-off and landing safety position. The monitor unit (4) will then be arranged in a perpendicular direction to the columns in a half way downfolded position. In an embodiment a separate locking and unlocking device (LD), pin, handle or the like, is arranged for holding the monitor unit (4) in this position and release it to open to unfolded position, or fold down to an un operative position allowable when the computer modules (CM) are removed. When the aircraft is used for passenger business, the computer modules may not be onboard or placed secured in another storage space onboard in the aircraft, and the monitor unit (4) will be folded all the way down for a minimal space demand. This is a major advantage of the present invention. Another advantage is that the monitor unit (4) will rotate with the cylindrical beam so it may be tilted in different angles and adjusted according to the operator desire when in operative use. Thus, no adjustable seat has to be installed and a fixed passenger seat may be used together with the workstation. A tall operator need another angle on the monitor screen than a short operator. The possibility for the lateral movement of the bracket with the monitor toward aisle is another major advantage, please see illustration in Fig. 0 and 1A. Generally, the aeronautic computer systems should use large monitors due to a large amount of information that should be displayed at the same time. Thus, the available space in a small aircraft is a challenge. The present invention solves this problem by the possibility for lateral movement of the monitor. In most circumstances the leftward translation of the monitor unit must take place before the screen reaches its folded-up top position.

[0064] In an embodiment of the invention the right column (2R) is hollow and accommodates at least the rotation actuator (31), wherein the rotation actuator (31) comprises a gas spring (31P) operating on a moment arm (31M) on the cylindrical beam (2H). This mechanism will hold the monitor unit (4) in its folded down position with the gas spring (31P) that is holding the moment arm (31M) of the transverse beam (2H) in a down locked position. In an embodiment of the invention the gas spring (31P) has a force of 700 N to 7000 N which will allow it to lift and raise the monitor unit (4) up in the rearward direction up to an elevated position. Please see Fig. 6a. As an advantage of the workstation is to have it installed in the aircraft even when the aircraft is in a passenger business, it is also of importance to have a compact and protected design with few movable, vulnerable and extending portions, thus advantage to hide the moving gas spring (31P) and moment arm (31M) inside one of the columns. The reader observes from drawings that the right column (2R) is higher than the left column (2L). The above explains why the right column requires higher internal headroom than the elevation level of the bearings (2L, 2R) for the gas spring and moment arm mechanism in the upper position.

[0065] An embodiment of the invention has columns with a rectangular cross section, particularly the right column (2R) which accommodates the spring (31P) and the moment arm (31M). [0066] The moment arm (31M) is allowed to rotate from a lower position to an upper position inside the right column (2R), within the horizontal cross section of the right column (2R), and the right column (2R) extends at least the length of the moment arm (31M) above the right bearing (21R) for the horizontal cylindrical beam (2H) with the moment arm (31M) in the upper position. Please see Figs 6a, 4f and 4g. The right bearing for the horizontal beam will be arranged in a fore portion (near the front) of the right column (2H) and the gas spring (31P) will be arranged close to the opposite, rear portion of the right column (2R) at its lower axle, and having the upper axle connected to the moment arm (31M) over center in its lower position for locking the monitor (4) unit in its lower position. In this arrangement the gas spring will have its best moment arm 90 degrees out when the heavy monitor unit (4) is in its horizontal position on its way up or down. A lock for the monitor's (4) 90 degrees up position is preferable and may be arranged using a lock pin or the equivalent.

[0067] In an embodiment of the invention the left bearing (21L) is arranged at a top of the left column (2L) and the right bearing (21R) is arranged on the right column (2R) so as for allowing the monitor unit (4) to be laterally translated partly beyond the left column (2L). Please see Fig. 6d.

[0068] In an embodiment of the invention the monitor unit (4) comprise an integrated key board. According to an embodiment of the invention the left bearing (21L) is arranged at a front top edge of the left column (2L) so as for allowing the keyboard (6) of the monitor unit (4) to be folded out to the front while being allowed to be laterally translated partly beyond the left column (2L).

[0069] In an embodiment of the invention the monitor unit have a recess, a quarter- circle cut-out corner portion, across the rear end for allowing the monitor unit to traverse above the left bearing (21R) and at the same time contribute to a favorable compact design. Please see Figs. 6i and 6j.

[0070] For translation movement of the bracket (3) and, by this moving this, also moving the monitor unit (4), an embodiment of the workstation according to the invention comprises a horizontal gas spring (32H) arranged axial-parallel with the horizontal beam (2H) and having one end fixed by a transverse bolt (32B) to the horizontal beam (2H) and an opposite end attached in the bracket (3). The horizontal gas spring is (32H) arranged for moving the bracket with the monitor unit (4) to the left on and relative to the horizontal beam (2H). Please see Figs. 6g and 6j. The gas spring contributes to a soft movement of the monitor unit when releasing for moving the monitor (4) the desired distance (d) leftward, while expanding the gas spring, to an operative position and also holds the monitor unit (4) in place when moved and expanded.

[0071] In an embodiment of the invention the spring may have an expansion release actuator. A release and lock mechanism, such as a lock bolt, may be used and may be wire-and handle operated. In an embodiment of the invention the bracket (3) is provided with a horizontal main bore (26B) as illustrated in Fig. 6i, for the horizontal beam (2H), and further provided with a sliding slot (26H) for rollers (33H). The rollers (33H) are held on transverse bolts on the horizontal beam (2H), please see Figs. 6i and 6j. The sliding slot (26H) allows a desired left translation distance (d) for the bracket (3) with the monitor unit (4).

[0072] The workstation according to an embodiment of the invention has a monitor unit (4) with a main screen (41). In a further embodiment the invention comprises a second monitor screen (42) hinged on a left screen frame side of the first, main screen (41).

This second screen (42) may then be folded out across the aisle to extend the available display and easily be folded back to give passage way in the aisle and for take-off and landing safety, otherwise it would block the aisle escape route and also be vulnerable to hard landings. Again, the invention is contributing to a safe and compact design of the workstation for fitting into a small aircraft.

[0073] Regardless of embodiments the workstation according to the invention may be equipped with various devices such as one or more displays, recording devices, interface panels, control units, communication systems, joy stick control and touch screen systems. The adjustable and various positions for monitors utilize available cabin space. The workstation and the computer modules being fully module based, foldable and easily portable.

[0074] Different aircrafts may have different distance between the seat rails (5). In an embodiment of the invention the columns may be connected to the seat rails (5) via a seat rail adapter bracket.

The workstation (1 ) of any of the embodiments may have a left right mirrored equivalent design of the workstation to be placed on the left side of the aircraft or if a rearward facing operator position should be required.

Claims

1 Claims

1. An aeronautical foldable workstation (1) comprising

-a base portion (2) comprising

-a left column (2L),

-a right column (2R),

said columns (2L, 2R) arranged for being mounted on left and right floor rails on an aircraft cabin floor and comprising left and right bearings (21L, 21R) for a rotatable horizontal cylindrical beam (2H) provided with a laterally translatable bracket (3),

-a rotation actuator (31) for said cylindrical beam (2H),

- a monitor unit (4) comprising at least a first monitor screen (41) and arranged on said bracket (3),

- wherein said monitor unit (4) is rotatable with said horizontal cylindrical beam (2H) between an initial downfolded position between said columns (2L, 2R), and an upright unfolded operating position above said horizontal beam (2H).

2. The workstation (1) of claim 1, wherein

- said right column (2R) is hollow and accommodates at least said rotation actuator (31),

- wherein said rotation actuator (31) comprises a gas spring (31P) operating on a moment arm (31M) on said cylindrical beam (2H).

3. The workstation (1) of claim 1 or 2, wherein

- said right column (2R) has a rectangular horizontal cross section,

- said moment arm (31M) is allowed to rotate from a lower position to an upper position inside said right column (2R) within the horizontal cross section of said right column (2R)

- said right column (2R) extends at least the length of said moment arm (31M) above said right bearing (21R) for said horizontal cylindrical beam (2H) with said moment arm (31M) in said upper position.

4. The workstation (1) of any of the above claims,

- wherein said left bearing (21L) is arranged at a top of said left column (2L) and said right bearing (21R) is arranged on said right column (2R) so as for allowing said monitor unit (4) to be laterally translated partly beyond said left column (2L) when partly rotated to its elevated position.

5. The workstation (1) of any of the above claims,

- wherein said left bearing (21L) is arranged at a front top edge of said left column (2L) 2

so as for allowing a keyboard (6) of said monitor unit (4) to be folded out to the front while being allowed to be laterally translated partly beyond said left column (2L).

6. The workstation (1) of any of the above claims, comprising a horizontal gas spring (32H) arranged axial-parallel with said horizontal beam (2H) and having one end fixed by a transverse bolt (32B) to said horizontal beam (2H) and an opposite end attached in said bracket (3), said horizontal gas spring (32H) arranged for moving said bracket with said monitor unit (4) leftward along and relative to the horizontal beam (2H).

7. The workstation (1) of any of the above claims, wherein said bracket (3) provided with a horizontal main bore (26B) for said horizontal beam (2H), and further provided with a sliding slot (26H) for rollers (33H) held on transverse bolts on said horizontal beam (2H), said sliding slot allowing a left translation distance (d) for said bracket with said monitor unit (4).

8. The workstation (1) of any of the above claims, wherein said monitor unit (4) further comprises a second monitor screen (42) hinged on a left screen frame side of said first screen (41).