One-piece mounting system for equipment on an aircraft cockpit wall, associated aircraft cockpit

Abstract

One-piece system for mounting equipment on an aircraft cockpit wall, associated aircraft cockpit. The invention relates to a mounting system (36) for equipment (34) on a wall (26) of an aircraft cockpit, the mounting system (36) comprising: - a first part (44) having a first attachment portion (44A) for a first edge (28) of the cockpit wall (26); and - a device (50) for attaching the equipment (34). The first attachment portion (44A) forms a receiving recess (52) for said first edge (28), and the first part (44) includes a device for adjusting the volume of said receiving recess (52). Figure for the abstract: Figure 2

Description

Title of the invention: One-piece mounting system for equipment on a wall of an aircraft cockpit, associated aircraft cockpit

[0001] The present invention relates to a system for mounting equipment on a wall of an aircraft cockpit.

[0002] The invention also relates to an aircraft cockpit, comprising a wall, equipment and such a system for mounting the equipment on the wall.

[0003] The invention therefore relates to the field of removable mounting systems for equipment in an aircraft cockpit. Such equipment, particularly electronic equipment such as image sensors or cameras, typically has a small size and weight, and is not generally intended to be permanently fixed in the aircraft cockpit. Indeed, it may be advantageous for the pilot to carry such equipment outside the aircraft when not flying. It may also be desirable for the pilot to carry the equipment mounting system outside the aircraft when not flying. Thus, a quick-release mounting / dismounting system for the equipment on the cockpit wall is advantageous.

[0004] Mounting such equipment in the aircraft cockpit is a known method of drilling through the cockpit wall to screw in a mounting bracket for the equipment. However, this entails a modification of the cockpit and potentially necessitates additional aeronautical certification. Furthermore, such a mounting system is difficult to reverse.

[0005] A suction cup mount is also known. However, such a mount is generally installed only once, and requires particular cleanliness, or preparation, of the surface of the cockpit wall on which it is mounted, to ensure good adhesion of the suction cup.

[0006] One of the aims of the invention is therefore to propose a system for mounting equipment on a wall of an aircraft cockpit, which remedies the aforementioned disadvantages and is in particular easy and quick to install and uninstall in the cockpit.

[0007] To this end, the invention relates to a system for mounting equipment on a wall of an aircraft cockpit, the mounting system comprising:

[0008] - a first part comprising a first portion for attaching to a first edge from the cockpit wall; and

[0009] - an equipment attachment device.

[0010] The first attachment portion forms a receiving housing for said first edge and the first part includes a device for adjusting the volume of said receiving housing.

[0011] According to other advantageous aspects of the invention, the mounting system comprises one or more of the following features, taken individually or in all technically possible combinations:

[0012] - the adjustment of the volume of the receiving housing is such that the first portion the hook grips the first edge, the mounting system being fixed to the first edge by the first portion of the hook;

[0013] - the first attachment portion comprises a curved fixed part formed by a upper branch and a lower branch, and the adjustment device includes a movable part relative to the fixed part, the movable part being configured to move between the upper branch and the lower branch;

[0014] - the receiving housing extends between the upper branch and the movable part;

[0015] - the equipment attachment device is mechanically coupled to the branch upper part of the fixed section;

[0016] - the adjustment device includes at least one threaded rod extending between a first end and a second end, the threaded rod passing through the upper branch and the receiving housing, the first end being mechanically coupled to the moving part, the second end being able to be driven in translation along the extension axis of the threaded rod to generate a translation of the moving part between the upper branch and the lower branch, along said extension axis;

[0017] - the adjustment device includes at least one elastic compression element arranged between the upper branch and the moving part and / or an elastic tension element arranged between the lower branch and the moving part;

[0018] - the fastening device includes a means for compensating for the inclination of the wall, such as a ball joint or a compensating wedge; and / or the equipment includes a means of compensating for the inclination of the wall, such as image processing software;

[0019] - the first bonding portion comprises a flexible layer applied to at least a surface between an external surface of the first attachment portion and an internal surface, opposite to the external surface, of the first attachment portion;

[0020] - the mounting system further comprises a second part comprising a second attachment portion to a second edge of the cockpit wall, the second piece being separate from the first piece, the second edge being separate from the first edge, and a device for attaching the second piece to the first piece.

[0021] The invention also relates to an aircraft cockpit, comprising a wall, equipment and a system for mounting the equipment on the wall, the mounting system being as defined above.

[0022] According to other advantageous aspects of the invention, the aircraft cockpit comprises one or more of the following features, taken individually or in all technically possible combinations:

[0023] - the wall includes at least one fixing hole, the first part of the system of assembly including at least one additional fixing hole, the mounting system being additionally fixed to the wall via a rod passing through the additional fixing hole(s) and the fixing hole(s);

[0024] - the equipment is electronic equipment; the electronic equipment being preferably an image sensor(s), the sensor being specifically configured to take at least one image of the aircraft pilot's face; and

[0025] - the cockpit further includes a seat for an aircraft pilot, and the system The mounting is arranged so that the equipment is located at a distance of approximately between 0.3 m and 1.1 m from the pilot's head.

[0026] The invention will become clearer upon reading the following description, given solely by way of non-limiting example, and made with reference to the drawings in which:

[0027] [Fig-1] [Fig.1] is a schematic representation of an aircraft cockpit according to the invention;

[0028] [Fig.2] [Fig.2] is a three-dimensional representation of a mounting system for equipment on the cockpit wall according to the invention, the mounting system comprising a first part with a first attachment portion on a first edge of the wall; and

[0029] [Fig.3] [Fig.3] is a cross-sectional representation of a device for adjusting the volume of the receiving housing of the first edge defined by the first part of the mounting system of [Fig.2].

[0030] In the following description, the expression "approximately equal to" defines a relationship of equality to plus or minus 20%, preferably to plus or minus 10%, preferably still to plus or minus 5%; and similarly the expression "approximately between A and B" means that each boundary A, B is likely to vary by plus or minus 20%, preferably by plus or minus 10%, preferably still by plus or minus 5%.

[0031] In [Fig.1], an aircraft 10 includes a cockpit 12 inside which a pilot 14 is installed.

[0032] Herein, aircraft 10 means any airplane or helicopter or any other flying machine that can be piloted by a pilot 14 from that machine.

[0033] The cockpit 12 includes a floor 16, at least one seat 18 fixed to the floor 16, a display screen 20 and a windscreen 22 at least partially transparent and separating the interior of the cockpit 12 from the external environment of the aircraft 10, the head 24 of the pilot 14 looking towards the display screen 20 and the windscreen 22.

[0034] In the example of [Fig.1], seat 18 is a seat for pilot 14.

[0035] The display screen 20 is also commonly referred to as a head-down display screen, and is typically configured to display information from an avionics system, not shown.

[0036] In [Fig.2], the cockpit 12 comprises a wall 26 having at least a first edge 28, and a support surface 32 extending from the first edge 28.

[0037] For example, the cockpit 12 further includes a second edge 30 and the support surface extends between the first edge 28 and the second edge 30.

[0038] The cockpit 12 further includes equipment 34 and a mounting system 36 for the equipment 34 on the wall 26.

[0039] In the example of [Fig. 2], the wall 26 is, for example, located near the windshield 22 and extends in a substantially horizontal plane. In other words, the wall 26 is substantially parallel to the floor 16 of the cockpit 12. The support surface 32 then also extends in this substantially horizontal plane.

[0040] Alternatively, the wall 26 extends in a plane slightly inclined with respect to the horizontal. For example, the wall 26 extends in a plane forming an angle of between 1° and 20° with a horizontal plane.

[0041] For example, the wall 26 is inclined relative to the horizontal plane, towards the nose of the aircraft, and / or laterally, towards the left and right sides of the pilot 14.

[0042] The bearing surface 32 includes, for example, one or more smooth or tapped holes, not shown, useful for fixing any equipment present on board the cockpit 12.

[0043] In a particular embodiment, the first edge 28 is an edge of a projection extending horizontally beyond a substantially vertical, or slightly inclined face relative to the vertical, of the cockpit 12 on which the display screen 20 is typically arranged, the projection then forming a sun visor for the display screen 20.

[0044] The sun visor, for example, has a thickness, taken perpendicular to the horizontal, greater than 5 mm.

[0045] In a particular embodiment, the second edge 30 is for example an edge of a ventilation opening, not shown, the ventilation opening typically allowing air to circulate towards the windshield 22, in particular for demisting the windshield 22.

[0046] Alternatively, the second edge 30 is a completely different type of cavity provided in the bearing surface 32, or a corner or a lip located close to the windshield 22.

[0047] Alternatively or in addition, the second edge 30 corresponds to one or more smooth or tapped holes existing on the bearing surface 31.

[0048] For example, the first edge 28 and the second edge 30 typically extend along respective vanishing lines which are secant.

[0049] Equipment 34 is typically electronic equipment.

[0050] The electronic equipment 34 is, for example, an image sensor(s) or camera, the sensor being configured in particular to take at least one image of the face of the pilot 14 of the aircraft 10. Alternatively, the electronic equipment is an electronic tablet, such as an EFB (Electronic Flight Bag).

[0051] Equipment 34, for example, has a mass approximately between 50 g and 700 g.

[0052] Equipment 34, for example, has a volume substantially between 0.04 L and 1 L.

[0053] The equipment 34 typically has a footprint contained within a rectangular parallelepiped with a length between 20 mm and 100 mm, a width between 10 mm and 30 cm, and a height between 10 mm and 30 cm.

[0054] The mounting system 36 is configured to mount, that is to say to hang, fix, or attach, the equipment 34 on the wall 26. In other words, the mounting system 36 is configured to mechanically connect the equipment 34 to the wall 26.

[0055] Advantageously, the mounting system 36 is arranged so that the equipment 34 is located at a distance substantially between 30 cm and 1.1 m from the head 24 of the pilot 14. Preferably, the mounting system 36 is arranged so that the equipment 34 is mounted as close as possible to the first edge 28 of the wall 26 of the cockpit.

[0056] According to the invention, the mounting system 36 comprises a first part 44 configured to hook onto the first edge 28 of the cockpit wall 26, and a device 50 for attaching the equipment 34.

[0057] The first part 44 is typically a rigid part. For example, the first part 44 is made of metal, such as an aluminum and / or titanium alloy and / or stainless steel. Alternatively, the first part 44 is made of plastic, for example, polyetherimide (PEI). In one particular embodiment, the first part 44 is made of a thermoplastic known as "ULTEM" resin (registered trademark) manufactured by SAB IC. Alternatively, or in addition, the first part 44 is made of a matrix reinforced with reinforcing elements, for example, carbon fibers.

[0058] The first part 44 is for example manufactured by additive manufacturing, for example by a powder laser sintering process (in English Selective Laser Sintering, SLS).

[0059] The first part 44, for example, has a mass approximately between 5 g and 100 g.

[0060] The first part 44 typically has a length between 50 mm and 300 mm, a width between 30 mm and 100 mm, and a height between 5 mm and 50 mm.

[0061] The first part 44 includes a first hook portion 44A configured to hook onto the first edge 28 of the wall 26 and a substantially flat portion 44B, called the first flat portion, configured to bear against the bearing surface 32 of said wall 26.

[0062] In the example of [Fig.2], the first attachment portion 44A is configured to attach to the first edge 28 corresponding to the edge of the projection forming the sun visor.

[0063] According to the invention, the first attachment portion 44A forms a receiving housing 52 for the first edge 28 and the first piece 44 includes an adjustment device 54 for the volume of the receiving housing 52.

[0064] As will be described in more detail later, the adjustment of the volume of the receiving housing 52 by the adjustment device 54 is in particular such that the first hook portion 44A grips the first edge 28 in order to fix the mounting system 36 on the first edge 28 of the cockpit 12.

[0065] In the example of [Fig.2], the first attachment portion 44A includes a fixed part 56 that is curved, preferably downwards and inwards, i.e. downwards and towards the bearing surface 32.

[0066] The fixed part 56 is formed by an upper branch 58 and a lower branch 60. The upper branch 58 forms the planar portion 44B and is offset from the lower branch 60 along a normal to the plane of the planar portion 44B. Such a normal to the plane of the planar portion 44B will hereafter be referred to as the "elevation direction" and will be designated by the reference "Z", as shown in [Fig. 2]. The upper branch 58 and lower branch 60 extend, for example, in a substantially parallel manner.

[0067] The upper branch 58 is intended to extend over a part of the bearing surface 32 of the wall 26.

[0068] The lower branch 60 extends opposite at least part of the upper branch 58. In the example of [Fig.2], the lower branch 60 has a length strictly less than the length of the upper branch 58, but sufficient to hook the first edge 28 of the wall 26.

[0069] The fixed part 56 therefore has substantially a U or C shape.

[0070] Advantageously, the fixed part 56, and more generally the first part 44, has a blunt, rounded shape, and does not have any sharp angle or edge that could injure a user or damage the aircraft 10.

[0071] The adjustment device 54 includes a movable part 62 relative to the fixed part 56. The movable part 62 is configured to move between the upper branch 58 and the lower branch 60. In other words, the movable part 62 is able to be translated, along the elevation direction Z, between the upper branch 58 and the lower branch 60.

[0072] The movable part 62 extends, for example, in a manner substantially parallel to the upper 58 and lower 60 branches.

[0073] The movable part 62 has, for example, a length between the length of the upper arm 58 and the lower arm 60.

[0074] The receiving housing 52 of the first edge 28 extends between the upper arm 58 and the movable part 62. The movable part 62 is then intended to come into contact with a lower surface of the wall 26.

[0075] Thus, by translating the movable part 62 along the elevation direction Z, the volume of the receiving housing 52 can be adjusted. A user can therefore adjust the volume of the receiving housing 52 so that the first attachment portion 44A grips the first edge 28 in order to fix the mounting system 36 to the first edge 28 of the cockpit 12.

[0076] In a particular embodiment, shown in detail in [Fig.3], the adjustment device 54 includes at least one threaded rod 64 extending between a first end 66 and a second end 68 opposite the first end 66 along an extension axis A of the threaded rod 64. For example, only the second end 68 of the rod 64 is threaded.

[0077] As shown in [Fig.2], the adjustment device 54 comprises two threaded rods 64, spaced apart according to the width of the first piece 44, each threaded rod 64 passing through the upper arm 58 and the receiving housing 52.

[0078] In what follows, only one threaded rod 64 will be described in detail. It is understood that the two, or more, threaded rods 64 are similar.

[0079] For example, the threaded rod 64 extends between the upper arm 58 and the receiving housing 52 in the elevation direction Z. The extension axis A of the threaded rod 64 and the elevation direction Z are then substantially parallel when the mounting system 36 is assembled on the wall 26.

[0080] The first end 66 of the threaded rod 64 is mechanically coupled to the moving part 62.

[0081] By "mechanically coupled", it is understood that the first end 66 of the threaded rod 64 is coupled, directly or indirectly, with the moving part 62, so that a displacement, along the elevation direction Z, of the threaded rod 64 causes a displacement along the elevation direction Z, of the moving part 62.

[0082] In particular, the first end 66 of the threaded rod 64 is welded, glued or crimped to the moving part 62.

[0083] In one variant, an elastic return system, such as a compression spring, not shown, is disposed between the moving part 62 and the upper arm 58 so as to bring the moving part 62 and the upper arm 58 closer together.

[0084] As a further alternative, not shown, an elastic return system, such as a tension spring, is arranged between the moving part 62 and the lower arm 60 so as to bring the moving part 62 and the upper arm 58 closer together.

[0085] The second end 68 of the threaded rod 64 passes through the upper branch 58, for example through an opening provided in the upper branch 58.

[0086] The second end 68 of the threaded rod 64 is able to be driven in translation along the extension axis A of the threaded rod 64 to generate a translation of the movable part 62 between the upper branch 58 and the lower branch 60, along the extension axis A.

[0087] For example, the second end 68 of the threaded rod 64 is provided with a nut or a clamping wheel 70 screwed onto the second end 68. The rotation of the clamping wheel 70 around the extension axis A causes the translation of the movable part 62 between the upper arm 58 and the lower arm 60, along the extension axis A.

[0088] Thus, by a simple and quick-to-use system, a user can adjust the volume of the receiving housing 52 in order to fix, reversibly, the mounting system 36 to any type of wall 26 of the cockpit 12, and in particular to the first edge 28 of the cockpit 12.

[0089] Advantageously, each second end 68 is provided with flat and elastic corrugated washers 72a, 72b (also called "onduflex") arranged under each wheel 70, along the extension axis A.

[0090] The flat washers 72a below and the onduflex washer 72b above allow the wheels 70 (or nuts) to be locked and secured in the tightened position, in order to keep the moving part 62 at a desired distance from the upper arm 58, and to keep the wheels 70 in position on the threaded rods 64.

[0091] Advantageously, a clearance Jl, shown in [Fig. 3], is present between the threaded rod 64 and the edges of the opening in the upper arm 58. Thus, the threaded rod 64, as well as the movable part 62, can be inclined slightly relative to the elevation direction Z. This feature allows the first The attachment portion 44A is designed to best fit the shape of the wall 26. For example, if the upper and lower surfaces of the wall 26 are not exactly parallel, it is possible to slightly tilt the movable part 62 relative to the upper arm 58 in order to best grip the wall 26.

[0092] The fastening device 50 is for example mechanically coupled to the first part 44.

[0093] The attachment device 50 of the equipment 34 is, for example, mechanically coupled to the upper arm 58 of the fixed part 56.

[0094] The fastening device 50 fixes, for example, the equipment 34 to the wall 26 by means of a reversible snap-fit ​​system by cooperation of geometric shapes, or screws, of the equipment 34 on the upper branch 58 of the fixed part 56.

[0095] For example, the attachment device 50 is an attachment device with a ball joint, or a wedge compensating for the inclination of the wall 26 relative to the floor 16 along the three directional axes, to facilitate the orientation of the equipment 34 relative to the mounting system 36. The ball joint, or the wedge, is advantageously equipped with a means of locking the orientation of the equipment 34 relative to the mounting system 36, after said orientation has been set by a user, such as the pilot 14.

[0096] Alternatively, the attachment device 50 is a magnetic attachment device to facilitate removable attachment of the equipment 34 relative to the mounting system 36. According to this alternative, the mounting system 36 includes a magnetic closure loop necessary to prevent magnetic leakage and interference with instruments operating using a magnetic field on board the cockpit 12.

[0097] As a further alternative, the attachment device 50 includes a suction cup, clip or screw system such as in [Fig.2] (not visible).

[0098] For simple attachment devices 50 (not allowing, for example, adjustment of the orientation of the equipment 34), image processing software is advantageously included in the equipment 34 in order to compensate for the inclination of the support surface 31 and to obtain an image in a substantially horizontal plane.

[0099] Advantageously, such an attachment device 50 and / or such equipment 34 therefore allows the inclination of the wall 26 to be compensated whether in a direction pointing towards the nose of the aircraft, or in a lateral direction, towards the left and right sides of the pilot 14.

[0100] The attachment device 50 therefore makes it possible to keep the equipment 34 in a stable position inside the cockpit 12.

[0101] In a particular embodiment, the first tack portion 44A comprises a flexible layer 80 applied to at least one surface among a surface external 82 of the first attachment portion 44A and an internal surface 84, opposite the external surface 82, of the first attachment portion 44A.

[0102] For example, the flexible layer 80 is applied to at least a portion of each of the external 82 and internal 84 surfaces, the upper 58, lower 60 branches, and the movable part 62.

[0103] In the embodiment shown in [Fig.3], the flexible layer 80 is for example also applied to the surface of the movable part 62 facing the receiving housing 52 and along the portion of the threaded rod 64 which extends into the receiving housing 52. Thus, the first edge 28 is protected from potentially damaging contact with the movable part 62 and with the threaded rod 64.

[0104] The flexible layer 80 is for example made of an elastomeric or rubbery material chosen from a silicone or silicone foam, an EPDM rubber (ethylene, propylene, diene and monomer), or an EPDM foam.

[0105] The flexible layer 80 is a layer applied, for example by bonding or overmolding, to the surface or surfaces mentioned above, and has, for example, a thickness between 1 mm and 13 mm.

[0106] Such a flexible layer 80 advantageously allows the absorption of vibrations generated by the aircraft 10 for the equipment 34, the limitation of mechanical wear from friction on the mounting system 36 as well as on the wall 26 of the cockpit 12, and the absorption (i.e., compensation) of irregularities in the support surface 31.

[0107] In a particular embodiment, and illustrated in [Fig.2], the wall 26 includes a fixing hole, not shown, and the first part 44 includes a complementary fixing hole 83.

[0108] In particular, the additional orifice or each additional orifice 83 is provided in the flat portion 44B, and allows additional or alternative fixing of the mounting system 36 to the wall 26.

[0109] For example, a fastener, such as a screw, is inserted through the additional hole(s) 83 and the fixing hole(s) of the wall 26, so as to reversibly fix the flat portion 44B on the wall 26.

[0110] In a particular embodiment, not shown, the mounting system 36 includes a second part, separate from the first part 44, configured to hook onto the second edge 30 of the wall 26 of the cockpit 12.

[0111] A device for fixing the second part to the first part is typically provided. The first 44 and second parts are initially (i.e., before assembly) separated from each other, then mechanically connected to each other via the fixing device.

[0112] The fastening device is, for example, a third part distinct from one and / or the other of the first and second parts, or is chosen from the group consisting of: a snap-fit ​​of the second part with the first part 44; a screw-nut assembly connecting the second part to the first part 44; a screw-tap assembly connecting the second part to the first part 44, the tapping being carried out in at least one part between the first part 44 and the second part; a ball joint connection between the first part 44 and the second part.

[0113] Such a configuration allows, for example, the distance between the first and second parts, taken in the plane of the support surface 32, to be modulated so as to adapt the mounting system 36 to the specific geometry of the cockpit 12.

[0114] Moreover, with such a configuration, robust retention of the mounting system 36 to the cockpit 12 is obtained.

[0115] A method of using a mounting system 36 according to the invention will be briefly described below.

[0116] Initially, the mounting system 36 and the equipment 34 are supplied in the cockpit 12.

[0117] The user adjusts the volume of the receiving housing 52 of the mounting system 36 using the adjustment device 54.

[0118] For example, the user moves the movable part 62 away from the upper arm 58 by rotating each wheel 70 around the extension axis A.

[0119] Once the volume of the receiving housing 52 is sufficient to hook the first hook portion 44A to the first edge 28 of the wall 26, the user positions the first piece 44 around the first edge 28.

[0120] The user then adjusts the volume of the receiving housing 52 of the mounting system 36 using the adjustment device 54 so as to tighten the first portion of the hook 44A around the first edge 28.

[0121] For example, the user brings the movable part 62 closer to the upper arm 58 by rotating each wheel 70 around the extension axis A.

[0122] Once the desired pressure is reached, the mounting system 36 is securely fixed to the first edge 28 of the wall 26.

[0123] The user then mounts the equipment 34 onto the mounting system 36 using the attachment device 50.

[0124] Notwithstanding the embodiments and variants described above, the mounting system 36 according to the invention makes it easier and faster to mount the equipment 34 on the wall 26 of the cockpit 12 of the aircraft 10, avoiding the need to drill into the structure of the cockpit 12, in particular avoiding drilling into the wall 26.

[0125] Thanks to its limited number of parts, the mounting system 36 according to the invention is also compact, lightweight, and has a minimal height, measured along the elevation direction Z. Thus, such a mounting system 36 is minimally intrusive in the cockpit 12 and does not obstruct the pilot's 14 field of vision.

[0126] The mounting system 36 according to the invention is also advantageous compared to prior art mounting systems with suction cups, in that it does not require the wall 26 to be particularly clean, unlike a suction cup system which requires the wall 26 to be very clean in order to then ensure good adhesion of the suction cup.

[0127] In addition, the mounting system 36 according to the invention is much more easily and quickly demountable, and then remountable, compared to the wall 26 of the cockpit 12. Such a mounting system 36 is also easily transportable outside the aircraft 10.

[0128] Finally, the mounting system 36 does not have any edge or angle that could damage the aircraft 10 or injure a user and / or is equipped with the soft layer 80 that protects both the aircraft 10, the mounting system 36 and the users.

Claims

Demands

1. Mounting system (36) for equipment (34) on a wall (26) of an aircraft cockpit (12) (10), the mounting system (36) comprising: - a first part (44) having a first attachment portion (44A) to a first edge (28) of the wall (26) of the cockpit (12); and - a device (50) for attaching the equipment (34); characterized in that the first attachment portion (44A) forms a receiving housing (52) of said first edge (28) and the first part (44) has an adjustment device (54) for the volume of said receiving housing (52).

2. Mounting system (36) according to claim 1, wherein the adjustment of the volume of the receiving housing (52) is such that the first hook portion (44A) encloses the first edge (28), the mounting system (36) being fixed to the first edge (28) by the first hook portion (44A).

3. Mounting system (36) according to claim 1 or 2, wherein the first hook portion (44A) comprises a curved fixed part (56) formed by an upper arm (58) and a lower arm (60), and the adjustment device (54) comprises a movable part (62) relative to the fixed part (56), the movable part (62) being configured to move between the upper arm (58) and the lower arm (60).

4. Mounting system (36) according to claim 3, wherein the receiving housing (52) extends between the upper arm (58) and the moving part (62).

5. Mounting system (36) according to claim 3 or 4, wherein the attachment device (50) of the equipment (34) is mechanically coupled to the upper arm (58) of the fixed part (56).

6. A mounting system (36) according to any one of claims 3 to 5, wherein the adjustment device (54) comprises at least one threaded rod (64) extending between a first end (66) and a second end (68), the threaded rod (64) passing through the upper arm (58) and the receiving housing (52), the first end (66) being mechanically coupled to the moving part (62), the second end (68) being capable of being driven in translation along the extension axis (A) of the threaded rod (64) to generate a translation of the movable part (62) between the upper arm (58) and the lower arm (60), along said extension axis (A).

7. Mounting system (36) according to any one of claims 3 to 5, wherein the adjustment device (54) comprises at least one elastic compression element disposed between the upper arm (58) and the movable part (62) and / or an elastic tension element disposed between the lower arm (60) and the movable part (62).

8. Mounting system (36) according to any one of the preceding claims, wherein: - the attachment device (50) includes a means for compensating the inclination of the wall (26), such as a ball joint or a compensating wedge; and / or - the equipment (34) includes a means for compensating the inclination of the wall (26), such as image processing software.

9. Mounting system (36) according to any one of the preceding claims, wherein the first attachment portion (44A) comprises a flexible layer (80) applied to at least one surface among an external surface (82) of the first attachment portion (44A) and an internal surface (84), opposite the external surface (82), of the first attachment portion (44A).

10. Mounting system (36) according to any one of the preceding claims, further comprising - a second part having a second attachment portion to a second edge (30) of the wall (26) of the cockpit (12), the second part being separate from the first part (44), the second edge (30) being separate from the first edge (28), and - a device for attaching the second part to the first part (44).

11. Aircraft cockpit (12) (10), comprising a wall (26), equipment (34) and a mounting system (36) for the equipment (34) on the wall (26), characterized in that the mounting system (36) is according to any one of the preceding claims.

12. Cockpit (12) according to claim 11, wherein the wall (26) comprises at least one fixing hole, the first part (44) of the mounting system (36) comprising at least one hole additional fixing, the mounting system (36) being additionally fixed to the wall (26) via a rod passing through the additional fixing hole(s) and the fixing hole(s).

13. Cockpit (12) according to claim 11 or 12, wherein the equipment (34) is electronic equipment; the electronic equipment preferably being an image sensor(s), the sensor being in particular configured to take at least one image of the face of a pilot (14) of the aircraft (10).

Images