Modular system for mounting equipment on the wall of an aircraft cockpit, associated aircraft cockpit

Abstract

Modular system for mounting equipment on an aircraft cockpit wall, associated aircraft cockpit. The invention relates to a system (36) for mounting equipment (34) on an aircraft cockpit wall, the mounting system (36) comprising: - a first part (44) having a first portion (44A) for attaching to a first edge of the wall; - a device (50) for attaching the equipment (34); The mounting system (36) further comprises: - a second separate part (46) having a second portion (46A) for attaching to a second separate edge of the wall; and - a device (48) for attaching the second part (46) to the first part (44). The attachment device (50) is mechanically coupled to at least one element among the first part (44), the second part (46), and the attachment device (48). Figure for the abstract: Figure 2

Description

Title of the invention: Modular system for mounting equipment on the 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] For mounting such equipment in the aircraft cockpit, it is known to drill 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.

[0005] A support that clips onto a predetermined surface of the cockpit is also known. However, such a support has dimensions specifically adapted for mounting in a predetermined position in the cockpit, and is therefore not adaptable.

[0006] 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.

[0007] 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.

[0008] To this end, the invention relates to a mounting system for equipment on a wall of an aircraft cockpit, the mounting system comprising:

[0009] - a first part comprising a first portion for attaching to a first edge from the cockpit wall; and

[0010] - an equipment attachment device.

[0011] The mounting system further comprises:

[0012] - a second part comprising a second portion for attaching to a second edge of the cockpit wall, the second piece being distinct from the first piece, the second edge being distinct from the first edge; and

[0013] - a device for fixing the second part to the first part.

[0014] The fastening device is mechanically coupled to at least one element among the first part, the second part and the fastening device.

[0015] 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:

[0016] - the fastening device is configured to bring the second part into contact with the first room;

[0017] - the fastening device is chosen from the group consisting of: a snap-on the second part with the first part; a screw-nut assembly connecting the second part to the first part; a screw-tap assembly connecting the second part to the first part, the tapping being carried out in at least one part between the first part and the second part; a ball joint connection between the first part and the second part;

[0018] - the fastening device comprises a third part distinct from the first and second piece, the third piece being mechanically coupled to the first piece and the second piece;

[0019] - the fastening device comprises at least one elastic return element arranged between the first part and the second part and / or between the fastening device and one of the first and second parts;

[0020] - the first part and / or the second part comprises at least two extending arms each between a first end and a second end, each second end forming one of the first attachment portion and the second attachment portion, at least a portion of one of the arms being preferably telescopic, the distance separating the first end from the second end of said arm being adjustable;

[0021] - each first end is coupled to the fastening device; the device of fastening comprising at least one pivot joint; at least one of the arms being rotatable about an axis of the pivot joint relative to the fastening device and / or at least one of the first attachment portion and the second portion the attachment being mobile in rotation relative to the attachment device, around a longitudinal axis perpendicular to the axis of the pivot joint;

[0022] and / or the fastening device comprising at least one ball joint;

[0023] - the first edge is an edge of a sun visor, and the first portion The hook is configured to hook onto the first edge; the first portion of the hook preferably having a curved shape and / or

[0024] the second edge is an edge of a ventilation opening, and the second hook portion is configured to hook said second edge through the ventilation opening; the second hook portion preferably having a curved shape.

[0025] 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.

[0026] 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:

[0027] - the wall includes at least one fixing hole, the first and / or the second part of the mounting system comprising 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);

[0028] - 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

[0029] - 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.

[0030] 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:

[0031] [Fig-1] [Fig.1] is a schematic representation of an aircraft cockpit according to the invention;

[0032] [Fig. 2] [Fig. 2] is a three-dimensional representation of a mounting system for equipment on a cockpit wall according to a first embodiment of the invention, the mounting system comprising a first part having a first portion for attaching to a first edge of the cockpit wall, an equipment attachment device, a second part having a second portion attachment to a second edge of the cockpit wall, and a device for attaching the second piece to the first piece;

[0033] [Fig.3] [Fig.3] is a three-dimensional representation of the mounting system of [Fig.2] mounted on a wall of the cockpit;

[0034] [Fig.4] [Fig.4] is a view analogous to that of [Fig.2] according to a second mode of realization of the invention, the second part of the mounting system comprising two arms forming the second attachment portion;

[0035] [Fig.5] [Fig.5] 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.4];

[0036] [Fig.6] [Fig.6] is a view analogous to that of [Fig.4] according to a variant of the mounting system of [Fig.4], the first part and the second part of the mounting system comprising two arms forming the first attachment portion and the second attachment portion;

[0037] [Fig.7] [Fig.7] is a view analogous to that of [Fig.4] according to a variant of the mounting system of [Fig. 4], the first part and the second part of the mounting system comprising two arms forming the first and second attachment portions; and

[0038] [Fig.8] [Fig.8] is a three-dimensional representation of the mounting systems of figures 6 and 7 mounted on a wall of the cockpit.

[0039] 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%.

[0040] In [Fig. 1], an aircraft 10 includes a cockpit 12 inside which a pilot 14 is installed.

[0041] Herein, aircraft 10 means any airplane or helicopter or any other flying machine that can be piloted by a pilot 14 from that machine.

[0042] 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.

[0043] In the example of [Fig.1], seat 18 is a seat for pilot 14.

[0044] 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.

[0045] Generally, as shown for example in Figures 3 and 8, the cockpit 12 comprises a wall 26 having a first edge 28, a second edge 30 and a support surface 31 extending between the first edge 28 and the second edge 30.

[0046] 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 31 then also extends in this substantially horizontal plane.

[0047] 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.

[0048] 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.

[0049] In a particular embodiment, the first edge 28 is an edge of a projection 32 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 32 then forming a sun visor for the display screen 20.

[0050] The sun visor, for example, has a thickness, taken perpendicular to the horizontal, greater than 5 mm.

[0051] In a particular embodiment, the second edge 30 is for example an edge of a ventilation opening 33, the ventilation opening 33 typically allowing air circulation towards the windshield 22, in particular for defogging the windshield 22.

[0052] Alternatively, the second edge 30 is a completely different type of cavity provided in the bearing surface 31, or a corner or a lip located close to the windshield 22.

[0053] Alternatively or in addition, the second edge 30 corresponds to one or more smooth or tapped holes existing on the bearing surface 31.

[0054] In the example of [Fig.2], the first edge 28 and the second edge 30 extend typically along respective vanishing lines which are intersecting.

[0055] The cockpit 12 further includes equipment 34 and a mounting system 36 for the equipment 34 on the wall 26.

[0056] Equipment 34 is typically electronic equipment.

[0057] The electronic equipment is for example a motion sensor 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).

[0058] Equipment 34, for example, has a mass approximately between 50 g and 700 g.

[0059] Equipment 34, for example, has a volume substantially between 0.04 L and 0.1 L.

[0060] 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.

[0061] 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.

[0062] 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 12.

[0063] According to the invention, the mounting system 36 comprises a first piece 44 configured to hook onto the first edge 28 of the wall 26 of the cockpit, a second piece 46 configured to hook onto the second edge 30 of said wall 26, and a fastening device 48 of the second piece 46 to the first piece 44.

[0064] The second part 46 is distinct from the first part 44. In other words, the first 44 and second 46 parts are initially (i.e. before assembly) separate from each other, then mechanically connected to each other via the fastening device 48.

[0065] Each part 44, 46 is typically a rigid part.

[0066] For example, each part 44, 46 is made of metal, such as an aluminum and / or titanium alloy and / or stainless steel. Alternatively, each part 44, 46 is made of plastic, for example, polyetherimide (PEI). In one particular embodiment, each part 44, 46 is made of a thermoplastic known as "ULTEM" resin (registered trademark), manufactured by SAB IC. Alternatively or in addition, each part 44, 46 is made of a matrix reinforced with reinforcing elements, for example, carbon fibers.

[0067] Each part 44, 46 is for example manufactured by additive manufacturing, for example by a powder laser sintering process (in English Selective Laser Sintering, SLS).

[0068] Each piece 44, 46 for example has a mass approximately between 5 g and 100 g.

[0069] Each piece 44, 46 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.

[0070] The mounting system 36 further comprises a device 50 for attaching the equipment 34, the attachment device 50 being mechanically coupled to an element among the first part 44, the second part 46 and the fastening device 48. In other words, the fastening device 50 is mechanically coupled to the first part 44 or to the second part 46 or to the fastening device 48.

[0071] With reference to figures 2 and 3, the mounting system 36 according to a first embodiment will now be described in detail.

[0072] In this first embodiment, each part 44, 46 comprises a hook portion 44A, 46A configured to hook onto a respective edge 28, 30 of the wall 26, and a substantially flat portion 44B, 46B, referred to as the flat portion, configured to bear against the bearing surface 31 of said wall 26. For the first part 44, the corresponding hook portion 44A is also called the first hook portion 44A, and the corresponding flat portion 44B is also called the first flat portion 44B. Similarly, for the second part 46, the corresponding hook portion 46A is also called the second hook portion 46A, and the corresponding flat portion 46B is also called the second flat portion 46B.

[0073] The first attachment portion 44A is then configured to attach to the first edge 28 of the wall 26 of the cockpit 12, corresponding to the edge of the extension 32 forming the sun visor, and the second attachment portion 46A is configured to attach to the second edge 30 of said wall 26.

[0074] Preferably, each attachment portion 44A, 46A has a limited height, so as to adapt to different aircraft 10 and not to disturb existing elements in the cockpit 12, such as the ventilation system when the second edge 30 is an edge of the ventilation opening 33.

[0075] In the example of figures 2 and 3, the first portion of the hook 44A has a curved shape, preferably downwards and inwards, i.e. downwards and towards the second part 46. In this example, the second portion of the hook 46A has a curved shape, preferably downwards and inwards, i.e. downwards and towards the first part 44.

[0076] In other words, each attachment portion 44A, 46A forms a receiving housing for the first edge 28 and the second edge 30, respectively.

[0077] Each attachment portion 44A, 46A is formed by an upper branch 58, 59 and a lower branch 60, 61.

[0078] In particular, the first portion of the attachment 44A is formed by the upper branch 58 and the lower branch 60.

[0079] Similarly, the second attachment portion 46A is formed by the upper branch 59 and the lower branch 61.

[0080] The upper branches 58, 59 respectively form the planar portions 44B, 46B and are separated from the lower branches 60, 61 along a normal to the plane of the planar portions 44B, 46B. Such a direction normal to the plane of the planar portions 44B, 46B will hereafter be called the "elevation direction" and will bear the reference "Z", as shown in [Fig. 2]. The upper branches 58, 59 and lower branches 60, 61 extending, for example, in a substantially parallel manner to each other.

[0081] The upper branches 58, 59 are intended to extend over part of the bearing surface 31 of the wall 26.

[0082] The lower branches 60, 61 extend opposite at least part of the respective upper branches 58, 59. In the example of [Fig.2], the lower branches 60, 61 have a length strictly less than the length of the respective upper branches 58, 59, but sufficient to hook the first edge 28 and the second edge 30, respectively, of the wall 26.

[0083] Each attachment portion 44A, 46A therefore has substantially a U or C shape.

[0084] Each attachment portion 44A, 46A, when fitted onto the edges 28, 30, then allows the mounting system 36 to be held stably and reversibly on the wall 26 of the cockpit.

[0085] Advantageously, each attachment portion 44A, 46A, and more generally the first part 44 and the second part 46, has a blunt, rounded shape, and does not have any sharp angle or edge that could injure a user or damage the aircraft 10.

[0086] In this first embodiment, the fastening device 48 comprises a third part 65 distinct from the first 44 and second 46 parts, the third part 65 being configured to be coupled to the first part 44 on the one hand and to the second part 46 on the other. The third part 65 then forms a mechanical link between the first 44 and second 46 parts.

[0087] The fastening device 48, by means of the third part 65, is for example configured to put the second part 46 in contact with the first part 44.

[0088] According to this example, the first part 44 and the second part 46 are in contact with each other typically via their respective flat portions 44B, 46B, that is to say that at least a part of the first flat portion 44B is in contact with at least a part of the second flat portion 46B.

[0089] The dimensions of the first 44 and second 46 pieces are thus sufficient to allow an overlap, i.e. a superposition, of one piece with respect to the other, for example of the second piece 46 with respect to the first piece 44, typically an overlap or superposition at least in part of the first flat portion 44B and the second flat portion 46B.

[0090] Advantageously, in order to limit the mass of the mounting system 36, the first and second parts 44, 46 are hollowed out over any part not necessary for support of equipment 34, or to the fixing of the first and second parts 44, 46 to each other, or to the fixing of the first and second attachment portions 44A, 46A to the first and second edges 28, 30 respectively.

[0091] The third part 65 is typically a rigid part.

[0092] In one embodiment, not shown, the third part 65 is, for example, made of metal, such as an aluminum and / or titanium alloy and / or stainless steel. Alternatively, the third part 65 is made of plastic, for example, polyetherimide (PEI). In a particular embodiment, the third part 65 is made of a thermoplastic known as "ULTEM" resin (registered trademark), manufactured by SAB IC. Alternatively or in addition, the third part 65 is made of a matrix reinforced with reinforcing elements, for example, carbon fibers.

[0093] The third part 65 is for example manufactured by additive manufacturing, for example by a powder laser sintering process (in English Selective Laser Sintering, SLS).

[0094] The third part 65, for example, has a mass approximately between 5g and 100g.

[0095] The third part 65 typically has a length between 40 mm and 300 mm, a width between 30 mm and 100 mm, and a height between 1 mm and 50 mm.

[0096] The third part 65 is for example coupled to the first part 44, and respectively to the second part 46, in a manner known per se and as a function of the respective materials of the first 44, second 46 and third 65 parts.

[0097] In the example of figures 2 and 3, the third part 65 is formed of two threaded rods 68 arranged apart from each other according to the width of the first part 44 and joined, by a first end 68A of each threaded rod 68, to the first part 44.

[0098] In other words, each first end 68A of each threaded rod 68 is mechanically coupled, directly, with the first part 44, and in particular with the upper arm 58. For example, each first end 68A of each threaded rod 68 is welded, glued or crimped with the upper arm 58.

[0099] Each threaded rod 68 includes a second end 68B opposite the first end along an extension axis A of the threaded rod 68. For example, only the second end 68B of the rod 68 is threaded.

[0100] The extension axis A is for example substantially parallel to the elevation direction Z when the mounting system 36 is assembled.

[0101] The second end 68B of the threaded rod 68 passes through the upper branch 59 of the second part 46, for example through an orifice 69 provided in the upper branch 59.

[0102] As shown in [Fig. 2], each orifice 69 is an oblong orifice. This feature allows the position of the second part 46 to be adjusted relative to the first part 44 in order to adapt the overall length of the mounting system 36. The mounting system 36 is then easily and quickly adaptable to any type of wall geometry 26.

[0103] The threaded rod 68 is suitable for being driven in translation along the extension axis A in the orifice 69, to clamp the second part 46 onto the first part 44, along the extension axis A.

[0104] For example, the second end 68B of each threaded rod 68 is fitted with a nut, or with a tightening knob 70 screwed onto the second end 68B. Rotation of the tightening knob 70 around the extension axis A causes the second part 46 to be clamped onto the first part 44, along the extension axis A.

[0105] Thus, by a simple and quick-to-use system, a user can reversibly fix the first part 44 with the second part 46.

[0106] Advantageously, each element of the fastening device 48 (threaded rods 68 and knobs 70 in particular) is a non-detachable element of one of the first and second parts 44, 46.

[0107] Thus, the mounting system 36 is easily mounted and dismounted, without risk of losing an element in the cockpit 12 of the aircraft 10.

[0108] Also advantageously, the fastening device 48 is provided with a pair of convex-concave washers 72a, 72b arranged at the junctions between each threaded rod 68 and the first part 44, as well as at the junctions between each threaded rod 68 and the second part 46.

[0109] The convex-concave washers 72a, 72b allow the second piece 46 to be slightly tiltable, around the elevation direction Z, relative to the first piece 44, so as to follow the curve of the bearing surface 31 and / or of the second and / or first piece 44, 46.

[0110] Also advantageously, the fastening device 48 is provided with flat and elastic wavy washers (also called onduflex washer) 73 arranged under each wheel 70, according to the elevation direction Z.

[0111] The flat washers and onduflex 73 allow the knobs 70 (or nuts) to be locked and secured in the tightened position, in order to robustly fix the second part 46 with the first part 44.

[0112] In a variant, not shown, the third part 65 is fixed to the first part 44, and respectively to the second part 46, by snapping.

[0113] As an optional addition, the fastening device 48 includes at least one elastic return element 75 disposed between the first part 44 and the second part 46. In the example of [Fig. 2], the fastening device 48 includes two elastic elements 75 reminders arranged in alignment with the oblong orifices 69 according to the length of the first and second pieces 44, 46.

[0114] This optional addition makes it easier to attach the mounting system 36 to the wall 26 of the cockpit 12, by providing a preliminary mechanical link between the first part 44 and the second part 46, while allowing a separation of the second part 46 from the first part 44 by means of the elastic return element 75, this to facilitate the positioning of the first 44 and second 46 parts with respect to the wall 26.

[0115] In a particular embodiment, each attachment portion 44A, 46A comprises a flexible layer 80 applied to at least one surface among an external surface 82, 83 of the attachment portions 44A, 46A and an internal surface 84, 85, opposite to the respective external surface 82, 83, of the attachment portions 44A, 46A.

[0116] For example, the flexible layer 80 is applied to at least a portion of each of the external surfaces 82, 83 and internal surfaces 84, 85, of the upper branches 58, 59, and lower branches 60, 61.

[0117] 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.

[0118] The flexible layer 80 is a layer applied, for example by gluing, to the surface or surfaces mentioned above, and has, for example, a thickness between 1 mm and 13 mm.

[0119] 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.

[0120] The attachment device 50 is known per se.

[0121] In the example of Figures 2 and 3, the attachment device 50 is mechanically coupled to the first part 44. The attachment device 50 of the equipment 34 is, for example, mechanically coupled to the upper arm 58 of the first part 44.

[0122] 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 first part 44.

[0123] In the example of Figures 4, 6 and 7, the fastening device 50 is advantageously a fastening device with a ball joint, or a wedge for 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 for locking the orientation of the equipment 34 vis-à-vis the mounting system 36, after said orientation has been set by a user, such as the pilot 14.

[0124] 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.

[0125] As a further alternative, the attachment device 50 includes a suction cup, clip or screw system as shown in Figures 2, 3 and 4 (not visible).

[0126] 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.

[0127] 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.

[0128] The attachment device 50 allows the equipment 34 to be held in a stable position inside the cockpit 12.

[0129] Advantageously, a foam or shock-absorbing element, not shown, is provided between the attachment device 50 and the equipment 34.

[0130] As shown in [Fig.2], an attachment element 90 for the cables of the equipment 34, not shown, is advantageously provided on the first or second part 44, 46. Such an attachment element 90 allows the cables of the equipment 34 to be routed to the windshield 22 so that they do not obstruct the visibility of the pilot 14 and do not hinder the pilot 14 in his movements in the cockpit 12.

[0131] With reference to [Fig. 4], a mounting system 36' according to a second embodiment will now be described in detail. Throughout, the mounting system 36' is similar to the mounting system 36 of the first embodiment. Only the features differing from the mounting system 36 of the first embodiment will be described in detail below. Features similar to the mounting system 36 of the first embodiment will bear the same reference numerals.

[0132] A person skilled in the art will understand that any technically feasible combination of the first and second embodiments is covered by the invention.

[0133] In this second embodiment, as seen in [Fig. 4], the second part 46 comprises at least two arms 94, 96, each extending between a first end 94A, 96A and a second end 94B, 96B along a longitudinal direction L1, L2, respective.

[0134] Each arm 94, 96 is for example an elongated cylinder along the corresponding longitudinal direction L1, L2, of circular section.

[0135] Each second end 94B, 96B forms the second attachment portion 46A.

[0136] For example, each second end 94B, 96B includes a hook 99 suitable for hooking the second edge 30 of the wall 26 of the cockpit 12.

[0137] Each hook 99 is advantageously adjustable in length to adapt to the geometry of the wall 26. For example, each hook 99 is telescopic along its extension direction, which is, for example, the elevation direction Z in [Fig. 4]. This feature allows the grip provided by the hooks 99 to be adjusted to the specific thickness of the sun visor.

[0138] In a particular example, at least a portion of one of the arms 94, 96 is telescopic along the corresponding longitudinal direction L1, L2.

[0139] In the example of [Fig.4], each arm 94, 96 is telescopic along the corresponding longitudinal direction L1, L2.

[0140] In other words, the distance separating each first end 94A, 96A from each second end 94B, 96B of the arms 94, 96, along the corresponding longitudinal direction L1, L2, is adjustable.

[0141] Such a feature allows the position of the second part 46 to be adjusted relative to the first part 44 in order to adapt the overall length of the mounting system 36'. The mounting system 36' is then easily and quickly adaptable to any type of wall geometry 26.

[0142] For this purpose, each arm 94, 96 is for example provided with a sliding system with a nut 100 and a lock nut 102, allowing the deployment, according to the corresponding longitudinal direction L1, L2, of at least a portion of the arm 94, 96 relative to the first end 94A, 96A.

[0143] An absorption element 104, such as an O-ring, is optionally provided around the nut 100 and / or the locknut 102 so as to absorb shocks and limit friction between the wall 26 and the arms 94, 96. The absorption element 104 is for example made of silicone or rubber, for example EPDM rubber.

[0144] Furthermore, each arm 94, 96 is for example provided with orifices 110 allowing the attachment of the hooks 99 and for example the insertion of an additional retaining hook, or the insertion of additional equipment to be fixed to the wall 26 via the mounting system 36'.

[0145] Since the orifices 110 are through each arm 94, 96, it is possible to fix the hooks 99 in two positions in opposite directions along the elevation direction Z, as shown in [Fig.8].

[0146] Furthermore, each arm 94, 96 comprises, for example, a plurality of orifices 110 extending perpendicularly between them. For example, each arm 94, 96 comprises, for example, a plurality of orifices 110 passing through in a vertical direction and a plurality of orifices 110 passing through in a horizontal direction.

[0147] Thus, not only is it possible to fix the hooks 99 in two positions in opposite directions along the elevation direction Z, but also in two positions in opposite directions along a direction perpendicular to the elevation direction Z.

[0148] When the second edge 30 consists of one or more smooth or tapped holes present on the bearing surface 31, on a vertical surface or on a surface forming an angle with the bearing surface 31, the orifices 110 can also allow each arm 94, 96 to be fixed to the second edge 30 by cooperation between the orifices 110, the smooth or tapped holes, and a fixing element (such as a screw).

[0149] In the example of [Fig.4], each first end 94A, 96A is coupled to the fastening device 48. The fastening device 48 includes a pivot joint and / or a ball joint 111 mechanically linking each arm 94, 96 to the first part 44.

[0150] Each arm 94, 96 is then rotationally mobile around the first part 44, about three axes perpendicular to each other (the three degrees of freedom being the three possible fundamental rotations of space). In particular, each arm 94, 96 is rotationally mobile relative to the first part 44 about the corresponding longitudinal direction L1, L2.

[0151] This feature allows the hooks 99 to be oriented through 360° in order to adapt the mounting system 36' to all configurations of the wall 26, as shown in figures 6 and 8.

[0152] Furthermore, each arm 94, 96 is, for example, rotationally movable relative to the first part 44 in a plane parallel to the support surface 31. In other words, each arm 94, 96 is, for example, rotationally movable relative to the first part 44 around the elevation direction Z. Thus, the spacing, in the plane of the support surface 31, between each hook 99 is adjustable to adapt the mounting system 36' to the specific configuration of the wall 26 of the cockpit 12.

[0153] This feature also allows the 36' mounting system to be folded by bringing each arm 94, 96 closer together. This makes the 36' mounting system more compact and easier to transport.

[0154] Optionally, as shown in [Fig.4], the first attachment portion 44A forms a receiving housing 112 for the first edge 28 and the first part 44 includes an adjustment device 114 for the volume of the receiving housing 112.

[0155] The adjustment of the volume of the receiving housing 112 by the adjustment device 114 is in particular such that the first portion of the hook 44A encloses the first edge 28 in order to fix the mounting system 36' on the first edge 28 of the cockpit 12.

[0156] For this purpose, the adjustment device 114 includes, for example, a movable part 116 capable of being translated, according to the elevation direction Z, between the upper branch 58 and the lower branch 60.

[0157] The movable part 116 extends for example substantially parallel to the upper branches 58 and lower branches 60, and has for example a length between the length of the upper branch 58 and the lower branch 60.

[0158] The receiving housing 112 of the first edge 28 extends between the upper arm 58 and the movable part 116. The movable part 116 is then intended to come into contact with a lower surface of the wall 26.

[0159] In the particular example of [Fig.4], and shown in more detail in [Fig.5], the adjustment device 114 comprises two threaded rods 120, spaced apart according to the width of the first piece 44, each threaded rod 120 passing through the upper arm 58 and the receiving housing 112.

[0160] Each threaded rod 120 extends between a first end 120A and a second end 120B opposite the first end 120A along an extension axis I of the threaded rod 120. For example, only the second end 120B of the rod 120 is threaded.

[0161] For example, each threaded rod 120 extends between the upper arm 58 and the receiving housing 112 in the elevation direction Z. The extension axis I of the threaded rods 120 and the elevation direction Z are then substantially parallel when the mounting system 36' is assembled.

[0162] The first end 120A of each threaded rod 120 is mechanically coupled to the moving part 116, so that a displacement, along the elevation direction Z, of each threaded rod 120 causes a displacement along the elevation direction Z, of the moving part 116. For example, the first end 120A of each threaded rod 120 is welded, glued or crimped to the moving part 116.

[0163] The second end 120B of each threaded rod 120 passes through the upper branch 58, for example through an opening provided in the upper branch 58.

[0164] The second end 120B of each threaded rod 120 is able to be driven in translation along the extension axis I to generate a translation of the movable part 116 between the upper branch 58 and the lower branch 60, along the extension axis I.

[0165] For example, the second end 120B of each threaded rod 120 is provided with a nut or a tightening knurled knob 122 screwed onto the second end 68B. The rotation of the tightening knurled knob 122 around the extension axis I causes the movable part 116 to translate between the upper arm 58 and the lower arm 60, along the extension axis I.

[0166] Thus, by a simple and quick-to-use system, a user can adjust the volume of the receiving housing 112 in order to reversibly fix 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.

[0167] Advantageously, each second end 120B is provided with flat and onduflex washers 128a, 128b arranged under each wheel 122, along the extension axis I.

[0168] The flat washers 128a below and the onduflex washers 128b above allow the wheels 122 (or nuts) to be locked and secured in the tightened position, in order to keep the moving part 116 at a desired distance from the upper arm 58, and to keep the wheels 122 in position on the threaded rods 120.

[0169] In this embodiment, as shown in [Fig.5], the flexible layer 80 is for example also applied to the surface of the movable part 116 facing the receiving housing 112 and along the portion of the threaded rod 120 which extends into the receiving housing 112. Thus, the first edge 28 is protected from potentially damaging contact with the movable part 116 and with the threaded rod 120.

[0170] Advantageously, a clearance Jl, shown in [Fig. 5], is also present between the threaded rod 120 and the edges of the opening in the upper arm 58. Thus, the threaded rod 120, as well as the movable part 116, can be inclined slightly relative to the elevation direction Z. This feature allows the first gripping portion 44A to conform as closely as possible to 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 incline the movable part 116 relative to the upper arm 58 in order to best grip the wall 26.

[0171] A person skilled in the art will understand that such an adjustment device 114 is of course compatible with the first embodiment as well.

[0172] A variant of the second embodiment, with reference to [Fig.6], will now be described.

[0173] In this variant, the first part 44 also includes at least two arms 130, 132 each extending between a first end 130A, 132A and a second end 130B, 132B in a longitudinal direction L3, L4, respective.

[0174] Each second end 130B, 132B forms the first attachment portion 44A.

[0175] Each arm 130, 132 is, for example, similar to arms 94, 96.

[0176] According to this example, the fastening device 50 is mechanically coupled to the fastening device 48.

[0177] As an optional addition, the mounting system 36' of [Fig. 6] includes at least one elastic element, not shown, disposed between the arms 94, 96 and between the arms 130, 132. For example, the mounting system 36' includes two torsion springs, arranged in the fixing device 48, and generating a restoring force, in the plane of the bearing surface 31, between the arms 94 and 96 and 130 and 132 towards each other.

[0178] This optional addition makes it easier to dismantle and retract for transport the 36' mounting system.

[0179] In an alternative, not shown, the first and / or second part(s) 44, 46 comprise(s) more than two arms 94, 96, 130, 132, angularly distributed around the fastening device 48.

[0180] A variant of the second embodiment, with reference to [Fig.7], will now be described.

[0181] In this variant, the first part 44 and the second part 46 each comprise two arms 140, 141, and 142, 143 extending each between a first end and a second end along the corresponding longitudinal direction L1, L2, L3, L4.

[0182] Each arm 140, 141, 142, 143 is for example an elongated rod along the corresponding longitudinal direction L1, L2, L3, L4, with a rectangular cross-section.

[0183] Each arm 140, 141, 142, 143 is preferably telescopic along the corresponding longitudinal direction L1, L2, L3, L4.

[0184] For this purpose, each arm 140, 141, 142, 143 comprises for example a fixed receiving portion 150 and a mobile sliding portion 152 extending the fixed receiving portion 150 along the corresponding longitudinal direction L1, L2, L3, L4.

[0185] Each fixed receiving portion 150 is hollow and configured to receive at least a part of the respective sliding moving portion 152.

[0186] Each sliding movable portion 152 is movable in translation in the corresponding receiving fixed portion 150 so as to adjust the length of each arm 140, 141, 142, 143 according to the corresponding longitudinal direction L1, L2, L3, L4.

[0187] Each sliding movable portion 152 comprises, for example, a plurality of orifices 158 spaced apart from each other along the corresponding longitudinal direction L1, L2, L3, L4.

[0188] A locking pin 160 is disposed through one of the orifices 158 of each sliding movable portion 152 in order to block any translation of the sliding movable portions 152 relative to the fixed receiving portions 150.

[0189] Each pawl 160 then determines and fixes the length of each arm 140, 141, 142, 143 according to the corresponding longitudinal direction L1, L2, L3, L4.

[0190] Advantageously, each pin 160 does not need to be completely unscrewed from the orifice 158 in order for the sliding movable portions 152 to be translated into the fixed receiving portions 150. Thus, it is not possible to misplace the pawl 160 in the cockpit 12 of the aircraft 10.

[0191] Advantageously, each pin 160 is provided with flat and onduflex washers, not shown, allowing the pin 160 to be locked and braked, in order to ensure that the pin 160 is tightened on the orifice 158.

[0192] Alternatively, each orifice 158 and / or each pin 160 is fitted with a self-locking nut comprising a spring ring disposed inside the thread. Such a nut is known, for example, as a "nylstop" nut (registered trademark).

[0193] The orifices 158 present on the movable sliding portions 152 also serve to fix the hooks 99 forming the first and second hooking portions 44A, 46A.

[0194] Since the orifices 158 are through each sliding movable portion 152, it is possible to fix the hooks 99 in two positions in opposite directions along the elevation direction Z, as shown in [Fig.8].

[0195] This is particularly advantageous when the bearing surface 31 of the wall 26 is not flat but has, for example, two parts facing each other and spaced along the elevation direction Z, as illustrated in [Fig.8].

[0196] In a similar manner to the orifices 110, where the bearing surface 31 includes one or more smooth or tapped holes, the orifices 158 can also allow each arm 141, 142, 143, 144 to be fixed to the bearing surface, by cooperation between the orifices 158, the smooth or tapped holes, and a fixing element (such as a screw).

[0197] The mounting system 36' is then suitable for being fixed on any type of wall geometry 26 of the cockpit 12.

[0198] As an optional addition, the mounting system 36' of [Fig.7] includes at least one elastic return element 170 disposed between the fixing device 48 and one of the pins 160. In the example of [Fig.7], the mounting system 36' includes four elastic return elements 170, each disposed between the fixing device 48 and one of the pins 160.

[0199] As an optional addition, the mounting system 36' of [Fig.7] includes at least one elastic element, not shown, disposed between arms 140 and 141, and / or between arms 142, 143. For example, the mounting system 36' includes two torsion springs, disposed in the fixing device 48, and generating a restoring force, in the plane of the bearing surface 31, between arms 140 and 141 and / or 142 and 143 towards each other.

[0200] These optional additions make it easier to install, remove and retract for transport the 36' mounting system.

[0201] A method of using a mounting system 36, 36' according to the invention will be briefly described below.

[0202] Initially, the mounting system 36, 36' and the equipment 34 are supplied in the cockpit 12.

[0203] The user adjusts the distance between the first and second pieces 44, 46 in order to hook each edge 28, 30 using the respective hook portions 44A, 46A.

[0204] Once the mounting system 36, 36' is positioned on the wall 26, the user fixes the first and second parts 44, 46 together using the fixing device 48.

[0205] After the first and second parts 44, 46 have been fixed together, the mounting system 36, 36' is robustly fixed to the first and second edges 28, 30 of the wall 26.

[0206] The user then mounts the equipment 34 onto the mounting system 36, 36' using the attachment device 50.

[0207] Notwithstanding the embodiments and variants described above, the mounting system 36, 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. Indeed, the mounting system 36, 36' according to the invention uses the shapes and / or holes already existing on the wall 26, for the attachment of the equipment 34.

[0208] Thanks to its limited number of parts and / or non-detachable parts, the mounting system 36, 36' according to the invention is also compact, not very bulky and has a minimum height along the elevation direction Z. Thus, such a mounting system 36, 36' is not very intrusive in the cockpit 12, and does not obstruct the field of vision of the pilot 14, nor does it disturb the existing elements in the cockpit 12, such as the ventilation system.

[0209] The mounting system 36, 36' according to the invention is also more evolutive than prior art mounting systems, and can more easily be fixed in different places of the cockpit 12, by virtue of its first and second parts 44, 46 each hooking to a respective edge 28, 30 of the wall 26, and then by virtue of the fixing device 48 which then allows the second part 46 to be mechanically secured in position relative to the first part 44 taking into account the respective positions of the edges 28, 30 of the wall 26.

[0210] The mounting system 36, 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 good cleanliness of the wall 26, or preparation of the wall 26, or the gluing of an interface pad configured to accommodate the suction cup, to then ensure good adhesion of the suction cup.

[0211] In addition, the mounting system 36, 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, 36' is also easily transportable outside the aircraft 10.

[0212] Finally, the mounting system 36, 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 to protect both the aircraft 10, the mounting system 36, 36' and the users.

Claims

Demands

1. A system (36; 36') for mounting equipment (34) on a wall (26) of an aircraft cockpit (12) (10), the mounting system (36; 36') comprising: - a first part (44) having a first portion (44A) for attaching to a first edge (28) of the cockpit wall (26) (12); - a device (50) for attaching the equipment (34); characterized in that it further comprises: - a second part (46) having a second portion (46A) for attaching to a second edge (30) of the cockpit wall (26) (12), the second part (46) being distinct from the first part (44), the second edge (30) being distinct from the first edge (28); and - a device (48) for attaching the second part (46) to the first part (44); the fastening device (50) being mechanically coupled to at least one element among the first part (44), the second part (46) and the fastening device (48).

2. Mounting system (36; 36') according to claim 1, wherein the fastening device (48) is configured to bring the second part (46) into contact with the first part (44).

3. Mounting system (36; 36') according to claim 2, wherein the fastening device (48) is selected from the group consisting of: a snap-fit ​​of the second part (46) with the first part (44); a screw-nut assembly connecting the second part (46) to the first part (44); a screw-tap assembly connecting the second part (46) to the first part (44), the tapping being carried out in at least one part from the first part (44) and the second part (46); a ball joint (111) between the first part (44) and the second part (46).

4. Mounting system (36; 36') according to claim 1, wherein the fastening device (48) comprises a third part (65) distinct from the first (44) and second (46) parts, the third part (65) being mechanically coupled to the first part (44) and the second part (46).

5. Mounting system (36; 36') according to claim 4, wherein the fastening device (48) comprises at least one elastic return element (75; 170) disposed between the first part (44) and the second part (46) and / or between the fastening device (48) and one of the first part (44) and the second part (46).

6. Mounting system (36; 36') according to any one of the preceding claims, wherein the first part (44) and / or the second part (46) comprises at least two arms (94, 96, 130, 132; 140, 141, 142, 143) each extending between a first end (94A, 96A, 130A, 132A) and a second end (94B, 96B, 130B, 132B), each second end (94B, 96B, 130B, 132B) forming one of the first attachment portion (44A) and the second attachment portion (46A), at least a portion of one of the arms (94, 96, 130, 132; 140, 141, 142, 143) being preferably telescopic, the distance separating the first end (94A, 96A, 130A, 132A) from the second end (94B, 96B, 130B, 132B) of said arm (94, 96, 130, 132; 140, 141, 142, 143) being adjustable.

7. Mounting system (36; 36') according to claim 6, wherein each first end (94A, 96A, 130A, 132A) is coupled to the fastening device (48); the fastening device (48) comprising at least one pivot joint; at least one of the arms (94, 96, 130, 132; 140, 141, 142, 143) being rotatable about an axis of the pivot joint relative to the fastening device (50) and / or at least one of the first hook portion (44A) and the second hook portion (46A) being rotatable relative to the fastening device (50), about a longitudinal axis perpendicular to the axis of the pivot joint; and / or the fastening device (48) comprising at least one ball joint (111).

8. Mounting system (36; 36') according to any one of the preceding claims, wherein: - the first edge (28) is an edge of a sun visor, and the first hook portion (44A) is configured to hook onto the first edge (28); the first hook portion (44A) preferably having a curved shape; and / or - the second edge (30) is an edge of a ventilation opening (33), and the second hook portion (46A) is configured to hook onto said second edge (30) through the ventilation opening (33); the second attachment portion (46A) preferably having a curved shape.

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

10. Cockpit (12) according to claim 9, wherein the wall (26) comprises at least one fixing hole, the first and / or second part (44, 46) of the mounting system (36; 36') comprising at least one additional fixing hole, the mounting system (36; 36') being additionally fixed to the wall (26) via a rod passing through the additional fixing hole(s) and the fixing hole(s).

11. Cockpit (12) according to claim 9 or 10, 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