Aircraft painting device comprising painting booth having reduced cross-section

Abstract

The invention relates to a coating device suitable for coating the fuselage of an aircraft, comprising a coating booth (20) located on a platform (S). The painting booth (20) comprises: at least first and second lateral openings (22.1) configured to allow the aircraft wing (14) to pass through the painting booth (20); and at least two elements (56, 58, 60, 62), at least one of which is movable between a closed state of the painting booth (20) in which the two elements (56, 58, 60, 62) are adjacent and an open state of the painting booth (20) in which the fuselage (12) is located between the two elements (56, 58, 60, 62).

Description

Technical Field

[0001] The application relates to an aircraft painting installation comprising a painting booth with a reduced cross-section. Background Art

[0002] According to one embodiment, an aircraft includes a fuselage, wings disposed on both sides of the fuselage, and a tail located at the tail of the fuselage.

[0003] Once assembled (rigged), the aircraft is positioned in a painting building, which is generally parallelepiped-shaped and sized to accommodate the aircraft to be sanded and then painted. Considering the size of the tail and wings, the ceiling and side walls of the building are far from the fuselage.

[0004] The sanding operation on the aircraft generates fine particles, which are suspended around the aircraft and / or deposited on the surface of the ground, the aircraft and / or the plant. During the painting operation, these fine particles may be re-suspended and deposited on the newly painted surface of the aircraft. In parallel, when the paint spray is applied to the surface of the aircraft, a part of the sprayed paint is not deposited on the surface of the aircraft and a paint cloud is generated. In order to limit the deposition of paint on the walls and ceiling of the paint shop, the paint shop is equipped with at least one ventilation and exhaust system, which includes at least one vent and an exhaust port, the vent is configured to inject an air flow into the paint shop, and the exhaust port is configured to extract the air present in the paint shop. Considering the large size of the paint shop, the ventilation and exhaust system is (high) energy consuming because it needs to handle a large amount of air.

[0005] According to another problem, after the coating is applied (coated or coated), it dries in a drying phase, which requires that the temperature inside the plant be maintained at a given value. This temperature maintenance is energy-intensive, considering the amount of air present in the plant. Summary of the invention

[0006] The object of the present invention is to remedy all or part of the disadvantages of the prior art.

[0007] To this end, the object of the invention is a painting plant suitable for painting the fuselage of an aircraft comprising wings and a tail, each wing forming a given angle with the fuselage, the painting plant comprising a platform.

[0008] According to the present invention, the painting equipment includes a painting booth positioned on a platform, the painting booth including at least: a first and a second lateral opening, the first and the second lateral opening being configured to allow the wings of an aircraft to pass through the painting booth; and at least two elements, at least one of the two elements being movable between an approach position and a separation position, the approach position corresponding to a closed state of the painting booth, in which the two elements are adjacent; the separation position corresponding to an open state of the painting booth, in which the fuselage can be located between the two elements in the separation (spaced apart) position.

[0009] This solution allows obtaining a small cross-section painting cabin adapted to the cross-section of the fuselage, which allows reducing the volume of air to be (needed to be) treated by the ventilation and extraction systems or to be heated to dry the paint. Thus, it is possible to reduce energy consumption and simplify and optimize the management of air characteristics (temperature, humidity, quality, etc.).

[0010] According to another feature, the paint booth has a top opening sized to allow the rear wing to pass through the booth.

[0011] According to another feature, the paint room includes at least a first component and a second component, the first component includes at least a portion of the first side wall and a first portion of the top wall, the second component includes at least a portion of the second side wall and a second portion of the top wall, when the first component and the second component are in an approached position, the first portion and the second portion of the top wall are adjacent, and the first portion and the second portion of the top wall include a cutout so as to form a top opening when the first component and the second component are in an approached position.

[0012] According to another feature, the first component and the second component are movable between an approximated position and a separated position and are symmetrical relative to a vertical mid-plane.

[0013] According to another feature, the painting device includes, for each of the first component and the second component, at least one sliding connection connecting the first component or the second component and the platform and configured to allow the first component or the second component to translate between an approach position and a separation position, each sliding connection forming an angle with the vertical median plane substantially equal to the angle formed between the fuselage and each wing.

[0014] According to another feature, the painting room comprises a first section and a second section, each of the first section and the second section respectively comprising a first end face and a second end face positioned in a transverse plane perpendicular to the vertical middle plane, and at least one of the first and second sections can be moved between a first position in which the first and second transverse faces are pressed against each other and a second position in which the first and second transverse faces are separated.

[0015] According to another feature, the first section is fixed. Furthermore, the second section comprises a first part and a second part movable between a position separated from the vertical median plane and a position close to the vertical median plane.

[0016] According to another feature, the first section comprises first and second lateral openings opening into the first end face.

[0017] According to another feature, the paint booth comprises at least one flexible barrier configured to fill the space between the paint booth and the rear wing and to completely close (block) the top opening.

[0018] According to another feature, for at least one of the first and second lateral openings, the painting booth comprises a respective at least one flexible barrier configured to be able to fill the space between the painting booth and the wing and thus completely close the first or second lateral opening.

[0019] According to another feature, the paint booth comprises a structure configured as a supporting wall and a plurality of longitudinal rails integral with the structure, parallel to one another and configured to allow at least one support to move along a body located in the paint booth by sliding along the rails. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Other features and advantages will become apparent from the following description of the invention, given by way of example and with reference to the accompanying drawings, in which:

[0021] - Figure 1 is a perspective view showing a coating apparatus according to an embodiment of the present invention along a first viewing angle, the coating apparatus comprising a coating room in an open state,

[0022] - Figure 2 yes Figure 1 A perspective view of the coating equipment shown from a second angle,

[0023] - Figure 3 is a perspective view showing the structure of a coating room in an open state according to an embodiment of the present invention,

[0024] - Figure 4 yes Figure 3 A perspective view of the structure of the paint booth in the closed state, visible in

[0025] - Figure 5 is a rear view showing a coating device according to an embodiment of the present invention,

[0026] - Figure 6 is a perspective view showing the structure of a coating equipment according to an embodiment of the present invention,

[0027] - Figure 7 is a perspective view showing a part of the structure of a coating equipment according to an embodiment of the present invention,

[0028] - Figure 8 1 is a perspective view showing a lower portion of a coating apparatus equipped with an air suction unit (air suction port) according to an embodiment of the present invention,

[0029] - Fig. 9 is a side schematic diagram showing a ventilation and exhaust (suction) system of one embodiment of the present invention,

[0030] - Fig.10 is a perspective schematic diagram showing a ventilation and exhaust system according to an embodiment of the present invention,

[0031] - Fig.11 is a perspective view of a portion of a ventilation and exhaust system showing a ventilation and exhaust system of an embodiment of the present invention, the system including a movable exhaust unit which is in a retracted position in part (A) and in an extended position in part (B). DETAILED DESCRIPTION

[0032] according to Figure 1 In the embodiment shown in FIG. 1 , the aircraft 10 comprises a fuselage 12 extending between a nose 12.1 and a tail 12.2, wings 14 extending on either side of the fuselage 12, and a tail 16 positioned at the tail 12.2, the tail comprising a vertical portion 16.1 and horizontal portions 16.2 positioned on either side of the tail 12.2. The aircraft 10 has an aircraft longitudinal axis XX which is horizontal and passes through the nose 12.1 and the tail 12.2 when the aircraft 10 is on the ground.

[0033] The length of the fuselage 12 corresponds to the dimension of the fuselage 12 measured horizontally from the nose 12.1 to the tail 12.2, and the width corresponds to the dimension of the fuselage 12 measured horizontally in a transverse plane perpendicular to the longitudinal axis XX of the aircraft. The fuselage 12 has a front portion 12A located in front of the wings 14 and a rear portion 12B located behind the wings 14. Each wing 14 comprises a trailing edge 14.1 and forms a given angle with the fuselage 12, the angle being measured between the trailing edge 14.1 and the fuselage 12.

[0034] Aircraft 10 includes a propulsion assembly 18 connected to wing 14 and spaced apart from fuselage 12 .

[0035] like Figure 5As shown, a painting device suitable for painting an aircraft 10 includes a painting room 20, which is located on a platform S (such as the ground) inside a factory building, and the platform is configured to allow the aircraft to be painted to be parked, and the painting room 20 includes a first side wall 22 and a second side wall 24 parallel to each other and a top wall 26 away from the platform S, the top wall is substantially parallel to the platform S and connects the first side wall 22 and the second side wall 24. The size of the factory building where the painting room 20 is located is determined to allow the aircraft to enter. The tunnel-shaped painting room 20 separates the internal area between the walls 22, 24, 26 and the platform S from the external area. The painting room 20 extends between a first end 20.1 and a second end 20.2. According to one arrangement, the top wall 26 is substantially horizontal and the first side wall 22 and the second side wall 24 are substantially vertical.

[0036] Of course, the present invention is not limited to painting operations. Thus, the painting device can be used to perform preparatory operations for the painting operation, such as preliminary inspection operations, sanding operations, cleaning operations or masking operations, and / or subsequent operations, such as decorative operations or final inspection operations.

[0037] In addition, the coating equipment may not include a factory building. In this case, the coating room 20 is located on a platform S in the open air (outside the factory building).

[0038] In the remaining description, the longitudinal direction refers to the horizontal direction (substantially parallel to the platform S) and is substantially parallel to the first side wall 22 and the second side wall 24. The vertical middle plane PMV refers to a vertical plane parallel to the longitudinal direction, which is located equidistant from the first side wall 22 and the second side wall 24. The transverse plane is a vertical plane and is perpendicular to the vertical middle plane PMV. The transverse direction is a horizontal direction and is perpendicular to the longitudinal direction.

[0039] The walls 22 , 24 , 26 are rigid and have a length (measured in the longitudinal direction) greater than or equal to the length of the fuselage 12 so that the fuselage 12 of the aircraft can be accommodated in the interior area delimited by the painting booth 20 .

[0040] According to a feature, the first side wall 22 and the second side wall 24 include a first lateral opening 22.1 and a second lateral opening 24.1, which are sized to allow the wing 14 to pass through the first side wall 22 and the second side wall 24, while leaving a small gap around the wing 14. By means of these lateral openings 22.1, 24.1, the first side wall 22 and the second side wall 24 are close to the fuselage 12, which allows to reduce the volume of the interior area in which the fuselage 12 is located. According to one arrangement, the fuselage 12 is substantially centered between the first side wall 22 and the second side wall 24. According to one configuration, the first side wall 22 and the second side wall 24 are spaced apart by a distance between 1.5 and 3 times the width of the fuselage. Typically, each first side wall 22 or second side wall 24 is located between the fuselage 12 and the propulsion assembly 18 closest to the fuselage 12.

[0041] According to an embodiment, for at least one of the first lateral opening 22.1 and the second lateral opening 24.1, the painting booth 20 comprises at least one flexible barrier, such as a curtain, which is integral with the first side wall 22 or the second side wall 24 and is configured to be able to fill the space between the first side wall 22 or the second side wall 24 and the wing 14 and thus completely close the first lateral opening 22.1 or the second lateral opening 24.1. According to one configuration, the painting equipment comprises at least one flexible barrier located at each of the first lateral opening 22.1 and the second lateral opening 24.1.

[0042] according to Figure 4 , the top wall 26 comprises a top opening 26.1, the dimensions of which are determined to allow the empennage 16, and in particular its vertical portion 16.1, to pass through the top wall 26, while leaving a small gap around the empennage 16. By means of this top opening 16.1, the top wall 26 can be close to the fuselage 12, which allows reducing the volume of the interior area in which the fuselage 12 is located. The top wall 26 is spaced from the platform S by a distance between 1.5 and 3 times the height of the fuselage 12 (measured in the vertical direction).

[0043] According to one configuration, the paint booth 20 comprises at least one flexible barrier, for example a curtain, which is integral with the top wall 26 and is configured to be able to fill the space between the top wall 26 and the rear wing 16 and thus completely close the top opening 26 . 1 .

[0044] Of course, the present invention is not limited to these embodiments of the painting booth. For example, the walls 22, 24, 26 may also be non-rigid. Regardless of the embodiment, the painting booth 20 includes at least a first lateral opening 22.1 and a second lateral opening 24.1, which are configured to allow the wing of the aircraft to pass through the painting booth 20. This solution allows a painting booth 20 with a reduced cross-section to be obtained. According to one configuration, the painting booth 20 includes a top opening 26.1, the size of which is determined to allow the tail 16 to pass through the painting booth 20. The painting booth is tunnel-shaped (e.g., formed by walls 22, 24, 26), the length of which is greater than or equal to the length of the fuselage 12 and the width is less than three times the width of the fuselage 12.

[0045] The fact of providing a paint booth 20 with a reduced cross section adapted to the cross section of the fuselage allows reducing the volume of air to be treated by the ventilation and extraction systems and to be (needed to) be heated for drying the paint, which allows reducing the energy consumption for the treatment and drying of the air. Reducing the volume of air in the paint booth 20 also allows facilitating and optimizing the management of the characteristics of the air (temperature, humidity, quality, etc.).

[0046] The painting installation comprises at least one ventilation and exhaust system 28, which comprises at least one ventilation opening 30 configured to inject gas (particularly air) into the painting room 20 and positioned at a first area of ​​the painting room 20, and at least one exhaust opening 32 configured to extract gas (particularly air) present in the painting room 20 and positioned in a second area of ​​the painting room 20 opposite to the first area. According to one arrangement, the ventilation and exhaust system 28 comprises a plurality of ventilation openings 30 regularly distributed between the first end 20.1 and the second end 20.2 of the painting room 20 and / or a plurality of exhaust openings 32 regularly distributed between the first end 20.1 and the second end 20.2 of the painting room 20.

[0047] The ventilation and extraction system 28 may include at least one regulation system that allows control of the flow rate (flow velocity) of the gas leaving the vents 30 and / or entering the extraction vents 32, the temperature and / or humidity of the gas leaving the vents 30, or any other characteristic of the gas leaving the vents 30 and / or entering the extraction vents 32.

[0048] The fact of combining a painting booth 20 of reduced cross-section adapted to the cross-section of the fuselage and a ventilation and extraction system 28 allows to obtain a laminar (undisturbed) flow around the fuselage 12, which avoids the paint particles from remaining in suspension and limits the phenomenon of paint depositing on the walls of the painting booth 20 and the subsequent shedding of particles that could embed themselves in the new paint and reduce the quality of the paint coating.

[0049] Of course, the invention is not limited to air as gas. For example, the gas may be nitrogen or an air mixture enriched with nitrogen to reduce the oxygen concentration. This solution allows to reduce or eliminate the risk of explosion and fire. Furthermore, under these conditions, the application (coating) of the coating is less sensitive to temperature and humidity conditions.

[0050] According to one configuration, the vents and exhaust ports 30, 32 are located at or near the top wall 26 and the platform S. According to one configuration, as Fig. 9 As shown, the ventilation opening 30 is positioned at or near the top wall 26 , and the air extraction opening 32 is positioned at or near the platform S.

[0051] Of course, the present invention is not limited to this arrangement. For example, the ventilation and air extraction ports 30, 32 may be positioned at each end of the fuselage to generate horizontal airflow.

[0052] According to an embodiment, the ventilation and extraction system 28 comprises at least two longitudinal rows R30 of vents 30, symmetrical with respect to a vertical median plane PMV, the two longitudinal rows each extending from a first end 20.1 to a second end 20.2 of the paint booth 20. According to one configuration, the ventilation and extraction system 28 comprises at least one air flow generator 30.1 and for each row R30 of vents 30 comprises at least one ventilation duct 30.2 extending parallel to the vertical median plane PMV and comprising an end connected to the air flow generator 30.1, said ventilation duct 30.2 having a plurality of orifices and / or slots forming the vents 30. Whatever the configuration, the rows R30 of vents 30 are positioned above the fuselage 12, in the top part of the paint booth 20 and as close as possible to the vertical median plane PMV, the rows R30 of vents being spaced apart by a distance less than the width of the fuselage 12. As a variant, the ventilation and extraction system 28 may comprise a plurality of ventilation ducts 30 . 2 connected to the same air flow generator 30 . 1 .

[0053] Of course, the present invention is not limited to this embodiment. Therefore, the ventilation and exhaust system 28 can only include a row of longitudinal vents aligned with the vertical middle plane PMV. As a variation, the ventilation and exhaust system 28 can include two main longitudinal rows of longitudinal vents, which are symmetrical with respect to the vertical middle plane PMV and close to the vertical middle plane, and two secondary longitudinal rows of vents, which are symmetrical with respect to the vertical middle plane PMV and away from the vertical middle plane. Preferably, the two main longitudinal rows of longitudinal vents produce large air flow rates (high air velocity), and the two secondary rows of vents can produce small air flow rates and help reduce the occurrence of vortex flow in the upper corners of the coating room 20.

[0054] According to an embodiment, the ventilation and extraction system 28 comprises at least two longitudinal rows R32 of extraction openings 32, symmetrical with respect to a vertical median plane PMV, the at least two longitudinal rows each extending from a first end 20.1 to a second end 20.2 of the paint booth 20. According to one configuration, the ventilation and extraction system 28 comprises at least one air extractor 32.1 and for each row R32 of the ventilation openings 32 comprises at least one extraction duct 32.2 extending parallel to the vertical median plane PMV and comprising an end connected to the air extractor 32.1, the extraction duct 32.2 having a plurality of orifices and / or slots forming the extraction openings 32. Whatever the configuration, the rows R32 of the extraction openings 32 are positioned below the fuselage 12, in the lower part of the paint booth 20 and as close as possible to the vertical median plane PMV, the rows R32 of the extraction openings 32 being spaced apart by a distance less than the width of the fuselage 12. As a variant, the ventilation and extraction system 28 may comprise a plurality of extraction ducts 32 . 2 connected to the same air extractor 32 . 1 .

[0055] Of course, the present invention is not limited to this embodiment. For example, the ventilation and exhaust system 28 may include only one longitudinal row of exhaust ports aligned with the vertical middle plane PMV or two rows connected to each other in the vertical middle plane. As a variant, the ventilation and exhaust system 28 may include two main longitudinal rows of exhaust ports, which are symmetrical with respect to the vertical middle plane PMV and close to the vertical middle plane, and two secondary longitudinal rows of exhaust ports, which are symmetrical with respect to the vertical middle plane PMV and away from the vertical middle plane.

[0056] According to one configuration, each exhaust duct 32 . 2 is positioned on the platform S. According to this configuration, no infrastructure is integrated into the platform S.

[0057] according to Fig.11 As can be seen in the structure, at least one exhaust duct 32.2 can be moved between a retracted position and an extended position, the retracted position being Fig.11 As can be seen in part (A), in the retracted position, the exhaust duct 32.2 is spaced apart from the vertical middle plane PMV and clears the passage for at least one landing gear of the aircraft 10, and in the deployed position Fig.11 As can be seen in part (B), in the deployed position, the exhaust duct 32.2 is close to the vertical middle plane PMV and is placed on the platform S. According to one construction, the ventilation and exhaust system 28 includes two exhaust ducts 32.2 that are symmetrical relative to the vertical middle plane and movable between the retracted and deployed positions, and the two exhaust ducts 32.2 are connected to each other in the deployed position. This construction allows the exhaust port 32 to be positioned as close as possible to the vertical middle plane PMV when the exhaust duct 32.2 is in the deployed position, while allowing the aircraft 10 to be positioned in the painting room 20 when the exhaust duct 32.2 is in the retracted position. According to one embodiment, the ventilation and exhaust system 28 includes, for each exhaust duct 32.2, a longitudinal support 34 fixed to the platform S and a hinge 36 connecting the longitudinal support 34 and the exhaust duct 32.2.

[0058] According to one embodiment, each extraction duct 32.2 is a rigid tubular duct of square or rectangular cross section. As an example, the hinge 36 includes two connecting rods, each of which has a first end connected to the longitudinal support 34 and a second end connected to the extraction duct 32.2. The ventilation and extraction system 28 may include at least one motorized device to displace each extraction duct 32.2 between the retracted and deployed positions.

[0059] according to Fig.10 In the embodiment visible in the drawing, the ventilation and extraction system 28 comprises at least one end extraction opening 38 at the first end 20.1 of the painting booth 20. According to one arrangement, the ventilation and extraction system 28 comprises at least one row R38 of end extraction openings 38 perpendicular to the vertical midplane PMV and positioned at the first end 20.1 of the painting booth 20.

[0060] according to Fig.10 In the embodiment visible in the drawing, the ventilation and extraction system 28 comprises at least one end extraction opening 40 at the second end 20.2 of the painting booth 20. According to one arrangement, the ventilation and extraction system 28 comprises at least one row R40 of end extraction openings 40 perpendicular to the vertical midplane PMV and positioned at the second end 20.2 of the painting booth 20.

[0061] The fact of positioning the end air extraction openings 38 , 40 at the first end 20 . 1 and the second end 20 . 2 of the painting booth 20 allows preventing the occurrence of (vortex) vortices due to the conical shape of the nose 12 . 1 and the tail 12 . 2 of the fuselage 12 .

[0062] The paint booth 20 includes at least one structure 42 ( Figure 3 and Figure 4 According to an embodiment, the structure 42 comprises frames 42.1 positioned in a transverse plane and longitudinal beams 42.2 connecting the frames 42.1 to each other and oriented parallel to the longitudinal direction. Of course, the invention is not limited to this configuration of the structure 42.

[0063] According to one embodiment, the painting booth 20 comprises a plurality of longitudinal rails 44 integral with the structure 42, parallel to each other and to the longitudinal direction, positioned on either side of the vertical median plane PMV. Figure 5 As can be seen in the arrangement shown in FIG. 4 , the structure 42 comprises, on both sides of the vertical median plane PMV, a plurality of longitudinal rails 44, 44' offset in height. As an example, the structure 42 comprises two longitudinal rails 44, 44' located on each side of the vertical median plane PMV. According to one configuration, each longitudinal rail 44, 44' comprises two longitudinal rails 44.1, 44.2, 44.1', 44.2' offset in height.

[0064] Each rail 44, 44' is configured to allow at least one support member, such as a pod 46 ( Figure 7 ) or cart 48 (chariot or trolley) ( Figure 8 ), by sliding along the guide rails 44, 44' and displacing along the body 12 positioned in the coating room 20. Figure 7 As can be seen in the arrangement, the pod 46 may be connected to the track 44 by at least one telescopic connection 50 that is configured to displace the pod 46 in a lateral direction relative to the rails 44, 44'.

[0065] Each guide rail 44, 44' may include a plurality of sections arranged end to end.

[0066] The paint booth 20 may include corridors 52 at multiple levels configured to allow operators to move around the fuselage 12 , and stairs and / or elevators 54 to facilitate movement of operators from one corridor 52 to another.

[0067] According to one embodiment, the coating room 20 includes at least a first component 56 and a second component 58, which respectively include at least a portion of the first side wall 22 and the second side wall 24. At least one of the first component 56 and the second component 58 can be configured as follows: Figures 1 to 3 The separated position shown corresponds to the open state of the coating room 20 and Figure 4 and Figure 5 The movement between the illustrated approach position corresponds to the closed state of the paint booth 20 , and in the separated position the fuselage of the aircraft can be positioned between the first component 56 and the second component 58 .

[0068] The first component 56 includes at least a portion of the first side wall 22 and a first portion of the top wall 26. The second component 58 includes at least a portion of the second side wall 24 and a second portion of the top wall 26. When the first component 56 and the second component 58 are close and the coating room 20 is in a closed state, the first portion and the second portion of the side wall are aligned along the joint plane PJ ( Figure 5 ) adjacent.

[0069] According to one configuration, the first component 56 and the second component 58 are substantially symmetrical with respect to the vertical median plane PMV. In this case, when the first component 56 and the second component 58 are close, the joint plane PJ coincides with the vertical median plane PMV. According to this configuration, the first and second portions of the top wall 26 include cutouts 26.2, 26.3, thereby forming a top opening 26.1 when the first component 56 and the second component 58 are close (they are moved together).

[0070] According to one embodiment, the first member 56 and the second member 58 are movable between open and closed conditions.

[0071] According to one embodiment, the painting device comprises, for each of the first component 56 and the second component 58, at least one sliding connection 56.1, 58.1 connecting the first component 56 or the second component 58 and the platform S, which is configured to allow the first component 56 or the second component 58 to translate between an open state and a closed state.

[0072] In operation, when the fuselage 12 of the aircraft 10 to be painted is positioned in the painting booth 20, the longitudinal axis XX of the aircraft is substantially located in the vertical median plane PMV. In order to reduce the size of the lateral openings 22.1, 24.1, each sliding connection 56.1, 58.1 forms with the vertical median plane PMV an angle substantially equal to that formed between the fuselage 12 and each wing 14. According to one embodiment, each sliding connection 56.1, 58.1 comprises a plurality of tracks parallel to each other, which form substantially equal angles formed between the fuselage 12 and the corresponding wing 14. Thus, when the aircraft is positioned for painting, the track associated with the first part 56 or the second part 58 is substantially parallel to the trailing edge 14.1 of the wing 14 cooperating with the corresponding first part 56 or second part 58.

[0073] According to one configuration, the painting device comprises, for each of the first component 56 and the second component 58 , at least one motorized device for displacing the first component 56 and the second component 58 .

[0074] according to Figures 1 to 4 In the illustrated embodiment, the painting room 20 includes a first section 60 configured to accommodate the front part 12A and a second section 62 configured to accommodate the rear part 12B. The first section 60 and the second section 62 respectively include a first end face 60.1 and a second end face 62.1 positioned in a transverse plane. At least one of the first section 60 and the second section 62 can be moved between a first position and a second position, the first position corresponding to the closed state of the painting room 20, in which the first transverse end face 60.1 and the second transverse end face 62.1 are pressed against each other, and the second position corresponds to the open state of the painting room 20, in which the first and second transverse end faces 60.1, 62.2 are separated.

[0075] According to one configuration, the first section 60 is fixed. In addition, the second section 62 includes a first component 56 and a second component 58, which can be in a separated position relative to the vertical middle plane (corresponding to the open state of the painting room 20, such as Figures 1 to 3 ) and the close position with the vertical middle plane (corresponding to the closed state of the coating room 20, as shown Figure 4 This construction allows limiting the size of the moving parts and their travel.

[0076] According to one configuration, the first section 60 comprises lateral openings 22.1, 24.1 which open into the first end face 60.1. As a variant, the lateral openings 22.1, 24.1 are located on the second section 62 or straddle the first section 60 and the second section 62.

[0077] According to one operating mode, in a first phase, the fuselage 12 of the aircraft 10 is painted, followed by the painting of the wings 14 and the empennage 16 in a second phase.

[0078] like Figure 1 As shown, when the first part 56 and the second part 58 of the second section 62 are in the separated position, the aircraft 10 to be painted is displaced to introduce its front part 12A into the first section 60, as shown in FIG. Figure 2 and Figure 3 Then, the first and second components 56 and 58 are moved to close the coating chamber 20, as shown. Figure 4 and 5 shown.

[0079] Of course, the present invention is not limited to Figures 1 to 5 Embodiments of the painting booth 20 described. Other solutions can also be considered to obtain a painting booth 20 of small dimensions, which allow the fuselage 12 to be painted to be confined in a reduced volume. For example, the first part 56 and the second part 58 can extend from the first end 20.1 of the painting booth to the second end 20.2. Whatever the embodiment, the painting booth 20 comprises at least two elements, namely the first part 56 and the second part 58 and / or the first section 60 and the second section 62; at least one of the two elements can be moved between an approach position and a separation position, the separation position corresponding to the closed state of the painting booth 20, in which the two elements are adjacent; the approach position corresponds to the open state of the painting booth 20, in which the aircraft fuselage can be positioned between the two elements.

Claims

1. A painting device, the painting device being suitable for painting a fuselage (12) of an aircraft, the aircraft comprising wings (14) and a tail (16), each wing (14) forming a given angle with the fuselage (12), the painting device comprising a platform (S); It is characterized in that The painting equipment comprises a painting booth (20), which is positioned on the platform (S) and comprises at least a first lateral opening (22.1) and a second lateral opening (24.1) configured to allow the wing (14) of the aircraft to pass through the painting booth (20) and at least two elements (56, 58, 60, 62), at least one of the two elements (56, 58, 60, 62) being movable between an approach position corresponding to a closed state of the painting booth (20) and a separation position corresponding to an open state of the painting booth (20), wherein in the approach position the two elements (56, 58, 60, 62) are adjacent, and in the separation position the fuselage (12) is positionable between the two elements (56, 58, 60, 62).

2. The coating equipment according to claim 1, characterized in that: The painting booth (20) comprises a top opening (26.1) which is dimensioned to allow the fin (16) to pass through the painting booth (20).

3. The coating equipment according to claim 2, characterized in that: The coating room (20) comprises at least a first component (56) and a second component (58), wherein the first component (56) comprises at least a portion of a first side wall (22) and a first portion of a top wall (26), and the second component (58) comprises at least a portion of a second side wall (24) and a second portion of the top wall (26), wherein when the first component (56) and the second component (58) are in the close position, the first portion and the second portion of the top wall (26) are adjacent to each other, and the first portion and the second portion of the top wall (26) comprise cutouts (26.2, 26.3), thereby forming the top opening (26.1) when the first component (56) and the second component (58) are in the close position.

4. The coating arrangement according to claim 3, characterized in that: The first component (56) and the second component (58) are movable between the approximated position and the separated position and are symmetrical with respect to a vertical median plane (PMV).

5. The coating equipment according to claim 4, characterized in that: The painting equipment comprises, for each of the first component (56) and the second component (58), at least one sliding connection (56.1, 58.1), respectively, wherein the sliding connection (56.1, 58.1) connects the first component (56) or the second component (58) to the platform (S) and is configured to allow the first component (56) or the second component (58) to translate between the approach position and the separation position, each sliding connection (56.1, 58.1) forming an angle with the vertical middle plane (PMV) that is substantially equal to the angle formed by the fuselage (12) and each wing (14).

6. The coating equipment according to claim 4 or 5, characterized in that: The coating room (20) comprises a first section (60) and a second section (62) respectively having a first end face (60.1) and a second end face (62.1), wherein the first end face (60.1) and the second end face (62.1) are positioned in a transverse plane perpendicular to the vertical middle plane (PMV), and at least one of the first section (60) and the second section (62) is movable between a first position and a second position, wherein in the first position, the first transverse face (60.1) and the second transverse face (62.1) are pressed against each other, and in the second position, the first transverse face (60.1) and the second transverse face (62.1) are separated.

7. The coating equipment according to claim 6, characterized in that: The first section (60) is fixed and the second section (62) includes a first component (56) and a second component (58) which are movable between a position spaced apart from the vertical median plane (PMV) and a position close to the vertical median plane (PMV).

8. The coating equipment according to claim 7, characterized in that: The first section (60) comprises a first lateral opening (22.1) and a second lateral opening (24.1) leading to a first end surface (60.1).

9. The coating equipment according to any one of claims 2 to 8, characterized in that: The painting booth (20) comprises at least one flexible barrier, which is configured to fill the space between the painting booth (20) and the rear wing (16) and thereby completely close the top opening (26.1).

10. A coating plant according to any one of the preceding claims, characterised in that For at least one of the first lateral opening (22.1) and the second lateral opening (24.1), the painting booth (20) comprises at least one corresponding flexible barrier, the flexible barrier being configured to fill the space between the painting booth (20) and the wing (14) and thereby completely close the first lateral opening (22.1) or the second lateral opening (24.1).

11. The coating equipment according to any one of claims 3 to 8, characterized in that: The paint booth (20) comprises a structure (42) configured to support a plurality of walls (22, 24, 26) and a plurality of longitudinal guide rails (44) integral with the structure (42), the longitudinal guide rails (44) being parallel to each other and configured to allow at least one support member to move along the fuselage (12) located in the paint booth (20) by sliding along the guide rails (44, 44').

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