Abstract: A referential positioning device configured to position relative to each other at least one cabin floor grid and one side shell of an aircraft in order to assemble a fuselage barrel of the aircraft is disclosed having at least one fixing support for fixing the referential positioning device to the top of an alignment post of an assembly platform, and a partially spherical support having a spherical surface (S) intended to receive the V-shaped surface of an end of an arm of a transport system for a cabin floor grid of an aircraft. The referential positioning device makes it possible to arrange the cabin floor grid precisely on the assembly platform with respect to the other elements of the fuselage barrel.

Abstract: An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.

Abstract: To make an aircraft assembly installation modulable, the latter includes a floor, assembly stations distributed on the floor, and structures for accessing the aircraft during their assembly, each structure being mobile on the ground. The access structures include at least one access structure at an orbital junction between two fuselage sections, at least one access structure at the two junctions between a fuselage section and each of the two aircraft wings, and at least one access structure at the junctions between a rear fuselage section and tail units. In addition, the installation is designed to be able to adopt several distinct configurations, each having a different distribution of the access structures between the assembly stations.

Abstract: A gripping device for a panel of a section of a fuselage of an aircraft, the panel including a skin and having an arcuate shape about a longitudinal axis X. The gripping device includes two gripping subsystems arranged at a distance from one another parallel to the longitudinal axis X, and each gripping subsystem includes a central element fastened to the panel, and two lateral elements fastened on either side of the central element by fasteners, and each lateral element includes pressurizers which come against the skin to apply a tension thereto in the opening direction of the arcuate shape. Such a gripping device makes it possible to ensure the shape of the panel when it is transported and until it is fastened to other panels in order to produce the section of the fuselage.

Abstract: A facility for simplifying the facilities and tools required to assemble a first aircraft fuselage section and a second aircraft fuselage section by the ends thereof, these sections being fragile, large elements. The facility includes a logistics trolley that can be moved on the floor and immobilized in a position to carry the first section, at least one adjustable support installed on the floor at another position that is adjustable with six degrees of freedom, to carry the second section. Each support can be commanded to adjust the position of the second section in relation to the first section, such as to position one end of the second section in geometric conformity with one end of the first section. This arrangement enables all movements to be made directly on the floor, obviating the need to provide lifting machines or overhead traveling cranes within the assembly facility.

Abstract: A transport carriage for wings that are secured together, wherein the transport carriage comprises a chassis mounted on wheels, cradles mounted on positioning cylinders, support cylinders that each have a support mounted on the stem of the support cylinder, a central support having a frame and, for each wing, a rotatable lateral cradle, wherein the frame is movable vertically, for each wing, a lifting system with a mast and an arm, wherein each arm is movable vertically on the mast between a low position and a high position, and for each arm, at least two bearing points for the wing. The use of different movable elements allows good loading of the wings and makes it easier to move the wings thus loaded.

Abstract: A transport trolley for transporting a load comprising a base mounted on motorized wheels, a deck mounted to be translationally mobile on the base in a direction of translation, a first motorized system displacing the deck, a hexapod platform comprising a platform and a set of six jacks in which each is mounted articulated between the deck and the platform. The platform comprises a plurality of bearing points configured to come under the load and each bearing point takes the form of a receptacle with its opening oriented upwards. A control unit controls each motorized wheel, the first motorized system and each jack. The use of a hexapod platform makes it possible to finely position the wing at its position of fixing onto the fuselage and the use of a mobile deck supporting the hexapod platform allows for adjustability of the position despite a smaller footprint around the aircraft.

Abstract: A carriage with two hexapod platforms, each having a base, a plate, and a set of six cylinders associated in pairs. Each cylinder is articulatedly mounted with the plate. For each pair, a slider is able to move in translation on the base. For a first pair, the two cylinders of the first pair are mounted in an articulated manner on the slider. The articulation of one of the two cylinders of the first pair with the plate is adjacent to the articulation of one of the two cylinders of a second pair with the plate. The articulation of the other of the two cylinders of the first pair with the plate is adjacent to the articulation of one of the two cylinders of a third pair with the plate. For each slider, a movement system moves the slider. A control unit controls each cylinder and the movement system.

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

Abstract: A facility for simplifying the facilities and tools required to assemble a first aircraft fuselage section and a second aircraft fuselage section by the ends thereof, these sections being fragile, large elements. The facility includes a logistics trolley that can be moved on the floor and immobilized in a position to carry the first section, at least one adjustable support installed on the floor at another position that is adjustable with six degrees of freedom, to carry the second section. Each support can be commanded to adjust the position of the second section in relation to the first section, such as to position one end of the second section in geometric conformity with one end of the first section. This arrangement enables all movements to be made directly on the floor, obviating the need to provide lifting machines or overhead traveling cranes within the assembly facility.

Abstract: A method for assembling a fuselage section which comprises producing a lower part of the section from at least two panels and an upper part of the section from at least two panels, then assembling the lower and upper parts so as to obtain the fuselage section. A lower or upper mounting support, a gear and a production unit are used in the method.

Abstract: An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.

Abstract: An assembly of a central aircraft fuselage section includes a longitudinal master wall for fixing of two aircraft air foil boxes. The method includes providing a trolley that can be moved on the ground, including a supporting structure in a station, supplying the station with the master wall, installing and mechanically immobilizing the master wall at a reference position on the supporting structure of the trolley, supplying the station with a transverse wall, installing and mechanically immobilizing this transverse wall at a reference position situated at a rectilinear edge upstream or downstream of the master wall, fixing the transverse wall to the master wall, and moving the trolley to another station.

Abstract: To make an aircraft assembly installation modulable, the latter includes a floor, assembly stations distributed on the floor, and structures for accessing the aircraft during their assembly, each structure being mobile on the ground. The access structures include at least one access structure at an orbital junction between two fuselage sections, at least one access structure at the two junctions between a fuselage section and each of the two aircraft wings, and at least one access structure at the junctions between a rear fuselage section and tail units. In addition, the installation is designed to be able to adopt several distinct configurations, each having a different distribution of the access structures between the assembly stations.

Abstract: An assembly of a central aircraft fuselage section includes a longitudinal master wall for fixing of two aircraft air foil boxes. The method includes providing a trolley that can be moved on the ground, including a supporting structure in a station, supplying the station with the master wall, installing and mechanically immobilizing the master wall at a reference position on the supporting structure of the trolley, supplying the station with a transverse wall, installing and mechanically immobilizing this transverse wall at a reference position situated at a rectilinear edge upstream or downstream of the master wall, fixing the transverse wall to the master wall, and moving the trolley to another station.

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

Abstract: A gripping device for a panel of a section of a fuselage of an aircraft, the panel including a skin and having an arcuate shape about a longitudinal axis X. The gripping device includes two gripping subsystems arranged at a distance from one another parallel to the longitudinal axis X, and each gripping subsystem includes a central element fastened to the panel, and two lateral elements fastened on either side of the central element by fasteners, and each lateral element includes pressurizers which come against the skin to apply a tension thereto in the opening direction of the arcuate shape. Such a gripping device makes it possible to ensure the shape of the panel when it is transported and until it is fastened to other panels in order to produce the section of the fuselage.

Abstract: An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.

Abstract: A slinging device for a piece includes a sling with a nonextensible part and a section with a spring device, enabling an elastic lengthening or shortening of the sling under load by a limited amplitude in response to a limited change in the load on the piece, the device including a frame and a floating support, the spring device holding the floating support in the absence of application of force to the piece along a vertical axis, in a position of equilibrium centered vertically with respect to the frame under the weight of the piece, and a way for regulating and adapting the position of equilibrium of the floating support depending on the weight of the piece.

Abstract: A sling device for a piece, including a sling provided with a non-extending piece and a section with spring means permitting an elastic lengthening or shortening under load of a limited given amplitude for the sling in response to a limited given change in load on the piece.