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公开(公告)号：US11987390B2
公开(公告)日：2024-05-21
申请号：US17165076
申请日：2021-02-02
CPC分类号： B64F5/10 , B64C2001/0045 , B64C1/18
摘要： 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.
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公开(公告)号：US11643223B2
公开(公告)日：2023-05-09
申请号：US17487617
申请日：2021-09-28
发明人： Cédric Godard , Florian Collado , Jacques Bouriquet , Jean-Marc Datas , Nicolas Darbonville , André Aquila
摘要： 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.
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公开(公告)号：US20220097870A1
公开(公告)日：2022-03-31
申请号：US17487617
申请日：2021-09-28
发明人： Cédric Godard , Florian Collado , Jacques Bouriquet , Jean-Marc Datas , Nicolas Darbonville , André Aquila
摘要： 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.
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公开(公告)号：US11091277B1
公开(公告)日：2021-08-17
申请号：US17159685
申请日：2021-01-27
摘要： 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.
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公开(公告)号：US20210061492A1
公开(公告)日：2021-03-04
申请号：US17005898
申请日：2020-08-28
发明人： Patrick Guibert , Jean-Mickael Brindeau , Jacques Bouriquet , Jean-Marc Datas , Thomas Autret , Nicolas Darbonville
摘要： 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.
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公开(公告)号：US11260994B2
公开(公告)日：2022-03-01
申请号：US17005898
申请日：2020-08-28
发明人： Patrick Guibert , Jean-Mickael Brindeau , Jacques Bouriquet , Jean-Marc Datas , Thomas Autret , Nicolas Darbonville
摘要： 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.
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公开(公告)号：US20210237905A1
公开(公告)日：2021-08-05
申请号：US17165076
申请日：2021-02-02
摘要： 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.
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公开(公告)号：US20210229837A1
公开(公告)日：2021-07-29
申请号：US17159685
申请日：2021-01-27
摘要： 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.
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公开(公告)号：US11718417B2
公开(公告)日：2023-08-08
申请号：US17003515
申请日：2020-08-26
发明人： Jean-Marc Datas , Jacques Bouriquet , Jean-Mickael Brindeau , André Aquila , Patrick Guibert , Nicolas Darbonville , Thomas Autret
CPC分类号： B64F5/10 , B25J9/02 , B25J9/10 , B25J15/0052 , B25J15/0616
摘要： 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.
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公开(公告)号：US20210061489A1
公开(公告)日：2021-03-04
申请号：US17003515
申请日：2020-08-26
发明人： Jean-Marc Datas , Jacques Bouriquet , Jean-Mickael Brindeau , André Aquila , Patrick Guibert , Nicolas Darbonville , Thomas Autret
摘要： 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.
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