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公开(公告)号：US20240242335A1
公开(公告)日：2024-07-18
申请号：US18407079
申请日：2024-01-08
发明人： Loïc MEIFFRE , Thomas BAIZEAU , Sagar APSHANKAR
CPC分类号： G06T7/001 , B21D53/78 , G06T2207/20081 , G06T2207/30164
摘要： A process for shaping a part (12) of the turbine vane type, includes providing a part (12) comprising a blade (14) in an initial shape, providing a nominal definition representing the part in a nominal shape, comparing the initial shape with the nominal definition to determine compliance or non-compliance, for a non-compliant datum, determining a force to be applied to the part to deform said part, applying a force to obtain the part in a deformed shape, comparing the deformed shape with the nominal definition to determine compliance or non-compliance, and training a self-learning algorithm (82).
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公开(公告)号：US11999031B2
公开(公告)日：2024-06-04
申请号：US16649138
申请日：2018-09-21
申请人： LISI AEROSPACE
发明人： Steven Palette , Julien Brachet , Vincent Defrance
CPC分类号： B25B13/488 , B25B23/0085 , B25B31/005 , F16B19/109
摘要： The present invention concerns a fastening socket (112) for assembling at least two previously drilled structures, said socket comprising a substantially cylindrical body (34) and an enlarged head (35); said enlarged head comprising first mounting surfaces (42, 46) suitable for being assembled to a first installation component and for preventing said first installation component from rotating about the main axis. The socket comprises a first substantially cylindrical recess (40) extending along the main axis from the first end, said first recess ending at a planar shoulder (44) substantially perpendicular to said main axis, the first recess and the planar shoulder being received inside the enlarged head, the first mounting surfaces (42, 46) being formed by an inner surface of the first recess.
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公开(公告)号：US11384575B2
公开(公告)日：2022-07-12
申请号：US16032516
申请日：2018-07-11
申请人： LISI AEROSPACE
发明人： Bastien Bellavia , Boris Hummel
摘要： The invention involves a keeper (20) to interact with a bolt (16) of a lock (10);
The keeper includes a bracket (22) for attachment to a structure, and a keeper rod (24) secured to the bracket, the keeper rod extending from one surface (27) of the bracket.
In the keeper, a shaft (32) is attached to the bracket and can rotate freely relative to the bracket such that it extends in a longitudinal direction (X); a blade (40) is mounted on the shaft (32) on one side of the bracket near the keeper rod in such a way as to always rotate along with the shaft; an angular position indicator (46) is also mounted so as to always rotate along with the shaft; the blade being so positioned that it can be rotated by the latch when the latch hooks on to or releases from the keeper rod, and the angular position indicator (46) being capable of indicating the angular position of the blade.
The invention is for example intended to be used on an aircraft door such as that of a helicopter.-
公开(公告)号：US20210025424A1
公开(公告)日：2021-01-28
申请号：US17045957
申请日：2019-04-17
申请人： LISI AEROSPACE
发明人： JULIEN BRACHET
摘要： The present invention concerns a fastener (110) for the temporary assembly of at least two previously drilled structures (112) comprising: a hollow body (122) comprising a bearing surface (40); elastic clips (24) which are movable relative to the body and which form a projection relative to the bearing surface; a spacer (26) around which the elastic clips are positioned; a connecting element (130), extending within the body and secured to the elastic clips (24); and an actuating element (132) linked to connecting element by a thread/tapping (67, 84). The connecting element is traversed by a lateral opening (70) axially extended between two closed ends (72, 74); and the fastener also comprises a transverse stop (28) secured to the spacer, the said stop being capable of sliding between the axial ends of the said lateral opening.
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公开(公告)号：US20200248737A1
公开(公告)日：2020-08-06
申请号：US16622940
申请日：2018-06-14
申请人： LISI AEROSPACE
发明人： Loïc MEIFFRE
摘要： The invention relates to a positive locking fastener comprising: a screw (1), a threaded portion (11) of which has a blind hole (110) and a groove (111); a nut (2) having a tightening portion (21); a cap (3); and a pin (4). The cap (3) has an immobilizing portion (31) intended to engage with the tightening portion (21) and a locking portion (32) intended to cooperate with the blind hole (110) to prevent said cap from rotating relative to the screw (1). The locking portion (32) also comprises openings (322) suitable for allowing the pin (4) to be inserted into said openings and into the groove (111) in order to hold the screw (1) and the cap (3) together.
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公开(公告)号：US10520005B2
公开(公告)日：2019-12-31
申请号：US14910671
申请日：2014-08-01
申请人： LISI AEROSPACE
发明人： Florent Verdier
摘要： A cage nut and a method of installing a cage nut include a nut with a tubular body and a flange, and a nut support having a nut cage for receiving the nut. The nut support includes a tubular portion wherein an external surface of the tubular portion includes longitudinal splines having a diameter smaller than a diameter of a bore of a workpiece, and at least two longitudinal ribs having a diameter greater than the diameter of the bore.
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7.发明申请公开(公告)号：US20190195268A1
公开(公告)日：2019-06-27
申请号：US16273558
申请日：2019-02-12
申请人： LISI AEROSPACE
发明人： Alexandre Berthou , Florent VERDIER , Charles PHAM
摘要： The invention relates to a fastener for assembling at least two structural elements, comprising a aperture, the fastener comprising an enlarged head (12) and a shank (14) exhibiting, prior to fitting, an outside diameter (D1) greater than an inside diameter (DS) of the aperture, and a locking portion comprising a screw thread or annular grooves. The fastener further comprises a lubricating sacrificial ring (40) on the exterior surface of the fastener, extending at least between a distal end of the shank and a proximal end of the locking portion, said ring having, before the fastener is fitted into the structure, an outside diameter greater than a diameter of the aperture. The sacrificial ring comprises a polymer resin forming a matrix encapsulating dispersant molecules and oil molecules.The invention applies to the assembly of aircraft structures.
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公开(公告)号：US20190186522A1
公开(公告)日：2019-06-20
申请号：US16307131
申请日：2017-07-03
申请人： LISI AEROSPACE
发明人： Guy Pailhories , Olivier Gay
CPC分类号： F16B19/1072 , B21J15/045 , F16B19/1054
摘要： A rivet may include a pin comprising: a threaded portion (36), a shank (38) and a head (40); and a bushing (32) comprising an essentially cylindrical body, said body comprising a deformation zone designed to form an external bulge (80); a collar (70) designed to receive the head of the pin; and a tapped portion (66) designed to engage with the threaded portion of the pin. The shank (38) of the pin comprises a first cylindrical portion (44) and a second cylindrical portion (46) connected by a shoulder (48), the first portion being adjacent to the head and having a first diameter, the second portion being adjacent to the threaded portion and having a second, smaller diameter.
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公开(公告)号：US20190017304A1
公开(公告)日：2019-01-17
申请号：US16032516
申请日：2018-07-11
申请人： LISI AEROSPACE
发明人： Bastien Bellavia , Boris Hummel
摘要： The invention involves a keeper (20) to interact with a bolt (16) of a lock (10);The keeper includes a bracket (22) for attachment to a structure, and a keeper rod (24) secured to the bracket, the keeper rod extending from one surface (27) of the bracket.In the keeper, a shaft (32) is attached to the bracket and can rotate freely relative to the bracket such that it extends in a longitudinal direction (X); a blade (40) is mounted on the shaft (32) on one side of the bracket near the keeper rod in such a way as to always rotate along with the shaft; an angular position indicator (46) is also mounted so as to always rotate along with the shaft; the blade being so positioned that it can be rotated by the latch when the latch hooks on to or releases from the keeper rod, and the angular position indicator (46) being capable of indicating the angular position of the blade.The invention is for example intended to be used on an aircraft door such as that of a helicopter.
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公开(公告)号：US20180238372A1
公开(公告)日：2018-08-23
申请号：US15735180
申请日：2016-06-10
申请人： LISI AEROSPACE
发明人： Antoine Villet , Nicolas Naretto , Olivier Gay , Guy Pailhories
IPC分类号： F16B19/10
摘要： The invention concerns a fastener used to attach structural components that have aligned perforations with a nominal diameter (D), where the fastener comprises a minimum grip plane (Gmin) and a maximum grip plane (Gmax), and A screw (12) comprising an enlarged head and a threaded portion (22); A sleeve (30) comprising an enlarged head, a cylindrical tubular body and a tapped portion (36) that engages the threaded portion (22) of the screw, where the tapped portion (36) is adjacent to an internally smooth portion of the body (34) of the sleeve. This smooth portion has a thickness (E), a non-deformable area (A) adjacent to the head of the sleeve and a deformable area (B) adjacent the non-deformable area (A). The sleeve's deformable area (B) can be deformed into a bulb (48) intended to come into contact with a blind side (46) of the structural components. The deformable area (B) extends over a length (L) greater than a minimum length (Lmin) and less than a maximum length (Lmax), such as: Lmin=D/2+2E+(Gmax−Gmin); Lmax=(E/0.092) In particular, the invention applies to the assembly of aircraft structures.
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