EP4140615A1 - Procédé d'installation d'un élément de fixation aveugle et utilisation de passage longitudinal de manchon d'un élément de fixation aveugle - Google Patents

Procédé d'installation d'un élément de fixation aveugle et utilisation de passage longitudinal de manchon d'un élément de fixation aveugle Download PDF

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Publication number
EP4140615A1
EP4140615A1 EP21192693.6A EP21192693A EP4140615A1 EP 4140615 A1 EP4140615 A1 EP 4140615A1 EP 21192693 A EP21192693 A EP 21192693A EP 4140615 A1 EP4140615 A1 EP 4140615A1
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EP
European Patent Office
Prior art keywords
sleeve
longitudinal passage
inspection
blind
deformed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP21192693.6A
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German (de)
English (en)
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EP4140615B1 (fr
Inventor
Thorsten ROYE
Jörg Jendrny
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Airbus Operations GmbH
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Airbus Operations GmbH
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Publication date
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Priority to EP21192693.6A priority Critical patent/EP4140615B1/fr
Publication of EP4140615A1 publication Critical patent/EP4140615A1/fr
Application granted granted Critical
Publication of EP4140615B1 publication Critical patent/EP4140615B1/fr
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Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/02—Riveting procedures
    • B21J15/04—Riveting hollow rivets mechanically
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/02—Riveting procedures
    • B21J15/04—Riveting hollow rivets mechanically
    • B21J15/043—Riveting hollow rivets mechanically by pulling a mandrel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/10—Riveting machines
    • B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
    • B21J15/142—Aerospace structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/10—Riveting machines
    • B21J15/28—Control devices specially adapted to riveting machines not restricted to one of the preceding subgroups

Definitions

  • the invention relates to a method for installing a blind fastening device in a bore provided in a structure, in particular in the field of aircraft or spacecraft production. Furthermore, the invention relates to a use of a longitudinal passage of a sleeve provided for forming part of a blind fastening device, particularly of a blind fastening device of this kind, in particular in the field of aircraft or spacecraft production.
  • blind fasteners are considered useful for enabling efficient automated production. A reason for this is that for installing the fastener, access is only necessary from a single side of the structure. Also, blind fasteners are used today for applications such as, for example, the closing of box-like structures. Furthermore, blind nuts are installed today widely in aircraft structures and are used for fastening a component using a bolt.
  • FR 2 999 707 A1 for example, a method for installing a blind fastener having a breaking point has been proposed, wherein the method includes receiving acoustic signals during the installation process.
  • FR 2 999 707 A1 describes that using this process, it is possible to follow the installation and make sure that the installation and resulting assembly fulfill the mechanical requirements regarding traction and preload.
  • the rivet comprises a screw and a bushing.
  • the bushing has an essentially cylindrical body having a deformation zone that is initially cylindrical and is designed to form an external bulge, as well as a tapped portion engaging with a threaded portion of the screw.
  • the bushing is inserted into a bore of a structure from the side of a first surface thereof, a collar of the bushing is maintained in contact with the first surface, and axial traction is applied to the screw in order to form the external bulge. Then, the screw is screwed into the bushing until a head of the screw contacts the collar of the bushing.
  • a bushing or sleeve may be installed and fixed in a first step using a dedicated installation pin, which is then removed in a subsequent step before inserting the final core bolt to complete the connection.
  • the problem to be solved by the present invention is to enable more efficient quality control and/or additional work on blind fastening devices and/or to enable or facilitate the production of efficient and reliable blind structures.
  • this problem is solved by a method for installing a blind fastening device having the features of claim 1 and/or by a use of a longitudinal passage having the features of claim 15.
  • the invention provides a method for installing a blind fastening device in a bore provided in a structure.
  • the structure has a first side and a second side.
  • the method comprises steps of:
  • the invention provides a use of a longitudinal passage of a sleeve, provided for forming part of a blind fastening device and installed in a structure having a first side and a second side,
  • the sleeve is partially arranged within a bore provided in the structure. Moreover, the sleeve comprises a deformed sleeve zone engaging the structure on the second side thereof.
  • the longitudinal passage of the sleeve is configured for at least partially receiving a core bolt in such a manner that the core bolt can be accessed from the first side and can be tightened with respect to the installed sleeve.
  • An idea underlying the invention is to perform, between two steps of a two-step installation process of a blind fastening device, one or more operations related to quality control, or one or more operations related to "re-work” to be done on the seated sleeve, or both quality control and "re-work” operations, by using an access to a blind side of a structure through a passage extending through the sleeve of the fastening device and in particular temporarily unblocked between these two steps.
  • the operations of checking and/or performing additional work are carried out between the installation of the sleeve and the final installation of the core bolt.
  • the core element that is arranged in the longitudinal passage of the sleeve for being used for forming the deformed sleeve zone may be a temporary core element which is not identical to the final core bolt but is a separate element and may be of different type, or instead the core element may be or correspond to the core bolt which, in this case, is used to form the deformed sleeve zone, temporarily removed from the longitudinal passage and, after the inspection and/or additional work, is re-inserted into the longitudinal passage as the final core bolt and tightened.
  • the invention in particular contributes to securing the performance of blind fasteners used in closed-box structures and to enabling implementation of truly blind structures that it has not been possible to produce hitherto, or that could be produced hitherto only with considerable difficulty and expense. Also, the invention significantly facilitates automated production of closed box structures, and in particular of really blind structures with substantially no access to the blind side. Because quality control and re-work on blind fastening devices are made possible by the invention in the production of truly blind structures, assembly concepts can be envisaged that were not feasible hitherto.
  • the invention advantageously makes it possible to economically inspect substantially all of them for correct installation, and to make sure all of the fastening devices are correctly set.
  • the invention also makes it possible to ensure that each of the fastening devices complies not only with the mechanical requirements, but also with requirements that may necessitate additional treatment of the fastening device or in the vicinity thereof on the blind side, such as requirements of electrical conductivity and lightning strike compatibility and/or resistance to corrosion, for example. This may be advantageous in particular for fastening devices in closed boxes or "blind" installations.
  • the invention in particular makes it possible to employ quality control and testing procedures that hitherto could not be used on blind fasteners, such as eddy current testing for detection of flaws or cracks in the deformed sleeve zone, for example.
  • the invention in particular proposes to perform some or all checks required or desirable to secure the quality of the installation, and/or additional work which may comprise work steps such as sealing or painting operations, on the blind side of the fastening devices, between two fastener installation steps - the installation of the sleeve, and the installation of the final core bolt - via access through the sleeve element.
  • the invention enables to check up to 100 percent of the deformed part of the blind fastening devices even in truly blind applications.
  • the number and dimensions of the blind fastening devices can be even more precisely selected to meet the relevant requirements without unnecessarily increasing work load and structural weight.
  • the inspection of the installed sleeve comprises non-destructive testing of the installed sleeve or of at least a portion thereof.
  • the non-destructive testing may in particular by carried out using an electromagnetic non-destructive testing procedure, for example using eddy-current testing, or using a laser-based non-destructive testing procedure, for example a non-destructive testing procedure including laser scanning.
  • Other non-destructive testing procedures may be used in other developments.
  • non-destructive testing is performed in a non-contact manner, but non-destructive testing involving contact is conceivable in alternative developments, too.
  • the method comprises inserting, using and removing, as the inspection device, a non-destructive testing device.
  • the non-destructive testing device may, in particular, be an electromagnetic testing device.
  • the non-destructive testing device may be an eddy-current testing device.
  • the non-destructive testing device may be a laser-based testing device, for example a testing device configured to perform laser scanning.
  • the non-destructive testing device is a device configured for performing intrusive non-destructive testing, in other words non-destructive testing including intrusion into an opening or a passage, more specifically into the longitudinal passage of the sleeve.
  • the non-destructive testing device comprises at least a forward portion insertable into the longitudinal passage of the installed sleeve.
  • the forward portion may, for example, be formed as or comprise a probe that is used to perform the non-destructive testing.
  • non-destructive testing it can hence be checked in an economical manner whether the properties, in particular the geometrical dimensions and/or deformation mode, meet pre-defined requirements. Also, it can be economically and reliably verified that the sleeve is free from cracks or other mechanical anomalies that might appear when forming the deformed sleeve zone. In particular, using the insertable forward portion, it is possible to make use of the unblocked passage for performing non-destructive testing in advantageous manner.
  • the inspection of the installed sleeve comprises visual inspection of the installed sleeve or of at least a portion thereof on the second side of the structure, in particular visual inspection of the deformed sleeve zone or of a portion thereof.
  • the method comprises inserting, using and removing, as the inspection device, a borescope comprising a forward portion that is insertable into and through the longitudinal passage of the installed sleeve.
  • Such visual inspection can additionally contribute to the safety and reliability of the structure that is produced, and anomalies that due to their nature may not or not easily be detectable using the chosen non-destructive testing procedure can be discovered and corrected.
  • the inspection of the installed sleeve includes inspecting a geometry of the installed sleeve.
  • the inspection of the installed sleeve may include inspecting actual geometrical dimensions of a portion of the installed sleeve protruding from the second side of the structure. More particularly, the inspection may include inspecting an axial length of the portion of the installed sleeve protruding from the second side of the structure and/or a width or outer diameter of the deformed sleeve zone. Dimensional values may relatively easily be detected and compared to a set of target values and provide a useful indication regarding whether the installation of the sleeve has been accomplished as desired or, on the contrary, an anomaly occurs.
  • the inspection of the installed sleeve includes testing the installed sleeve or at least a portion thereof for the presence of cracks and/or includes inspecting the deformed sleeve zone for the presence of a target mode of deformation or for the presence of an undesired mode of deformation or both. In this manner, it can be ensured that the sleeve is appropriately installed and securely mechanically fixed in the bore and/or has the required mechanical resistance.
  • performing the additional work on the installed sleeve includes coating or re-coating at least a portion of the installed sleeve, in particular by coating or re-coating the deformed sleeve zone or at least a portion thereof.
  • coating or re-coating at least a portion of the installed sleeve in particular by coating or re-coating the deformed sleeve zone or at least a portion thereof.
  • the method comprises inserting, using and removing, as the working device, a coating applying device comprising a forward portion that is insertable into and through the longitudinal passage of the installed sleeve and is formed with a coating material outlet region.
  • the coating material outlet region may in particular be configured as a nozzle adapted for ejection of the coating material. Accordingly, the coating material can be delivered in a targeted manner onto a target region.
  • performing the additional work on the installed sleeve includes applying a sealant, for example along a contact region between the deformed sleeve zone and the structure on the second side thereof, wherein the sealant in particular is applied as a liquid or as a paste-like material. This may contribute to ensure that the sleeve is tightly sealed against the structure, even in case the structure is truly blind.
  • the method comprises inserting, using and removing, as the working device, a sealant applying device comprising a forward portion that is insertable into and through the longitudinal passage of the installed sleeve and is formed with a sealant outlet region.
  • the sealant outlet region may in particular be configured as a nozzle adapted for ejection of the sealant.
  • sealant and/or coating in line with the developments described above, i.e. the sealing or painting operations performed using the access via the longitudinal passage, make it possible to efficiently secure corrosion resistance, lightning strike performance, tightness and/or conservation in closed structures.
  • the blind fastening device is a blind rivet.
  • the blind fastening device comprises a blind rivet nut.
  • the sleeve of the blind fastening device may be formed as a blind rivet nut.
  • the blind fastening device may be a high-strength blind fastening device.
  • the core element for forming the deformed sleeve zone, may in particular be axially moved while the sleeve is maintained in its position relative to the bore and/or the core element may, for forming the deformed sleeve zone, be rotated while the sleeve is maintained in its position and orientation relative to the bore.
  • the invention may in various developments thereof be used in connection with so-called pull-type blind fastening devices, in which, for forming the deformed sleeve zone, an axial pulling motion is imparted to the core element, or the invention may be used in connection with so-called thread-type blind fastening devices, in which, for forming the deformed sleeve zone, a rotational motion is imparted to the core element. Also, in further developments, the invention may be used in connection with blind fastening devices in which pulling and threading motion of the core element are combined.
  • the sleeve is provided, within a part of a section of the sleeve that protrudes from the second side of the structure after insertion of the sleeve into the bore, with an internal thread engageable with an external thread of the core element.
  • the final core bolt comprises an external thread engageable with the internal thread of the installed sleeve and the step of inserting and tightening the core bolt comprises screwing the core bolt into the installed sleeve.
  • a sleeve that is provided with a thread, for threaded engagement with the core element and the final core bolt, makes it possible to comparatively easily remove the core element and perform inspection and/or additional work via the unblocked tapped portion of the passage, before installing the final core bolt by re-installing the core element as the final core bolt or by installing a core bolt being an element different from the core element that is temporarily used to form the deformed sleeve zone.
  • the sleeve or blind nut element and/or the core bolt may be of a type that as such is/are currently available and suitable for installing a blind fastening device in a two-step process, in particular using a separate, removable installation pin.
  • the invention may be applied in connection with a wide variety of types of blind fastening devices.
  • the inspection of the sleeve or of at least a portion thereof and/or the additional work on the sleeve and/or in the vicinity thereof on the second side of the structure is or are performed at least partially within a space between a containment cap arranged on the second side of the structure and the portion of the installed sleeve protruding from the structure on the second side.
  • the inspection device(s) and/or the working device(s) may be partially inserted into the space between the containment cap and the protruding portion of the installed sleeve.
  • the containment cap may in particular be a containment cap for lightning protection.
  • the containment cap is attached to a component of the structure, in a region where the bore is or will be formed, before the structure is closed.
  • the invention thus advantageously can enable or facilitate inspection and/or additional work which otherwise would be very difficult or would not be possible due to the presence of the containment cap.
  • the structure is a closed-box structure.
  • the method and use of the invention can be particularly useful for installing blind fastening devices in closed-box structures, in which access for performing inspection or re-work otherwise is difficult.
  • the structure in particular is a structure of an aircraft or spacecraft.
  • the structure can be a wing or a part of a wing, a wing box or a part of a wing box, a center-wing box or a part of a center-wing box, or a stabilizer or a part of a stabilizer.
  • the structure may be a rudder or a part thereof, an elevator or a part thereof, an aileron or a part thereof, a flap or a part thereof, or a slat or a part thereof.
  • the invention can be useful for producing in an efficient and reliable manner a great variety of different, large or small box-like structures.
  • the invention may be applied in wide variety of structural assembly processes in aircraft or spacecraft production.
  • additional quality control may be performed during forming the deformed sleeve zone for installing the sleeve in the structure, for example by monitoring force and/or torque applied to the core element and/or by monitoring axial and/or rotational displacement of the core element, during forming the deformed sleeve zone.
  • reliability can additionally be increased further.
  • additional quality control may be performed during tightening the core bolt for installation thereof, for example by monitoring torque applied to the core bolt and/or by monitoring an angle through which the core bolt is rotated during tightening and/or by inspecting a final head projection of the core bolt.
  • quality control can also be performed to make sure that the final core bolt is correctly set and tightened.
  • Fig. 1 shows an airplane 1, e.g. a commercial passenger airplane, as an example of an aircraft or spacecraft in which embodiments of the invention may be used in exemplary and advantageous manner.
  • the aircraft 1 comprises a fuselage 3, wings 4, an empennage 6 including a vertical stabilizer 10 and a horizontal stabilizer 15, as well as engines 8 attached to the wings 4.
  • the wings 4 each have a trailing edge 5, the vertical stabilizer 10 has a trailing edge 11, and the horizontal stabilizer 15 has a trailing edge 16.
  • Reference sign 19 schematically indicates the location of a center wing-box.
  • the structure or airframe of the aircraft 1 may be formed, for example, from light metal components, such as from components made from one or more aluminum alloys, or may be formed from fibre-reinforced composite components including a synthetic matrix and reinforcing fibres embedded therein, or from a combination of metal and fibre-reinforced composite components.
  • the structure or airframe of the aircraft 1 includes various box-like structures, at least some of which can be designed as truly closed boxes.
  • the wings 4 or parts thereof for instance the wing-box, the center wing-box 19 and/or the stabilizers 15, 16 or a part of these may form such closed-box structures.
  • a rudder in the region of the trailing edge 11 of the vertical stabilizer 10 an elevator in the region of the trailing edge 16 of the horizontal stabilizer 15, ailerons in the region of the trailing edge 5 of the wings 4, and/or a flap or slat provided on the wing 4, or part thereof, may form a closed-box structure.
  • a fully closed box-type structure 200 is schematically illustrated.
  • the structure 200 has a bottom and top wall, a front and back wall, as well as side walls.
  • the walls are substantially closed without any significant opening that would allow access to an interior of the structure 200.
  • the geometry of the structure 200 in Fig. 2 is merely exemplary and shown for purposes of illustration, but it should be understood that the invention can be applied to a wide variety of structures, and in particular to a wide variety of closed-box structures, in particular in an aircraft or spacecraft, for example to any one of the closed-box structures of the aircraft 1 described herein above.
  • Fig. 2 also schematically illustrates, in exemplary manner, two connection regions 201 and 202, in which fastening devices are installed for connecting components to the structure 200 and/or for connecting another element to a component of the structure 200.
  • the structure 200 may include only one of the regions 201, 202, or may be provided with a plurality of regions 201 and/or 202.
  • connection region 201 two overlapping components of the structure 200, which are not illustrated in more detail in Fig. 2 , are connected to each other using a plurality of blind fastening devices 100. Furthermore, in the connection region 202, a further element has been attached to a component of the structure 200 using a plurality of blind fastening devices 100a.
  • the blind fastening devices 100 and 100a and operations carried out during installation thereof will be explained in the following with reference to Figs. 3 to 5 .
  • the explanations will refer, regarding Figs. 3 and 5 , to a structure 20, and regarding Fig. 4 , to a structure 20a.
  • the structures 20, 20a each can correspond to the box-type structure 200 shown in exemplary manner in Fig. 2 , or to a structure of another type.
  • the structures 20, 20a can be box-type structures of the aircraft 1 such as a wing, wing box, center-wing box, stabilizer, rudder, elevator, aileron, flap or slat, or part thereof.
  • Fig. 3 schematically illustrates steps of embodiments of a method for installing a blind fastening device or blind fastener 100, which is formed as a blind rivet, in a bore 28 provided in a structure 20. Only a portion of the structure 20 is shown in Fig. 3 .
  • the structure 20 comprises two at least partially overlapping first and second components 21, 22, which can each be formed from a sheet-type material.
  • the components 21, 22 may be metal sheets or sheets made from a fibre-reinforced synthetic material, or a combination thereof, but the components 21, 22 could be made from other material and/or be shaped in a different manner.
  • Fig. 3 shows two components 21, 22 in exemplary manner, but it should be understood that the structure 20 can in variants of the embodiment comprise more than two components 21, 22, for example more than two overlapping sheets.
  • the structure 20 has a first side A and a second side B.
  • the structure 20 may, in advantageous embodiments, be a closed-box structure of the aircraft 1, with the first side A being an outer, accessible side, and the second side B being an inner, "blind" side of the structure 20 that can be accessed only with difficulty or not at all.
  • the bore 28 is provided in the form of a through-hole extending through both components 21, 22 along a center axis C of the bore 28.
  • the bore 28 preferably is substantially circular in cross-section and can be obtained by drilling through the arrangement of the first component 21 and the second component 22, or, if more than two components 21, 22 are provided, through the plurality of components.
  • reference sign S1 indicates a situation in which a sleeve 31, which may be substantially rotationally symmetric, has been inserted into the bore 28 along the center axis C, from the first, accessible side A.
  • the sleeve 31 comprises a longitudinal internal passage 32 along a longitudinal axis of the sleeve 31, which coincides with the centerline C when the sleeve 31 has been inserted into the bore 28 as shown for situation S1.
  • the sleeve 31 On one end thereof, oriented towards the first side A, the sleeve 31 is provided with a collar 34.
  • the bore 28 has been countersunk from the first side A in order to accommodate the collar 34. In this way, an abutment for the sleeve 31 is provided.
  • a temporary core element 36 in the form of a temporary core bolt is inserted into the passage 32 and may be screwed into the sleeve 31.
  • the temporary core bolt 36 comprises an external thread 45 engageable with the internal thread 46 of the sleeve 31.
  • the temporary core bolt 36 can be accessed from the first side A.
  • the sleeve 31 is maintained in its position and orientation relative to the bore 28, for example restrained against being pulled out of the bore 28 and against being rotated, by a suitable tool, not shown in Fig. 3 .
  • the temporary core bolt 36 is axially pulled along the center axis C toward the first side A, in such a way that axial traction 55 acts on that portion of the sleeve 31 having the internal thread 46.
  • a deformed sleeve zone 33 of the sleeve 31, or "bulb" 33 is formed, which engages a surface of the second component 22 of the structure 20 on the second side B to firmly attach the sleeve 31 to the structure 20 and firmly connect the first and second components 21, 22.
  • the temporary core bolt 36 can be rotated about a longitudinal axis thereof parallel to the centerline C.
  • axial traction 55 can be applied to the portion of the sleeve 31 having the internal thread 46, whereby the unthreaded part of the section 35 can be deformed to form the deformed sleeve zone 33 or "bulb".
  • the head of the temporary core element 36 and the threads 45 thereof can be accordingly adapted for a "pull-type” or “threaded-type” installation of the sleeve 31 or a combination thereof.
  • the temporary core element 36 is removed from the longitudinal passage 32.
  • the threads 45, 46 are disengaged by unscrewing the temporary core element 36, which is then taken out of the passage 32 from the first side A.
  • the internal, longitudinal passage 32 is unblocked.
  • the installed sleeve, comprising the deformed sleeve zone 33, will be denoted by reference numeral 31' in the following.
  • An inner diameter of the passage 32 may, for example, be within a range of about 4 mm to about 10 mm, although passages 32 having smaller or larger inner diameters are conceivable, too.
  • the sleeve 31 which may also be termed a "nut element"
  • the sleeve 31 is deformed in order to securely connect the components 21, 22 to each other, or more than two components if the bore 28 extends through more than two of such components, and at the same time to secure the sleeve 31 within the bore 28, it may be desirable that an appropriate target deformation mode of the circumferential wall of the sleeve 31 be obtained. Also, it may be desirable that cracks in the sleeve 31 and more specifically in the deformed sleeve zone 33 or "bulb" be detected. Checking the final properties of the seated sleeve 31 or nut element is hence desirable, and performing these checks before installing a final core bolt element offers the advantage of being able to access the inside of the passage 32 as well as the second or back side B.
  • the longitudinal passage 32 of the installed sleeve 31' is used for inspecting the sleeve 31' and accessing the backside B.
  • electromagnetic non-destructive testing of the installed sleeve 31' or portions thereof is performed, in particular eddy-current testing, which makes use of induction.
  • an inspecting device 64 is partly inserted from the first, accessible side A of the structure 20 into the longitudinal passage 32.
  • the inspection device 64 is an electromagnetic testing device for inspection using the eddy current testing method and may, for example, be rotated, as indicated by reference numeral 65, during testing. Electromagnetic, non-contact inspection of the sleeve 31' using eddy current is performed in situation S2 to verify that the geometry of the installed sleeve 31', corresponds, e.g. within a specified range of permissible deviation, to a predefined target geometry. Further, the electromagnetic inspection indicated by S2 can be used to verify that a target mode of deformation is present in the deformed sleeve zone 33, i.e. that this zone has been formed as desired. Further, the electromagnetic inspection in situation S2 is used to verify that the sleeve 31', in particular in the deformed sleeve zone 33, is free from cracks or other flaws.
  • the inspection device 64 may be a laser-based testing device for performing non-destructive testing based on laser technology, for example using laser scanning of the sleeve 31', in order to verify the correctness of the geometry and deformation mode of the sleeve 31' and detect any cracks or anomalies introduced when the deformed sleeve zone 33 is formed, if cracks or anomalies are present. In this manner, it is possible to detect e.g. cracks or the presence of undesirable deformation modes or incorrect geometry even in case the fastener 100 is to be installed in a truly blind structure 20.
  • the inspection device 64 is not shown in Fig. 3 in its entirety. Instead, a forward portion configured as a probe for performing the electromagnetic or laser-based testing is schematically displayed. The forward portion is inserted into the longitudinal passage 32 from the first, accessible side A. The corresponding forward movement of insertion is indicated in Fig. 3 by an arrow 66. In this manner, using the inspection device 64, intrusive inspection involving intrusion of the forward portion into the passage 32 is performed.
  • the inspection device 64 After inspection by means of the inspection device 64 is terminated, the inspection device 64 is removed from the passage 32 towards the first side A.
  • the tip of the borescope 76 has been guided past the thread 46 and out of an end of the sleeve 31' on the second side B.
  • visual inspection in particular of the portion of the installed sleeve 31' protruding from the component 22 on the second side B of the structure 20 is carried out, for quality control of the installed sleeve 31'.
  • an operator can visually inspect the installed sleeve 31', and an area surrounding it if desired, on the inaccessible, blind side B of the structure 20.
  • the tip portion of the borescope 76 is moveable, e.g. to perform a pivoting movement 78.
  • the borescope 76 can be rotated substantially about the center line C, the rotational movement being indicated by reference numeral 79.
  • the visual inspection may include visual inspection of the portion of the sleeve 31 projecting from the structure 20 on the second side B for any visually apparent irregularities, for example within the deformed zone 33.
  • the eddy-current-based or laser-based non-destructive testing as explained above with reference to S2 may be used to inspect the geometry of the sleeve 31', in particular actually obtained geometrical dimensions such as an axial length L of the portion of the installed sleeve 31' protruding on the second side B from the structure 20 and/or a width or outer diameter D of the deformed sleeve zone 33
  • the visual inspection as explained above with reference to S3 may be used, too, for checking the dimensional properties of the deformed sleeve 31', e.g. by verifying that L and/or D is/are within respective permissible ranges.
  • D may also be designated a "bulb diameter".
  • the borescope 76 is removed again from the longitudinal passage 32 towards the first side A.
  • the longitudinal passage 32 of the installed sleeve 31' is used for performing additional work on the sleeve 31' and/or in the vicinity thereof on the second side B, via the passage 32.
  • Fig. 3 shows that in the state S4, a coating applying device 84 as a working device has been inserted from the first side A with a forward portion thereof, in a direction 85 substantially parallel to the center axis C of the bore 28, into and through the longitudinal passage 32 of the sleeve 31'.
  • Reference sign 85 indicates the insertion movement.
  • the coating applying device 84 comprises a coating material outlet region formed as a nozzle 87 for ejecting or spraying coating material onto a target region.
  • the tip of the coating applying device 84 including the nozzle 87 is inserted through the passage 32 and past the thread 46, out of the passage 32 on the second side B.
  • the tip of the coating applying device 84 including the nozzle 87 may be moved, for example, in the manner of a pivoting movement 88, and at least the forward portion of the coating applying device 84 extending within and through the passage 32 can be rotated.
  • Fig. 4 shows a corresponding turning movement 89 of the coating applying device 84.
  • the pivoting movement 88 may also be omitted.
  • a portion of the installed sleeve 31' extending beyond the structure 20 on the second side B can be coated or re-coated with coating material ejected or sprayed from the nozzle 87 in order to enhance protection of the blind fastener 100 against corrosion and/or in order to enhance electrical conductivity and lightning strike compatibility.
  • coating material ejected or sprayed from the nozzle 87 in order to enhance protection of the blind fastener 100 against corrosion and/or in order to enhance electrical conductivity and lightning strike compatibility.
  • painting or re-painting of the deformed sleeve zone 33 or "bulb" is performed using the access through the passage 32.
  • Fig. 3 shows a coating 86 on the bulb 33 applied in this manner.
  • the device 84 is removed again from the passage 32 towards the first side A.
  • a sealant applying device 91 has been inserted from the first side A with a forward portion thereof, using an insertion movement 92 substantially parallel to the center axis C of the bore 28, into and through the longitudinal passage 32 of the sleeve 31'.
  • the sealant applying device 91 comprises a sealant outlet region formed as a nozzle 94 for ejecting the sealant towards a target region.
  • the tip of the sealant applying device 91 including the nozzle 94 is inserted through the passage 32 and past the thread 46, out of the passage 32 on the second side B.
  • the tip of the sealant applying device 91 including the nozzle 94 may or may not be movable, for example pivotable, relative to other portions of the sealant applying device 91, analogous to the movement 88 illustrated for situation S4. Further, at least the forward portion of the sealant applying device 91 which extends within and through the passage 32 can be rotated in a manner analogous to movement 89 illustrated for situation S4.
  • Fig. 3 illustrates that in embodiments of the invention, sealant 93 is applied using the device 91 along an interface between the deformed bulb 33 and a surface of the second component 22 on the second side B.
  • the sealant may be a paste or viscous liquid ejected from the nozzle 94.
  • sealant may be applied to other locations on or in the vicinity of the sleeve 31' if required.
  • the device 91 is removed from the longitudinal passage 32 of the sleeve 31' towards the first side A.
  • a final core bolt 105 is inserted from the first side A into the longitudinal passage 32 of the installed, checked, coated and sealed sleeve 31'. This is shown in Fig. 3 by situation S6.
  • the final core bolt 105 comprises a head adapted to an internal geometry of the collar 34, and an external thread 106 that can be threaded into the internal thread 46 of the installed sleeve 31'.
  • the core bolt 105 is screwed into the installed sleeve 31' and tightened with respect to the sleeve 31' therein, preferably by means of a tool not illustrated in Fig. 3 . In this manner, the core bolt 105 is finally installed and the connection obtained using the blind fastener 100 is provided with its desired final strength.
  • the tightening of the core bolt 105 is accomplished from the first side A.
  • the final core bolt 105 is an element that is distinct from the temporary core element 36. Accordingly, the core element 36, which is temporarily inserted into the passage 32, is a separate element not identical with the final core bolt 105.
  • the core element 36 used to form the deformed sleeve zone 33 can correspond to the final core bolt 105.
  • a core element which will form the final core bolt 105 is temporarily arranged, in the state S1, in the passage 32 as a core element 36 in order to perform the deformation and creation of the deformed sleeve zone 33.
  • the deformed sleeve zone 33 is in this case formed in the same manner as described above in detail with reference to the use of the temporary core element 36 in Fig. 3 .
  • the core element which will also be used as the final core bolt 105 is then removed from the passage 32, the steps S2, S3, S4, S5 or a selection thereof are performed, and after completion of inspection and/or additional work, the core bolt 105 is installed again as the final core bolt 105.
  • the steps S2, S3, S4, S5 are, in an exemplary embodiment explained above, performed in this order between the installation of the sleeve 31 as indicated by situation S1 and the insertion of the final core bolt 105 illustrated at reference sign S6.
  • one or more of the steps or actions S2, S3, S4, S5 can be omitted e.g. if unnecessary in a particular application.
  • the order of the steps S2, S3, S4, S5 or of the selected subset thereof can be changed according to the requirements of the particular application.
  • one or more of the steps S2, S3, S4, S5 could also be performed more than once for the same fastener 100. For instance, an action of coating or of sealing, or both, as indicated by reference numerals S4 and/or S5, could be followed by another visual inspection, as in situation S3, to verify that the coating and/or sealant has/have been correctly applied.
  • Fig. 4 schematically illustrates some steps of embodiments of a method for installing another blind fastening device 100a, which comprises a sleeve 31a, 31a' that is formed as a blind rivet nut, in a structure 20a.
  • the structure 20a has a first, accessible side A and a second, "blind" side B that is difficult to access.
  • the structure 20a can be a closed-box structure of the aircraft 1 as described above.
  • the undeformed sleeve 31a is inserted into a bore 28a extending through a single component 22a, which e.g. may be formed as a metal sheet or a sheet of a fibre-reinforced synthetic material.
  • the bore 28a preferably is circular in cross-section and may be drilled, for example, through the component 22a.
  • the sleeve 31a comprises a collar 34a which abuts flat against an outer surface of the component 22a on the first side A.
  • the bore 28a does not comprise a countersunk portion, but countersinking may be performed in variants if desired.
  • Fig. 4 also illustrates a temporary core element 36a analogous to the temporary core element 36 of Fig. 3 , but comprising a head that is formed differently, in order to cooperate with the collar 34a.
  • the sleeve 31a is installed in the situation S1a in the same manner as explained above with reference to Fig. 3 .
  • the sleeve 31a is securely attached to the component 22a by forming a deformed sleeve zone 33a on the second side B that engages the component 22a.
  • the temporary core bolt 36a comprises an external thread 45a analogous to the thread 45 in Fig. 3
  • the sleeve 31a comprises an internal thread 46a analogous to the thread 46 in Fig. 3
  • axial traction is applied to an end portion of the sleeve 31a on the second side B to form the deformed sleeve zone 33a, as explained above.
  • steps S2, S3, S4, S5 are performed in the same manner as explained above with reference to Fig. 3 , in particular for quality control on the installed sleeve or blind nut 31a' and/or for performing additional work like coating or sealing, for example.
  • a further component 21a having another bore is provided, a final core bolt 105a is inserted through the bore of the component 21a and into the passage 32 of the attached sleeve 31a', and the core bolt 105a is screwed into the sleeve 31a' and firmly tightened in order to attach the further component 21a to the component 22a.
  • the sleeve 31a' has a function of a blind rivet nut for the purpose of attaching the component 21a to component 22a.
  • the core bolt 105a has an external thread 106a cooperating with the internal thread 46a.
  • the temporary core element 36a and the final core bolt 105a may be separate and distinct elements, while in other variants, the core element which will form the final core bolt 105a may be used in the situation S1a to form the deformed sleeve zone 33, as described above in relation to elements 36, 105. In the latter case, the core bolt 105a, used to create the "bulb" 33, is re-used, after completion of the inspection and/or additional work, as a final core bolt 105a in the completed connection.
  • such core elements may in some variants comprise a portion that may be separated from the core element e.g. when forming the bulb 33, for example at a predetermined breaking point.
  • a separately provided final core bolt 105, 105a may for example in some variants comprise a predetermined breaking point where a portion of the core bolt 105, 105a may separate when finally tightening the core bolt 105, 105a.
  • an interior space of the closed-box structure 20, 20a may accommodate fuel.
  • a nut cap or containment cap 150 may be arranged on the second side B of the structure 20, or 20a, enclosing the protruding portions of the blind fastener 100, 100a. Such a situation is schematically illustrated in Fig. 5 .
  • the cap 150 is, for example, made from a synthetic material.
  • Fig. 5 shows the visual inspection using the inspection device 76, already described above with reference to Fig. 3 , in case the containment cap 150 is provided.
  • the cap 150 has been attached to the second component 22 on the second, blind side B of the structure 20 before closing the structure 20.
  • Fig. 5 illustrates that even in case the cap 150 is provided, an inspection of the blind side of the sleeve 31' is made possible, using the inspection device 76 and inspecting via the longitudinal passage 32. A tip of the device 76 is inserted through the passage 32 into a space between the cap 150 and the installed sleeve 31'.
  • steps S2, S4 and/or S5 may be carried out as well also in case the containment cap 150 is provided. Specifically, in the case of steps S4 or S5, the tip comprising the nozzle 87 or 94, respectively, of the device 84 or 91, is inserted into the space between the cap 150 and the sleeve 31' for performing additional work within this space.
  • axial force and/or torque that is/are externally applied by a tool to the core element 36, 36a, as well as axial displacement and/or angle of rotation of the core element 36, 36a may be additionally detected and monitored during forming the bulb 33 for additional quality control. Such detection and monitoring may be performed in analogous manner if the core bolt 105 or 105a is temporarily used as the core element 36 or 36a.
  • the torque applied to the core bolt 105, 105a as well as the angle through which the core bolt 105, 105a is rotated during the tightening may be detected and monitored for further improved quality control of the finally assembled fastening device 100, 100a.
  • a distance by which the head of the core bolt 105 or 105a projects from a reference surface of the structure 20, 20a at the end of the tightening step may be detected and compared with a target value.
  • efficient quality control can be carried out in economical manner on up to 100 percent of all blind fastening devices 100, 100a installed in a structure 20, 20a, even if the structure 20, 20a is a truly blind, closed-box structure.
  • the performance of each one of the entire set of blind fastening devices 100, 100a installed in the structure 20, 20a can be ensured in efficient manner, for example by additionally performing sealing or painting operations on the blind side as described above with reference to S4, S5.
  • steps S2 to S5 or a desired subset thereof between situations S1, S6 or S1a, S6a, closed-box structures 20, 20a, 200, in particular for the aircraft 1, are made possible which can be "truly blind” with substantially no or strongly limited access to the second side B for inspection or re-work, after finally installing the fastening devices 100, 100a.
  • being able to check substantially 100 percent of the blind fastening devices 100, 100a in blind applications may contribute to saving weight, parts and workload, as a smaller number of blind fastening devices 100, 100a may be appropriate to obtain a reliable structure 20, 20a or the dimensions of the fastening devices 100, 100a may be varied.

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EP21192693.6A 2021-08-24 2021-08-24 Procédé d'installation d'un élément de fixation aveugle et utilisation de passage longitudinal de manchon d'un élément de fixation aveugle Active EP4140615B1 (fr)

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EP21192693.6A EP4140615B1 (fr) 2021-08-24 2021-08-24 Procédé d'installation d'un élément de fixation aveugle et utilisation de passage longitudinal de manchon d'un élément de fixation aveugle

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EP21192693.6A EP4140615B1 (fr) 2021-08-24 2021-08-24 Procédé d'installation d'un élément de fixation aveugle et utilisation de passage longitudinal de manchon d'un élément de fixation aveugle

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2999707A1 (fr) 2012-12-14 2014-06-20 Airbus Operations Sas Procede et dispositif d'installation controlee d'un element de fixation aveugle
WO2018007324A1 (fr) 2016-07-06 2018-01-11 Lisi Aerospace Rivet de fixation aveugle avec fût épaulé et procédé d'installation associé
US20180238372A1 (en) * 2015-06-11 2018-08-23 Lisi Aerospace Attachment fitted on a single side
WO2018178186A1 (fr) * 2017-03-30 2018-10-04 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Procédé de pose d'un raccordement assemblé par technique de formage

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2999707A1 (fr) 2012-12-14 2014-06-20 Airbus Operations Sas Procede et dispositif d'installation controlee d'un element de fixation aveugle
US20180238372A1 (en) * 2015-06-11 2018-08-23 Lisi Aerospace Attachment fitted on a single side
WO2018007324A1 (fr) 2016-07-06 2018-01-11 Lisi Aerospace Rivet de fixation aveugle avec fût épaulé et procédé d'installation associé
US20190186522A1 (en) 2016-07-06 2019-06-20 Lisi Aerospace Blind Fitting Rivet Having A Shoulder Sleeve, And Associated Installation Method
WO2018178186A1 (fr) * 2017-03-30 2018-10-04 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Procédé de pose d'un raccordement assemblé par technique de formage

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