• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Device (1) damping fastening between two elements (2, 3) to be assembled, the fixing device comprising: - a tubular internal part (4) along an axis (A) for fixing,; - A tubular outer part (11) along the axis (A) of fixation, hollow, the inner part (4) being housed in the outer part (3) so that the outer surface of the inner part is screwed to -vis the inner surface of the outer part; a layer (18) of elastomer between the outer piece (11) and the inner piece (4), the layer (18) of elastomer, when seen in section in a longitudinal plane (P) comprising the axis (A); ), comprises: - on each side of the axis (A) of attachment, at least three portions (28a, 28b, 38a, 38b, 29a, 29b) said longitudinal, and - at least two portions (27a, 27b) , 37a, 37b, 29a, 29b) said transverse.
    公开号:FR3031146A1
    申请号:FR1463334
    申请日:2014-12-24
    公开日:2016-07-01
    发明作者:De Beaupre Rene Jean Cheynet；Patrick Camarasa
    申请人:Airbus Defence and Space SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a damping fastening device of two elements to be assembled together, intended to isolate the elements between them to limit the transmission of shocks and / or vibrations. The present invention finds particular application in the field of satellites and spacecraft.
    [0002] In known manner, a satellite comprises a body forming a support structure on which are fixed various equipment and instruments. Examples include platform equipment (propellant tanks, batteries, telemetry / remote control antennas) or payloads (measuring instruments, telecommunication antennas).
    [0003] The equipment and instruments are for the most part sensitive to shocks and vibrations. Shocks and vibrations, for a satellite, can occur especially during the launch of the satellite and when the satellite is operating in orbit. Indeed, for the launch of the satellite, the latter is placed in a launcher, on which it is removably attached. During the take-off phase, on the trajectory, then during the separation of the stages of the launcher, events produce shocks and vibrations. The shocks and vibrations of the launcher are transmitted to the satellite, then to the instruments and equipment propagating in the supporting structure. These shocks and vibrations, of high amplitude and low frequencies, may disrupt or even damage instruments and equipment. In addition, when the satellite is in orbit, shocks and vibrations, generally smaller amplitudes but higher frequencies, also occur, for example during the deployment of equipment and instruments or the launching of thrusters. These shocks and vibrations are also propagated in the carrier structure of the satellite to the instruments and equipment. It is interesting and sometimes necessary to put in place means to dampen shocks and vibrations and prevent their transmission between two elements assemble. This minimizes oversizing structures and equipment or improves the pointing accuracy of a payload. Shock and vibration problems can be bypassed in several ways, for example: By oversizing the elements to be assembled, but this solution is accompanied by an increase in weight and cost.
    [0004] 3031146 2 By installing insulation modules interfacing between the part to be insulated and a room propagating vibrations. For example, such modules are found between a satellite interface ring of the launcher and a satellite launcher interface ring. US Pat. No. 7,249,756 shows an example of such a module, comprising elastomeric parts for absorbing shocks and vibrations and metal parts for ensuring the rigidity of the module. However, such modules increase the congestion by being housed in a space between the two interface rings. They are therefore unsuitable for mounting instruments and equipment on the body of the satellite, where congestion is problematic. They also add weight to the set. As an additional piece to handle, they further complicate the assembly. By using damping fastening devices, called inserts, integrated in one of the elements to be assembled, in order to reduce the bulk. JP 2000-145889 discloses an example of such a fastener for assembling a load on a honeycomb plate. The fixing device comprises a lower portion forming a housing 15 for an insertion body, the inner walls of the housing being covered with bodies of viscoelastic material. The bottom piece is co-fired with the honeycomb plate. Then, the insertion body is placed in the housing, and a top piece closes the housing. The insertion body emerges partially out of the housing, so that the load can be fixed on it by bolting. During the relative movements between the filler and the honeycomb plate, the insertion body abuts against the inside walls of the housing, on the bodies of viscoelastic material, providing shock absorption and vibration. This type of isolation device has a small footprint, the load being in contact with the honeycomb plate without the interposition of a part. However, placing the fastener on the load and on the honeycomb plate by means of such a structure proves tedious. In addition, the stiffness of the insulation means depends inter alia on the surface of the bodies of viscoelastic material, so that the stiffness is limited by the dimensions of the housing formed by the lower part. There is therefore a need for a new damping fastening device 30 to overcome the aforementioned drawbacks. Thus, a first object of the invention is to propose a shock-absorbing fastening device that is easy to install, not requiring the qualification of a new laying technique. A second object of the invention is to propose a device for damping mount does not increase the size on the satellite. A third object of the invention is to provide a damping fastening device to have characteristics, such as stiffness, adaptable to the needs. A fourth object of the invention is to provide a damping fastening device that does not require any particular modification of existing equipment. A fifth object of the invention is to provide a damping fastening device that does not increase the mass or the integration costs.
    [0005] According to a first aspect, the invention proposes a damping fastening device between two elements to be assembled. The fixing device comprises in particular: a tubular inner part according to a fixing axis, intended to be rigidly fixed to a first element to be assembled, and comprising an outer lateral surface; a tubular outer part according to the fixing axis, hollow, intended to be rigidly fixed to the second element to be assembled and comprising an inner lateral surface, the inner part being housed in the outer part so that the outer surface of the inner part is vis-à-vis the inner surface of the outer part; an elastomer layer between the outer piece and the inner piece. The outer side surface of the inner piece comprises at least one irregular portion and the inner side surface of the outer piece comprises at least one irregular portion complementary to the irregular portion of the outer surface of the inner piece. On the other hand, the elastomer layer comprises a first side adhered to the irregular portion of the lateral outer surface of the inner part, and a second side, opposite to the first side, adhered to the irregular portion of the inner side surface of the inner part. the outer part. The elastomer layer, when viewed in section in a longitudinal plane comprising the attachment axis, comprises: on each side of the attachment axis, at least three so-called longitudinal portions, distributed in the direction of the attachment axis according to a predetermined pitch, at least one of the three longitudinal portions working opposite the two other portions in the direction of the longitudinal axis and at least two so-called transverse portions, working in a direction transverse to the axis of attachment, a first portion being located on a first side of the attachment axis and the second portion being located on the other side of the attachment axis.
    [0006] The device thus forms a damping insert, in particular for mounting equipment on the body of a satellite, or for effecting the interface between a satellite and its launcher, whose damping characteristics can be easily adapted in according to needs. In fact, since the elastomer layer is located on irregularities of the lateral surfaces of the internal and external parts, the geometry of the elastomer layer can be modified without modifying the overall geometry of the insert. In particular, the number, the pitch and the dimensions of the longitudinal portions and the transverse portions can be adapted. According to one embodiment, the irregular portion of the outer surface of the inner piece and the irregular portion of the inner surface of the outer piece comprise rings about the longitudinal direction. The elastomer layer adhered to these rings thus forms the longitudinal and transverse portions. By adapting the geometry of the rings, the geometry of the elastomer layer is also adapted. For example, the rings may be substantially perpendicular to the longitudinal direction and of rectangular shape. According to another embodiment, the irregular portion of the outer surface of the inner piece comprises at least one thread around the longitudinal direction, and the irregular portion of the inner surface of the outer piece comprises at least one additional thread of the inner thread. the inner part, and the elastomer layer covering the threads at least partially. Thus, by adapting the geometry of the threads, the geometry of the elastomer layer and thus the characteristics of the device are advantageously adapted according to the needs. The net shape further facilitates the assembly of the inner part in the outer part allowing screwing. The nets can take multiple forms. Rectangular or triangular nets may be mentioned.
    [0007] In the latter case, the transverse portions and the longitudinal portions of the elastomer layer are merged. Preferably, the inner part and the outer part are metal parts. Their physical properties are such that they provide good mechanical strength for applications, particularly in aeronautics, envisaged. In addition, the inner and outer parts 30 can be obtained by casting, or by 3D printing. When the device is at rest, the thickness of the elastomer layer, between its two faces, is preferably constant, so that the inner part is centered in the outer part, allowing better performance control.
    [0008] According to one embodiment, the elastomer layer is continuous in the longitudinal direction and around the longitudinal direction, so that the elastomer layer is in the form of a single piece of elastomeric material. The elastomer layer thus provides damping whatever the direction of stress. The inner part may include a bore, for example tapped, to allow its assembly to the first element simply by using screws. According to a second aspect, the invention provides a method of manufacturing the damping fastening device as set forth above, comprising the following steps: making a device blank comprising an inner part blank on which an outer surface is formed and an outer part blank on which an inner surface is formed, the inner surface of the outer part blank being opposite the outer surface of the inner part blank; Inserting an elastomer between the outer surface of the inner part blank and the inner surface of the outer part blank; adhesion of the elastomer on the one hand on the outer surface of the inner part blank and on the other hand on the inner surface of the outer part blank. The insertion step of the elastomer is for example an injection step.
    [0009] According to a first embodiment of the method, the manufacture of the device blank comprises the following operations: machining of the internal part blank, the external surface forming a thread, machining of the blank of the external part, the internal surface forming a thread-like thread, screwing the inner part blank into the outer part blank to obtain the device blank. According to a second embodiment of the method, the manufacture of the device blank comprises the following operations: simultaneous three-dimensional printing of the outer part blank and the inner part blank in position in the outer part blank manufacturing at least one bridge between the external part blank and the inner part blank ensuring the maintenance of their relative position.
    [0010] The method finally finally comprises a final step of machining the blank to the desired final dimensions of the device. According to a third aspect, the invention proposes an assembly comprising at least two elements assembled by means of at least one device as presented above, the external part being fixed rigidly to a first element, the inner part being fixed rigidly. on the second element. When the inner part comprises a bore, the second element is fixed rigidly to the inner part by means of a screw passing through the bore. In a first example, the first element is a carrier structure, such as the body of a satellite and the second element is a satellite equipment. In a second example, the first element is a launcher interface ring and the second element is a satellite interface ring. According to a fourth aspect, the invention proposes a method of assembling a support assembly as presented above, comprising a step of rigidly securing the external part of the fixing device on the first element and a fixing step rigid of the second element on the inner part of the fixing device. Other advantages will emerge in the light of the description of particular embodiments of the invention accompanied by the figures in which: FIG. 1 is a longitudinal sectional view of a first embodiment of a damping fastening device , housed in a first plate-like element; Figure 2 is a longitudinal sectional view of an outer part of the device of Figure 1; Figure 3 is a longitudinal sectional view of an inner part of the device of Figure 1; FIG. 4a is a longitudinal sectional view similar to that of FIG. 1, a second element being assembled on the first; The freeze 4b is a detail view of FIG. 4a; Figure 5a is a view similar to that of Figure 4a for a variant of the damping fastening device according to the first embodiment; Figure 5b is a detail view of Figure 5a; Figure 6a is a longitudinal sectional view of an inner part and an outer part of a damping fastening device according to a second embodiment; Figure 6b is a detail view of Figure 6a; Figure 7 is a first example of an assembly comprising two assembled elements; Figure 8 is a second example of an assembly comprising two assembled elements; Figures 9a to 9e each represent a step of a first embodiment of a method of manufacturing the damping fastening device; Figures 10a to 10d each represent a step of a second embodiment of a method of manufacturing the damping fastening device; Figure 11a is a longitudinal sectional view of the damping fastening device obtained according to a variant of the second embodiment of the manufacturing method; Figure 11b is a detail view of Figure 11a. In Figure 1, there is shown a damping fastening device 1, as a whole, for ensuring both the fixing and the filtration of vibrations between two elements, including a satellite. For example, a first element 2 is a carrier structure, such as a body, of the satellite, a vibration generator, and the second element 3 is an equipment, or a set of equipment and instruments, of the satellite to be isolated. vibrations. Only the carrier structure 2 is partially illustrated in Figure 1. It is for example a panel having a honeycomb structure. Such a fixing device 1 is also called insert. Such an insert makes it possible not to add substantially weight or to increase the space requirement, since it has just been housed in one of the elements to be assembled. The damping fastening device 1 comprises an internal part 4, of generally tubular shape of fixing axis A. The inner part 4 has an outer lateral surface 5, and extends longitudinally between two substantially flat transverse surfaces 6, 7. It is preferably metallic.
    [0011] In what follows, the term "longitudinal" and its variants designate a direction parallel to the attachment axis A; the adjective "transverse" and its variants designate any direction in a plane perpendicular to the axis A fixation.
    [0012] 3031146 8 The term "outside" should be understood as describing what is distant or turned in the opposite direction of the fixing axis A, whereas the term "inner" should be understood, on the contrary, as qualifying what is close or turned towards the axis A of fixation. A first transverse surface 6 of the inner part 4 is said to be upper, and is intended to be in contact with the satellite equipment 3 to be fixed. The second transverse surface 7 is then called lower. The adjectives "upper" and "lower" are taken here for purposes of simplifying the description with reference to the natural orientation of the figures, and should not be interpreted as implying any structural limitation.
    [0013] The inner part 4 further has a bore 8 symmetrical of revolution about the fixing axis A which, as will be explained later, is advantageously threaded. The outer wall 5 is irregular on at least one portion, that is to say that it has, in a longitudinal plane P comprising the fixing axis A, at least one relief 9.
    [0014] By relief, here is meant a recess followed by a projection, that is a recess on the outer surface towards the attachment axis A, followed in the direction of the attachment axis A. a protuberance on the outer surface 5 away from the attachment axis A. Each relief then forms in the direction of the attachment axis A at least three portions of the outer surface, at least one of the portions being oriented along the fastening axis A in a direction opposite to the other two. More precisely, for each relief of the outer surface, it is defined successively in the direction of the fastening axis A a first portion oriented along the fastening axis A in a first direction, a second portion oriented in the second direction opposite to the first, and a third portion oriented in the first direction.
    [0015] The fixing device 1 further comprises an external piece 11, of generally tubular shape, also with fixing axis A. The outer part 11 has an inner side surface 12. The outer part 11 also extends between two surfaces 13, 14 transverse, namely a first surface 13 said upper, may be in contact with the satellite equipment 2 and a second surface 14 30 said lower. The outer member 11 further has an outer side surface 15 which, as will be explained later, serves as an interface for attachment to the satellite panel 3. It is also preferably metallic.
    [0016] The diameter of the inner side surface 12 of the outer member 11 is greater than the diameter of the inner side surface of the inner member 4, so that the inner member 4 can be accommodated in the outer member 11, the surface 5 outer side of the inner part 4 being vis-à-vis the inner side surface 12 of the piece 11 5 external. More specifically, the inner lateral surface 12 of the outer part 11 also comprises at least one irregular portion, complementary to the irregular portion of the outer lateral surface of the internal part 4, so that the internal part 4 can be housed in the part 11, the outer side surface 5 of the inner member 4 facing the inner side surface 12 of the outer member 11. More specifically, in a longitudinal plane P comprising the fixing axis A, the outer part 11 comprises at least one relief 16 complementary to the relief 9 of the inner part 4, also extending 360 ° about the axis A of fixation. More specifically, when the relief 9 of the inner part 4 is, in the longitudinal direction, a hollow followed by a projection, then the relief 16 of the outer part 11 is a projection, that is to say that forms a protuberance on the inner sidewall 12 towards the attachment axis A, followed by a recess, i.e. it forms on the inner side surface 12 a recess opposite the A fixing axis; conversely, when the relief 9 of the inner part is a projection followed by a hollow, the relief 16 of the outer part 11 is a hollow followed by a projection. In addition, the relief 9 of the inner part 4 and the relief 16 of the outer part 11 are dimensioned so that they can be housed one inside the other. The dimensions of the inner part 4 and the outer part 11 are such that a gap is formed between the outer lateral surface of the inner part 4 and the inner side surface 12 of the outer part 11. This space may not be of constant dimensions, even when the device 1 is at rest, that is to say when it is not subjected to any effort. The device 1 then comprises damping means placed in this space, between the two reliefs 9, 16. The damping means comprise at least one layer 18 of elastomer. The layer 18 has a thickness defined between a first surface 19, said inner surface, adhered to the irregular portion of the outer lateral surface of the inner part 4 and a second surface 20, said outer surface, adhered to the irregular portion of the inner side surface 12 of the outer part 11. Preferably, but not necessarily, when the device 1 is at rest, the thickness of the elastomer layer 18 is constant, so that the behavior of the device 1 is symmetrical whatever the direction of the forces applied. The elastomer layer 18 extends continuously around the attachment axis A, that is to say that it completely fills, over 360 °, the space around the fixing axis A between the inner side surface 12 of the inner part 10 and the outer side surface 5 of the inner part 4. Preferably, the space, and therefore the elastomer layer 18, are centered on the fixing axis A. By "adhered" is meant here the assembly of the elastomer layer 18 on the inner part 4 and on the outer part 11 by any adhesion mechanism, that is to say that an intimate contact is formed on the one hand between the inner surface 19 of the elastomer layer 18 on the outer lateral surface of the inner part 4 and on the other hand between the outer surface of the elastomer layer 18 and the inner side surface 12 the outer part 11, so that the surfaces 19, 20 of the elastomer layer 18 do not move relative to the inner part 4 and the outer part 11. The adhesion can then be direct or made by means of another material, for example an adhesive. From the reliefs 9, 16, whatever the direction and the direction of the forces due to the vibrations, the elastomer layer 18 damps the vibrations, and the damping by the layer 18 of elastomer is adaptable according to the needs.
    [0017] Indeed, thanks to the reliefs 9, 16, the elastomer layer 18 always comprises portions working in tension and portions working in compression in a complementary manner. The operation of the fixing and damping device 1 will be explained with reference to embodiments.
    [0018] According to a first embodiment, illustrated in Figures 1 to 5a and 5b, the relief 9 of the inner part 4 is formed by a thread 21 its outer lateral surface, in the manner of a thread, and describing at least 360 ° around the fixing axis A. Alternatively, the reliefs 9 may be formed by a plurality of threads 21. Thus, when seen in longitudinal section in a plane P containing the fixing axis A as illustrated in FIG. 1, the thread 21 forms on the surface 5 external side of the internal part 4 irregularities in the form of a succession in the direction of the axis A fixing, recesses 22 and projections 23, and on both sides of the axis A of fixation. Similarly, the relief 16 of the outer member 11 is formed by at least one thread 24 on its inner side surface 12, in the manner of a tapping, and describing at least 360 ° 30 about the axis A fixing. Thus, when seen in longitudinal section in a plane P containing the fastening axis A as illustrated in FIG. 1, the thread 24 forms irregularities in the form of an internal surface 12 on the inner side surface 12. succession, in the direction of the axis A fixing, recesses 25 and projections 26, and on both sides of the axis A fixing. According to a first example of the first embodiment, the threads 21, 24 are of square or rectangular shape, so that the cross section of the recesses 22, 25 and 5 of the projections 23, 26 is also square or rectangular. The layer 18 of elastomer covers the threads 21, 24, so that the layer 18 of elastomer comprises two so-called transverse sections 27, whose thickness is defined in the transverse direction. A first transverse section 27 covers the top of the thread 24 of the outer part 11, that is to say covers the bottom of the recesses 22 of the inner part 4 and the end of the projections 26 of the outer part 11. The second cross section 27 covers the top of the net 21 of the inner part 4, that is to say covers the end of the projections 23 of the inner part 4 and the bottom of the recesses 25 of the outer part 11. The layer 18 of elastomer further comprises two so-called longitudinal sections 28, the thickness of which is defined in the longitudinal direction, connecting the transverse sections 27 to one another, following the reliefs 9, 16. When seen in section in a plane Longitudinal P comprising the fixing axis A, the elastomer layer 18 then comprises portions working longitudinally in tension and in compression opposite one another, and portions working in shear, whatever the direction of the forces applied. between the inner part 4 and the outer part 11. More specifically, always when seen in section in a longitudinal plane P, the longitudinal sections 28 form, on each side of the attachment axis A, longitudinal portions 28a, 28b succeeding in the longitudinal direction in a determined step. Each transverse portion 27 comprises, on one side of the axis A for fastening the first transverse portions 27a offset from one another in a slot in the transverse direction and on the other side of the second transverse portions 27b, also offset from each other. others in niche in the transverse direction. Thus, when the device 1 is biased in a longitudinal direction, the longitudinal sections 28 work longitudinally, in tension and in compression, and the transverse sections 27 work transversely in shear. More precisely, in this case, when viewed in a longitudinal plane P, if a longitudinal portion 28a of a first longitudinal section 28 is working in compression, then the following longitudinal portion 28b of the second longitudinal section 28 is working in tension, and vice versa. . With the reliefs 9, 16, there are always at least three longitudinal portions, at least one of which works longitudinally opposite the two others. For example, if a first portion 28a of a first section 28 is working in tension, then the following portion 28b in the longitudinal direction, of the second longitudinal section 28, works in compression, and the third portion 28a, of the first longitudinal section 28. , works in traction. Preferably, the device comprises at least four longitudinal portions 28a, 28b, two portions 28a of a first longitudinal section 28 working in a longitudinal direction and two portions 28b of the second longitudinal section working in the other longitudinal direction. The portions 27a, 27b transverse work in this case in shear.
    [0019] When the device 1 is biased in a transverse direction, the longitudinal sections 28 work in shear, and the transverse sections 27 work in tension and in compression. More specifically, considering a transverse plane P comprising the fixing axis A, when the device 1 is biased in a transverse direction, so that the transverse portions 27a on one side of the fastening axis A 15 work for example in traction, then the transverse portions 27b located on the other side of the fastening axis A work in compression, and vice versa. According to a second example of the first embodiment, the threads 21, 24 are of triangular shape, so that the cross section of the recesses 22, 25 and projections 23, 26 is also triangular. Thus, when seen in longitudinal section in a plane 20 comprising the fixing axis A, the recesses 22, 25 and the projections 23, 26 form a sawtooth pattern. The layer 18 of elastomer covering the threads 21, 24 then have at least two sections 29 inclined with respect to each other in a longitudinal plane P, each section 29 being oriented, according to its thickness, both in accordance with a longitudinal component and according to a transverse component. More specifically, when the device is seen in section in a longitudinal plane P, a first section 29 comprises portions 29a spaced from each other in the longitudinal direction and, but not necessarily, parallel to each other, and the second section 29 includes portions 29b also at a distance from one another and, but not necessarily, parallel to each other, the portions 29a of the first section 29 being inclined with respect to the portions 29b of the second section 29, so as to define, on each side of the fixing axis A, a sawtooth pattern. When the device 1 is biased in a longitudinal direction, a first section 29 works longitudinally in tension and transversely in shear, while the second section 29 works longitudinally in the opposite direction, that is to say in compression, and transversely in shear. More specifically, when the portions 29a of a first section 29 works in traction, then the portions 29b of the second section 29 works in compression, and vice versa. As previously, thanks to the reliefs 9, 16 formed by the threads 21, 24, there are always at least three portions 29a, 29b working longitudinally, with at least one of the three portions working longitudinally opposite the two other. For example, a first portion 29a of a first section 29 operates in tension, the second portion 29b in the longitudinal direction, of the second section 29, works in compression, and the third portion 29a in the longitudinal direction of the first section 29, works in traction.
    [0020] Thus, by counterbalancing the work in a direction of two portions 29a by at least one portion 29b working in the opposite direction, the non-linear behaviors are reduced. Preferably, the device comprises at least four portions 29a, 29b, namely two portions of each section 29, so as to always have two portions working in compression and two portions working in tension.
    [0021] When the device 1 is biased in a transverse direction, each inclined section 29 works in shear and in tension or in compression. More specifically, considering a transverse plane P comprising the fixing axis A, when under the effect of a bias in the transverse direction, the portions 29a, 29b of the sections 29 located on one side of the axis A of For example, the fasteners work in traction, while the portions 29a, 29b on the other side of the fastening axis A work in compression, and vice versa. Thus, irrespective of the direction of the forces due to vibrations, the elastomer layer 18 still works both in tension, in compression and in shear. The shape of the nets 21, 24 can be arbitrary. For example, the threads 21, 24 may be trapezoidal or rounded. By simply playing on the pitch of the threads 21, 24 and their number, it is possible to adjust the amount of material of the elastomer layer 18, and thus adjust the stiffness and the damping coefficient of the device 1. The Adjusting the pitch of the threads 21, 24 also makes it possible to play on the dimension of the recesses 22, 25 and projections 23, 26, so as to determine which direction the vibrations will be damped in preferentially or vice versa. restraint. The first embodiment of the device 1 for fixing and damping makes it possible in particular to maintain the external part 4 and the internal part 11 assembled one to the other by screwing, as will be seen later, even in case rupture of the layer 18 of elastomer. According to a second embodiment, the inner part 4 and the outer part 11 each comprise a plurality of reliefs 9, 16.
    [0022] The reliefs 9 of the inner part 4 are formed by symmetrical rings 30 of revolution, but not necessarily, around the fixing axis A, projecting on the lateral surface. Thus, the rings 30 form in themselves projections 31 and form between two successive rings 30 in the longitudinal direction of the recesses 32. In a longitudinal plane comprising the attachment axis A, the projections 31 and the recesses 32 are therefore 10 symmetrical with respect to the fixing axis A. Similarly, still according to the second embodiment, the reliefs 16 of the outer part 11 are formed by rings 33 symmetrical of revolution, but not necessarily, around the axis A of attachment, projecting on the inner surface surface 12 of the outer part 11. The rings 33 in themselves form projections 34 15 on the inner lateral surface 12 of the outer part 11 and form between two successive adjacent rings 33, in the longitudinal direction, depressions 35. According to the illustrated example, but not necessarily the rings 30, 33 are of square or rectangular cross-section and extend perpendicularly to the longitudinal direction, i.e. they extend transversely on the outer surface of the inner workpiece 4 and the surface 12 inside of the outer 11 piece. Thus, the layer 18 of elastomer extends between the projections 31, 34 and the recesses 32, 35 of the two parts 4, 11, so that when viewed in longitudinal section in a plane comprising the fixing axis A, the layer 18 of elastomer forms crenellations, on either side of the axis A fixation. More specifically, the elastomer layer 18 comprises a plurality of transverse sections, whose thickness is defined in a transverse direction, between the end of a projection 31 of the inner part 4 and the bottom of a hollow 35 of the outer part 11 and between the end of a projection 34 of the outer part 11 and the bottom of a hollow 32 of the inner part 4. The elastomer layer 18 also comprises a plurality of longitudinal sections 38, whose thickness is defined in the longitudinal direction, interconnecting the cross sections 37 in pairs. Thus, each projection 31, 34 is covered with two longitudinal sections 38 and a transverse section. When viewed in a longitudinal plane P comprising the fixing axis A, the transverse sections 37 thus form, on one side of the fastening axis A, transverse portions 37a, offset one from the other in the slot in the transverse direction, and on the other side of the attachment axis A, transverse portions 37b also offset from one another in square in the transverse direction. The longitudinal sections 38 form longitudinal portions 38a, 38b spaced from each other longitudinally 5 in a predetermined pitch, on each projection 31, 34, two longitudinal portions 38a, 38b and a portion 37a, 37b transverse are adhered . Thus, the behavior of the elastomer layer 18 is substantially similar to that described in the first embodiment with square or rectangular nets.
    [0023] When the device 1 according to this second embodiment is biased in a longitudinal direction, the transverse sections 37 work in shear and the longitudinal sections 38 work in tension and in compression. More precisely, when seen in section in a longitudinal plane P comprising the axis A, when a longitudinal portion 38a of a first longitudinal section 38 is working in compression, then the following longitudinal portion 38b in the longitudinal direction works in compression, And so on. When the device 1 is biased in a transverse direction, the transverse sections 37 work in tension and in compression, and the longitudinal sections 38 work in shear. More precisely, when viewed in section in a longitudinal plane P comprising the axis A, when a portion 37a of a transverse section 37, on a first side of the fixing axis A, is working in compression, then the portion 37b of the same cross section 37 on the other side of the axis A fixing works in tension, and vice versa. Thus, as before, regardless of the direction and direction of the forces 25 due to vibration, the elastomer layer 18 always works at the same time in traction, in compression and in tension. The shape of the rings 30, 33 is not necessarily square or rectangular, but may be triangular, trapezoidal or rounded. The stiffness and the damping coefficient of the device can thus be adjusted simply by adapting the number of rings 30, 33 and their distance between them, in order to obtain longitudinal portions 37a, 37b and 38a, 38b having the characteristics dimensional dimensions.
    [0024] The fixing and damping device 1 thus formed has great adaptability for a given space requirement. Indeed, the size of the fixing device 1 is given by the outer dimensions of the outer part 11. However, it is not necessary to modify these dimensions 5 to modify the characteristics of the device 1. In particular, by dimensioning the reliefs 9, 16, that is to say the threads 21, 24 or the rings 30, 33, it is possible to obtain different performances for the device 1 according to the desired applications. For example, as has already been described, it is possible to obtain on the layer 18 of elastomer as much material which works in traction and compression at each moment by forming as many portions which work in traction as portions who work in compression, and this at all times. Such an arrangement makes it possible in particular to minimize the non-linear behavior of the damping. It is also possible to promote the damping of the vibrations in the longitudinal direction or the transverse directions by adapting the dimension of the portions of the corresponding elastomer layer 18. By playing on the pitch between the portions 28a and 28b, 29a and 29b, 38a and 38b, the stiffness can again be adapted. Furthermore, the longitudinal dimension of the inner part 4 may be substantially equal to that of the outer part 11, so that the whole of the outer lateral surface 12 of the outer part 11 is opposite the surface 5 outer side of the inner part, as shown in Figures 1, 4a and 6b. However, it may be otherwise, and the longitudinal dimension of the inner part 4 can be quite lower than that of the outer part 11. Thus, it is still possible to adapt the number of portions of the elastomer layer 18, and thereby the stiffness and the damping coefficient of the device 1.
    [0025] It is also possible, for the same size, to modify the thickness of the elastomer layer 18 by modifying the outer diameter of the inner part 4 without modifying the outer dimensions of the device 1. Preferably, but not necessarily, only the outer lateral surface of the inner part 4 and the inner side surface 12 of the inner part 11 serve to support the elastomer layer 18 and participate in the damping, that is to say that their surfaces 6, 13 upper and 7, 14 lower are devoid of elastomeric element. However, the stiffness of the device 1 is substantially proportional to the total adhered surface of the elastomer layer 18. By dimensioning the reliefs 9, 16, the inner part 4 and the outer part 11, it is then possible to obtain the desired stiffness. Thus, by locating the elastomer layer 18 between the outer lateral surface 5 of the inner part 4 and the inner lateral surface 12 of the outer part 11, the modifications made to the reliefs 9, 16 make it possible to easily modify, without reviewing the outer dimensions of the device 1, the characteristics of the layer 18 of elastomer for a given device space 1. The device 1 is mounted between the panel 2 and the equipment 3 in the following manner.
    [0026] The device 1, comprising the inner part 4, the outer part 11 and the elastomer layer 18 rigidly connecting the two parts 4, 11, is placed in an opening on the panel 2 provided for this purpose. The outer lateral surface of the outer member 11 is then rigidly fixed to the panel 2 in the opening provided. For example, the diameter of the opening in the panel is greater than the outside diameter of the inner part 11.
    [0027] The gap between the outer side surface and the surface of the opening in the panel 2 is filled with a glue-like substance 39, providing the rigid attachment. The device 1 is then embedded in the panel 2. The equipment 3 is then rigidly attached to the internal part 4. For example, the equipment 3 comprises a tab 40 which bears on the upper surface 6 of the inner part 4. The tab 40 includes a bore, which is placed coaxially with the bore 8 in the inner part 4. A screw-type fastening means 41 is then inserted into the piercing of the lug 40 and the piercing 8 of the internal part 4, to cooperate with the tapping of the piercing 8 of the internal part 4. The equipment 3 is then rigidly fixed on the internal part 4. The device 1 thus makes it possible to ensure the rigid attachment between the panel 2 and the equipment 3 while offering a damping of the vibrations of the panel 2 to the equipment 3, or the reverse, by the layer 18 of elastomer. In practice, a plurality of devices 1 is used to ensure the attachment between the panel 2 and the equipment 3. For example, the devices 1 are distributed at the periphery of the equipment 3, and are arranged parallel to each other, that is, their fixing axes A are parallel, as illustrated in FIG. 7. As a variant, the devices 1 may be arranged to form an angle between them, that is to say that their fixing axes A are not parallel. For example, 3031146 18 in Figure 8, two devices 1 are arranged at 90 ° to allow to rigidly join two panel-type elements 2 by means of an intermediate plate 42. In another variant, the device 1 can be used to assemble interface rings between a launcher and a satellite. For example, the first element 2 is a launcher interface ring, mounted on a satellite body, and the second element 3 is a satellite interface ring, mounted on a launcher. It will now be described a method of manufacturing the device 1 for fixing and damping. As already indicated, the inner part 4 and the outer part 11 are preferably made of metal. One of the difficulties in the manufacturing process of the device 1 is to make sure that the relative position of the internal part 4 with respect to the outer part 11 is maintained so that the space between them respects the desired dimensioning of the part. layer 18 of elastomer. According to a first embodiment of the manufacturing method (FIGS. 9a to 9e), the inner part 4 and the outer part 11 are first machined each from a blank. In particular a first blank 4 ', intended to form the inner part 4, has an outer lateral surface 5' which is machined so as to have reliefs 9 '; a second blank 11 ', intended to form the outer piece 11, has an inner lateral surface 12' which is machined so as to have reliefs 16 'complementary to those 9' of the first blank 4 '. This first embodiment of the manufacturing method is particularly adapted to the device 1 described with reference to the first embodiment, in which the reliefs 9, 16 are formed by threads 21, 24. Thus, the lateral surface 5 'of the first blank is threaded to form a thread 21 'and the inner side surface 12' of the second blank 11 'is threaded to form a complementary thread 24'.
    [0028] Advantageously, means are provided for assembling and centering the first blank 4 'with the second blank 11' along the fastening axis A. For example, the first blank 4 'comprises at one end a conical head 43, and the second blank 11' comprises at one end a conical seat shoulder 44, complementary to the head 43.
    [0029] The first blank 4 'can then be screwed into the second blank 11' with their complementary threads 21 ', 24', until the head 43 is housed in the seat 44 with minimal or no play, ensuring the relative position between the two blanks 4 ', 11', in which a space 45 is formed between them.
    [0030] Thus, a blank 1 'is obtained, the dimensions of which are greater than that of the final device 1'. An elastomer can then be injected into the space 45. For example, the head 43 of the first blank 4 'comprises channel openings 46 for the pressure injection of the elastomer, to form the elastomer layer 18 . The elastomer then fills the space 45. A step of adhesion of the elastomer to the inner wall 5 'of the first blank 4' and the inner side wall 12 'of the second blank 11' is provided. Adhesion is obtained for example by heating the assembly. The elastomer is thus fixed rigidly to the blanks 4 ', 11'.
    [0031] Alternatively, before screwing the first blank 4 'into the second blank 11', the thread 21 'of the first blank is covered with an elastomeric tube which adheres to the outer side wall 5'. Then, the first blank 4 'thus covered is screwed with force into the second blank 11'. An additional bonding step allows the elastomeric tube to adhere to the inner side wall 12 'of the first blank. Finally, the blank 1 'of device 1 is machined so as to obtain the desired final dimensions of the device 1 for the upper surfaces 6, 13, the lower surfaces 7, 14 and the outer lateral surface of the outer part 11. In particular, the head 43 and the seat 44 are cut.
    [0032] According to a second embodiment of the manufacturing method (FIGS. 10a to 10d), a first blank 4 'of the internal part 4 is manufactured simultaneously with a second blank 5' of the internal part 5, in the same step, during of which the relative position between the two blanks respects the final relative position between the inner part 4 and the desired outer part 5.
    [0033] Thus, according to a first example, the blank 1 'of the device comprising the first blank 4' and the second blank 11 'is manufactured by three-dimensional printing, and more particularly by the so-called "ALM" ("Additive Layer Manufacturing") technique. . The first blank 4 'and the second blank 11' are then obtained simultaneously. As before, the first blank 4 'has on the outer surface 5' of the reliefs 9 'complementary reliefs 16' on the inner surface 12 'of the second blank 11'. Bridges 47 of material are formed on the blank 1 complete at both ends between the two blanks 4 ', 11' to maintain their relative positioning, a space 45 being formed between them.
    [0034] In a variant, the two blanks 4 ', 11' forming the complete blank 1 'and the bridges 47 may be obtained by casting. The elastomer is injected between the bridges 47 in the space 45 between the two blanks 4 ', 11' so as to cover their reliefs 9 ', 16' and adhere to the outer surface 5 'of the first blank 4' and the inner surface 12 'of the second blank 11'. The blank 1 'of device 1 has dimensions greater than those of the final device 1, so that, as previously, the blank 1' is machined to obtain the desired final dimensions of the device 1, the bridges 47 being then 10 eliminated. The fact that the first blank 4 'and the second blank 11' are not to the final dimensions of the inner part 4 and the outer part 11 makes it possible to inject the elastomer under pressure into the space 45 between the blanks 4 ' , 11 'avoiding the risk of material rupture. In particular, the thickness of the outer part 11, that is to say the dimension between its inner surface 12 and its outer surface, may have to be small to respect the dimensioning of the elastomer layer 18 and the reliefs. 9, 16, while respecting a maximum size. By forming the second blank 11 'thicker, the risk of rupture at the time of injection under pressure is reduced.
    [0035] Furthermore, by injecting the elastomer under pressure, it is possible to maintain this pressure within the elastomer layer 18. The latter is then compressed between the inner part 4 and the outer part 11. By adapting this pressure within the layer 18 of elastomer, it is possible to obtain a device 1 whose stiffness is greater than that of the known inserts. Indeed, the higher the pressure, the less elastomer layer 18 can stretch, increasing the stiffness of the device 1. However, it is conceivable to directly produce blanks 4 ', 11' to the final dimensions of the internal part 4 and the outer part 11, connected together by bridges 47 of material as before, between on the one hand the upper surface 6 of the inner part 4 and the upper surface 13 of the outer part 11 and on the other hand part between the lower surface 7 of the inner part 4 and the lower surface 14 of the outer part 11 (Figures 11a and 11b). In this case, once the elastomer has been injected and adhered to form the elastomer layer 18, the bridges 47 are broken.
    [0036] The device 1 can then be assembled between the two elements 2, 3 of the satellite as previously described. The device 1 is therefore a single piece to handle for the assembly of the two elements 2, 3, making the assembly easier. The number of pieces to be stored is also decreased, making management easier and therefore less expensive. The device 1 thus formed also allows great adaptability while maintaining a given size by sizing on the one hand the space 45 between the blanks 4 ', 11' and on the other hand the reliefs 9, 16 according to the desired performance.
    权利要求:
    Claims (20)
    [0001]
    REVENDICATIONS1. Device (1) for damping fastening between two elements (2, 3) to be assembled, the fixing device comprising: a tubular internal part (4) along an axis (A) for attachment, intended to be rigidly fixed to an element (3) ) to be assembled, and comprising an outer lateral surface (5); a tubular outer part (11) along the hollow fixation axis (A) intended to be rigidly fixed to another element (2) to be assembled and comprising an inner lateral surface (12), the internal piece (4) being housed in the outer piece (3) so that the outer surface of the inner piece is vis-à-vis the inner surface of the outer piece; a layer (18) of elastomer between the outer piece (11) and the inner piece (4), the fixing device being characterized in that the outer lateral surface (5) of the internal piece (4) comprises at least one an irregular portion and the inner lateral surface (12) of the outer piece (11) comprises at least one irregular portion complementary to the irregular portion of the outer surface (5) of the inner piece (4), the layer (18) of elastomer comprising a first face (19) adhered to the irregular portion of the lateral outer surface (5) of the internal piece (4), and a second face (20), opposite to the first face (19), adhered to the portion irregularly of the lateral inner surface (12) of the outer piece (11), and in that the layer (18) of elastomer, when seen in section in a longitudinal plane (P), comprising the fixing axis (A). , comprises: on each side of the axis (A) of attachment, at least three porti ss (28a, 28b, 38a, 38b, 29a, 29b) said longitudinal, distributed in the direction of the axis (A) of attachment in a predetermined pitch, at least one of the three portions (28a, 28b, 38a, 38b, 29a, 29b) working opposite the other two portions in the direction of the longitudinal axis (A) and at least two portions (27a, 27b, 37a, 37b, 29a, 29b) said transverse, working in one direction transverse to the axis (A) of attachment, a first portion (27a, 29a, 37a) being located on a first side of the axis (A) of attachment and the second portion (27b, 29b, 37b) being located on the other side of the axis (A) of attachment. 3031146 23
    [0002]
    The device (1) according to claim 1, wherein the irregular portion of the outer surface (5) of the inner workpiece (4) and the irregular portion of the inner surface (12) of the outer workpiece (11) comprise rings (30, 33) around the longitudinal direction. 5
    [0003]
    3. Device (1) according to claim 2, wherein the rings (30, 33) are substantially perpendicular to the longitudinal direction and of rectangular shape.
    [0004]
    4. Device (1) according to any one of the preceding claims, wherein the irregular portion of the outer surface (5) of the inner part (4) comprises at least one thread (21) around the longitudinal direction, and wherein the irregular portion of the inner surface (12) of the outer piece (11) comprises at least one thread (24) complementary to the thread (21) of the inner piece (4), and the layer (18) of elastomer covering the threads (21, 24) at least partially. 15
    [0005]
    5. Device (1) according to claim 4, wherein the threads (21, 24) are rectangular.
    [0006]
    6. Device (1) according to claim 4, wherein the threads (21, 24) are triangular. 20
    [0007]
    7. Device (1) according to any one of the preceding claims, wherein the piece (4) internal and the piece (11) external are metal parts.
    [0008]
    8. Device (1) according to any one of the preceding claims, wherein, when the device is at rest, the thickness of the layer (18) of elastomer, between its two faces (19, 20), is constant.
    [0009]
    The device (1) according to any one of the preceding claims, wherein the elastomeric layer (18) is continuous in the longitudinal direction and around the longitudinal direction, so that the elastomer layer (18) present in the form of a single piece of elastomeric material.
    [0010]
    10. Device (1) according to any one of the preceding claims, wherein the piece (4) internal comprises a bore (8). 3031146 24
    [0011]
    11. A method of manufacturing the damping fastening device according to any one of the preceding claims, comprising the following steps: manufacturing a blank (1 ') of device comprising a blank (4') of part (4) internal on which an outer surface (5 ') is formed and an outer blank (11') on which an inner surface (12 ') is formed, the inner surface (11') of the blank (11 ') outer piece (11) facing the outer surface (5 ') of the blank (4') of the inner piece (4); inserting an elastomer between the outer surface (5 ') of the blank (4') of the inner workpiece (4) and the inner surface (12 ') of the blank (11') of the outer workpiece (11); Adhesion of the elastomer on the one hand on the outer surface (5 ') of the blank (4') of the inner part (4) and on the other hand on the inner surface (12 ') of the blank ( 11 ') of outer part (11).
    [0012]
    12. The manufacturing method according to claim 11, wherein the step of inserting the elastomer is an injection step.
    [0013]
    A manufacturing method according to claim 11 or claim 12, wherein the manufacture of the device blank (1 ') comprises the following operations: machining the blank (4') of the workpiece (4) internally, the external surface (5 ') forming a thread, machining the blank (11') of the external workpiece (11), the internal surface (12 ') forming a complementary tapping of the thread, screwing the blank (4 ') internal piece (4) in the blank (11') of part (11) external to obtain the blank (1 ') device (1). 25
    [0014]
    The manufacturing method according to claim 13, wherein the manufacture of the device blank (1 ') comprises the following operations: simultaneous three-dimensional printing of the blank (11') of the outer piece (11) and of the blank (4 ') of the internal part (4) in position in the blank (11') of the outer part (11), manufacture of at least one bridge (47) between the blank (11 ') outer piece (11) and the blank (4 ') of internal part (4) ensuring the maintenance of their relative position. 3031146 25
    [0015]
    15. Manufacturing method according to any one of claims 11 to 14, comprising a final step of machining the blank (1 ') to the desired final dimensions of the device (1). 5
    [0016]
    16. An assembly comprising at least two elements assembled by means of at least one device (1) according to any one of claims 1 to 11, the piece (11) external being rigidly attached to a first element (2), the piece (4) internal being fixed rigidly on the second element (3). 10
    [0017]
    17. An assembly according to claim 16, wherein the internal part (4) comprises a bore (8), the second element (3) being rigidly fixed to the internal part (4) by means of a screw passing through the bore. (8).
    [0018]
    18. An assembly according to claim 16 or claim 17, wherein the first element (2) is a carrier structure, such as the body of a satellite and the second element (3) is a satellite equipment.
    [0019]
    19. An assembly according to any one of claims 17 to 18, wherein the first element (2) is a launcher interface ring and the second element (3) is a satellite interface ring.
    [0020]
    20. A method of assembling a support assembly according to any one of claims 16 to 19, comprising a step of rigid attachment of the outer part (11) of the device (1) for attachment to the first element (2) and a rigid fixing step of the second element (3) on the part (4) internal of the device (1) fixing.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3237762B1|2019-02-06|Device for the shock-absorbing attachment of two elements to be assembled, method for producing such a device, set of two elements assembled using such a device, and assembly method
    EP2527781B1|2014-02-19|Joining element for a body made of a composite material of a military penetrating projectile
    EP0454545A1|1991-10-30|Device for the temporal mechanical assembly and for its fast separation of an ejecting object attached to a support
    EP3589550B1|2021-03-31|Method and device for the connection and linear separation of two elements stuck together
    EP0651228B1|1997-06-04|Armour module for ballistic protection of a structure
    EP0454546B1|1993-11-18|Device for temporal holding of an object to a support, with a traction calibrated breaking neck
    EP2448818B1|2015-09-02|System for attaching a propeller drive
    FR3021625A1|2015-12-04|FLEXIBLE CONNECTION BETWEEN THE FLOOR STRUCTURE AND THE HULL STRUCTURE OF AN AIRCRAFT.
    FR3013684A1|2015-05-29|SATELLITE CARRIER STRUCTURE COMPRISING A DAMPING LINK DEVICE
    FR2829662A1|2003-03-14|SUSPENSION FOR ELECTRONIC MODULE TO OPERATE DURING AND AFTER SEVERE IMPACTS
    FR2974566A1|2012-11-02|TEMPORARY BONDING METHOD BETWEEN TWO PIECES, SUCH AS TWO STAGES OF A SPATIAL LAUNCHER, AND A SET OF TWO TEMPORARYLY CONNECTED PIECES
    EP0988446B1|2004-04-07|Device for anchoring a member activating an adjustable nozzle
    EP2715100B1|2015-04-08|System for reducing the dynamics of the mobile segment of a deployable rocket motor nozzle
    WO2004088150A2|2004-10-14|Launcher assembly comprising a fixing device capable of isolating an equipment from a dynamic or pyrotechnic environment
    FR2927139A3|2009-08-07|Vibration attenuating device for gearbox control module of motor vehicle, has sleeve and rings are elastic, such that sleeve and rings carry out dampening connection between inertia mass and fixation shaft
    WO2021122660A1|2021-06-24|Intermediate deformation layer with adjustable macroscopic stiffness for bonded assembly
    EP1217326A1|2002-06-26|Ignition device for explosive charge and explosive charge comprising such a device
    EP3023733A1|2016-05-25|Pyrotechnical separator comprising a bump absorbing element
    FR3078952A1|2019-09-20|WORKING ORBIT SYSTEM FOR A SATELLITE
    WO2022008386A1|2022-01-13|Damped machined primary structure for a spacecraft, satellite incorporating this primary structure and method for manufacturing such a satellite
    FR3021079A1|2015-11-20|DECOUPLER FOR ANTI-VIBRATION MOUNTING DEVICE AND ANTI-VIBRATION FIXING DEVICE COMPRISING SUCH A DECOUPLER
    WO2020165128A1|2020-08-20|Device comprising a set of vibration absorbers, and vehicle equipped with such a device
    EP1285182A1|2003-02-26|Variable or non-variable amplitude vibrating wave damping device
    FR2957192A1|2011-09-09|ELECTRONIC POWER MODULE FOR AN ACTUATOR FOR AN AIRCRAFT
    同族专利:
    公开号 | 公开日
    JP2018508715A|2018-03-29|
    CN107002727A|2017-08-01|
    EP3237762B1|2019-02-06|
    ES2722024T3|2019-08-07|
    EP3237762A1|2017-11-01|
    JP6286109B1|2018-02-28|
    US20180266461A1|2018-09-20|
    FR3031146B1|2017-01-13|
    WO2016102792A1|2016-06-30|
    US10400804B2|2019-09-03|
    CN107002727B|2018-12-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4973208A|1989-08-31|1990-11-27|Gauron Richard F|Inset panel fastener with floating member|
    JP2000145889A|1998-11-09|2000-05-26|Nec Eng Ltd|Fastening structure of on-board mounted apparatus|
    US2074340A|1933-04-17|1937-03-23|Transit Res Corp|Vehicle springing system|
    US3975007A|1974-05-20|1976-08-17|Ace Controls, Inc.|Resilient mounting structure|
    US4922573A|1989-04-14|1990-05-08|Grumman Aerospace Corporation|Compression fitted bushing installation|
    DE4413743A1|1994-04-20|1995-10-26|Hilti Ag|Fastening anchor|
    US5551661A|1994-10-11|1996-09-03|Bunker; Donald D.|Automotive transmission mount|
    JPH0972379A|1995-09-07|1997-03-18|Nec Eng Ltd|Vibration insulation fastening mechanism|
    DE19625176A1|1996-06-24|1998-01-08|Upat Max Langensiepen Kg|Fastening element for non-resting loads|
    US5876023A|1996-09-18|1999-03-02|Lord Corporation|Vibration isolation insert for aircraft floor planels and the like|
    US6601818B1|2000-10-12|2003-08-05|Lord Corporation|Tilting mount with integral flange|
    DE20105013U1|2001-03-22|2002-08-01|Fischer Artur Werke Gmbh|Anchor sleeve for fixing the injection|
    JP2003104229A|2001-09-28|2003-04-09|Mazda Motor Corp|Suspension cross member fitting bushing and suspension cross member fitting structure|
    DE102004019917A1|2004-04-21|2005-11-17|Zf Friedrichshafen Ag|Warehouse for a motor vehicle|
    US7249756B1|2006-02-01|2007-07-31|Csa Engineering, Inc.|Low-profile, multi-axis, highly passively damped, vibration isolation mount|
    JP5210018B2|2008-03-28|2013-06-12|本田技研工業株式会社|Mount bush|
    EP2333154B1|2009-12-09|2016-02-24|Vossloh-Werke GmbH|Screw-in dowel for rail fixings|
    JP4865907B1|2010-12-29|2012-02-01|ジェイ・バス株式会社|Honeycomb panel with combined honeycomb piece structure|EP3372390B1|2017-03-09|2021-11-10|AIRBUS HELICOPTERS DEUTSCHLAND GmbH|A method of repairing a sandwich component having a core element that is arranged between a first and a second cover plate|
    US11084230B1|2018-03-29|2021-08-10|Kineticure, Llc|Bonded nutplate rapid cure system|
    EP3564542A1|2018-05-03|2019-11-06|A. Raymond et Cie|Shipping bolt spacer and method of use thereof|
    CN109555960B|2018-11-30|2020-11-24|长光卫星技术有限公司|Variable-rigidity flexible damping support leg|
    DE102020103436A1|2020-02-11|2021-08-12|Airbus Operations Gmbh|Method and device for attaching a cabin component to a primary structure|
    EP3892885A1|2020-04-09|2021-10-13|Nederlandse Organisatie voor toegepast- natuurwetenschappelijk Onderzoek TNO|Device for mounting a load to a carrier, assembly, vehicleand methods|
    WO2022008386A1|2020-07-08|2022-01-13|Airbus Defence And Space Sas|Damped machined primary structure for a spacecraft, satellite incorporating this primary structure and method for manufacturing such a satellite|
    法律状态:
    2015-12-30| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-01| PLSC| Search report ready|Effective date: 20160701 |
    2016-12-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-12-18| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-13| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210806 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1463334A|FR3031146B1|2014-12-24|2014-12-24|DEVICE FOR FASTENING AMORTIZATION BETWEEN TWO ELEMENTS TO BE ASSEMBLED, METHOD FOR MANUFACTURING SUCH DEVICE, ASSEMBLY OF TWO ELEMENTS ASSEMBLED BY SUCH A DEVICE, AND METHOD OF ASSEMBLY|FR1463334A| FR3031146B1|2014-12-24|2014-12-24|DEVICE FOR FASTENING AMORTIZATION BETWEEN TWO ELEMENTS TO BE ASSEMBLED, METHOD FOR MANUFACTURING SUCH DEVICE, ASSEMBLY OF TWO ELEMENTS ASSEMBLED BY SUCH A DEVICE, AND METHOD OF ASSEMBLY|
    US15/537,232| US10400804B2|2014-12-24|2015-11-24|Device for the shock-absorbing attachment of two elements to be assembled, method for producing such a device, set of two elements assembled using such a device, and assembly method|
    JP2017533849A| JP6286109B1|2014-12-24|2015-11-24|Shock absorber mounting device for two components to be assembled, method for manufacturing the device, set of two components assembled using the device, and method for assembling|
    EP15817452.4A| EP3237762B1|2014-12-24|2015-11-24|Device for the shock-absorbing attachment of two elements to be assembled, method for producing such a device, set of two elements assembled using such a device, and assembly method|
    PCT/FR2015/053192| WO2016102792A1|2014-12-24|2015-11-24|Device for the shock-absorbing attachment of two elements to be assembled, method for producing such a device, set of two elements assembled using such a device, and assembly method|
    ES15817452T| ES2722024T3|2014-12-24|2015-11-24|Buffer fixing device between two elements to be assembled, manufacturing procedure of such a device, set of two assembled elements with the help of such a device and assembly procedure|
    CN201580066321.4A| CN107002727B|2014-12-24|2015-11-24|Damping attachment device, manufacturing method, with device assemble set group and assemble method|
    [返回顶部]