• 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:
    The invention relates to a tool for extracting a plate (22) flush with a surface (14) of a wall, characterized in that the tool comprises: - a temporary and activatable connection system which comprises a first surface ( 56) configured to be pressed against the plate (22), - at least two rods, - at one end of each rod, a shoe (42) configured to bear against the surface (14) of the wall, - the rods being positioned so that in operation the pads (42) are in contact with the surface (14) of the wall when the first surface (56) of the temporary and activatable connection system is pressed against the plate (22), the screwing the rods causing the separation of the temporary connection system and activatable relative to the surface (14) of the wall.
    公开号:FR3041893A1
    申请号:FR1559429
    申请日:2015-10-05
    公开日:2017-04-07
    发明作者:Christophe Menard
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TOOL FOR EXTRACTING A PLATE FLUSHING TO AN OUTER WALL OF A
    The invention relates to a tool for extracting a plate flush with an outer wall of an aircraft.
    Some equipment of an aircraft is positioned within the outer surface of the fuselage. This is the case for example probes used to measure the static pressure. According to one configuration, the outer surface of the fuselage comprises a recess closed by a plate in which such a probe is positioned. This recess comprises at the periphery a bearing surface shifted inwardly of the fuselage relative to the outer surface of the fuselage against which the plate is plated. The offset between the bearing surface and the outer surface of the fuselage is determined so that the plate is flush with the outer surface of the fuselage. If necessary, at least one wedge is interposed between the bearing surface of the recess and the plate.
    The plate is attached to the bearing surface of the recess by a plurality of screws.
    To optimize the aerodynamics of the aircraft, a bead of caulk is provided around the plate, in the groove delimited by the bearing surface, the edge of the plate and the edge of the fuselage surrounding the recess. In addition, a layer of sealant is also provided between the plate and the bearing surface or the wedge (s).
    When operating the aircraft, when it is necessary to access the probe to ensure its maintenance for example, it is necessary to unscrew the screws. However, because of the presence of the bead and the sealant layer, the plate remains attached to the fuselage despite the removal of the screws. According to a first operating mode, the end of a sharp tool is inserted into the bead of mastic to loosen the plate by levering. This first operating mode is not satisfactory because the risk of damage to the fuselage with the tool is relatively high.
    According to a second operating mode, the plate is peeled off by pushing it from inside the aircraft. This second procedure is not satisfactory because it is necessary to disassemble many elements to access the probe and the risk of damage to the probe are high.
    Also, the present invention aims to overcome the disadvantages of the prior art. For this purpose, the invention relates to a tool for extracting a plate flush with a surface of a wall. The tool is characterized in that it comprises: a body, a temporary and activatable linking system which is connected to the body and which has a first surface configured to be pressed against the plate, a command to activate or deactivate the system of temporary connection and activatable, at least two rods each having at least one threaded portion configured to screw into a tapping of the body, at one end of each rod, a pad which has a contact surface configured to bear against the surface of the wall, the rods being positioned so that in operation the pads are in contact with the surface of the wall when the first surface of the temporary and activatable connection system is pressed against the plate.
    In the case of a plate flush with the outer surface of the fuselage of an aircraft, this tool removes the plate from outside the fuselage, without risk of damage to the outer surface of the fuselage.
    Advantageously, the temporary and activatable connection system is a suction cup.
    According to another feature, the body threads have axes perpendicular to the first surface of the temporary connection system and activatable. Preferably, the axes of the threads are positioned equidistant from a longitudinal axis perpendicular to the first surface of the temporary connection system and activatable and passing through the center of said first surface, said axes of the threads being regularly distributed about said longitudinal axis.
    Advantageously, each rod comprises a section with a shape facilitating pivoting of the rod. According to one embodiment, each rod comprises a star-shaped head.
    According to another characteristic, at least the contact surface of each pad is made of a material limiting the risk of damaging the surface of the wall.
    Preferably, each pad is connected to the rod by a connection configured to allow at least one rotational movement along the axis of rotation of the rod between the pad and the rod. Other features and advantages will become apparent from the following description of the invention, a description given by way of example only, with reference to the appended drawings in which:
    FIG. 1 is a perspective view of an aircraft,
    FIG. 2 is a sectional view of a portion of the fuselage of an aircraft illustrating a probe positioned in a recess closed by a plate,
    FIG. 3 is a perspective view of a tool for extracting a plate which illustrates an embodiment of the invention,
    Figures 4A and 4B are perspective views of the tool before and after removal of a plate.
    In Figure 1, there is shown in 10 an aircraft. As illustrated in FIG. 2, this aircraft comprises a fuselage 12 with an outside surface 14. The aircraft 10 also comprises a probe 16 positioned outside the fuselage 12.
    The fuselage 12 comprises a recess 18 in which the probe 16 is positioned and which is delimited by a peripheral edge 20.
    This recess 18 is closed by a plate 22.
    To receive the plate 22, the recess 18 comprises peripherally a bearing surface 24 which is shifted inwardly of the fuselage relative to the outer surface 14 of the fuselage so that the plate 22 is flush with the outer surface 14 of the fuselage 12 If necessary, at least one shim 26 is interposed between the bearing surface 24 and the plate 22.
    The plate 22 is fixed to the fuselage 12 by a series of screws 28 which pass through the plate 22 and are screwed into the bearing surface 24. The screws 28 are distributed around the periphery of the plate 22.
    Once mounted, there remains between the edge of the plate 22 and the peripheral edge 20 of the recess 18 a game which is filled by a cord of material 30 to limit the impact on the aerodynamics of the aircraft. By way of example, the bead of material 30 is a PR type putty.
    According to one embodiment, a layer of mastic is interposed between the plate 22 and the bearing surface 24 and / or the shim 26.
    When the plate 22 must be removed for example to access the probe 16, the screws 28 are unscrewed. Despite the removal of the screws 28, the plate 22 remains secured to the fuselage due to the presence of the cord of material 30.
    In FIGS. 3, 4A and 4B, a tool 32 is shown for extracting the plate 22.
    This tool 32 comprises: a body 34, a suction cup 36 integral with the body 34 and configured to temporarily fasten to the plate 22 by a suction phenomenon, a control 38 to activate or deactivate the suction cup 36, at least two rods 40 which each comprise at least one threaded portion configured to be screwed into the body 34, at one end of each rod 40, a pad 42 configured to bear against the outer surface 14 of the fuselage 12.
    According to one embodiment, each rod 40 comprises a threaded rod 46 which comprises at a first end a head 48 and at a second end a connection 50 with the pad 42. The head 48 comprises a section 44 which has a shape configured to make rotate the rod 40. In one configuration, the head 48 has a star shape. Other solutions may be envisaged to facilitate the pivoting of the rods 40. According to another embodiment, the rod 40 comprises a section with at least one flat part for pivoting the rod 40.
    The link 50 is configured to allow at least one rotational movement along the axis of rotation of the threaded rod 46 between said threaded rod 46 and the pad 42. Thus, when the rods 40 pivot, the pads 42 remain stationary relative to the outer surface 14 of the fuselage 12.
    Preferably, the link 50 is a ball joint. According to a configuration, the second end of the threaded rod 46 comprises a spherical head positioned in a spherical housing of the pad 42.
    The pad 42 comprises a planar contact surface 52. Preferably, at least the contact surface 52 is of a material limiting the risk of damage to the outer surface 14 of the fuselage. According to a first embodiment, the entire pad 42 is made of a material limiting the risk of damage to the outer surface 14 of the fuselage. According to a second embodiment, the pad 42 comprises a coating made of a material limiting the risk of damaging the outer surface 14 of the fuselage, said coating being applied against the contact surface 52. By way of example, the limiting material the risk of damage to the outer surface 14 of the fuselage is polytetrafluoroethylene.
    The suction cup 36 comprises a base 54 with a first surface 56 approximately flat and operatively oriented towards the outer surface 14 of the fuselage 12 and a second surface 58 opposite the first surface 56.
    For the rest of the description, the first surface 56 is called the suction surface.
    The suction cup 36 is configured to occupy a first deactivated state in which the suction cup 36 is not secured to the plate 22 and a second activated state in which the suction cup 36 is temporarily connected to the plate 22 and can not detach of the plate 22.
    According to one embodiment, the suction surface 56 has a disc shape whose diameter is smaller than the smallest dimension of the plate 22. Whatever its geometry, the suction surface 56 has a section smaller than the section of the plate 22 so that the entire suction surface 56 is in contact with the plate 22.
    The suction cup 36 also includes a handle 60 which overcomes the second surface 58. In one configuration, the control 38 is positioned on the second surface 58 of the suction cup.
    According to one embodiment, the control 38 comprises a lever 62 rotatable between a raised position visible in Figure 3 which corresponds to the deactivated state of the suction cup 36 and a lowered position visible in Figures 4A and 4B which corresponds to the activated state of the suction cup 36.
    The body 34 is connected by a rigid connection to the suction cup 36.
    The body 34 comprises a tapping 64 for each rod 40. These tapped holes 64 are configured to allow the threaded portion of the rods 40 to be screwed on. Advantageously, the tappings 64 are oriented perpendicular to the suction surface 56 of the suction cup 36.
    The threads 64 have axes positioned equidistant from a longitudinal axis L perpendicular to the suction surface 56 and passing through the center of said suction surface 56. The axes of the threads 64 are regularly distributed around the longitudinal axis L. This configuration makes it possible to limit the occurrence of a moment and to obtain a pulling force perpendicular to the plate 22.
    The distance between the axes of the tappings 64 is configured so that the pads 42 are positioned outside the plate 22, against the outer surface 14 of the fuselage 12 when the suction surface 56 of the suction cup 36 is plated. against the plate 22.
    According to a configuration, the tool 32 comprises two rods 40. In this case, the body 34 comprises a bar 66 with two threads 64 diametrically opposite to the longitudinal axis L.
    According to an embodiment visible in FIG. 3, the bar 66 is connected by a screw 68 to the handle 60 of the suction cup 36.
    The procedure for removing the plate 22 with the tool 32 is as follows:
    At first, all the screws 28 are unscrewed.
    Following, the suction cup 36 is pressed against the plate 22 so that the entire suction surface 56 is in contact with the plate 22 and does not cover orifices of the plate 22, and that the pads 42 are arranged at outside the plate 22, in front of the outer surface 14 of the fuselage 12.
    When correctly positioned, the suction cup 36 is activated by lowering the lever 62, as illustrated in FIG. 4. As a result, the tool 32 is secured to the plate 22.
    Following, the threaded rods 46 are rotated, simultaneously or in a coordinated manner with the heads 48. The direction of rotation of the threaded rods 46 is chosen so that for each of them, the rotation of the threaded rod 46 causes the spacing of the pad 42 relative to the tapping 64 of the body 34. As soon as the pads 42 bear against the outer surface 14, the rotation of the threaded rods 46 causes the suction cup 36 to exert on the plate 22 a tearing force which tends to spread the plate 22 of the fuselage 12, as shown in Figure 4B.
    Of course, the invention is not limited to the embodiments described above. Thus, in the case of a metal part, the suction cup 36 may be replaced by an electromagnet or by any temporary and activatable connection system, configured to occupy an active state in which the connection system secures the plate 22 to the tool 32 and a deactivated state in which the plate 22 is not secured to the tool 22. The tool 32 provides the following advantages: a time saving insofar as it is not necessary to disassemble elements to the inside the fuselage to push it from inside the recess.
    A reduction in the risk of damage to the fuselage, the probe and the plate itself so that it can be reassembled.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Tool for extracting a plate (22) flush with a surface (14) of a wall, characterized in that the tool comprises: a body (34), a temporary and activatable connection system which is connected to the body ( 34) and having a first surface (56) configured to be pressed against the plate (22), a control (38) for activating or deactivating the temporary and activatable linking system, at least two rods (40) each having at least one threaded portion configured to thread into a tapping (64) of the body (34), at one end of each shank (40), a shoe (42) having a contact surface (52) configured to bear against the surface (14) of the wall, the rods being positioned so that in operation the pads (42) are in contact with the surface (14) of the wall when the first surface (56) of the temporary connection system and activatable is pressed against the plate (22).
    [2" id="c-fr-0002]
    2. Tool according to claim 1, characterized in that the temporary connection system and activatable is a suction cup (36).
    [3" id="c-fr-0003]
    3. Tool according to claim 1 or 2, characterized in that the threads (64) of the body have axes perpendicular to the first surface (56) of the temporary connection system and activatable.
    [4" id="c-fr-0004]
    4. Tool according to claim 3, characterized in that the axes of the threads (64) are positioned equidistant from a longitudinal axis (L) perpendicular to the first surface (56) of the temporary connection system and activatable and passing through the center of said first surface (56), said axes of the threads (64) being evenly distributed about said longitudinal axis (L).
    [5" id="c-fr-0005]
    5. Tool according to one of the preceding claims, characterized in that each rod (40) comprises a section (44) with a shape facilitating pivoting of the rod (40).
    [6" id="c-fr-0006]
    6. Tool according to the preceding claim, characterized in that each rod (40) comprises a head (48) in the form of a star.
    [7" id="c-fr-0007]
    7. Tool according to one of the preceding claims, characterized in that at least the contact surface (52) of each pad (42) is of a material limiting the risk of damaging the surface (14) of the wall .
    [8" id="c-fr-0008]
    8. Tool according to one of the preceding claims, characterized in that each pad (42) is connected to the rod (40) by a connection configured to allow at least one rotational movement along the axis of rotation of the rod ( 40) between the pad (42) and the rod (40).
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    FR3041893B1|2018-03-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3207503A|1962-07-03|1965-09-21|Martin Marietta Corp|Holding or clamping apparatus|
    US3712106A|1968-07-24|1973-01-23|Raymond P Wolgast|Shaping tool for planar sheets|
    US6722179B1|2003-01-30|2004-04-20|Miracle Industries, Inc.|Dent puller|
    US20120324722A1|2011-06-27|2012-12-27|Hon Hai Precision Industry Co., Ltd.|Disassembly device|EP3587281A1|2018-06-27|2020-01-01|The Boeing Company|Enhanced rig check and leak detection of aircraft doors|
    CN111002244A|2019-12-10|2020-04-14|友达光电有限公司|Material taking equipment and method thereof|
    CN111604854B|2020-05-28|2021-12-03|广东电网有限责任公司|Fuse extracting tool|
    法律状态:
    2016-10-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
    2017-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559429|2015-10-05|
    FR1559429A|FR3041893B1|2015-10-05|2015-10-05|TOOL FOR EXTRACTING A FLATPLATE PLATE TO AN OUTER WALL OF AN AIRCRAFT|FR1559429A| FR3041893B1|2015-10-05|2015-10-05|TOOL FOR EXTRACTING A FLATPLATE PLATE TO AN OUTER WALL OF AN AIRCRAFT|
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