Aircraft laminate part drilling fixture

Abstract

The utility model belongs to mechanical clamping technical field discloses aircraft laminated piece drilling clamping device, this aircraft laminated piece drilling clamping device includes drill jig frame, vertical board, baffle, hanging plate and fixed part, and vertical board is provided with positioning hole, and vertical board and the drill jig plate between drill jig frame are used to accommodate laminated piece, and baffle is installed in vertical board, and is used for receiving laminated piece. Hanging plate is located above baffle and is installed in vertical board, and hanging plate is hung in the crossbeam of drill jig frame, fixed part is worn in positioning hole and can contact with laminated piece, and fixed part moves along its axial movement, so that laminated piece can be tightly closed on drill jig plate. Laminated piece is fixed immovably relative to drill jig plate, and is firmly clamped, and is not easy to come loose, and it is convenient to carry out drilling to laminated piece through drill jig plate.

Description

Technical Field

[0001] This utility model relates to the field of mechanical clamping technology, and in particular to a hole-making and clamping device for aircraft laminated parts. Background Technology

[0002] In the manufacturing process of aircraft, the most important connection methods for aircraft assembly are riveting and bolting. Both of these connection methods require mechanical drilling, so drilling is an essential part of the assembly process.

[0003] Aircraft assembly laminates consist of multiple test plates connected by paper tape. Holes are drilled into these laminates using drilling equipment. However, the number of holes is large, and the precision and quality requirements are extremely high. If the laminates are not properly clamped and fixed during the drilling process, they may move relative to the drill template, or even loosen and fall off, affecting the drilling process.

[0004] Therefore, there is an urgent need for a hole-making and clamping device for aircraft laminated parts to solve the above problems. Utility Model Content

[0005] The purpose of this utility model is to provide a hole-making clamping device for aircraft laminated parts, which is firmly clamped, not easy to loosen, and facilitates hole making of laminated parts through a drilling template.

[0006] To address the aforementioned problems in the existing technology, this utility model adopts the following technical solution:

[0007] An aircraft laminated component hole-making and clamping device, comprising:

[0008] Drill jig frame;

[0009] The upright plate has positioning holes, and the space between the upright plate and the drilling template of the drilling jig is used to accommodate the stacked parts;

[0010] A baffle plate is installed on the upright plate and is used to support the stacked components;

[0011] A hanging plate, which is located above the baffle and installed on the upright plate, and is hung on the crossbeam of the drilling jig;

[0012] A fastener passes through the positioning hole and is able to contact the stacked component. The fastener moves along its axial direction so that the stacked component can be pressed against the drill template.

[0013] Preferably, there are multiple positioning holes, and the multiple positioning holes are spaced apart along the length direction of the upright plate.

[0014] Preferably, the aircraft laminated component hole-making and clamping device further includes a positioning component, the mounting plate has a fixed hole and a connecting hole that are connected together, the upright plate is slidably inserted through the connecting hole, and the positioning component is sequentially inserted through the fixed hole and any of the positioning holes, so that the upright plate is fixed relative to the mounting plate.

[0015] Preferably, the hanging plate has a handle protruding from it, the handle has the fixing hole, and the connecting hole extends along the length of the upright plate to the top end face of the handle.

[0016] Preferably, the aircraft laminate hole-making and clamping device further includes a locking pin, the positioning member has an installation hole, the locking pin passes through the installation hole and abuts against the side wall of the handle, so that the positioning member is fixed relative to the handle.

[0017] Preferably, the fastener includes a mounting portion and an adjusting portion, the mounting portion being threadedly connected to any of the positioning holes, the adjusting portion being rotatably connected to the mounting portion, and the adjusting portion being capable of moving along the axial direction of the mounting portion to abut against the stacked component.

[0018] Preferably, the aircraft laminate hole clamping device further includes a locking member, which passes through the baffle and is connected to any of the positioning holes.

[0019] Preferably, the hanging plate has a protruding limiting plate, the limiting plate is spaced apart from the upright plate and there is a limiting area between them, the limiting area is used to accommodate the crossbeam.

[0020] Preferably, the aircraft laminate hole clamping device further includes a fastener, the limiting plate has a connecting hole, the fastener passes through the connecting hole and abuts against the crossbeam, so that the limiting plate can be fixed relative to the crossbeam.

[0021] Preferably, the aircraft laminated component hole-making clamping device further includes an adjusting member, and the mounting plate is provided with an adjusting hole. The adjusting member is rotatably inserted through the adjusting hole and abuts against the crossbeam. The adjusting member can move linearly along its axial direction to adjust the distance between the mounting plate and the crossbeam.

[0022] The beneficial effects of this utility model are as follows:

[0023] The aircraft laminated component drilling and clamping device provided by this utility model has a positioning hole on the upright plate. The space between the upright plate and the drill template of the drill jig is used to accommodate the laminated component. A baffle is installed on the upright plate and serves to support the laminated component. A hanging plate is located above the baffle and installed on the upright plate, and is hung on the crossbeam of the drill jig. A fixing member passes through the positioning hole and can contact the laminated component. The fixing member moves along its axial direction so that the laminated component can be pressed tightly against the drill template. The laminated component is fixed relative to the drill template, securely clamped, and not easily loosened, facilitating drilling of the laminated component through the drill template. Attached Figure Description

[0024] Figure 1 A schematic diagram of the structure of the aircraft laminated component hole-making and clamping device provided in this embodiment of the utility model;

[0025] Figure 2 A schematic diagram of the structure of the upright plate, hanging plate, and baffle provided in an embodiment of this utility model;

[0026] Figure 3 A side view of the upright plate, hanging plate, and baffle provided for an embodiment of this utility model;

[0027] Figure 4 A schematic diagram of the structure of the baffle provided in an embodiment of this utility model;

[0028] Figure 5 This is a schematic diagram of the structure of the hanging plate provided in an embodiment of the present utility model.

[0029] Figure label:

[0030] 1. Drilling formwork; 11. Drilling template; 12. Crossbeam;

[0031] 2. Vertical plate; 21. Positioning holes;

[0032] 3. Baffle;

[0033] 4. Mounting plate; 41. Fixing hole; 42. Connecting hole; 43. Adjustment hole;

[0034] 5. Fasteners; 51. Mounting parts; 52. Adjustment parts;

[0035] 6. Positioning components;

[0036] 7. Handle;

[0037] 8. Locking components;

[0038] 9. Limiting plate; 91. Connecting hole;

[0039] 10. Fasteners;

[0040] 20. Adjusting components. Detailed Implementation

[0041] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0042] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0043] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0044] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0045] like Figures 1-5 As shown, in this embodiment, the aircraft laminated component drilling and clamping device includes a drill jig frame 1, a vertical plate 2, a baffle 3, a hanging plate 4, and a fixing member 5. The vertical plate 2 has a positioning hole 21, and the space between the vertical plate 2 and the drill template 11 of the drill jig frame 1 is used to accommodate the laminated component. The baffle 3 is installed on the vertical plate 2 and is used to support the laminated component. The hanging plate 4 is located above the baffle 3 and installed on the vertical plate 2, and is hung on the crossbeam 12 of the drill jig frame 1. The fixing member 5 passes through the positioning hole 21 and can contact the laminated component. The fixing member 5 moves along its axial direction so that the laminated component can be pressed against the drill template 11.

[0046] For example, the laminated part to be processed is composed of multiple test plates stacked together. The drill jig 1 has a crossbeam 12. Along the vertical height direction of the drill jig 1, the crossbeam 12 includes an upper crossbeam and a lower crossbeam. The drill template 11 is located between the upper crossbeam and the lower crossbeam and is fixedly installed on the drill jig 1. The drill template 11 serves as a standard hole-making component and is used to make holes in conjunction with the hole-making equipment. The drill template 11 is provided with multiple standard holes of different sizes. According to the hole-making processing requirements of different sizes of the laminated part, the hole-making equipment and the drill template 11 are used to make holes in the laminated part.

[0047] The upright plate 2 is located between the crossbeam 12 and the drilling template 11. The laminated part to be processed is placed between the upright plate 2 and the drilling template 11. The baffle 3 is installed below the upright plate 2 and is used to support the laminated part between the upright plate 2 and the drilling template 11. The hanging plate 4 is installed above the upright plate 2 and spaced apart from the baffle 3. It is hung on the upper crossbeam of the drilling jig frame 1 by the hanging plate 4, so that the laminated part is in a suitable position on the drilling template 11. The fixing member 5 is a tightening bolt, and the positioning hole 21 is a threaded hole. The fixing member 5 is threadedly engaged with the positioning hole 21. The fixing member 5 can rotate relative to the positioning hole 21 and can move linearly along the axis of the positioning hole 21, so that the fixing member 5 presses the laminated part against the drilling template 11. The laminated part is fixed relative to the drilling template 11, and the clamping is firm and not easy to loosen, which facilitates drilling holes in the laminated part through the drilling template 11.

[0048] The operation procedure of the aircraft laminated component drilling and clamping device is as follows: First, assemble the upright plate 2, baffle 3, and hanging plate 4, and place the laminated component on the baffle 3. Second, pre-install the fixing component 5 according to the position of the laminated component, that is, the fixing component 5 is installed on the upright plate 2 through the positioning hole 21. Then, hang the hanging plate 4 on the crossbeam 12 of the drill jig frame 1, so that the laminated component is placed between the drill template 11 and the upright plate 2. Rotate the fixing component 5, and the fixing component 5 will press the laminated component tightly against the drill template 11, so that the laminated component is fixed relative to the drill template 11. Finally, connect the drilling equipment to the drill template 11, and drill holes in the laminated component through the drill template 11 according to the processing parameters. After drilling is completed, rotate the fixing component 5 in the opposite direction, the fixing component 5 separates from the laminated component, the hanging plate 4 separates from the crossbeam 12 of the drill jig frame 1, and the laminated component with completed drilling is removed.

[0049] In this embodiment, there are two upright plates 2, which are parallel and spaced apart. There are four fasteners 5, which are respectively installed in the positioning holes 21 of the upright plates 2. The four fasteners 5 correspond to the four corner positions of the stacked component, providing multi-point positioning and further improving the fixing effect of the stacked component relative to the drill template 11.

[0050] Furthermore, referring to Figure 1 and Figure 2 There are multiple positioning holes 21, which are spaced apart along the length of the vertical plate 2.

[0051] Depending on the position of the stacked components, the fixing members 5 can be installed in any of the positioning holes 21. In this embodiment, the four fixing members 5 are respectively installed in the four positioning holes 21 corresponding to the two upright plates 2, so that the four fixing members 5 can correspond to the four corners of the stacked components, ensuring that the fixing members 5 provide a certain supporting force to the stacked components with the help of the upright plates 2. The hanging plate 4 and the baffle 3 can both be installed on the upright plate 2 through any of the positioning holes 21, so that the height of the hanging plate 4 and the baffle 3 relative to the upright plate 2 in the vertical height direction can be adjusted, especially the height of the baffle 3, so that the baffle 3 can be aligned with the bottom of the drill template 11.

[0052] Furthermore, referring to Figures 1 to 5 The aircraft laminated component hole clamping device also includes a positioning component 6. The hanging plate 4 has a fixed hole 41 and a connecting hole 42 that are connected. The upright plate 2 is slidably inserted through the connecting hole 42. The positioning component 6 is sequentially inserted through the fixed hole 41 and any positioning hole 21 so that the upright plate 2 is fixed relative to the hanging plate 4.

[0053] The positioning component 6 is set as a pin, and the axial direction of the fixing hole 41 is perpendicular to the axial direction of the connecting hole 42. After the upright plate 2 passes through the connecting hole 42 of the hanging plate 4, the positioning component 6 passes through the fixing hole 41 of the hanging plate 4 and connects with any positioning hole 21 of the upright plate 2, so that the upper and lower ends of the upright plate 2 can contact the upper and lower crossbeams of the drilling jig frame 1 respectively, ensuring that the installation is in place.

[0054] Furthermore, continue to refer to Figure 1 and Figure 2 The hanging plate 4 has a handle 7 protruding from it. The handle 7 has a fixing hole 41 and a connecting hole 42 extending along the length of the upright plate 2 to the top end face of the handle 7.

[0055] The handle 7 and the hanging plate 4 are integrally formed. The upright plate 2 passes through the connecting hole 42 of the handle 7 and the connecting hole 42 of the hanging plate 4, which is connected to the connecting hole 42 of the handle 7. It is then connected to the positioning hole 21 of the hanging plate 4 by the positioning member 6, which passes through the fixing hole 41 of the handle 7, so that the upright plate 2 is fixed relative to the hanging plate 4. At the same time, it is convenient for the operator to hold the handle 7 and hang the hanging plate 4 on the upper crossbeam 12 of the drilling jig frame 1. The handle 7 not only serves to connect the hanging plate 4 and the upright plate 2, but also provides a lifting part for the operator.

[0056] Furthermore, referring to Figure 2 The aircraft laminated component hole clamping device also includes a locking pin. The positioning member 6 has a mounting hole, and the locking pin passes through the mounting hole and abuts against the side wall of the handle 7 so that the positioning member 6 is fixed relative to the handle 7.

[0057] After the positioning component 6 securely connects the upright plate 2 and the hanging plate 4, a locking pin passes through the mounting hole at the tail of the positioning component 6, fixing the positioning component 6 relative to the hanging plate 4 along its own axis, ensuring that the upright plate 2 will not move relative to the hanging plate 4 and that the installation is secure. Conversely, the positioning component 6 can be disassembled by simply pulling out the locking pin, making disassembly and replacement convenient.

[0058] Furthermore, referring to Figure 2 and Figure 3 The fastener 5 includes a mounting part 51 and an adjusting part 52. The mounting part 51 is threaded to any positioning hole 21, and the adjusting part 52 is rotatably connected to the mounting part 51. The adjusting part 52 can move along the axial direction of the mounting part 51 to press against the stacked parts.

[0059] Mounting part 51 is configured as a tightening bolt, positioning hole 21 is provided with internal thread, and adjusting part 52 is configured as a pressure block with threaded hole. Before installation, mounting part 51 and adjusting part 52 are respectively located on both sides of the upright plate 2 and correspond to positioning hole 21. Mounting part 51 is threaded to positioning hole 21 and extends out. Then, adjusting part 52 is threaded to the tail of mounting part 51. By screwing on adjusting part 52, adjusting part 52 can abut against the stacked part, so that fixing part 5 can support and position the stacked part.

[0060] Furthermore, referring to Figure 2 and Figure 4 The aircraft laminated component hole clamping device also includes a locking element 8, which passes through the baffle 3 and is connected to any positioning hole 21.

[0061] The locking element 8 is a locking bolt, and the baffle 3 has an L-shaped structure. A threaded hole is provided on one side wall of the baffle 3. The locking element 8 is threadedly connected to the threaded hole of the baffle 3 and passes through the positioning hole 21. Then, a locking nut is used to lock the locking element 8, fixing the baffle 3 firmly to the vertical plate 2, ensuring it is securely installed and not easily loosened. The locking element 8 can be connected to any of the positioning holes 21 on the vertical plate 2 to adjust the height of the baffle 3 relative to the vertical plate 2, ensuring that the baffle 3 is aligned with the bottom of the drill template 11.

[0062] Furthermore, referring to Figures 1-3 The aircraft laminated component hole-making and clamping device also includes a fastener 10. The mounting plate 4 has a protruding limiting plate 9, which has a connecting hole 91. The limiting plate 9 and the upright plate 2 are spaced apart and have a limiting area between them. The limiting area is used to accommodate the crossbeam 12. The fastener 10 passes through the connecting hole 91 and abuts against the crossbeam 12 so that the limiting plate 9 can be fixed relative to the crossbeam 12.

[0063] The hanging plate 4 and the limiting plate 9 are integrally formed, and the fastener 10 is set as a mounting bolt. The hanging plate 4 is hung on the crossbeam 12 of the drill jig frame 1 through the limiting plate 9. Under the action of the limiting plate 9 and the vertical plate 2, the crossbeam 12 of the drill jig frame 1 is limited. The hanging plate 4 is pressed against the upper end face of the crossbeam 12. Then, the fastener 10 is threaded to the connecting hole 91 and abuts against the crossbeam 12, so that the crossbeam 12 abuts against the vertical plate 2 and is relatively fixed, thus fixing the position of the clamping device.

[0064] Furthermore, referring to Figure 2 and Figure 3 The aircraft laminated component hole clamping device also includes an adjusting component 20. The mounting plate 4 is also provided with an adjusting hole 43. The adjusting component 20 is rotatably inserted through the adjusting hole 43 and abuts against the crossbeam 12. The adjusting component 20 can move linearly along its axial direction to adjust the distance between the mounting plate 4 and the crossbeam 12.

[0065] The adjusting component 20 is set as an adjusting bolt, and the adjusting hole 43 is provided with an internal thread. The adjusting component 20 is threadedly connected to the adjusting hole 43 and moves along its axial direction to abut against the end face of the crossbeam 12. After the hanging plate 4 is hung on the crossbeam 12, the adjusting component 20 is rotated to finely adjust the height of the hanging plate 4 relative to the crossbeam 12 in the vertical direction, so that the stacked component is in a suitable position on the drilling template 11, which facilitates drilling holes in the stacked component through the drilling template 11.

[0066] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A hole-making and clamping device for aircraft laminated parts, characterized in that, include: Drill jig frame (1); The upright plate (2) has a positioning hole (21) and the drilling template (11) of the drilling jig frame (1) is used to accommodate the stacked parts; A baffle (3) is installed on the vertical plate (2) and is used to support the stacked components; Hanging plate (4), the hanging plate (4) is located above the baffle (3) and installed on the upright plate (2), and the hanging plate (4) is hung on the crossbeam (12) of the drilling jig (1); The fixing member (5) passes through the positioning hole (21) and can contact the stacked member. The fixing member (5) moves along its axial direction so that the stacked member can abut against the drill template (11).

2. The aircraft laminated component hole-making and clamping device according to claim 1, characterized in that, There are multiple positioning holes (21), and the multiple positioning holes (21) are spaced apart along the length direction of the upright plate (2).

3. The aircraft laminated component hole-making and clamping device according to claim 2, characterized in that, The aircraft laminated component hole clamping device also includes a positioning component (6). The hanging plate (4) has a fixed hole (41) and a connecting hole (42) that are connected. The upright plate (2) is slidably inserted through the connecting hole (42). The positioning component (6) is sequentially inserted through the fixed hole (41) and any of the positioning holes (21) so that the upright plate (2) is fixed relative to the hanging plate (4).

4. The aircraft laminated component hole-making and clamping device according to claim 3, characterized in that, The hanging plate (4) has a handle (7) protruding from it. The handle (7) has a fixing hole (41) and the connecting hole (42) extends along the length of the upright plate (2) to the top end face of the handle (7).

5. The aircraft laminated component hole-making and clamping device according to claim 4, characterized in that, The aircraft laminate hole clamping device also includes a locking pin. The positioning member (6) has an installation hole. The locking pin passes through the installation hole and abuts against the side wall of the handle (7) so that the positioning member (6) is fixed relative to the handle (7).

6. The aircraft laminated component hole-making and clamping device according to claim 2, characterized in that, The fastener (5) includes a mounting part (51) and an adjusting part (52). The mounting part (51) is threaded to any of the positioning holes (21). The adjusting part (52) is rotatably connected to the mounting part (51) and can move along the axial direction of the mounting part (51) to abut against the stacked member.

7. The aircraft laminated component hole-making and clamping device according to claim 2, characterized in that, The aircraft laminate hole clamping device further includes a locking member (8), which passes through the baffle (3) and is connected to any of the positioning holes (21).

8. The aircraft laminated component hole-making and clamping device according to claim 1, characterized in that, The hanging plate (4) is provided with a limiting plate (9), the limiting plate (9) and the upright plate (2) are spaced apart and there is a limiting area between them, the limiting area is used to accommodate the crossbeam (12).

9. The aircraft laminated component hole-making and clamping device according to claim 8, characterized in that, The aircraft laminated component hole clamping device also includes a fastener (10). The limiting plate (9) has a connecting hole (91). The fastener (10) passes through the connecting hole (91) and abuts against the crossbeam (12) so that the limiting plate (9) can be fixed relative to the crossbeam (12).

10. The aircraft laminated component hole-making and clamping device according to claim 1, characterized in that, The aircraft laminated component hole clamping device also includes an adjusting component (20), and the mounting plate (4) is also provided with an adjusting hole (43). The adjusting component (20) is rotatably inserted through the adjusting hole (43) and abuts against the crossbeam (12). The adjusting component (20) can move linearly along its axial direction to adjust the distance between the mounting plate (4) and the crossbeam (12).

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