CN216706815U - Clamping device and processing equipment suitable for aircraft skin laminated structure - Google Patents
Clamping device and processing equipment suitable for aircraft skin laminated structure Download PDFInfo
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- CN216706815U CN216706815U CN202220016137.6U CN202220016137U CN216706815U CN 216706815 U CN216706815 U CN 216706815U CN 202220016137 U CN202220016137 U CN 202220016137U CN 216706815 U CN216706815 U CN 216706815U
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Abstract
The utility model relates to the technical field of aircraft manufacturing, and discloses a clamping device suitable for an aircraft skin laminated structure. The control module can control the clamping module to clamp the aircraft skin laminated structure, the clamping module comprises clamping assemblies capable of being magnetically adsorbed, at least two groups of clamping assemblies are arranged, and an area clamped between two adjacent groups of clamping assemblies on the aircraft skin laminated structure is a hole making area of the aircraft skin laminated structure. The control module electricity is connected in clamping component, and control module is used for magnetizing and demagnetizing clamping component to and give aircraft skin laminated structure demagnetization, and control module can also be used for adjusting clamping component's magnetic force size, adjusts the clamp force, in order effectively to guarantee the clamp to aircraft skin laminated structure, the hole limit burr of skin binding face department produces when preventing the system hole, effectively restraines the smear metal and gets into between the skin stromatolite, still provide a processing equipment, including foretell clamping device who is applicable to aircraft skin laminated structure.
Description
Technical Field
The utility model relates to the technical field of aircraft manufacturing, in particular to a clamping device and machining equipment suitable for an aircraft skin laminated structure.
Background
The hole making on the skin laminated structure is a key link in the process of aircraft assembly, and a temporary fastening process is generally required before the hole making, so that the gap of the skin binding surface is eliminated, the hole making burrs at the binding surface are reduced, and cutting scraps are prevented from entering between skin layers. Furthermore, in the process of drilling the skin lamination structure, if the lamination is not guaranteed to be clamped, cutting chips can enter between the laminations, and therefore the quality of skin sealing assembly is affected.
Currently, the method of temporarily fastening the aircraft skin laminated structure mainly adopts a method of arranging piercing clips at certain distance positions before hole making, and then performing hole making at other positions, but the method easily causes stress on the preassembled nail holes during hole making, so that the stress concentration of the preassembled nail holes or the deformation of the preassembled holes occur. In addition, because the piercing clip temporarily fastens the skin structure, separation between lamination abutting surfaces is also likely to occur at a position away from the piercing clip, resulting in hole edge burrs between laminations and allowing chips to enter between skin layers.
Therefore, a clamping device and a processing device suitable for an aircraft skin laminated structure are needed to solve the above problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a clamping device suitable for an aircraft skin laminated structure, which can clamp the aircraft skin laminated structure, prevent the separation of skin binding surfaces, avoid the generation of hole edge burrs between laminated layers, effectively inhibit cuttings from entering the space between skin laminated layers and ensure the assembly quality of an aircraft.
As the conception, the technical scheme adopted by the utility model is as follows:
the clamping device suitable for the aircraft skin laminated structure comprises a clamping module and a control module, wherein the control module can control the clamping module to clamp the aircraft skin laminated structure;
the clamping module comprises clamping assemblies capable of being magnetically adsorbed, at least two groups of the clamping assemblies are arranged, and the area clamped between two adjacent groups of the clamping assemblies on the aircraft skin laminated structure is a hole making area of the aircraft skin laminated structure;
the control module is electrically connected with the clamping assembly, and is used for magnetizing and demagnetizing the clamping assembly and demagnetizing the aircraft skin laminated structure, and the control module can also be used for adjusting the magnetic force of the clamping assembly.
Optionally, the clamping assembly includes an electro-permanent magnet piece and a permeable magnet piece respectively disposed on two sides of the aircraft skin laminated structure, the electro-permanent magnet piece is electrically connected to the control module, and the electro-permanent magnet piece can adsorb the permeable magnet piece to move in a direction close to the electro-permanent magnet piece, and clamp the aircraft skin laminated structure between the electro-permanent magnet piece and the permeable magnet piece.
Optionally, a plurality of the electro-permanent magnetic pieces are provided, the curvatures of first abutting surfaces of the plurality of electro-permanent magnetic pieces are the same or different, and the first abutting surface is a surface where the electro-permanent magnetic piece abuts against the aircraft skin laminated structure;
the magnetic-permeable pieces are arranged in a plurality of numbers, the curvatures of second abutting surfaces of the magnetic-permeable pieces are the same or different, and the second abutting surfaces are surfaces of the magnetic-permeable pieces abutting against the aircraft skin laminated structure.
Optionally, the electric permanent magnet piece includes a first housing, a first abutting piece and an electric permanent magnet piece body, the first abutting piece is disposed on the first housing and can abut against the aircraft skin laminated structure, the first abutting piece is provided with the first abutting surface, the electric permanent magnet piece body is disposed in the first housing and is electrically connected to the control module, and the electric permanent magnet piece body can generate magnetic force for adsorbing the magnetic piece to clamp the aircraft skin laminated structure.
Optionally, the shape of first casing is the cuboid, the length of first casing is X, and 160mm is less than or equal to X and is less than or equal to 200mm, the width of first casing is Y, and 160mm is less than or equal to Y and is less than or equal to 200mm, the height of first casing is Z, and 70mm is less than or equal to Z and is less than or equal to 90mm, first butt piece set up in the face that long limit and the broadside place of first casing.
Optionally, the magnetically permeable member is a plate-shaped structure capable of being processed into any angle, the length of the plate-shaped structure is L, L is greater than or equal to 160mm and less than or equal to 200mm, the width of the plate-shaped structure is W, W is greater than or equal to 160mm and less than or equal to 200mm, the thickness of the plate-shaped structure is H, H is greater than or equal to 9mm and less than or equal to 11mm, and the second abutting surface is a surface where a long side and a wide side of the magnetically permeable member are located.
Optionally, the curvature and size of the first and second abutment surfaces are the same.
Optionally, the supporting portion further comprises a first supporting member, the magnetic permeable member is disposed on the first supporting member, the first supporting member can move along with the magnetic permeable member when the magnetic permeable member is adsorbed by the permanent magnetic member, and can also drive the magnetic permeable member to move when the permanent magnetic member is not adsorbed by the permanent magnetic member.
Optionally, the support portion further comprises a second support for supporting the electro-permanent magnet in position abutting the aircraft skin laminate structure.
The utility model also aims to provide processing equipment, which can prevent the generation of hole edge burrs at the joint surface of the skin during the hole making process, effectively inhibit chips from entering between skin laminations and ensure the assembly quality of the airplane.
As the conception, the technical scheme adopted by the utility model is as follows:
there is provided a machining apparatus comprising a hole making device and the above-mentioned clamping device for an aircraft skin laminated structure, the hole making device being configured to make a hole in the hole making region after the clamping module clamps the aircraft skin laminated structure.
The utility model has the beneficial effects that:
the utility model provides a clamping device suitable for an aircraft skin laminated structure. The control module can control the clamping modules to clamp the aircraft skin laminated structure, the clamping modules comprise clamping assemblies capable of being attracted magnetically, at least two groups of the clamping assemblies are arranged, and the area clamped between two adjacent groups of the clamping assemblies on the aircraft skin laminated structure is a hole making area of the aircraft skin laminated structure. The control module electricity is connected in clamping component, and control module is used for magnetizing and demagnetizing clamping component to and give aircraft skin laminated structure demagnetization, and control module can also be used for adjusting clamping component's magnetic force size, adjusts the clamp force, in order effectively to guarantee the clamp tight to aircraft skin laminated structure, prevent follow-up system hole in-process, the hole edge burr of skin binding face department produces, effectively restrain the smear metal and get into between the skin stromatolite, guarantee aircraft assembly quality.
The utility model has the beneficial effects that:
the processing equipment provided by the utility model can avoid the generation of hole edge burrs at the skin binding surface during hole making, effectively inhibit cuttings from entering between skin laminations and ensure the assembly quality of an airplane.
Drawings
Fig. 1 is a schematic structural diagram of a clamping device suitable for an aircraft skin laminate structure according to an embodiment of the present invention.
In the figure:
1. a clamping module; 11. an electro-permanent magnet; 12. a magnetically permeable member;
2. a control module;
3. an aircraft skin laminate structure; 31. and (4) forming a hole area.
Detailed Description
In order to make the technical problems solved, the technical solutions adopted and the technical effects achieved by the present invention clearer, the technical solutions of the present invention are further described below by way of specific embodiments with reference to the accompanying drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be further noted that, for the convenience of description, only some but not all of the elements associated with the present invention are shown in the drawings.
In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are used based on the orientations and positional relationships shown in the drawings, and are only for convenience of description and simplicity of operation, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.
The technical scheme of the utility model is further explained by the specific implementation mode in combination with the attached drawings.
In order to avoid the problems that when holes are made in the 3-layer laminated structure of the aircraft skin, the punching clamp is utilized for temporary fastening, then holes are made in other positions, the pre-assembly nail holes are stressed when the holes are made, stress concentration occurs in the pre-assembly nail holes, the pre-assembly holes deform, separation occurs between laminated binding surfaces at the positions far away from the punching clamp, hole edge burrs between laminated layers are caused, and cutting scraps enter the layers of the skin. The embodiment provides a clamping device suitable for an aircraft skin laminated structure, which can effectively prevent burr generation at the hole edge of a skin binding surface during subsequent hole making, inhibit cuttings from entering between skin laminations and ensure the assembly quality.
As shown in fig. 1, the clamping device for an aircraft skin laminated structure provided by the embodiment includes a clamping module 1 and a control module 2, and an operator manipulates the control module 2 to control the clamping module 1 to clamp an aircraft skin laminated structure 3 for subsequent hole making operation. In particular, the clamping module 1 comprises magnetically attractable clamping assemblies, which are provided in at least two groups in order to ensure the stability of the clamped aircraft skin laminate 3 during the hole making process, i.e. to ensure that the hole making region 31 of the clamped aircraft skin laminate 3 is located between two adjacent clamping assemblies clamped to the aircraft skin laminate 3. Thus, in use, the clamping module 1 provided in this embodiment may employ two sets of clamping assemblies for clamping the aircraft skin laminate structure 3, or may employ three sets of clamping assemblies, so that at least two hole-making regions 31 are left free. Of course, it is also possible to use more than two sets of clamping assemblies to increase the clamping force with which the aircraft skin laminate structure 3 is clamped, when only one hole-making region 31 has to be left free.
To achieve the aforementioned function of the clamping module 1, the control module 2 is electrically connected to the clamping assembly to demagnetize the clamping assembly and demagnetize the clamped aircraft skin laminate structure 3. Further, the control module 2 is also capable of adjusting the magnitude of the magnetic force of the clamping assembly, i.e. the clamping force applied by the clamping assembly to the aircraft skin laminate structure 3, to fit aircraft skins of different materials and thicknesses. Alternatively, the clamping device suitable for the aircraft skin laminated structure is suitable for clamping various metal plate, fiber reinforced, particle reinforced insulating resin-based or rubber-based composite material laminated layers. In addition, in order to meet the requirement of the aircraft assembly magnetic field residual, the control module 2 is also used for demagnetizing the aircraft skin laminated structure 3 in the magnetizing process so as to avoid the magnetic force on the clamping assembly from being residual on the aircraft skin laminated structure 3.
In this embodiment, the clamping assembly includes an electro-permanent magnet 11 and a permeable magnet 12 respectively disposed on both sides of the aircraft skin laminated structure 3, and the electro-permanent magnet 11 is electrically connected to the control module 2. In the process of magnetizing, the magnetic force of the electric permanent magnet piece 11 is continuously increased, and the magnetic permeable piece 12 can be adsorbed, so that the magnetic permeable piece 12 moves towards the direction close to the electric permanent magnet piece 11, and the aircraft skin laminated structure 3 is clamped between the electric permanent magnet piece 11 and the magnetic permeable piece 12. After the charging is completed, the magnetic force of the electro-permanent magnet pieces 11 remains unchanged, ensuring that the position of the aircraft skin laminated structure 3 clamped between the electro-permanent magnet pieces 11 and the magnetic permeable pieces 12 remains unchanged. After the hole is formed in the aircraft skin laminated structure 3, the control module 2 enables the electric permanent magnet piece 11 to be in a demagnetization process, the magnetic force of the electric permanent magnet piece 11 is continuously reduced in the demagnetization process, and finally the magnetic permeable piece 12 cannot be adsorbed, and then the distance between the electric permanent magnet piece 11 and the magnetic permeable piece 12 can be increased, so that the aircraft skin laminated structure 3 is separated from the clamping module 1.
In order to ensure the versatility of the clamping module 1, the multiple groups of clamping assemblies of the clamping module 1 should be capable of being adapted to the aircraft skin laminated structure 3 at different positions, and then the plurality of electro-permanent magnets 11 are provided, and the curvatures of the first abutting surfaces of the plurality of electro-permanent magnets 11 are the same or different, and the first abutting surfaces are the surfaces where the electro-permanent magnets 11 abut against the aircraft skin laminated structure 3. In accordance therewith, the plurality of magnetically permeable members 12 are provided, and the curvatures of the second abutment surfaces of the plurality of magnetically permeable members 12 are the same or different, and the second abutment surface is the surface where the magnetically permeable member 12 abuts the aircraft skin laminate structure 3.
The magnetic permeable pieces 12 and the electric permanent magnetic pieces 11 need to be used in a group, and the first abutting surface and the second abutting surface are completely attached to the aircraft skin laminated structure 3, so that local stress concentration can be avoided. Optionally, the curvature and size of the first and second abutment surfaces are the same
Further, in order to ensure the curvature of the abutting surface, the electro-permanent magnet part 11 includes a first housing, a first abutting part and an electro-permanent magnet part body, the first abutting part is disposed on one side of the first housing close to the aircraft skin laminated structure 3, and the first abutting surface is a side surface of the first abutting part, which can abut against the aircraft skin laminated structure 3. Alternatively, in order to adapt to different aircraft skin curvatures, it is possible to provide the electro-permanent-magnet pieces 11 with first abutments of different curvatures, which are detachably arranged on the first shell. The electro-permanent magnet body is disposed in the first housing and electrically connected to the control module 2, so that the electro-permanent magnet body can generate a magnetic force for attracting the magnetic permeable member 12, and the magnetic force can penetrate through the first housing and the first abutting member, so that the attracting magnetic permeable member 12 moves toward the side close to the electro-permanent magnet member 11.
Optionally, according to the requirement of clamping force not less than 500N and light weight of the product, the first housing is a cuboid, the length of the first housing is X, X is not less than 160mm and not more than 200mm, the width of the first housing is Y, Y is not less than 160mm and not more than 200mm, the height of the first housing is Z, and Z is not less than 70mm and not more than 90 mm. The first abutting parts are arranged on the surfaces of the long sides and the wide sides of the first shell, so that the side surface with the largest first shell area is enabled to apply force to the aircraft skin laminated structure 3.
Furthermore, the magnetic permeable member 12 is a plate-shaped structure capable of being processed into any angle, the length of the plate-shaped structure is L, L is more than or equal to 160mm and less than or equal to 200mm, the width of the plate-shaped structure is W, W is more than or equal to 160mm and less than or equal to 200mm, the thickness of the plate-shaped structure is H, H is more than or equal to 9mm and less than or equal to 11mm, and the second abutting surface is a surface where the long side and the wide side of the magnetic permeable member 12 are located, so as to ensure that a side surface with the largest area of the magnetic permeable member 12 applies force to the aircraft skin laminated structure 3. Alternatively, to adapt to different aircraft skin curvatures, a plurality of magnetically permeable members 12 with different curvatures may be provided.
The clamping device suitable for the aircraft skin laminated structure provided by the embodiment further comprises a supporting part for supporting the clamping module 1 so as to ensure the clamping precision of the aircraft skin laminated structure 3. The support part comprises a first support part, wherein the magnetic permeable part 12 is arranged on the first support part, and is used for ensuring that the magnetic permeable part 12 can be positioned on the same plane with the electric permanent magnet part 11 and can move along with the magnetic permeable part 12 when the magnetic permeable part 12 is adsorbed by the electric permanent magnet part 11. After the electro-permanent magnetic part 11 is demagnetized, the magnetic permeable part 12 is driven to move towards the side far away from the electro-permanent magnetic part 11, so that the full-automatic operation of the clamping process of the aircraft skin laminated structure 3 is realized
The support part further comprises a second support part, the electro-permanent-magnet piece 11 is arranged on the second support part, the electro-permanent-magnet piece 11 can be kept still in the whole clamping process, and the position of the electro-permanent-magnet piece 11 can be adjusted according to the positions of different aircraft skin laminated structures 3, so that the electro-permanent-magnet piece 11 can be abutted to the aircraft skin laminated structures 3 to carry out subsequent clamping actions. Optionally, the support part is a robot, and the electromagnetic piece 11 and the magnetic permeable piece 12 are respectively mounted at the tail ends of the robot arms, so that multi-station cooperation is realized, the machining automation degree is provided, and the high hole making efficiency is maintained.
The present embodiment also provides a machining apparatus comprising a hole-making device and a clamping device as described above, adapted for use in an aircraft skin laminate structure, with which holes are made in a hole-making region 31, whilst ensuring effective clamping of the aircraft skin laminate 3 in which holes are to be made. Optionally, the hole making device is disposed between two adjacent sets of clamping assemblies of the clamping modules 1.
The foregoing embodiments are merely illustrative of the principles and features of this invention, which is not limited to the above-described embodiments, but rather is susceptible to various changes and modifications without departing from the spirit and scope of the utility model, which changes and modifications are within the scope of the utility model as claimed. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (10)
1. A clamping device suitable for an aircraft skin laminate structure, characterized by comprising a clamping module (1) and a control module (2), the control module (2) being capable of controlling the clamping module (1) to clamp an aircraft skin laminate structure (3);
the clamping module (1) comprises clamping assemblies capable of being magnetically adsorbed, at least two groups of the clamping assemblies are arranged, and a region clamped between two adjacent groups of the clamping assemblies on the aircraft skin laminated structure (3) is a hole making region (31) of the aircraft skin laminated structure (3);
the control module (2) is connected in the electricity in the clamping component, control module (2) be used for to the clamping component magnetization and demagnetization, and give aircraft skin laminated structure (3) demagnetization, control module (2) can also be used for adjusting clamping component's magnetic force size.
2. The clamping device for aircraft skin laminates as claimed in claim 1, wherein the clamping assembly comprises an electro-permanent magnet (11) and a permeable magnet (12) disposed on either side of the aircraft skin laminate (3), the electro-permanent magnet (11) being electrically connected to the control module (2), the electro-permanent magnet (11) being capable of attracting the permeable magnet (12) to move in a direction approaching the electro-permanent magnet (11) and clamping the aircraft skin laminate (3) between the electro-permanent magnet (11) and the permeable magnet (12).
3. The clamping device for aircraft skin laminates according to claim 2, wherein the plurality of electro-permanent-magnetic pieces (11) are provided, and the curvature of the first abutting surfaces of the plurality of electro-permanent-magnetic pieces (11) is the same or different, and the first abutting surfaces are the surfaces of the electro-permanent-magnetic pieces (11) abutting against the aircraft skin laminates (3);
the magnetic-permeable pieces (12) are arranged in a plurality of numbers, the curvatures of second abutting surfaces of the magnetic-permeable pieces (12) are the same or different, and the second abutting surfaces are surfaces of the magnetic-permeable pieces (12) abutting against the aircraft skin laminated structure (3).
4. Clamping device for aircraft skin laminates according to claim 3, characterised in that said electro-permanent-magnet (11) comprises a first shell, a first abutment provided on said first shell and able to abut against said aircraft skin laminate (3), said first abutment having said first abutment surface thereon, and an electro-permanent-magnet body provided in said first shell and electrically connected to said control module (2), said electro-permanent-magnet body being able to generate a magnetic force that attracts said magnetically permeable member (12) in order to clamp said aircraft skin laminate (3).
5. The clamping device suitable for the aircraft skin lamination structure according to claim 4, wherein the first shell is shaped like a cuboid, the first shell has a length of X, X is larger than or equal to 160mm and smaller than or equal to 200mm, the first shell has a width of Y, Y is larger than or equal to 160mm and smaller than or equal to 200mm, the first shell has a height of Z, Z is larger than or equal to 70mm and smaller than or equal to 90mm, and the first abutting parts are arranged on the surfaces of the long sides and the wide sides of the first shell.
6. The clamping device suitable for the aircraft skin laminated structure according to the claim 3, wherein the magnetism-permeable member (12) is a plate-shaped structure capable of being processed into any angle, the length of the plate-shaped structure is L, L is more than or equal to 160mm and less than or equal to 200mm, the width of the plate-shaped structure is W, W is more than or equal to 160mm and less than or equal to 200mm, the thickness of the plate-shaped structure is H, H is more than or equal to 9mm and less than or equal to 11mm, and the second abutting surface is a surface where the long side and the wide side of the magnetism-permeable member (12) are located.
7. The clamping device for an aircraft skin laminate structure according to claim 3, wherein the first abutment surface and the second abutment surface are of the same curvature and size.
8. The clamping device for aircraft skin laminate structure according to claim 2, further comprising a support portion including a first support member on which the magnetically permeable member (12) is arranged, the first support member being capable of following the magnetically permeable member (12) when the magnetically permeable member (12) is attracted by the electro-permanent magnet (11) and of carrying the magnetically permeable member (12) when the electro-permanent magnet (11) is not attracted by the magnetically permeable member (12).
9. Clamping device for an aircraft skin laminate structure according to claim 8, characterised in that the bracing portion further comprises a second bracing member for bracing the electro-permanent magnet (11) in a position abutting the aircraft skin laminate structure (3).
10. Machining equipment, characterized in that it comprises a hole making device for making a hole in the hole making area (31) after the clamping module (1) clamps the aircraft skin laminate structure (3) and a clamping device for the aircraft skin laminate structure according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220016137.6U CN216706815U (en) | 2022-01-06 | 2022-01-06 | Clamping device and processing equipment suitable for aircraft skin laminated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220016137.6U CN216706815U (en) | 2022-01-06 | 2022-01-06 | Clamping device and processing equipment suitable for aircraft skin laminated structure |
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| Publication Number | Publication Date |
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| CN216706815U true CN216706815U (en) | 2022-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202220016137.6U Active CN216706815U (en) | 2022-01-06 | 2022-01-06 | Clamping device and processing equipment suitable for aircraft skin laminated structure |
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| CN (1) | CN216706815U (en) |
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