CN116408389A - Electromagnetic forming device for forming airplane skin piece and forming method thereof - Google Patents
Electromagnetic forming device for forming airplane skin piece and forming method thereof Download PDFInfo
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- CN116408389A CN116408389A CN202210006405.0A CN202210006405A CN116408389A CN 116408389 A CN116408389 A CN 116408389A CN 202210006405 A CN202210006405 A CN 202210006405A CN 116408389 A CN116408389 A CN 116408389A
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- 238000000034 method Methods 0.000 title claims description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 35
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000001514 detection method Methods 0.000 claims description 35
- 238000007493 shaping process Methods 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000012937 correction Methods 0.000 abstract description 5
- 230000000295 complement effect Effects 0.000 abstract 1
- 230000008569 process Effects 0.000 description 12
- 230000008439 repair process Effects 0.000 description 8
- 239000002131 composite material Substances 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000153 supplemental effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D35/00—Combined processes according to or processes combined with methods covered by groups B21D1/00 - B21D31/00
- B21D35/002—Processes combined with methods covered by groups B21D1/00 - B21D31/00
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C51/00—Measuring, gauging, indicating, counting, or marking devices specially adapted for use in the production or manipulation of material in accordance with subclasses B21B - B21F
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D25/00—Working sheet metal of limited length by stretching, e.g. for straightening
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D25/00—Working sheet metal of limited length by stretching, e.g. for straightening
- B21D25/04—Clamping arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
- B21D26/14—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces applying magnetic forces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/92—Making other particular articles other parts for aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
An electromagnetic forming apparatus for forming an aircraft skin article comprising: a die (130), a plurality of hydraulic rams (160), a connection mechanism (150), a solenoid (110), and a forming aid; the forming auxiliary device obtains scanning data by scanning the surface of the skin blank (170), compares the scanning data with 3D data of a preset skin piece, and correspondingly adjusts working parameters of a plurality of hydraulic cylinders (160) and electromagnetic coils (110) according to comparison results, so that precise forming or correcting processing is carried out on an unformed region or a formed region of the skin blank (170). According to the electromagnetic forming device, the forming precision of the skin blank can be improved, the manual correction and the complementary pulling deformation after the part forming are reduced, and meanwhile, the manufacturing period of the skin piece forming is shortened.
Description
Technical Field
The present invention relates to a process for forming and manufacturing multi-curvature metal parts, and more particularly, to an electromagnetic forming apparatus and a forming method for forming an aircraft skin member by a stretch-electromagnetic forming process.
Background
The skin is an important component of an aircraft, and the quality of the formation of the skin is directly related to the aerodynamic performance and the service life of the aircraft during service. The skin is used as a covering piece of the surface layer of the airplane, and has the remarkable characteristics of complex appearance structure, large appearance size, weak rigidity, large curvature change, hyperbolic or multi-curvature and the like. Meanwhile, in order to achieve the purpose of weight reduction of the airplane, the airplane skin piece has the design characteristic of unequal thickness, so that the phenomenon of thickness reduction of more local areas exists on the skin piece.
Currently, a common aircraft skin forming technique is a stretch forming process. The common processing process is that a pulling force and a bending moment are applied to a skin blank by means of jaws positioned at two ends of equipment on a numerical control skin stretcher, so that the plate is slowly attached to the molded surface of a die. In the skin drawing and forming process, the pulling force is mainly provided by the hydraulic cylinder, so that the skin blank wraps the mold surface in a large area. After this, in order to reduce the rebound after forming, it is also necessary to continue applying a small amount of supplemental pull. Therefore, the process parameters of the whole forming process are complex, and the equipment structure is heavy and huge. The uneven rebound, cracking or wrinkling of the skin is easily caused by the thin thickness and uneven stress of the skin. For the skin piece with complex outline and structure, the skin and the surface of the mould cannot be completely attached, so that workers are required to carry out close-range manual operation, trowelling and repairing are carried out on the crease, the forming efficiency is low, and the operation capability of the workers is high.
Disclosure of Invention
Therefore, the invention aims to overcome the defect that the existing stretch-electromagnetic forming process needs to carry out post-manual repair and correction processing on the skin with complex surface, and simultaneously provides the electromagnetic forming device and the forming method for the airplane skin piece with high forming efficiency, safety and reliability.
In order to solve the above technical problem, the present invention provides an electromagnetic forming apparatus for forming an aircraft skin piece, the electromagnetic forming apparatus comprising:
the hydraulic cylinders are used for carrying out stretching deformation on the skin blank, and piston ends of the hydraulic cylinders are connected with the skin blank through a clamping and connecting mechanism;
an electromagnetic coil configured to be able to apply a pulsed electromagnetic force to a region to be deformed of the skin blank, thereby deforming the skin blank;
the shaping auxiliary device can obtain data of the surface of the skin blank through real-time scanning, compares the scanned data with 3D data of a preset skin piece, and then correspondingly adjusts working parameters of the hydraulic cylinders and the electromagnetic coils according to comparison results, so that precise shaping or shaping processing is carried out on an unformed area or a formed area of the skin blank.
According to an embodiment of the present invention, the forming aid includes:
the detection mechanism is detachably fixed on the device for clamping the electromagnetic coil and can scan the surface of the deformation area when stretching force and pulse electromagnetic force act on the skin blank; and
the control unit is respectively in communication connection with the hydraulic cylinders, the electromagnetic coil and the detection mechanism and can receive scanning data from the detection mechanism in real time,
the control unit is configured to compare the scanning data from the detection mechanism with 3D data of a preset skin piece, and correspondingly adjust working parameters of the hydraulic actuators and the electromagnetic coils according to comparison results.
According to another embodiment of the invention, the piston ends of the plurality of hydraulic rams are hinged to the skin blank by the clamping connection and the other ends of the plurality of hydraulic rams opposite the piston ends are hinged to a movable rail mount.
According to yet another embodiment of the present invention, the plurality of hydraulic rams includes a plurality of horizontal hydraulic rams and a plurality of vertical hydraulic rams.
According to another embodiment of the invention, the detection mechanism can synchronously move along with the electromagnetic coil, and can also independently perform three-dimensional space position change.
According to another embodiment of the invention, the electromagnetic coil and the detection means are arranged on the other side of the skin blank opposite the mould.
According to still another embodiment of the present invention, the electromagnetic forming apparatus further includes: a die hydraulic ram disposed at the bottom of the die and capable of moving the die in a vertical direction upon actuation.
According to yet another embodiment of the invention, the detection mechanism is a three-dimensional scanner.
According to another embodiment of the invention, the electromagnetic coil is a universal electromagnetic coil.
According to a further embodiment of the invention, the detection mechanism may be moved by hand or held by a robotic arm controlled by the control unit for movement therewith.
According to a further embodiment of the invention, the electromagnetic coil may be clamped by a robot arm controlled by the control unit to move with the robot arm.
The invention also provides a forming method of the aircraft skin piece, which comprises the following steps:
placing the skin blank on a die, and clamping the edge of the skin blank by using the clamping connection mechanism;
driving the mold to a predetermined position by the mold hydraulic rams and actuating the plurality of hydraulic rams to stretch the skin blank so that it conforms to the mold;
moving the electromagnetic coil to a region to be deformed of the skin blank and applying electromagnetic pulse force;
and the detection mechanism scans the deformation area and transmits scanning data to the control unit, and the control unit compares the scanning data with 3D data of the skin piece and adjusts working parameters of the electromagnetic coil and the hydraulic cylinders according to a comparison result.
According to another embodiment of the invention, the detection means are configured to be able to scan the region of the skin blank to be deformed before the electromagnetic coil applies an electromagnetic pulse.
The invention has the positive progress effects that:
according to the electromagnetic forming device and the forming method thereof, the deformation degree of a local deformation area of the skin blank in the forming process can be monitored and corrected in real time, so that the tensile deformation force parameter and the working parameter when electromagnetic force is generated by the electromagnetic coil are synchronously and reasonably adjusted, the geometric dimension precision of a part of the skin piece after electromagnetic forming is greatly improved, the later manual forming and the repair time are reduced, the complicated and inaccurately controlled manual hammering deformation is greatly reduced, and the manufacturing period of the skin piece forming is shortened.
Drawings
Fig. 1 is a schematic view of an electromagnetic forming apparatus for forming an aircraft skin article according to a preferred embodiment of the present invention.
Fig. 2 schematically shows an operating state of the electromagnetic forming device shown in fig. 1 during processing.
Detailed Description
For the purposes of clarity, technical solutions and advantages of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings showing various embodiments according to the present application, it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden on the person of ordinary skill in the art based on the embodiments described herein, are intended to be within the scope of the present application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used in the description of the application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising," "including," "having," "containing," and the like in the description of the present application and in the claims and drawings are used for open ended terms. Thus, a method or apparatus that "comprises," includes, "" has "or" has, for example, one or more steps or elements, but is not limited to having only the one or more elements. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present application, it should be understood that directional terms, such as "left", "right", "upper", "lower", "front", "rear", etc., are used for convenience of description and simplifying the description based on the orientation or positional relationship shown in the drawings, and do not indicate or imply that the apparatus or element to be 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 application.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "attached" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
Reference in the specification to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly understand that the embodiments described herein may be combined with other embodiments.
As noted above, it should be emphasized that the term "comprises/comprising" when used in this specification is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The terms "a" and "an" in this specification may mean one, but may also be consistent with the meaning of "at least one" or "one or more".
The term "and/or" in this application is merely an association relation describing an associated object, and indicates that three relations may exist, for example, a and/or B may indicate: a exists alone, A and B exist together, and B exists alone. In this application, the character "/" generally indicates that the associated object is an or relationship.
As previously mentioned, the skin is an important component of an aircraft, and the quality of its formation will directly relate to the aerodynamic performance and the service life of the aircraft when in service. The skin is used as a covering piece of the surface layer of the airplane, and has the remarkable characteristics of complex appearance structure, large appearance size, weak rigidity, large curvature change, hyperbolic or multi-curvature and the like. Moreover, due to the weight reduction requirement of the aircraft, more local areas with reduced thickness exist on the skin parts. Therefore, the whole forming process of the skin has complex technological parameters, the equipment structure is heavy and huge, the forming efficiency is not high, and the operation capability of workers is high.
The electromagnetic forming technology is a high-efficiency special forming method for plastic processing of metal blanks by utilizing pulse electromagnetic force, can greatly improve the forming limit of light alloy, inhibit wrinkling, and has the advantages of simplifying a die, having high processing precision, being easy to realize production automation and the like. Therefore, electromagnetic forming techniques have been widely used in forming processes for multi-curvature members.
Chinese patent CN104785621a discloses a "stretch forming and electromagnetic composite progressive" technique for large thin-walled parts, and proposes an "stretch forming-electromagnetic-re-stretch forming-re-electromagnetic" alternating composite forming method, but the method is only suitable for forming a rotating member, and does not have a profile scanning device, needs repeated shutdown to verify the forming state of the part, and cannot perform real-time feedback and correction of the stretch-electromagnetic process. On the basis, chinese patent CN108856442a and chinese patent CN111167919a disclose "a warm electromagnetic forming device and method for skin piece" and "a stretch-electromagnetic composite forming device and method for multi-curvature skin piece", respectively, both of which use electromagnetic devices to improve the forming ability of skin blanks. However, the deformation degree of the deformation region cannot be synchronously and directly detected in real time, so that a large amount of later-stage repair and correction are often required, and the manufacturing period of skin piece forming cannot be effectively shortened.
Referring to fig. 1 and 2, an electromagnetic forming apparatus for forming an aircraft skin article according to a preferred embodiment of the present invention includes at least: a plurality of hydraulic rams 160, a die 130, a clamp connection 150, a solenoid 110, and a forming aid.
The piston ends of the plurality of hydraulic rams 160 are connected to the clamp connection 150, and the clamp connection 150 clamps the edge of the skin blank 170 to secure it. By the interaction of the plurality of hydraulic rams 160, the skin blank 170 is stretch deformed by the clamp connection 150.
Further, the piston ends of the plurality of hydraulic rams 160 are hinged to the skin blank 170 via the clamp connection 150, and the other ends of the plurality of hydraulic rams 160 opposite the piston ends are hinged to a movable rail mount. More specifically, the plurality of hydraulic rams 160 includes a plurality of horizontal hydraulic rams 162 and a plurality of vertical hydraulic rams 161. The skin blank 170 is stretch deformed by adjusting the piston segment position changes, the angle of articulation, the slide rail mount position changes in the horizontal hydraulic rams 162 and the vertical hydraulic rams 161.
The electromagnetic coil 110 applies a pulsed electromagnetic force F to the region of the skin blank 170 to be deformed M The skin blank 170 is deformed. Further, the electromagnetic coil 110 and the detecting mechanism 120 are disposed on the other side of the skin blank 170 opposite to the die 130.
Preferably, the electromagnetic coil 110 may be moved by being clamped by a mechanical arm of the control unit. The detection mechanism 120 can move synchronously with the electromagnetic coil 110, and can also independently perform three-dimensional spatial position change. More specifically, the detection mechanism 120 may be moved by being held by a worker, or may be moved by being held by a robot arm of the control unit alone, or may be moved by being held by a robot arm holding the electromagnetic coil 110 while holding the detection mechanism 120, so that the electromagnetic coil 110 and the detection mechanism 120 are moved synchronously.
Further, the electromagnetic coil 110 is a general electromagnetic coil, and the detection mechanism 120 is a three-dimensional scanner, for example, a three-dimensional infrared scanner or a three-dimensional blue light scanner. It should be understood that, the general electromagnetic coil refers to an electromagnetic coil that is not tailored to a certain piece and/or class of skin piece, and the general electromagnetic coil is usually larger in size, so that the electromagnetic forming speed of the skin piece can be increased, but the manufacturing cost of the specific electromagnetic coil is high, and the local fold area is difficult to repair again, so that in practical application, a worker is often required to perform manual shape correction and repair deformation. The general electromagnetic coil applied by the preferred embodiment of the invention is smaller than a special electromagnetic coil in size, and the electromagnetic forming speed of the skin piece is slightly slower than that of the special electromagnetic coil, but the general electromagnetic coil has low manufacturing cost, is easy to repair local fold areas, and greatly reduces the workload of subsequent workers for secondary checking and repair pulling.
The forming auxiliary device is used for scanning the surface of the skin blank 170 to obtain scanning data, comparing the scanning data with 3D data of a preset skin piece, and correspondingly adjusting working parameters of the hydraulic cylinders 160 and the electromagnetic coils 110 according to comparison results, so as to realize precise forming or shaping of a region to be formed or a formed region of the skin blank 170. It should be understood herein that the regions to be deformed of the skin blank include, but are not limited to, regions of relatively complex profiles of the corresponding skin members, and the skin blank at the complex profiles is typically unevenly stressed, which is prone to problems of uneven springback, localized non-molding or wrinkling of the skin blank, requiring manual repair again by a worker.
Preferably, the forming assistance device includes a detection mechanism 120 and a control unit in communication with the plurality of hydraulic rams 160, the solenoid 110, and the detection mechanism 120, respectively.
The detection mechanism 120 may be disposed with the electromagnetic coil 110, and when the control unit controls the electromagnetic coil 110 to move, the detection mechanism 120 is driven to move. More specifically, in the tensile force and the pulsed electromagnetic force F M When acting on the skin blank 170, the skin blank 170 deforms, and the detection mechanism 120 scans the surface of the deformed region and can receive the scanning data from the detection mechanism 120 in real time. The control unit compares the scan data from the detection mechanism 120 with the preset 3D data of the skin piece, and can correspondingly adjust the working parameters of the hydraulic actuators 160 and the electromagnetic coil 110 according to the comparison result. By means of the shaping aid, it is possible to detect in real time whether the deformation of the skin blank 170 corresponds to a skin pieceThe 3D data is consistent, and when an inconsistency is detected, the solenoid 110 can synchronously adjust reasonable operating parameters
Preferably, the electromagnetic forming device further includes a die hydraulic cylinder 140, and the die hydraulic cylinder 140 is disposed at the bottom of the die 130 and is capable of moving the die 130 in a vertical direction when actuated.
According to some preferred embodiments of the present invention, there may also be provided a forming method of forming an aircraft skin article by an electromagnetic forming device, the forming method comprising the steps of:
placing the skin blank 170 on the mold 130 and clamping the edge of the skin blank 170 with the clamp connection 150;
driving the mold 130 to a predetermined position by the mold hydraulic ram 140, and driving the plurality of hydraulic rams 160 to stretch the skin blank 170 so as to be attached to the mold 130;
moving the electromagnetic coil 110 to the region of the skin blank 170 to be deformed and applying an electromagnetic pulse force F M ；
The detection mechanism 120 is made to scan the deformed region and transmit the scanned data to the control unit, and the control unit compares the scanned data with the 3D data of the skin piece and adjusts the working parameters of the electromagnetic coil 110 and the plurality of hydraulic rams 160 according to the comparison result.
Further, the detection mechanism 120 can scan the area of the skin blank 170 to be deformed before the electromagnetic coil 110 applies an electromagnetic pulse. By pre-scanning the area of the skin blank 170 to be deformed by the solenoid 110, the operating parameters of the solenoid 110 and the plurality of hydraulic rams 160 may be more optimized, resulting in more accurate initial operating parameters.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (13)
1. An electromagnetic forming device for forming an aircraft skin article, the electromagnetic forming device comprising:
a plurality of hydraulic rams (160) for stretch deforming a skin blank (170), the piston ends of the plurality of hydraulic rams (160) being connected to the skin blank (170) by a clamp connection mechanism (150);
-an electromagnetic coil (110), the electromagnetic coil (110) being configured to be able to apply a pulsed electromagnetic force at a region of the skin blank (170) to be deformed, thereby deforming the skin blank (170);
the shaping auxiliary device can obtain data of the surface of the skin blank (170) through real-time scanning, compares the scanned data with 3D data of a preset skin piece, and then correspondingly adjusts working parameters of the hydraulic cylinders (160) and the electromagnetic coils (110) according to comparison results, so that precise shaping or shaping processing is carried out on an unformed region or a formed region of the skin blank (170).
2. Electromagnetic forming device for forming aircraft skin pieces according to claim 1, characterized in that the forming aid comprises:
a detection mechanism (120), wherein the detection mechanism (120) is detachably fixed on a device for clamping the electromagnetic coil (110) and can scan the surface of a deformation area when a stretching force and a pulse electromagnetic force act on the skin blank (170); and
the control unit is respectively in communication connection with the plurality of hydraulic cylinders (160), the electromagnetic coil (110) and the detection mechanism (120), and can receive scanning data from the detection mechanism (120) in real time;
wherein the control unit is configured to compare the scanning data from the detection mechanism (120) with 3D data of a preset skin piece, and correspondingly adjust the operating parameters of the hydraulic actuators (160) and the electromagnetic coil (110) according to the comparison result.
3. Electromagnetic forming device for forming aircraft skin pieces according to claim 1, characterized in that the piston ends of the plurality of hydraulic rams (160) are hinged to the skin blank (170) by the clamp connection (150), the other ends of the plurality of hydraulic rams (160) opposite the piston ends being hinged to a movable slide rail base.
4. An electromagnetic forming device for forming an aircraft skin article according to claim 3, wherein said plurality of hydraulic rams (160) comprises a plurality of horizontal hydraulic rams (162) and a plurality of vertical hydraulic rams (161).
5. Electromagnetic forming device for forming aircraft skin articles according to claim 2, characterized in that the detection means (120) are configured to be able to move synchronously with the electromagnetic coil (110) or to perform a position change in three dimensions independently.
6. Electromagnetic forming device for forming aircraft skin pieces according to claim 2, characterized in that both the electromagnetic coil (110) and the detection means (120) are arranged opposite the mould (130) on the other side of the skin blank (170).
7. The electromagnetic forming device for forming an aircraft skin article according to claim 1, further comprising:
-a mould hydraulic ram (140), the mould hydraulic ram (140) being arranged at the bottom of the mould (130) and being configured to be able to move the mould (130) in a vertical direction upon actuation.
8. Electromagnetic forming device for forming aircraft skin pieces according to claim 2, characterized in that the detection means (120) are three-dimensional scanners.
9. Electromagnetic forming device for forming aircraft skin pieces according to claim 1, characterized in that the electromagnetic coil (110) is a universal electromagnetic coil.
10. Electromagnetic forming device for forming aircraft skin pieces according to claim 2, characterized in that the detection mechanism (120) is configured to be able to move either by hand or by being gripped by a robotic arm controlled by the control unit to move with the robotic arm.
11. Electromagnetic forming device for forming aircraft skin pieces according to claim 2, characterized in that the electromagnetic coil (110) is configured to be clamped by a robotic arm controlled by the control unit to move with the robotic arm.
12. A forming method using an electromagnetic forming device for forming an aircraft skin article according to any one of claims 1-11, characterized in that the forming method comprises the steps of:
-placing the skin blank (170) on a mould (130) and clamping the edge of the skin blank (170) with the clamping connection (150);
driving the mold (130) to a predetermined position by the mold hydraulic ram (140) and actuating the plurality of hydraulic rams (160) to stretch the skin blank (170) so as to conform to the mold (130);
-moving the electromagnetic coil (110) to the region of the skin blank (170) to be deformed and applying an electromagnetic pulse force;
the detection mechanism (120) is enabled to scan the deformation area and transmit scanning data to the control unit, and the control unit compares the scanning data with 3D data of the skin piece and adjusts working parameters of the electromagnetic coil (110) and the plurality of hydraulic cylinders (160) according to a comparison result.
13. The forming method according to claim 12, characterized in that the detection mechanism (120) is configured to be able to scan the region of the skin blank (170) to be deformed before the electromagnetic coil (110) applies an electromagnetic pulse.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210006405.0A CN116408389A (en) | 2022-01-05 | 2022-01-05 | Electromagnetic forming device for forming airplane skin piece and forming method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210006405.0A CN116408389A (en) | 2022-01-05 | 2022-01-05 | Electromagnetic forming device for forming airplane skin piece and forming method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116408389A true CN116408389A (en) | 2023-07-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210006405.0A Pending CN116408389A (en) | 2022-01-05 | 2022-01-05 | Electromagnetic forming device for forming airplane skin piece and forming method thereof |
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| Country | Link |
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| CN (1) | CN116408389A (en) |
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- 2022-01-05 CN CN202210006405.0A patent/CN116408389A/en active Pending
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