CN115284001A - Full-process laser processing method for air rudder folding surface skin - Google Patents
Full-process laser processing method for air rudder folding surface skin Download PDFInfo
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- CN115284001A CN115284001A CN202210759384.XA CN202210759384A CN115284001A CN 115284001 A CN115284001 A CN 115284001A CN 202210759384 A CN202210759384 A CN 202210759384A CN 115284001 A CN115284001 A CN 115284001A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P23/00—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass
- B23P23/04—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass for both machining and other metal-working operations
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- 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
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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
- B21D5/00—Bending sheet metal along straight lines, e.g. to form simple curves
- B21D5/008—Bending sheet metal along straight lines, e.g. to form simple curves combined with heating or cooling of the bends
-
- 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
- B21D5/00—Bending sheet metal along straight lines, e.g. to form simple curves
- B21D5/04—Bending sheet metal along straight lines, e.g. to form simple curves on brakes making use of clamping means on one side of the work
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Bending Of Plates, Rods, And Pipes (AREA)
Abstract
The invention relates to a full-process laser processing method for a folding surface skin of an air rudder, belonging to the field of laser processing; cutting and blanking a plate blank of a skin to be manufactured by adopting a laser to obtain a plate material with a margin area; horizontally fixing the plate; processing a bending positioning hole on the plate by adopting a laser according to a preset bending line; rotating the plate to enable the part to be bent of the plate to be suspended relative to the base; scanning the bending line by using a laser to realize that the part to be bent of the plate is bent to a target angle; laser cutting and removing the allowance area around the plate by adopting a laser to obtain a bent skin; according to the invention, through full-flow laser processing, the manufacturing efficiency and the manufacturing quality of small-batch air rudder folded skin can be effectively improved, the plastic flow capacity and the forming limit of the material can be effectively improved through the heating effect of laser, the problem of cracking of the difficult-to-deform material plate during cold bending is avoided, a forming die and an external force are not needed in the whole process, the plate has no resilience, and the forming precision is high.
Description
Technical Field
The invention belongs to the field of laser processing, and relates to a full-process laser processing method for an air rudder folding surface skin.
Background
Air rudders are the actuators and key components of aircraft flight control systems. In recent years, with the improvement of performance indexes of aircrafts, air rudders are developed to be light and high in performance.
On the one hand, air rudders increasingly take the form of a skin skeleton structure. The skin is mostly in a bent shape, and at present, the original plate blank is subjected to plate shearing and blanking, and then the lower plate blank is subjected to numerical control bending or integral die pressing forming. The manufacturing process needs a plurality of devices to realize, the manual operation links are many, the forming process needs to be put into a die, the die manufacturing cost is high, the time is long, and the skin once the type is repaired again, so that the requirements of quick and low-cost development of small-batch models cannot be met.
On the other hand, the air rudder skin is more and more made of high-temperature resistant lightweight materials, such as titanium alloy, titanium-based composite material and titanium-aluminum alloy. The novel materials have poor plasticity, the skin of the novel materials has the problems of large resilience, easy local cracking and the like when being bent in a numerical control manner or formed by integral die pressing, and the rejection rate is high.
In the process of bending the sheet, the efficiency of manually measuring the bending angle of the sheet is low, and the error is large.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method has the advantages that the defects of the prior art are overcome, the full-process laser processing method for the air rudder folded skin is provided, the manufacturing efficiency and the manufacturing quality of the air rudder folded skin in small batches can be effectively improved through the full-process laser processing, the manufacturing cost is reduced, particularly in the laser bending link, the plastic flowing capacity and the forming limit of the material can be effectively improved through the laser heating effect, the problem that the plate of the material difficult to deform cracks when being bent in a cold mode can be solved, any die and external force are not needed in the whole process, the plate does not rebound, and the forming precision is high.
The technical scheme of the invention is as follows:
a full-process laser processing method for an air vane folding surface skin comprises the following steps:
cutting and blanking a plate blank of a skin to be manufactured by adopting a laser to obtain a plate material with a residual area;
horizontally fixing the plate;
processing a bending positioning hole on the plate by using a laser according to a preset bending line;
rotating the plate to enable the part to be bent of the plate to be suspended relative to the base;
scanning the bending line by using a laser to realize that the part to be bent of the plate is bent to a target angle;
and (3) carrying out laser cutting removal on the margin area around the plate by adopting a laser to obtain the bent skin.
In the full-process laser processing method for the air rudder folding surface skin, the laser power of the laser is 1000W; in the cutting and blanking process, the diameter of a light spot of a laser is set to be 0.5mm, and the cutting speed is 10mm/s.
In the full-process laser processing method for the air rudder folding skin, the shape of the plate is consistent with that of the skin to be manufactured, and the margin of the plate is 10-20mm larger than that of the skin to be manufactured, namely the margin area.
In the full-process laser processing method for the air rudder break surface skin, the method for horizontally fixing the plate comprises the following steps:
horizontally placing the base, and horizontally placing the plate on the upper surface of the base; placing the clamping plate on the upper surface of the plate; the clamping plate is fixed with the base, so that the plate is clamped and fixed.
In the full-process laser processing method for the air rudder folded surface skin, each bending line corresponds to 2 bending positioning holes, the 2 bending positioning holes are arranged at two ends of the corresponding bending line, and the bending positioning holes are positioned in the allowance area; the center of the bending positioning hole is 5-8mm away from the edge of the skin to be manufactured.
In the full-process laser processing method for the air rudder folding surface skin, the working parameters of the laser for processing the bending positioning hole are as follows:
the laser power is 1000W, and the spot diameter is 1mm.
In the full-process laser processing method for the air rudder break surface skin, when the plate is suspended, the bending line on the plate is kept parallel to the edge of the base.
In the above full-process laser processing method for the air rudder break surface skin, the working parameters when the laser scans the bend line are as follows:
the laser power was 1000W, the spot diameter was 2mm, and the scanning speed of the laser along the bend line was 100mm/s.
In the full-process laser processing method for the air rudder folded skin, the laser scans the bending line for multiple times, and monitors the bending angle of the part to be bent of the sheet material in real time through the laser emitter and the CCD camera; the laser emitter emits laser to the bending surface of the plate, the laser is reflected and scattered on the bending surface, and the reflected laser is received by the CCD camera; the reflected laser changes along with the angle change of the bending surface; and obtaining the real-time bending angle of the plate according to the change condition of the laser signal.
In the full-process laser processing method for the air rudder break surface skin, the working parameters of the laser for performing laser cutting removal on the margin area are as follows:
the laser power is 1000W, the spot diameter is 0.5mm, and the cutting speed is 10mm/s.
Compared with the prior art, the invention has the beneficial effects that:
(1) The full-process laser processing method of the air rudder break surface skin can effectively improve the manufacturing efficiency and the manufacturing quality of small-batch air rudder break surface skins and reduce the manufacturing cost, and particularly in the laser bending link, the heating effect of laser can effectively improve the plastic flowing capacity and the forming limit of materials;
(2) The invention can avoid the problem of cracking of the hard-to-deform material plate during cold bending, and the whole process does not need a forming die and an external force, the plate has no resilience, and the forming precision is high;
(3) The bending angle of the part to be bent of the plate is monitored in real time through the laser emitter and the CCD camera; the laser emitter emits laser to the bending surface of the plate, the laser is reflected and scattered on the bending surface, and the reflected laser is received by the CCD camera; the reflected laser changes along with the angle change of the bending surface; according to the change condition of the laser signal, the real-time bending angle of the plate is obtained, and the bending angle of the air rudder fold surface skin is ensured.
Drawings
FIG. 1 is a laser processing flow diagram of an air vane break surface skin according to the present invention;
FIG. 2 is a schematic view of the margin area and the bending positioning hole of the present invention;
FIG. 3 is a schematic view of a laser scanning bending line according to the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a full-flow laser processing method of air rudder folded skin, which can effectively improve the manufacturing efficiency and the manufacturing quality of small-batch air rudder folded skin, reduce the manufacturing cost, particularly in the laser bending link, effectively improve the plastic flow capacity and the forming limit of a material under the heating action of laser, avoid the problem of cracking of a difficult-to-deform material plate during cold bending, and has the advantages of no need of any mould and external force in the whole process, no rebound of the plate and high forming precision.
The full-process laser processing method of the air rudder folding surface skin, as shown in fig. 1, specifically comprises the following steps:
step one, cutting and blanking a plate blank of a skin to be manufactured by adopting a laser 1 to obtain a plate 2 with a margin area. The laser power of the laser 1 is 1000W; in the cutting and blanking process, the diameter of a light spot of the laser 1 is set to be 0.5mm, and the cutting speed is 10mm/s.
The shape of the panel 2 is consistent with that of the skin to be manufactured, and the edge of the panel 2 is 10-20mm larger than that of the skin to be manufactured, which is the margin area, as shown in fig. 2.
And step two, horizontally fixing the plate 2. The method for horizontally fixing the plate 2 comprises the following steps:
horizontally placing the base 4, and horizontally placing the plate 2 on the upper surface of the base 4; placing the clamping plate 3 on the upper surface of the plate 2; the clamping plate 3 and the base 4 are fixed, and the plate 2 is clamped and fixed.
And step three, processing bending positioning holes on the plate 2 by using a laser 1 according to a preset bending line. Each bending line corresponds to 2 bending positioning holes, the 2 bending positioning holes are arranged at two ends of the corresponding bending line, and the bending positioning holes are located in the allowance area; the center of the bending positioning hole is 5-8mm away from the edge of the skin to be manufactured.
The working parameters of the laser 1 during processing of the bent positioning hole are as follows: the laser power is 1000W, and the spot diameter is 1mm.
And step four, rotating the plate 2 to enable the part to be bent of the plate 2 to be suspended relative to the base 4. When the plate material 2 is suspended, the bending line on the plate material 2 is kept parallel to the edge of the base 4.
And step five, starting the laser 1 to emit laser beams to perform multi-pass scanning on the plate along the bending line by taking the positioning hole as a reference, so that the plate 2 is gradually bent to a target angle, as shown in fig. 3. The working parameters of the laser 1 when scanning the bending line are as follows:
the laser power was 1000W, the spot diameter was 2mm, and the scanning speed of the laser 1 along the bend line was 100mm/s.
The laser 1 scans the bending line for multiple times, and monitors the bending angle of the part to be bent of the plate 2 in real time through a laser emitter 5 and a CCD camera 6; the laser emitter 5 emits laser to the bending surface of the plate 2, the laser is reflected and scattered on the bending surface, and the reflected laser is received by the CCD camera 6; the reflected laser changes along with the angle change of the bending surface; and obtaining the real-time bending angle of the plate 2 according to the change condition of the laser signal.
And step six, performing laser cutting removal on the residual area around the plate 2 by using a laser 1 to obtain the bent skin.
The working parameters of the laser 1 when the laser cutting and removing are carried out on the allowance area are as follows:
the laser power is 1000W, the spot diameter is 0.5mm, and the cutting speed is 10mm/s.
According to the full-process laser processing method for the folded surface skin of the air rudder, provided by the invention, the laser is used as a processing tool in the whole manufacturing process from the original plate blank to the final finished product of the folded surface skin, and any die and press machine are not required in the whole process.
The bending forming of the skin is realized by scanning and bending with laser, and the change of the bending angle is measured in real time by the laser online measurement system in the bending process, so that the closed-loop control of the bending process is realized.
Particularly in the laser bending link, the plastic flowing capacity and the forming limit of the material can be effectively improved under the heating action of the laser, the problem of cracking of the plate of the material difficult to deform during cold bending can be avoided, a forming die and an external force are not needed in the whole process, the plate has no resilience, and the forming precision is high.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make possible variations and modifications of the present invention using the method and the technical contents disclosed above without departing from the spirit and scope of the present invention, and therefore, any simple modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention are all within the scope of the present invention.
Claims (10)
1. The full-process laser processing method of the air vane folding surface skin is characterized by comprising the following steps of: the method comprises the following steps:
cutting and blanking a plate blank of a skin to be manufactured by adopting a laser (1) to obtain a plate material (2) with a margin area;
horizontally fixing the plate (2);
according to a preset bending line, a laser (1) is adopted to process a bending positioning hole on a plate material (2);
rotating the plate (2) to enable the part to be bent of the plate (2) to be suspended relative to the base (4);
scanning the bending line by using a laser (1) to realize that the part to be bent of the plate (2) is bent to a target angle;
and (3) carrying out laser cutting removal on the margin area around the plate (2) by adopting a laser (1) to obtain the bent skin.
2. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: the laser power of the laser (1) is 1000W; in the cutting and blanking process, the diameter of a light spot of the laser (1) is set to be 0.5mm, and the cutting speed is 10mm/s.
3. The full-process laser processing method for the air rudder folded surface skin according to claim 1, characterized in that: the shape of the plate (2) is consistent with that of the skin to be manufactured, and the edge of the plate (2) is 10-20mm larger than that of the skin to be manufactured, namely the margin area.
4. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: the method for horizontally fixing the plate (2) comprises the following steps:
horizontally placing the base (4), and horizontally placing the plate (2) on the upper surface of the base (4); placing the clamping plate (3) on the upper surface of the plate (2); the clamping plate (3) is fixed with the base (4) to clamp and fix the plate (2).
5. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: each bending line corresponds to 2 bending positioning holes, the 2 bending positioning holes are arranged at two ends of the corresponding bending line, and the bending positioning holes are located in the allowance area; the center of the bending positioning hole is 5-8mm away from the edge of the skin to be manufactured.
6. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: the working parameters of the laser (1) during processing of the bent positioning hole are as follows:
the laser power is 1000W, and the spot diameter is 1mm.
7. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: when the plate (2) is suspended, the bending line on the plate (2) is kept parallel to the edge of the base (4).
8. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: the working parameters of the laser (1) when scanning the bending line are as follows:
the laser power is 1000W, the spot diameter is 2mm, and the scanning speed of the laser (1) along the bending line is 100mm/s.
9. The full-process laser processing method of the air rudder break surface skin according to claim 1, characterized by comprising the following steps of: the laser (1) scans the bending line for multiple times, and monitors the bending angle of the part to be bent of the plate (2) in real time through a laser emitter (5) and a CCD (charge coupled device) camera (6); the laser emitter (5) emits laser to the bending surface of the plate (2), the laser is reflected and scattered on the bending surface, and the reflected laser is received by the CCD camera (6); the reflected laser changes along with the angle change of the bending surface; and obtaining the real-time bending angle of the plate (2) according to the change condition of the laser signal.
10. The full-process laser processing method for the air rudder folded surface skin according to claim 1, characterized in that: the working parameters of the laser (1) when the allowance region is removed by laser cutting are as follows:
the laser power is 1000W, the spot diameter is 0.5mm, and the cutting speed is 10mm/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210759384.XA CN115284001A (en) | 2022-06-29 | 2022-06-29 | Full-process laser processing method for air rudder folding surface skin |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210759384.XA CN115284001A (en) | 2022-06-29 | 2022-06-29 | Full-process laser processing method for air rudder folding surface skin |
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| CN115284001A true CN115284001A (en) | 2022-11-04 |
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| CN202210759384.XA Pending CN115284001A (en) | 2022-06-29 | 2022-06-29 | Full-process laser processing method for air rudder folding surface skin |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004291082A (en) * | 2003-03-28 | 2004-10-21 | Toppan Forms Co Ltd | Laser beam machining system for bending line |
| CN105033004A (en) * | 2015-06-17 | 2015-11-11 | 北京卫星制造厂 | Lightweight wall plate laser-inducing flexible forming system and method |
| CN108817864A (en) * | 2018-07-20 | 2018-11-16 | 北京星航机电装备有限公司 | A kind of forming of titanium alloy arc-shaped workpiece and positional dissection method |
| CN110314980A (en) * | 2019-07-23 | 2019-10-11 | 大连理工大学 | A kind of line style light spot laser bending forming method of sheet metal |
| US20200047281A1 (en) * | 2018-08-09 | 2020-02-13 | U.S. Army Research Laboratory | Complex laser folding and fabrication |
| CN112427543A (en) * | 2020-10-21 | 2021-03-02 | 大连理工大学 | Laser bending forming method for knife holder seat of knife switch |
| CN214583091U (en) * | 2021-03-12 | 2021-11-02 | 华中科技大学 | Online measuring device for bending angle of plate |
-
2022
- 2022-06-29 CN CN202210759384.XA patent/CN115284001A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004291082A (en) * | 2003-03-28 | 2004-10-21 | Toppan Forms Co Ltd | Laser beam machining system for bending line |
| CN105033004A (en) * | 2015-06-17 | 2015-11-11 | 北京卫星制造厂 | Lightweight wall plate laser-inducing flexible forming system and method |
| CN108817864A (en) * | 2018-07-20 | 2018-11-16 | 北京星航机电装备有限公司 | A kind of forming of titanium alloy arc-shaped workpiece and positional dissection method |
| US20200047281A1 (en) * | 2018-08-09 | 2020-02-13 | U.S. Army Research Laboratory | Complex laser folding and fabrication |
| CN110314980A (en) * | 2019-07-23 | 2019-10-11 | 大连理工大学 | A kind of line style light spot laser bending forming method of sheet metal |
| CN112427543A (en) * | 2020-10-21 | 2021-03-02 | 大连理工大学 | Laser bending forming method for knife holder seat of knife switch |
| CN214583091U (en) * | 2021-03-12 | 2021-11-02 | 华中科技大学 | Online measuring device for bending angle of plate |
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