CN111733416A - Device for repairing airplane thin-wall beam through laser deposition and repairing method thereof - Google Patents
Device for repairing airplane thin-wall beam through laser deposition and repairing method thereof Download PDFInfo
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- CN111733416A CN111733416A CN202010764703.7A CN202010764703A CN111733416A CN 111733416 A CN111733416 A CN 111733416A CN 202010764703 A CN202010764703 A CN 202010764703A CN 111733416 A CN111733416 A CN 111733416A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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Abstract
The invention relates to a device for repairing an airplane thin-wall beam by laser deposition and a repairing method thereof, wherein the device comprises: the heating plate is used for bearing the thin-walled beam of the airplane to be repaired; the laser deposition platform is used for repairing the airplane thin-wall beam to be repaired; the alternating magnetic field auxiliary platform is used for providing a magnetic field with variable direction and intensity and is fixed on the laser deposition platform; the liquid nitrogen forced cooling device is used for cooling the repaired airplane thin-wall beam; the thin-wall beam of the airplane to be repaired is loaded on the heating plate to be heated, is repaired through the laser deposition platform under the magnetic field environment provided by the alternating magnetic field auxiliary platform, and is cooled under the action of the liquid nitrogen forced cooling device. The device for repairing the thin-walled beam of the airplane through laser deposition has the advantages of good overall repairing effect, high efficiency and low cost.
Description
Technical Field
The invention relates to laser deposition repairing equipment, in particular to a device for repairing an airplane thin-wall beam through laser deposition and a repairing method thereof.
Background
With the continuous development of the aviation manufacturing technology, the structural design of the airplane thin-wall beam gradually tends to be complicated and integrated, and meanwhile, in order to meet the requirements of the airplane on bearing load capacity and structural design, high-strength, high-cost and difficult-to-process alloy materials such as titanium alloy are widely used for production at present. Therefore, the thin-wall beam of the airplane has high cost, complex process and longer production period; meanwhile, the steel pipe is extremely easy to be damaged by cracks and the like under the action of huge alternating load force in the service process.
The Laser Deposition Repair (LDR) technology is a Laser remanufacturing technology which is started in the 80 th of 20 th century, and the technology is based on Laser cladding and rapid prototyping technology, takes metal powder as a raw material, and utilizes a high-energy Laser heat source to directly superpose and form the geometric appearance of a defective part layer by layer on the defective part according to the geometric shape of the defective part to be repaired, thereby achieving the purposes of recovering the geometric dimension of the part to be repaired and optimizing the tissue and the mechanical property. Compared with the traditional repair technology, the laser deposition repair technology has the advantages that the repair layer is metallurgically bonded with the substrate, the interface bonding strength is high, the dilution rate is low and controllable, the heat affected zone is small, the substrate is not easy to deform, the comprehensive mechanical property is excellent, the subsequent processing treatment is less, the flexible manufacturing is convenient to realize, and the like. However, the airplane thin-wall beam repaired by the existing laser deposition repairing technology has a serious edge collapse phenomenon, so that the repairing quality is greatly reduced, and the production cost is improved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the device for repairing the thin-walled beam of the airplane through laser deposition is provided.
The technical scheme adopted by the invention for solving the technical problems is as follows: an apparatus for laser deposition repairing an aircraft thin wall beam, comprising:
the heating plate is used for bearing the thin-walled beam of the airplane to be repaired;
the laser deposition platform is used for repairing the airplane thin-wall beam to be repaired;
the alternating magnetic field auxiliary platform is used for providing a magnetic field with variable direction and intensity and is fixed on the laser deposition platform;
the liquid nitrogen forced cooling device is used for cooling the repaired airplane thin-wall beam; wherein
And the thin-wall beam of the airplane to be repaired is loaded on the heating plate to be heated, is repaired through the laser deposition platform under the magnetic field environment provided by the alternating magnetic field auxiliary platform, and is cooled under the action of the liquid nitrogen forced cooling device.
Preferably, the laser deposition platform comprises a laser generator, a laser deposition head connected with the laser generator, a protective gas system communicated and connected with the laser deposition head, and a constant-temperature powder feeder communicated and connected with the laser deposition head; wherein
And the powder heated by the constant-temperature powder feeder is sprayed to the thin-wall beam of the airplane to be repaired, which is positioned on the heating plate, by the laser deposition head.
Preferably, the constant-temperature powder feeder comprises a box body with a stirring shaft, a first temperature sensor arranged in the box body, an
The inner wall of the box body is provided with a plurality of heating rods.
Preferably, the liquid nitrogen forced cooling device comprises a high-pressure liquid nitrogen tank, a liquid nitrogen containing box communicated and connected with the high-pressure liquid nitrogen tank through an electromagnetic valve, and two copper sheets connected with the liquid nitrogen containing box through pipelines; and
the high-pressure liquid nitrogen tank is provided with a liquid level meter.
Preferably, the device for repairing the airplane thin-wall beam by laser deposition further comprises a computer, an
The computer is respectively and electrically connected with the liquid level meter, the electromagnetic valve and the first temperature sensor.
The thin-wall beam repairing device has the beneficial effects that the thin-wall beam of the airplane to be repaired is heated through the heating plate; the repairing effect of the thin-wall beam of the airplane to be repaired is realized through the laser deposition platform; the alternating magnetic field auxiliary platform is used for providing a magnetic field in the repairing process, the liquid nitrogen forced cooling device is used for cooling the repaired airplane thin-wall beam, the overall repairing effect is good, the efficiency is high, and the cost is low.
The invention also provides a method for repairing the thin-wall beam of the airplane by laser deposition, wherein an alternating magnetic field with variable direction and adjustable strength is provided in the repairing process;
the area to be repaired is a regular area, and the repairing points are laser deposition points;
when the laser deposition point is positioned at the upper half part of the area to be repaired, the direction of the magnetic field force of the alternating magnetic field points to the central line of the area to be repaired from the upper boundary of the area to be repaired;
when the laser deposition point is positioned at the lower half part of the area to be repaired, the direction of the magnetic field force of the alternating magnetic field points to the central line of the area to be repaired from the lower boundary of the area to be repaired.
Preferably, before providing the alternating magnetic field:
s1, carrying out nondestructive flaw detection on the area to be repaired of the airplane thin-walled beam, cutting, trimming, regularizing, polishing, cleaning, wiping dry the damaged part of the thin-walled beam to be repaired, and clamping the damaged part on a laser deposition platform;
s2, building a three-dimensional model and planning a path according to the prefabricated repair size and shape by using a computing mechanism and feeding back the three-dimensional model to the laser deposition platform;
s3, heating the thin-walled beam of the airplane to be repaired to 300-600 ℃, and feeding back the temperature to a computer;
while providing the alternating magnetic field:
s4, adjusting the alternating magnetic field, inputting a preset alternating magnetic field program into a computer, inputting processing parameters into a laser deposition platform, and performing first-layer laser deposition repair processing, wherein the temperature of the thin-wall beam and the cladding layer of the airplane is higher than 600 ℃;
after the alternating magnetic field is provided:
s5, after the first layer of laser deposition repairing processing is finished, cooling the preliminarily repaired airplane thin-wall beam and the cladding layer to 300-600 ℃, and feeding back the temperature to the computer;
and S6, and the step S4 and the step S5 are repeated until the whole repairing process is completed.
Preferably, in step S1, 400-mesh sandpaper is used for polishing, and alcohol is used for cleaning and wiping; in the step S4, the processing parameters include laser power of 1200W-2000W, focal length of 300mm, scanning speed of 5 mm/S-7 mm/S, overlapping rate of 35% -50% and scanning interval of 2 mm; the strength of the alternating magnetic field is 40 mT-70 mT.
The repairing method has the beneficial effects that when the area to be repaired is in a repairing state, the effect of the alternating magnetic field is increased, the traditional 'edge collapse phenomenon' is well repaired, the internal defects of the repaired airplane thin-walled beam are eliminated, the comprehensive performance of the repaired airplane thin-walled beam is improved, and the high-quality, high-efficiency and low-cost repairing of the airplane thin-walled beam to be repaired is realized.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic diagram of a preferred embodiment of an apparatus for laser deposition repair of aircraft thin wall beams in accordance with the present invention;
FIG. 2 is a schematic structural view of a preferred embodiment of a laser deposition head and heating plate of the present invention;
FIG. 3 is a schematic structural view of a preferred embodiment of the constant temperature powder feeder of the present invention;
FIG. 4 is a schematic diagram of a preferred embodiment of the liquid nitrogen forced cooling apparatus of the present invention;
FIG. 5 is a schematic view of a repair path of a repair point of the present invention;
FIG. 6 is a schematic diagram of the alternating magnetic field and the repair point of the present invention.
In the figure:
the airplane thin-wall beam 1 and the heating plate 2;
a laser deposition platform 3;
the constant-temperature powder feeder 31, a stirring shaft 311, a box 312, a stirring blade 313, a heating rod 314 and a first temperature sensor 315;
a laser deposition head 32;
an alternating magnetic field auxiliary platform 4;
a liquid nitrogen forced cooling device 5, a copper sheet 501, a high-pressure liquid nitrogen tank 502, an electromagnetic valve 503, a liquid nitrogen containing box 504 and a liquid level meter 505;
computer 6, second temperature sensor 7.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic views illustrating only the basic structure of the present invention in a schematic manner, and thus show only the constitution related to the present invention.
Example one
As shown in fig. 1 to 4, the invention provides a device for repairing an airplane thin-wall beam by laser deposition, which comprises: the heating plate 2 is used for bearing the airplane thin-wall beam 1 to be repaired; the laser deposition platform 3 is used for repairing the airplane thin-wall beam 1 to be repaired; the alternating magnetic field auxiliary platform 4 is used for providing a magnetic field with variable direction and intensity, and the alternating magnetic field auxiliary platform 4 is fixed on the laser deposition platform 3; the liquid nitrogen forced cooling device 5 is used for cooling the repaired airplane thin-wall beam 1; the airplane thin-wall beam 1 to be repaired is loaded on the heating plate 2 to be heated, is repaired through the laser deposition platform 3 under the magnetic field environment provided by the alternating magnetic field auxiliary platform 4, and is cooled under the action of the liquid nitrogen forced cooling device 5.
The heating of the airplane thin-wall beam 1 to be repaired is realized through the heating plate 2; the repairing effect of the airplane thin-wall beam 1 to be repaired is realized through the laser deposition platform 3; the alternating magnetic field auxiliary platform 4 is used for providing a magnetic field in the repairing process, the liquid nitrogen forced cooling device 5 is used for cooling the repaired airplane thin-wall beam 1, and the airplane thin-wall beam repairing device is good in overall repairing effect, high in efficiency and low in cost.
In some embodiments, the laser deposition platform 3 comprises a laser generator, a laser deposition head 32 connected with the laser generator, a shielding gas system communicated with and connected with the laser deposition head 32, and a constant temperature powder feeder 31 communicated with and connected with the laser deposition head 32; wherein the powder heated by the constant temperature powder feeder 31 is sprayed by the laser deposition head 32 onto the thin-walled beam 1 of the airplane to be repaired on the heating plate 2.
It should be noted that the laser generator, the laser deposition head 32 and the shielding gas system are well known in the art and will not be described in detail herein.
In some embodiments, the constant temperature powder feeder 31 includes a box 312 having a stirring shaft 311 and a first temperature sensor 315 disposed inside the box 312, and the inner wall of the box 312 has a plurality of heating rods 314.
The stirring shaft 311 is rotatably disposed in the box 312, and the stirring shaft 311 is coaxially fixed with the output shaft of the motor, the stirring shaft 311 has a stirring blade 313, when the motor drives the stirring shaft 311 to rotate, the stirring blade 313 drives the powder in the box 312 to scrape up, thereby promoting the uniform heating effect of the subsequent heating rod 314, and the heating rod 314 itself has been widely used in the prior art, so that the description thereof is omitted here.
The first temperature sensor 315 is mainly used for monitoring the temperature of the powder stirred by the stirring shaft 311 under the heating effect of the heating rod 314 in real time.
In some embodiments, the liquid nitrogen forced cooling device 5 comprises a high-pressure liquid nitrogen tank 502, a liquid nitrogen containing box 504 communicated and connected with the high-pressure liquid nitrogen tank 502 through an electromagnetic valve 503, and two copper sheets 501 connected with the liquid nitrogen containing box 504 through pipelines; and the high-pressure liquid nitrogen tank 502 is provided with a liquid level meter 505.
The two copper sheets 501 are respectively positioned at two sides of the heating plate 2, the airplane thin-wall beam 1 to be repaired is arranged between the two copper sheets 501, and the change of the temperature of the copper sheets 501 can be directly transmitted to the airplane thin-wall beam 1 to be repaired, so that the heat conduction effect is realized.
Liquid nitrogen in the high-pressure liquid nitrogen tank 502 is injected into the liquid nitrogen containing box 504 through the electromagnetic valve 503 and then is sprayed to the copper sheet 501 through the pipeline, the copper sheet 501 has good heat conductivity and is rapidly cooled under the action of the liquid nitrogen, and the copper sheet 501 synchronously transfers the temperature to the thin-wall beam 1 of the airplane to be repaired, so that the rapid cooling effect is realized.
The liquid level meter 505 is mainly used for observing the capacity in the high-pressure liquid nitrogen tank 502, so that the liquid nitrogen can be increased in time.
In some embodiments, the apparatus for repairing an airplane thin-wall beam 1 by laser deposition further includes a computer 6, and the computer 6 is electrically connected to the liquid level meter 505, the solenoid valve 503 and the first temperature sensor 315 respectively.
The programs used by the computer 6, the liquid level meter 505, the electromagnetic valve 503 and the first temperature sensor 315 are conventional programs, and the computer 6 can adjust the electromagnetic valve 503 so as to control the capacity on the two copper sheets 501.
Example two
The second embodiment can be performed based on the first embodiment.
As shown in fig. 1 to 4, the second embodiment provides a method for repairing an airplane thin-walled beam 1 by laser deposition, and the method for repairing includes providing an alternating magnetic field during repairing, wherein the intensity and direction of the alternating magnetic field can be adjusted, and the adjustment of the intensity and direction is realized according to different processing parameters. The processing parameters comprise processing positions, processing areas and processing thicknesses, and the intensity of the alternating magnetic field is adjusted according to different processing thicknesses, namely, the deeper the thickness is, the stronger the intensity of the alternating magnetic field is. Wherein, the position of the alternating magnetic field only needs to be ensured to act on a laser cladding molten pool.
As for the processing position, it should be noted that the area to be repaired must be a regular area, such as a cube, a cuboid, a terrace, etc., and the laser repair is performed from one repair point to a second repair point, which is named as a laser deposition point.
If the area to be repaired is a cube, the area to be repaired starts from a square on the bottom surface of the cube when being processed.
When the laser deposition point is positioned on the upper half part of the bottom surface square, the direction of the magnetic field force of the alternating magnetic field points to the central line of the bottom surface square from the upper boundary of the bottom surface square; when the laser deposition point is positioned at the lower half part of the bottom surface square, the direction of the magnetic field force of the alternating magnetic field is directed to the central line of the bottom surface square from the lower boundary of the bottom surface square.
If the area to be repaired is a step, the processing is started from the bottom surface of the step in a trapezoidal manner.
When the laser deposition point is positioned at the upper half part of the bottom surface trapezoid, the direction of the magnetic field force of the alternating magnetic field points to the central line of the bottom surface trapezoid from the upper boundary of the bottom surface trapezoid; when the laser deposition point is positioned at the lower half part of the bottom surface trapezoid, the direction of the magnetic field force of the alternating magnetic field points to the central line of the bottom surface trapezoid from the lower boundary of the bottom surface trapezoid.
EXAMPLE III
As shown in FIGS. 1-4, the third embodiment is a supplement to the second embodiment.
S1, carrying out nondestructive flaw detection on the area to be repaired of the airplane thin-wall beam 1, cutting, trimming, regularizing, polishing, cleaning, wiping the damaged part of the thin-wall beam to be repaired, and clamping the thin-wall beam on the laser deposition platform 3;
s2, constructing a three-dimensional model by using the computer 6 according to the prefabricated repair size and shape, planning a path and feeding back to the laser deposition platform 3;
s3, heating the thin-walled beam 1 of the airplane to be repaired to 300-600 ℃, and feeding back the temperature to the computer 6;
s4, adjusting the alternating magnetic field, inputting a preset alternating magnetic field program into the computer 6, inputting processing parameters into the laser deposition platform 3, and performing first-layer laser deposition repair processing, wherein the temperature of the surface of the airplane thin-walled beam 1 repaired by the first layer is higher than 600 ℃;
s5, after the first layer of laser deposition repairing processing is finished, cooling the preliminarily repaired airplane thin-wall beam 1 and the cladding layer to 300-600 ℃, and feeding back the temperature to the computer 6;
and S6, and the step S4 and the step S5 are repeated until the whole repairing process is completed.
In step S1, 400-mesh sand paper is used for polishing, and alcohol is used for cleaning and wiping; in the step S4, the processing parameters include laser power of 1200W-2000W, focal length of 300mm, scanning speed of 5 mm/S-7 mm/S, overlapping rate of 35% -50% and scanning interval of 2 mm; the strength of the alternating magnetic field is 40 mT-70 mT.
Example four
As shown in fig. 1 to 4, the fourth embodiment is a combination of the third embodiment and the first embodiment.
S1, carrying out nondestructive flaw detection on the area to be repaired of the airplane thin-wall beam 1, cutting, trimming, regularizing, polishing, cleaning, wiping dry the damaged part of the airplane thin-wall beam 1 to be repaired, and clamping the damaged part on the laser deposition platform 3;
s2, constructing a three-dimensional model and planning a path by using the computer 6 according to the prefabricated repair size and shape;
s3, filling the powder required by repair into the constant-temperature powder feeder 31, heating the powder to 200-400 ℃, and feeding the powder back to the computer 6 through the first temperature sensor 315; meanwhile, the heating plate 2 is utilized to heat the airplane thin-wall beam 1 to be repaired to 300-600 ℃, and the heated airplane thin-wall beam is fed back to the computer 6 through a second temperature sensor 7 arranged on the heating plate 2;
s4, opening the alternating magnetic field auxiliary platform 4, inputting a preset alternating magnetic field program into the computer 6, opening the constant-temperature powder feeder 31 and the laser deposition platform 3, inputting processing parameters, and performing first-layer laser deposition repair processing;
s5, after the first layer of laser deposition repairing processing is finished, opening a liquid nitrogen forced cooling device 5, controlling the capacity of liquid nitrogen acting on the two copper sheets 501 through an adjusting electromagnetic valve 503, rapidly cooling the thin-walled beam 1 of the airplane to be repaired and the cladding layer to 300-600 ℃, and feeding back the temperature to a computer 6 through a second temperature sensor 7;
and S6, repeating the step S4 and the step S5 until the whole repairing process is finished.
Wherein, if the surface of the airplane thin-wall beam 1 to be repaired has cracks, magnetic powder inspection can be used, and if the surface of the airplane thin-wall beam 1 to be repaired has no obvious defects and has internal defects, ultrasonic inspection is used.
The software for constructing the three-dimensional model and planning the path may be Mastercam, and the software for the alternating magnetic field auxiliary platform 4 may be equipment for providing an alternating magnetic field, such as an alternating current coil.
EXAMPLE five
As shown in fig. 1 to 6, the fifth embodiment is a specific embodiment of the fourth embodiment, wherein the length of the area to be repaired of the thin-walled beam 1 of the aircraft to be repaired is 3500mm, the width is 80mm, and the depth is 5 mm.
As shown in FIG. 6, H has a value of 80mm, A, B is a repair point, i.e., a laser deposition point, FLFor magnetic force, O is the origin, as shown in FIG. 5, which is the repair path of the repair point.
Firstly, carrying out nondestructive flaw detection on an area to be repaired, removing surface cracks and potential damaged areas by adopting a mechanical means, cutting and trimming the damaged part of the thin-walled beam 1 of the airplane to be repaired into a regular rectangular area, then polishing by using 400-mesh abrasive paper, cleaning and drying by using alcohol, and clamping on a laser deposition platform 3.
Secondly, according to the prefabricated repair size and shape, a three-dimensional model to be repaired is constructed in the region to be repaired by Mastercam software in the computer 6 for layered slicing and path planning, and the path of laser deposition repair is realized in a cyclic reciprocating mode.
Then, titanium alloy powder required for repair is loaded into the constant-temperature powder feeder 31, the titanium alloy powder is stirred and uniformly heated to 300 ℃ by using the heating rod 314, the stirring shaft 311 and the stirring blade 313, the airplane thin-wall beam 1 is heated to 500 ℃ by using the heating plate 2, the temperature of the titanium alloy powder is fed back to the computer 6 by using the first temperature sensor 315, and the temperature of the airplane thin-wall beam 1 is fed back to the computer 6 by using the second temperature sensor 7.
As shown in fig. 6, next, the alternating magnetic field assisting stage 4 is opened, the upper vertex of the area a (coordinates of (0 mm, 40 mm)) is used as a starting point, and a program for inputting a predetermined alternating magnetic field into the computer 6 is calculatedThe machine 6 controls the direction of the magnetic field when the machining area is located at (0 mm, 40 mm)]When the magnetic field is in-F direction, namely within 40mm of the upper half part of the area to be repairedLThe magnetic field strength is set to 40 mT; the processing area is located at (0 mm, -40 mm)]When the magnetic field is in the direction of F, namely the lower half part of the area to be repaired is within 40mmLThe magnetic field strength is set to 40 mT. And opening the powder feeder and the laser deposition system, and inputting processing parameters, wherein the laser power is 1500W, the focal length is 300mm, the scanning speed is 6mm/s, the lap joint rate is 45%, and the scanning interval is 2 mm. And carrying out first layer laser deposition repair processing.
Then, after the laser deposition repair processing of the first layer is finished, the liquid nitrogen forced cooling device 5 is opened, heat is conducted through the two copper sheets 501, the airplane thin-wall beam 1 and the cladding layer are rapidly cooled to 500 +/-50 ℃, and the temperature of the airplane thin-wall beam 1 is fed back to the computer 6 through the second temperature sensor 7.
And finally, adjusting the alternating magnetic field, cladding the cladding layer and cooling the airplane thin-wall beam 1 repeatedly until the cladding layer is accumulated to five layers, and then finishing the repairing and processing of the whole damaged area.
Detection link
The method comprises the steps of detecting the airplane thin-wall beam 1 repaired under the condition of existence of an alternating magnetic field through detection equipment, wherein the areas to be repaired of the two airplane thin-wall beams 1 are completely the same, the materials are completely the same,
| edge collapse phenomenon | Tensile strength | Maximum load | Porosity of | |
| Without alternating magnetic field | Is provided with | 983.6MPa | 80.554kN | 13% |
| With alternating magnetic field | Is free of | 1181.6Mpa | 87.863kN | 4% |
The graph can undoubtedly obtain that the repairing effect of the airplane thin-wall beam 1 under the action of the alternating magnetic field is obviously superior to that of the airplane thin-wall beam 1 repaired without the alternating magnetic field.
In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (8)
1. A device for repairing an airplane thin-wall beam through laser deposition is characterized by comprising:
the heating plate is used for bearing the thin-walled beam of the airplane to be repaired;
the laser deposition platform is used for repairing the airplane thin-wall beam to be repaired;
the alternating magnetic field auxiliary platform is used for providing a magnetic field with variable direction and intensity and is fixed on the laser deposition platform;
the liquid nitrogen forced cooling device is used for cooling the repaired airplane thin-wall beam; wherein
And the thin-wall beam of the airplane to be repaired is loaded on the heating plate to be heated, is repaired through the laser deposition platform under the magnetic field environment provided by the alternating magnetic field auxiliary platform, and is cooled under the action of the liquid nitrogen forced cooling device.
2. The laser deposition apparatus for repairing an aircraft thin wall beam as claimed in claim 1,
the laser deposition platform comprises a laser generator, a laser deposition head connected with the laser generator, a protective gas system communicated and connected with the laser deposition head, and a constant-temperature powder feeder communicated and connected with the laser deposition head; wherein
And the powder heated by the constant-temperature powder feeder is sprayed to the thin-wall beam of the airplane to be repaired, which is positioned on the heating plate, by the laser deposition head.
3. The laser deposition apparatus for repairing an aircraft thin wall beam as claimed in claim 2,
the constant-temperature powder feeder comprises a box body with a stirring shaft, a first temperature sensor arranged in the box body, an
The inner wall of the box body is provided with a plurality of heating rods.
4. The laser deposition apparatus for repairing an aircraft thin wall beam as claimed in claim 3,
the liquid nitrogen forced cooling device comprises a high-pressure liquid nitrogen tank, a liquid nitrogen containing box communicated and connected with the high-pressure liquid nitrogen tank through an electromagnetic valve, and two copper sheets connected with the liquid nitrogen containing box through pipelines; and
the high-pressure liquid nitrogen tank is provided with a liquid level meter.
5. The laser deposition apparatus for repairing an aircraft thin wall beam according to claim 4,
the device for repairing the airplane thin-wall beam through laser deposition also comprises a computer, an
The computer is respectively and electrically connected with the liquid level meter, the electromagnetic valve and the first temperature sensor.
6. A method for repairing an airplane thin-wall beam through laser deposition is characterized in that an alternating magnetic field with variable direction and adjustable strength is provided in the repairing process;
the area to be repaired is a regular area, and the repairing points are laser deposition points;
when the laser deposition point is positioned at the upper half part of the area to be repaired, the direction of the magnetic field force of the alternating magnetic field points to the central line of the area to be repaired from the upper boundary of the area to be repaired;
when the laser deposition point is positioned at the lower half part of the area to be repaired, the direction of the magnetic field force of the alternating magnetic field points to the central line of the area to be repaired from the lower boundary of the area to be repaired.
7. The method for repairing an airplane thin-wall beam by laser deposition according to claim 6,
prior to providing the alternating magnetic field:
s1, carrying out nondestructive flaw detection on the area to be repaired of the airplane thin-walled beam, cutting, trimming, regularizing, polishing, cleaning, wiping dry the damaged part of the thin-walled beam to be repaired, and clamping the damaged part on a laser deposition platform;
s2, building a three-dimensional model and planning a path according to the prefabricated repair size and shape by using a computing mechanism and feeding back the three-dimensional model to the laser deposition platform;
s3, heating the thin-walled beam of the airplane to be repaired to 300-600 ℃, and feeding back the temperature to a computer;
while providing the alternating magnetic field:
s4, adjusting the alternating magnetic field, inputting a preset alternating magnetic field program into a computer, inputting processing parameters into a laser deposition platform, and performing first-layer laser deposition repair processing, wherein the temperature of the thin-wall beam and the cladding layer of the airplane is higher than 600 ℃;
after the alternating magnetic field is provided:
s5, after the first layer of laser deposition repairing processing is finished, cooling the preliminarily repaired airplane thin-wall beam and the cladding layer to 300-600 ℃, and feeding back the temperature to the computer;
and S6, and the step S4 and the step S5 are repeated until the whole repairing process is completed.
8. The method for repairing an airplane thin-walled beam by laser deposition according to claim 7,
in step S1, 400-mesh sand paper is adopted for polishing, and alcohol is adopted for cleaning and wiping;
in the step S4, the processing parameters include laser power of 1200W-2000W, focal length of 300mm, scanning speed of 5 mm/S-7 mm/S, overlapping rate of 35% -50% and scanning interval of 2 mm;
the strength of the alternating magnetic field is 40 mT-70 mT.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112372232A (en) * | 2020-11-05 | 2021-02-19 | 哈尔滨理工大学 | Method and device for repairing die by array injection |
| CN113102771A (en) * | 2021-04-09 | 2021-07-13 | 武汉理工大学 | In-situ laser additive repair method based on magnetic suspension principle |
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