CN114289730B - Airplane protective grating repairing substrate and repairing method based on laser selective melting process - Google Patents
Airplane protective grating repairing substrate and repairing method based on laser selective melting process Download PDFInfo
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- CN114289730B CN114289730B CN202111492208.6A CN202111492208A CN114289730B CN 114289730 B CN114289730 B CN 114289730B CN 202111492208 A CN202111492208 A CN 202111492208A CN 114289730 B CN114289730 B CN 114289730B
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Abstract
The invention relates to the technical field of laser selective melting additive manufacturing, in particular to an aircraft protective grating repairing substrate and a repairing method based on a laser selective melting process, wherein the substrate comprises a base, a base and a base, wherein the base is provided with a threaded hole which can be arranged on laser selective melting equipment; the lower end part of the bent pipe is arranged on the base through a bent pipe adjusting screw and a bent pipe cushion block; the top plate is installed on the upper end part of the bent pipe through a top plate adjusting screw and a top plate cushion block, and a plurality of clamping devices which can approach or depart from the center of the plate surface are uniformly distributed on the top plate. Compared with the traditional substrate, the special repairing substrate is added with the function of clamping parts, so that the repairing substrate is high in operability and adaptability; the damaged part of the damaged protective grating is removed along the 45-degree cross section of the side line, so that the protective grating can be directly formed by depending on a lower solid area, the workload is reduced, the defect between the first repair layer and the substrate is effectively reduced through the first layer of twice laser scanning, and the repair quality is improved.
Description
Technical Field
The invention relates to the technical field of laser selective melting additive manufacturing, in particular to an aircraft protective grating repairing substrate and a repairing method based on a laser selective melting process.
Background
The laser selective melting technology utilizes high-energy beam laser to melt thin layers of powder which are paved on a powder bed in advance, melts and stacks the formed parts layer by layer, is particularly suitable for preparing parts with complex structure and high precision, has the advantage of no need of processing or small amount of finish machining after forming, and is widely applied to the additive manufacturing field of aerospace, aviation and medical precision structural parts.
Aircraft grilles are typically mounted to the engine air intake to prevent foreign objects such as sand and stones from entering the engine. The part has a large number of grid structural characteristics, the thickness of the grid partition wall is about 1mm, the conventional preparation process is complex, and the part is usually prepared by adopting a machining and electric spark punching mode, so that the cost is high. For damaged aircraft fences, the conventional processing mode is direct replacement, and if the damaged aircraft fence is repaired, the cost is greatly reduced. At present, no repair mode for the part with the complex thin-wall grid structure exists, and the conventional laser cladding repair process is difficult to control the repair dimensional accuracy and repair the aircraft protective grating due to larger light spots, higher laser power, larger molten pool section size. The laser selective melting process has smaller light spot, smaller cross section size of the molten pool and high forming size precision. The patent provides an aircraft protection grating repairing method based on a laser selective melting process, and specifically solves the repairing problem of the aircraft protection grating.
Disclosure of Invention
Aiming at the technical problems, the invention provides an aircraft protective grating repairing substrate and an aircraft protective grating repairing method based on a laser selective melting process, and particularly solves the repairing problem of the aircraft protective grating.
The technical problems to be solved by the invention are realized by adopting the following technical scheme:
an aircraft protective grating repair substrate based on a laser selective melting process, comprising:
the base is provided with a threaded hole which can be arranged on the laser selective melting equipment;
the lower end part of the bent pipe is arranged on the base through a bent pipe adjusting screw and a bent pipe cushion block;
the top plate is installed on the upper end part of the bent pipe through a top plate adjusting screw and a top plate cushion block, and a plurality of clamping devices which can approach or depart from the center of the plate surface are uniformly distributed on the top plate.
Preferably, a rectangular boss is arranged on the base, a mounting tube with an extending section similar to an omega shape is arranged on the rectangular boss, and the lower end part of the bent tube is mounted on the mounting tube.
Preferably, the bent pipe comprises a first section of pipe body arranged in the installation pipe on the rectangular boss, a second section of pipe body vertically connected with the first section of pipe body, and a third section of pipe body horizontally connected with the second section of pipe body.
Preferably, the end section of the third section of pipe body is approximately omega-shaped, and the top plate is arranged on the third section of pipe body through the top plate adjusting screw and the top plate cushion block.
Preferably, a plurality of groups of threaded holes are uniformly distributed on the top plate, each group of threaded holes are distributed along the direction from the edge to the center, and the clamping device is correspondingly arranged on the threaded holes.
Preferably, the base is in the shape of a U-shaped opening.
The method for repairing the aircraft protective grating repairing substrate based on the laser selective melting process comprises the following steps:
removing damaged parts on a damaged aircraft protective grating, and polishing a section;
secondly, a three-dimensional model of the damaged aircraft protective grating is obtained through a three-dimensional laser scanner, and is compared with the intact aircraft protective grating to construct a damaged part model;
thirdly, mounting the damaged aircraft protective grating on the substrate through the clamping device, leveling, scanning the integral three-dimensional model of the substrate clamped with the damaged protective grating through the three-dimensional laser scanner, and determining the placement position of the three-dimensional model of the damaged aircraft protective grating in a forming bin and the height of the substrate to be lowered after mounting;
fourthly, mounting the substrate on a base of a forming bin of a laser selective melting device, lowering the height determined in the third step, paving powder layer by layer, and scanning by laser according to a preset model to finish the repair of the aircraft protective grating;
and fifthly, after the repair is finished, opening a forming bin of the laser selective melting equipment, removing the substrate, loosening a clamping device on the substrate, and taking out the repaired airplane protective grating.
As a further improvement of the repairing method in the invention, the removing mode in the step (one) is to remove the section at an angle of 45 degrees along the edge line, and the polishing requirement on the section is that the roughness reaches Ra0.8μm and the flatness reaches 2 μm.
As a further improvement of the repairing method in the invention, the powder in the step (four) is TC4 powder, the first layer powder is scanned twice, and the laser selective melting process parameters corresponding to the first layer powder are as follows: the laser power is 180-225W, the scanning speed is 1200-1500 mm/s, the scanning interval is 70-80 mu m, and the layer thickness is 30 mu m.
As a further improvement of the repairing method in the invention, the laser selective melting process parameters corresponding to the powder of the rest layers except the first layer in the step (four) are as follows: the laser power is 140-160W, the scanning speed is 1200-1500 mm/s, the scanning interval is 70-80 mu m, and the layer thickness is 30 mu m.
The beneficial effects of the invention are as follows:
1. compared with the traditional substrate, the special repairing substrate is added with the function of clamping parts, so that the operability is high; the rotating adjustment of the top plate along the x direction and the y direction can be realized, and the level of the surface to be repaired of the clamping sample is ensured; can realize the centre gripping of different size samples, the adaptability is strong.
2. The damaged part of the damaged protective grating is removed along the 45-degree cross section of the side line, so that the layer-by-layer forming direction is inclined by 45 degrees during repair, the lower solid area can be directly supported for forming, a cantilever structure which is not required to be additionally supported is omitted, and the workload is reduced.
3. The TC4 powder similar to the protective grating material is adopted for repairing, so that good wettability of a molten pool is ensured, related defects are reduced, the defects between the first repairing layer and the substrate are effectively reduced through twice laser scanning of the first layer, and the repairing quality is improved.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic view of a substrate according to the present invention;
FIG. 2 is a schematic view of a base structure according to the present invention;
FIG. 3 is a schematic view of a bent pipe structure according to the present invention;
FIG. 4 is a schematic view of the top plate of the present invention;
FIG. 5 is a schematic structural view of an aircraft protective grille;
FIG. 6 is a schematic view of the structure of the aircraft protective grating after the damaged portion is removed;
fig. 7 is a schematic illustration of placement of an aircraft protective barrier in a clamped condition.
In the figure: 1. a base; 2. a bent pipe adjusting screw; 3. a bent pipe cushion block; 4. bending the pipe; 5. a top plate adjusting screw; 6. a top plate cushion block; 7. a top plate; 8. and a clamping device.
Detailed Description
In order that the manner in which the invention is attained, as well as the features and advantages thereof, will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings.
As shown in figure 1, the aircraft protective grating repairing substrate based on the laser selective melting process mainly comprises a base 1, an elbow adjusting screw 2, an elbow cushion block 3, an elbow 4, a top plate adjusting screw 5, a top plate cushion block 6, a top plate 7 and a clamping device 8.
As shown in fig. 2, the four corners of the base 1 are provided with threaded holes, so that the base 1 can be installed on a laser selective melting device, the base 1 is in a U-shaped opening shape, the missing part provides more operation space for screwing or unscrewing the elbow adjusting screw 2, the base 1 is provided with a cuboid boss, and an installation tube with an approximately omega-shaped section extends out of the cuboid boss and is used for installing the elbow 4, the elbow cushion 3 and the elbow adjusting screw 2.
As shown in fig. 3, the bent pipe 4 may be divided into three sections, the first section is located in a pipe with a cross section of approximately Ω shape installed on a rectangular boss, the second section is perpendicular to the first section, the third section is perpendicular to a plane formed by the first section and the second section, and a cross section of an end of the third section is approximately Ω shape, and is used for installing the top plate 7, the top plate cushion 6 and the top plate adjusting screw 5.
The pipe bending cushion block 3 and the pipe bending adjusting screw 2 are arranged on a pipe with an omega-shaped upper section of the base 1, the pipe bending adjusting screw 2 is loosened, the pipe bending cushion block 3 and the pipe bending 4 are loosened, the pipe bending 4 and the connecting part thereof can rotate along the x axis, the pipe bending adjusting screw 2 is screwed, and the pipe bending cushion block 3 compresses the pipe bending 4 to fix the pipe bending 4.
As shown in fig. 4, the left lower end angular position of the top plate 7 extends out of a section of curved cylinder, the curved cylinder is inserted into a pipe with an approximately omega-shaped section on the third section of pipe body on the elbow 4, and the top plate adjusting screw 5 and the top plate cushion block 6 are also installed on the approximately omega-shaped pipe on the third section of pipe body on the elbow 4. The top plate adjusting screw 5 is loosened, the top plate cushion block 6 is loosened with the bending cylinder on the top plate 7, the top plate 7 and the connecting part thereof can rotate along the y axis, the bent pipe adjusting screw 2 is screwed down, and the top plate cushion block 6 compresses the bending cylinder on the top plate 7, so that the top plate 7 is fixed.
Four groups of threaded holes are uniformly distributed on the top plate 7, each group of threaded holes are distributed along the direction from the edge to the center, and the clamping device 8 is correspondingly arranged on the threaded holes. If the sample is large, the clamping device 8 is installed on the threaded hole near the edge, and if the sample is small, the clamping device 8 is installed on the threaded hole near the center, so that the clamping device 8 can be suitable for samples with different sizes.
The method for repairing the aircraft protective grating repairing substrate based on the laser selective melting process comprises the following steps:
as shown in fig. 5, the aircraft guard grating has a mesh structure. The damaged aircraft protection grating is polished, the damaged part is removed, the removal mode is to remove the aircraft protection grating along the 45-degree cross section of the side line, and the removed aircraft protection grating is shown in fig. 6. The section was polished to a roughness of Ra0.8μm and to ensure a flatness of the plane of 2. Mu.m.
And secondly, obtaining a three-dimensional model of the damaged aircraft protective grating through a three-dimensional laser scanner, and comparing the three-dimensional model with the intact aircraft protective grating to construct a damaged part model.
And (III) the repair surface of the damaged airplane protective grating faces upwards during clamping, as shown in fig. 7, the repair surface of the damaged airplane protective grating is horizontal by adjusting the bent pipe adjusting screw 2 and the top plate adjusting screw 5, and the included angle between the repair surface and the side surface of the airplane protective grating is 45 degrees. The advantage of putting like this is that during the restoration, the shaping direction of layer by layer is 45 orientation of slope, can directly rely on the shaping of below entity region, does not have the cantilever structure that must add the support. And the cantilever structure is not necessarily formed in the arrangement mode, if the cantilever structure is not supported, the powder is only below the powder, no solid support exists, a molten pool is lowered after laser scanning, the forming shape cannot be ensured, and if the support is added, the cantilever structure is removed later, so that the workload is increased.
And fourthly, after the clamping and leveling are finished, scanning the three-dimensional model of the whole substrate of the damaged aircraft protective grating by a three-dimensional laser scanner, and measuring the position of the damaged aircraft protective grating on the substrate and the whole height of the substrate clamped with the damaged protective grating, thereby determining the placement position of the three-dimensional model of the damaged protective grating in a forming bin and the height required to be lowered after the substrate is installed.
And fifthly, mounting the substrate on a base of a forming bin of the laser selective melting equipment, and lowering the height determined in the step (four). Powder is paved layer by layer, laser scans according to a preset model, and repair of the damaged aircraft protective grating is completed. The repair powder adopts TC4 powder similar to the material of the protective grating, so that the good wettability of a molten pool is ensured, and related defects are reduced.
In the repair: the laser selective melting process parameters corresponding to the first layer of powder are as follows: the laser power is 180-225W, the scanning speed is 1200-1500 mm/s, the scanning interval is 70-80 mu m, the layer thickness is 30 mu m, and the first layer is scanned twice. The rest layer process adopts laser power of 140-160W, scanning speed of 1200-1500 mm/s, scanning interval of 70-80 μm and layer thickness of 30 μm.
After the first layer of powder is paved, the thickness of the powder layer in the partial area is larger, the laser power in the first layer process is increased by about 1.3-1.8 times, the heat input is increased, the depth of a molten pool is increased, and the good metallurgical bonding between the melted powder and a matrix is ensured; if the heat input is insufficient, the depth of the molten pool is insufficient, and the metallurgical bonding cannot be ensured at the place with larger thickness of part of the powder layer, so that the repair fails. The defects between the first repair layer and the substrate can be effectively reduced by scanning the laser twice, and the repair quality is improved.
And (six) after the repair is finished, opening a forming bin of the laser selective melting equipment, removing the substrate, loosening a clamping device on the substrate, and taking out the repaired airplane protective grating.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (2)
1. The method for repairing the aircraft protective grating repairing substrate based on the laser selective melting process comprises the following steps of: a base (1) provided with a threaded hole which can be arranged on the laser selective melting equipment; the lower end part of the elbow (4) is arranged on the base (1) through an elbow adjusting screw (2) and an elbow cushion block (3); the top plate (7) is arranged on the upper end part of the bent pipe (4) through a top plate adjusting screw (5) and a top plate cushion block (6), and a plurality of clamping devices (8) which can approach or depart from the center of the plate surface are uniformly distributed on the top plate (7); a rectangular boss is arranged on the base (1), a mounting tube with an extending section similar to an omega shape is arranged on the rectangular boss, and the lower end part of the bent tube (4) is arranged on the mounting tube; the bent pipe (4) comprises a first section of pipe body arranged in the installation pipe on the rectangular boss, a second section of pipe body vertically connected with the first section of pipe body, and a third section of pipe body horizontally connected with the second section of pipe body; the cross section of the tail end of the third section of pipe body is approximately omega-shaped, and a top plate (7) is arranged on the third section of pipe body through a top plate adjusting screw (5) and a top plate cushion block (6); a plurality of groups of threaded holes are uniformly distributed on the top plate (7), each group of threaded holes are distributed along the direction from the edge to the center, and the clamping device (8) is correspondingly arranged on the threaded holes; the base (1) is in a U-shaped opening shape;
the method is characterized in that: the repairing method comprises the following steps:
removing damaged parts on a damaged aircraft protective grating, and polishing a section;
secondly, a three-dimensional model of the damaged aircraft protective grating is obtained through a three-dimensional laser scanner, and is compared with the intact aircraft protective grating to construct a damaged part model;
thirdly, mounting the damaged aircraft protective grating on the substrate through a clamping device (8), leveling, scanning the whole three-dimensional model of the substrate clamped with the damaged protective grating through a three-dimensional laser scanner, and determining the placement position of the three-dimensional model of the damaged aircraft protective grating in a forming bin and the height of the substrate to be lowered after mounting;
fourthly, mounting the substrate on a base of a forming bin of a laser selective melting device, lowering the height determined in the third step, paving powder layer by layer, and scanning by laser according to a preset model to finish the repair of the aircraft protective grating;
after repair is completed, opening a forming bin of the laser selective melting equipment, removing the substrate, loosening a clamping device (8) on the substrate, and taking out the repaired airplane protective grating;
the powder in the step (four) is TC4 powder, the first layer powder is scanned twice, and the laser selective melting technological parameters corresponding to the first layer powder are as follows: the laser power is 180-225W, the scanning speed is 1200-1500 mm/s, the scanning interval is 70-80 mu m, and the layer thickness is 30 mu m;
in the step (four), the laser selective melting process parameters corresponding to the powder of the other layers except the first layer are as follows: the laser power is 140-160W, the scanning speed is 1200-1500 mm/s, the scanning interval is 70-80 mu m, and the layer thickness is 30 mu m;
the repair surface of the damaged aircraft protective grating faces upwards during clamping, the repair surface of the damaged aircraft protective grating is horizontal through adjusting the bent pipe adjusting screw (2) and the top plate adjusting screw (5), and the included angle between the plane and the side surface of the aircraft protective grating is 45 degrees; the advantage of putting like this is that during the restoration, the shaping direction of layer by layer is 45 orientation of slope, can directly rely on the shaping of below entity region, does not have the cantilever structure that must add the support.
2. The method for repairing an aircraft protective grating repairing substrate based on a laser selective melting process according to claim 1, wherein the method comprises the following steps: the removing mode in the step (I) is to remove the section at an angle of 45 degrees along the edge line, and the polishing requirement on the section is that the roughness reaches Ra0.8μm and the flatness reaches 2 μm.
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| CN202111492208.6A CN114289730B (en) | 2021-12-08 | 2021-12-08 | Airplane protective grating repairing substrate and repairing method based on laser selective melting process |
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| CN202111492208.6A CN114289730B (en) | 2021-12-08 | 2021-12-08 | Airplane protective grating repairing substrate and repairing method based on laser selective melting process |
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| CN114289730B true CN114289730B (en) | 2023-09-19 |
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