Femtosecond laser device for drilling aircraft skin

Abstract

The utility model discloses a femtosecond laser device for aircraft skin drilling, which relates to the field of aircraft skin processing and comprises a machine body and a driving component, a clamping component and a first moving component are respectively mounted in a first mounting groove and a second mounting groove, and the driving component drives the first moving component on two sides. A second moving assembly is further arranged between the first moving assemblies on the two sides. Efficient and accurate punching operation is achieved through the clamping assembly, the moving assembly and the punching assembly which are accurately controlled, the clamping assembly can stably clamp the aircraft skin and ensure the stability and safety in the punching process, the moving assembly can drive the punching assembly to accurately move in the longitudinal and transverse directions, accurate positioning of a laser is achieved, and the punching efficiency is improved. And angle positioning of the laser device on the aircraft skin is completed through the punching assembly, high-precision and high-quality punching operation is achieved through the femtosecond laser technology, and the quality and efficiency of aircraft skin punching are improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft skin processing, specifically to a femtosecond laser device for creating holes in aircraft skin. Background Technology

[0002] With the continuous development of technology, the requirements for aircraft are gradually increasing. To meet the demand for lightweight aircraft, the skin of aircraft at present mostly uses thin alloy sheets of lightweight alloys. Using thin alloy sheets can effectively reduce the weight of the aircraft. At the same time, when the thin sheets are applied to different parts, they are easier to process into irregular shapes. In the aerospace manufacturing industry, the drilling operation of aircraft skin is an important part of the aircraft assembly process.

[0003] Traditional hole-making methods, such as mechanical drilling and punching, have many drawbacks, including slow drilling speed, poor hole diameter consistency, and numerous burrs on the hole edges. These problems not only affect the assembly quality of aircraft skin but also increase the difficulty and cost of subsequent processing steps. Therefore, this invention proposes a femtosecond laser device for hole making in aircraft skin. Utility Model Content

[0004] The purpose of this invention is to provide a femtosecond laser device for drilling holes in aircraft skin, in order to solve the many shortcomings of traditional hole-making methods such as mechanical drilling and punching mentioned in the background art, such as slow drilling speed, poor hole diameter consistency, and many burrs on the hole edge. These problems not only affect the assembly quality of aircraft skin, but also increase the difficulty and cost of subsequent processing procedures.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A femtosecond laser device for drilling holes in aircraft skin includes a body and a drive assembly. The body is U-shaped, and a first mounting groove and a second mounting groove are correspondingly opened on the upper and lower parts of the inner side of the body. A clamping assembly and a first moving assembly are respectively installed in the first mounting groove and the second mounting groove. The drive assembly drives the first moving assemblies on both sides. A second moving assembly is also provided between the first moving assemblies on both sides. A drilling assembly is provided on the second moving assembly.

[0007] Optionally, the clamping assembly includes a connecting rod fixedly disposed inside the first mounting groove, a connecting plate fixedly connected to the other end of the connecting rod, a lower clamping plate horizontally disposed at the bottom of the connecting plate, a sliding groove correspondingly disposed on the end face of the connecting plate, an upper clamping plate connected to the sliding groove by a sliding block, and an adjusting rod passing through the front and rear sides of the upper clamping plate.

[0008] Optionally, the first movable component includes a lead screw disposed in a second mounting groove, a guide rod provided on the side of the lead screw, and a follower gear sleeved on the outer surface of the lead screw, and a movable component connected to the outside of the lead screw and the guide rod.

[0009] Optionally, the drive assembly includes a dual-axis motor and a support plate. The dual-axis motor is mounted on the support plate, which is horizontally positioned between the inner sides of the machine body. The output ends of the dual-axis motor are each connected to a connecting shaft, and the other end of the connecting shaft is fixedly fitted with a main gear that meshes with the driven gear.

[0010] Optionally, the second moving component includes a U-shaped plate, which is installed between the two moving parts. The U-shaped plate has a rack along the plate body direction on its inner side, and a slide rail is provided on the outer side of the U-shaped plate. A slide block is slidably connected to the slide rail, and a first support rod is fixedly connected to the slide block.

[0011] Optionally, the drilling assembly includes a first mounting plate, which is fixedly connected to the upper end face of the first support rod. A stepper motor is fixedly mounted on the first mounting plate, and a spur gear is connected to the output end of the stepper motor through the lower part of the first mounting plate. A second mounting plate is fixedly connected to the top of the first mounting plate through the second support rod. A rotary motor is fixedly mounted on the second mounting plate, and an I-shaped plate is fixedly connected to the output end of the rotary motor through the second mounting plate. A pneumatic telescopic rod is provided on the side end face of the I-shaped plate, and the output ends of the two pneumatic telescopic rods are connected to a laser.

[0012] Optionally, the spur gear and the rack cooperate with each other.

[0013] The beneficial effects of this utility model are:

[0014] This invention achieves efficient and precise drilling operations through precisely controlled clamping, moving, and drilling components. The clamping component stably holds the aircraft skin, ensuring stability and safety during the drilling process. The moving component drives the drilling component to move precisely in the longitudinal and transverse directions, enabling precise positioning of the laser. Furthermore, the drilling component completes the angular positioning of the laser on the aircraft skin. By utilizing femtosecond laser technology, high-precision and high-quality drilling operations are achieved, which not only improves the quality and efficiency of drilling holes in aircraft skin but also reduces production costs and the difficulty of subsequent processing steps. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of a femtosecond laser device for creating holes in aircraft skin according to this utility model;

[0016] Figure 2 This is a schematic diagram of the femtosecond laser device for creating holes in aircraft skin according to this utility model from another perspective.

[0017] Figure 3 This is a cross-sectional view of the present invention;

[0018] Figure 4 for Figure 3 Enlarged view of point A in the middle;

[0019] Figure 5 This is a schematic diagram of the side structure after cutting in this utility model;

[0020] Figure 6 for Figure 5 Enlarged view of point B in the middle;

[0021] The numbers on the map are:

[0022] 1. Body; 101. First mounting slot; 102. Second mounting slot;

[0023] 2. Clamping assembly; 201. Connecting rod; 202. Connecting plate; 203. Lower clamping plate; 204. Sliding groove; 205. Sliding block; 206. Upper clamping plate; 207. Adjusting rod;

[0024] 3. First moving assembly; 301. Lead screw; 302. Guide rod; 303. Moving part; 304. Follower gear;

[0025] 4. Drive assembly; 401. Dual-axis motor; 402. Connecting shaft; 403. Support plate; 404. Main gear;

[0026] 5. Second moving component; 501. U-shaped plate; 502. Rack; 503. Slide rail; 504. Slide block; 505. First support rod;

[0027] 6. Drilling assembly; 601. First mounting plate; 602. Stepper motor; 603. Spur gear; 604. Second support rod; 605. Second mounting plate; 606. Rotary motor; 607. I-beam plate; 608. Pneumatic telescopic rod; 609. Laser. Detailed Implementation

[0028] To make the technical means, creative features, objectives and effects of this utility model easier to understand, the present utility model will be further described below in conjunction with specific embodiments.

[0029] The preferred embodiment of the present invention will be described below.

[0030] Please see Figure 1-6As shown, the femtosecond laser device for drilling holes in the aircraft skin includes a body 1 and a drive assembly 4. The body 1 is U-shaped, and the upper and lower parts of the inner side of the body 1 are respectively provided with a first mounting groove 101 and a second mounting groove 102. The first mounting groove 101 and the second mounting groove 102 are respectively equipped with a clamping assembly 2 and a first moving assembly 3. The drive assembly 4 drives the first moving assemblies 3 on both sides. A second moving assembly 5 is also provided between the first moving assemblies 3 on both sides. The second moving assembly 5 is provided with a drilling assembly 6.

[0031] Furthermore, the clamping assembly 2 includes a connecting rod 201 fixedly disposed inside the first mounting groove 101, and a connecting plate 202 fixedly connected to the other end of the connecting rod 201. A lower clamping plate 203 is horizontally disposed at the bottom of the connecting plate 202, and a sliding groove 204 is correspondingly opened on the end face of the connecting plate 202. An upper clamping plate 206 is connected to the sliding groove 204 by a sliding block 205. Adjusting rods 207 are passed through the front and rear sides of the upper clamping plate 206.

[0032] Specifically, the connecting rod 201 and the connecting plate 202 are fixed in the first mounting groove 101 of the body 1. The upper clamping plate 206 slides in the sliding groove 204 through the sliding block 205. With the adjustment of the adjusting rod 207, the clamping and release of the aircraft skin can be realized. In use, the surfaces of the lower clamping plate 203 and the upper clamping plate 206 are provided with rubber blocks.

[0033] Furthermore, the first moving component 3 includes a lead screw 301 disposed in the second mounting groove 102, a guide rod 302 disposed on the side of the lead screw 301, and a follower gear 304 sleeved on the outer surface of the lead screw 301. A moving member 303 is externally connected to the lead screw 301 and the guide rod 302.

[0034] Furthermore, the drive assembly 4 includes a dual-axis motor 401 and a support plate 403. The dual-axis motor 401 is mounted on the support plate 403, which is horizontally positioned between the inner sides of the machine body 1. The output ends of the dual-axis motor 401 are all connected to a connecting shaft 402. The other end of the connecting shaft 402 is fixedly fitted with a main gear 404 that meshes with the driven gear 304.

[0035] Specifically, the dual-axis motor 401 is started to drive the main gear 404 to rotate through the connecting shaft 402. The main gear 404 drives the driven gear 304 to rotate synchronously through the meshing relationship. The rotation of the driven gear 304 drives the lead screw 301 to rotate. The rotation of the lead screw 301 drives the moving part 303 to move along the guide rod 302, realizing the horizontal movement from one end of the machine body 1 to the other end. Thus, the moving part 303 drives the second moving component 5 to perform synchronous linear horizontal movement, realizing the drive component 4 to drive the first moving component 3.

[0036] In another embodiment provided by this utility model, such as Figure 5-6As shown, the second moving component 5 includes a U-shaped plate 501, which is installed between the two moving parts 303. A rack 502 is provided on the inner side of the U-shaped plate 501 along the plate body direction, and a slide rail 503 is provided on the outer side of the U-shaped plate 501. A slide block 504 is slidably connected to the slide rail 503, and a first support rod 505 is fixedly connected to the slide block 504.

[0037] Furthermore, the drilling assembly 6 includes a first mounting plate 601, which is fixedly connected to the upper end face of the first support rod 505. A stepper motor 602 is fixedly mounted on the first mounting plate 601. The output end of the stepper motor 602 passes through the lower part of the first mounting plate 601 and is connected to a spur gear 603. The top of the first mounting plate 601 is fixedly connected to a second mounting plate 605 via a second support rod 604. A rotary motor 606 is fixedly mounted on the second mounting plate 605. The output end of the rotary motor 606 passes through the second mounting plate 605 and is fixedly connected to an I-shaped plate 607. A pneumatic telescopic rod 608 is provided on the side end face of the I-shaped plate 607. The output ends of the two pneumatic telescopic rods 608 are connected to a laser 609.

[0038] Furthermore, the spur gear 603 and the rack 502 cooperate with each other.

[0039] Specifically, when the drilling assembly 6 needs to be moved horizontally, the stepper motor 602 starts, and its output drives the spur gear 603 to rotate. Since the spur gear 603 cooperates with the rack 502 on the inner side of the concave plate 501, the rotation of the spur gear 603 is converted into the horizontal movement of the slide block 504 and the entire drilling assembly 6 along the slide rail 503. By precisely controlling the rotation angle and speed of the stepper motor 602, the drilling assembly 6 can be precisely positioned and moved in the horizontal direction. After moving horizontally to the designated position, the rotary motor 606 starts, and its output drives the I-shaped plate 607 to rotate. The rotation of the I-shaped plate 607 changes the vertical position of the pneumatic telescopic rod 608 and the laser 609. This enables the laser 609 to be vertically positioned on the aircraft skin and to be angularly positioned on the aircraft skin. Once the laser 609 is aligned with the position to be drilled, the pneumatic telescopic rod 608 extends, pushing the laser 609 closer to the aircraft skin and emitting a femtosecond laser to drill. After drilling is completed, the pneumatic telescopic rod 608 shortens, and the laser 609 retracts to a safe position, ready for the next drilling operation. By repeating the above horizontal and vertical movement and drilling steps, the drilling assembly 6 can continuously drill multiple precise holes on the aircraft skin. Throughout the drilling process, efficient and precise drilling operations are achieved by precisely controlling the coordinated actions of the stepper motor 602, the rotary motor 606, and the pneumatic telescopic rod 608.

[0040] It should be noted that during actual drilling, the stepper motor 602, rotary motor 606, and pneumatic telescopic rod 608 need to exchange information with the external control terminal.

[0041] In use, the aircraft skin to be punched is placed on the clamping assembly 2 inside the fuselage 1. By adjusting the adjusting rod 207 in the clamping assembly 2, the upper clamping plate 206 slides along the sliding groove 204, and together with the lower clamping plate 203, clamps the aircraft skin. The rubber blocks on the surface of the clamping assembly 2 ensure that the skin is not damaged during clamping. The dual-axis motor 401 in the drive assembly 4 is started, which drives the main gear 404 to rotate through the connecting shaft 402. The meshing relationship between the main gear 404 and the driven gear 304 causes the lead screw 301 to rotate, thereby driving the moving part 303 to move horizontally along the guide rod 302. During this process, the moving part 303 drives the second moving assembly 5 to move synchronously until it reaches the predetermined longitudinal horizontal position. When the second moving assembly 5 reaches the designated position, the stepper motor 602 in the punching assembly 6 is started. The output end of the stepper motor 602 drives the spur gear 603 to rotate. Since the spur gear 603 is engaged with the rack 502 on the inner side of the concave plate 501, the rotation of the stepper motor 602 is converted into the horizontal movement of the punching assembly 6 along the slide rail 503. By precisely controlling the rotation angle and speed of the stepper motor 602, the drilling assembly 6 is accurately positioned in the horizontal direction. After horizontal positioning is completed, the rotary motor 606 is started, and its output end drives the I-shaped plate 607 to rotate. The rotation of the I-shaped plate 607 changes the vertical position of the pneumatic telescopic rod 608 and the laser 609, realizing the vertical positioning of the laser 609 on the aircraft skin and completing the angular positioning of the aircraft skin. When the laser 609 is aligned with the position to be drilled, the pneumatic telescopic rod 608 extends, pushing the laser 609 closer to the aircraft skin and emitting a femtosecond laser to drill. After drilling is completed, the pneumatic telescopic rod 608 shortens, and the laser 609 retracts to a safe position. By repeating the above horizontal movement, vertical adjustment and drilling steps, the drilling assembly 6 can continuously drill multiple precise holes at different positions on the aircraft skin, ensuring the efficiency and accuracy of drilling.

[0042] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A femtosecond laser device for drilling an aircraft skin, characterized in that: The device includes a body (1) and a drive assembly (4). The body (1) is U-shaped. The upper and lower parts of the inner side of the body (1) are provided with a first mounting groove (101) and a second mounting groove (102). The first mounting groove (101) and the second mounting groove (102) are respectively equipped with a clamping assembly (2) and a first moving assembly (3). The drive assembly (4) drives the first moving assembly (3) on both sides. A second moving assembly (5) is also provided between the first moving assembly (3) on both sides. A punching assembly (6) is provided on the second moving assembly (5).

2. The apparatus for drilling holes in an aircraft skin according to claim 1, characterized in that: The clamping assembly (2) includes a connecting rod (201) fixedly disposed inside the first mounting groove (101). The other end of the connecting rod (201) is fixedly connected to a connecting plate (202). The bottom of the connecting plate (202) is horizontally provided with a lower clamping plate (203). The end face of the connecting plate (202) is correspondingly provided with a sliding groove (204). The sliding groove (204) is connected to an upper clamping plate (206) by a sliding block (205). Adjusting rods (207) are provided on both the front and rear sides of the upper clamping plate (206).

3. The apparatus for drilling holes in aircraft skin according to claim 1, characterized in that: The first moving component (3) includes a lead screw (301) disposed in the second mounting groove (102), a guide rod (302) is provided on the side of the lead screw (301), and a follower gear (304) is also sleeved on the outer surface of the lead screw (301). A moving part (303) is connected to the outside of the lead screw (301) and the guide rod (302).

4. The apparatus for drilling holes in aircraft skin according to claim 1, characterized in that: The drive assembly (4) includes a dual-axis motor (401) and a support plate (403). The dual-axis motor (401) is mounted on the support plate (403), which is horizontally positioned between the inner sides of the machine body (1). The output ends of the dual-axis motor (401) are connected to a connecting shaft (402). The other end of the connecting shaft (402) is fixedly fitted with a main gear (404) that meshes with the driven gear (304).

5. The apparatus for drilling holes in aircraft skin according to claim 1, characterized in that: The second moving component (5) includes a concave plate (501), which is installed between the two moving parts (303). The inner side of the concave plate (501) is provided with a rack (502) along the plate body direction, and the outer side of the concave plate (501) is provided with a slide rail (503). A slide block (504) is slidably connected on the slide rail (503), and a first support rod (505) is fixedly connected on the slide block (504).

6. The apparatus for drilling holes in aircraft skin according to claim 1, characterized in that: The drilling assembly (6) includes a first mounting plate (601), which is fixedly connected to the upper end face of the first support rod (505). A stepper motor (602) is fixedly mounted on the first mounting plate (601). The output end of the stepper motor (602) passes through the lower part of the first mounting plate (601) and is connected to a spur gear (603). The top of the first mounting plate (601) is fixedly connected to a second mounting plate (605) through a second support rod (604). A rotary motor (606) is fixedly mounted on the second mounting plate (605). The output end of the rotary motor (606) passes through the second mounting plate (605) and is fixedly connected to an I-shaped plate (607). A pneumatic telescopic rod (608) is provided on the side end face of the I-shaped plate (607). The output ends of the two pneumatic telescopic rods (608) are connected to a laser (609).

7. The apparatus for drilling holes in an aircraft skin according to claim 6, characterized in that: The spur gear (603) and the rack (502) cooperate with each other.

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