A two-way drilling device for connecting the fuselage frame and the wing joint of an aircraft

Abstract

An embodiment of the present invention discloses a two-way drilling device for the connection frame of the aircraft fuselage skeleton and the wing joint, which includes a linear guide rail. A Y-axis linear slide is fixedly connected to the middle of the linear guide rail. A two-way drilling mechanism is fixedly installed on the slide of the Z-axis linear slide. Support seats are slidably installed at both ends of the linear guide rail respectively; on the two opposite side surfaces of the two-way drilling mechanism and the support seats, a drill bit extends outwards respectively; the two drill bits are coaxially arranged, and the two drill bits can rotate synchronously; the three-point positioning mechanism includes three groups of laser emitters and laser receivers, wherein the laser emitters and laser receivers are relatively aligned and arranged on the two support seats respectively; the present invention can separately and spacedly position and fix the connection frame of the aircraft fuselage skeleton and the wing joint, and then synchronously drill holes between them through two coaxial drill bits; the drilling efficiency is relatively high, and due to synchronous drilling and coaxial drilling, the consistency of the hole alignment is relatively high, and errors are not easily generated.

Description

Technical Field

[0001] The invention relates to the technical field of mechanical processing and drilling, and in particular to a bidirectional drilling device for a connection frame of an aircraft fuselage skeleton and a wing joint. Background Art

[0002] The aircraft skeleton connection frame achieves force transmission and distribution through its own structural strength and rigidity, as well as the connection method with other components. When the aircraft is subjected to external loads, the connection frame first receives the force from the components connected to it, and then decomposes and transmits these forces through its own structure, so that they are evenly distributed to other related components, thereby ensuring the balance and stability of the aircraft structure when subjected to force. For example, when the wing is subjected to upward aerodynamic force, the connection frame on the wing will transfer this force to the fuselage structure, and will also transfer other forces from the fuselage to various parts of the wing, ensuring the normal operation of the wing under complex force conditions.

[0003] The wing joint is the connecting part between the fuselage and the wing. The connection between the aircraft frame connection frame and the wing has high requirements. Each hole needs to be precisely aligned and of the same size. The higher the precision, the more stable and safer the connection between the wing and the fuselage.

[0004] However, due to the large overall structure of the aircraft, the number of holes drilled is also large, and the depth of the holes to be drilled is also deep, which makes the processing difficult. The existing general single step-by-step drilling has low drilling efficiency and is prone to errors in accuracy.

[0005] To this end, we propose a bidirectional drilling device for the aircraft fuselage skeleton connection frame and the wing joint. Summary of the invention

[0006] In view of this, the present invention provides a bidirectional drilling device for aircraft fuselage frame connection frame and wing joint, which is used to solve the problems of low drilling efficiency and easy error in precision between aircraft fuselage frame connection frame and wing joint in the prior art.

[0007] A bidirectional drilling device for a connection frame of an aircraft fuselage skeleton and a wing joint comprises a linear guide rail, a Y-axis linear slide is fixedly connected to the middle of the linear guide rail, a vertically arranged Z-axis linear slide is fixedly installed on the slide seat of the Y-axis linear slide, and a bidirectional drilling mechanism is fixedly installed on the slide seat of the Z-axis linear slide.

[0008] Support seats are slidably mounted at both ends of the linear guide rail, and the support seats are driven by the X-axis linear slide;

[0009] The two sides of the bidirectional drilling mechanism opposite to the support seat each extend outwards a drill bit; wherein the two drill bits are coaxially arranged and can rotate synchronously;

[0010] It also includes a three-point positioning mechanism, which includes three groups of laser transmitters and laser receivers, wherein the laser transmitters and laser receivers are respectively arranged on two supporting seats in relative alignment;

[0011] It also includes a PLC controller, the Y-axis linear slide, the Z-axis linear slide and two groups of X-axis linear slides are all controlled by the PLC controller, and the signal input end of the laser receiver is connected to the signal input end of the PLC controller.

[0012] Preferably, the three groups of laser emitters are not arranged on the same straight line.

[0013] Preferably, the bidirectional drilling mechanism comprises a servo motor, a gear reduction box and a driving shaft, wherein the driving shaft is rotatably mounted in the gear reduction box via a ball bearing and is connected to the servo motor via a gear set, and a driven gear is mounted on the driving shaft, wherein the gear set is meshedly connected to the driven gear; both ends of the driving shaft extend outwardly from both sides of the gear reduction box, and both ends of the driving shaft are arranged as regular hexagonal portions, and a regular hexagonal hole is provided in the regular hexagonal portion;

[0014] One end of the drill bit is arranged as a regular hexagonal prism, and the regular hexagonal prism is inserted into the regular hexagonal hole and is locked by a locking bolt.

[0015] Preferably, the above also includes a reversing mechanism, which is installed in the gear reduction box, and the reversing mechanism includes a linear bearing fixedly installed in the gear reduction box, a movable shaft is slidably installed inside the linear bearing, and two relatively arranged bevel gears A and bevel gear B are fixedly installed on the upper part of the movable shaft, a bevel gear C is fixedly installed on the output shaft of the servo motor, a column gear is installed on the movable shaft, and the column gear is meshed and connected with the gear set in the gear reduction box;

[0016] One end of the movable shaft is fixedly sleeved with a support bearing, a cylinder is fixedly installed inside the gear reduction box, and one end of the cylinder is fixedly connected to the support bearing through a connecting rod;

[0017] By extending and retracting the cylinder, the bevel gear A can be switched to mesh with the bevel gear C or the bevel gear B can be switched to mesh with the bevel gear C; thus, the rotation direction of the movable shaft can be adjusted.

[0018] Preferably, a pair of threaded holes are provided on each outer side surface of the regular hexagonal portion, and the locking bolts are threadedly installed in the threaded holes.

[0019] Preferably, the laser transmitter and the laser receiver are both fixed on the support base by means of a switch magnetic base, and the support base is made of ordinary steel or high-carbon steel and can be attracted by the switch magnetic base.

[0020] Preferably, insertion rods are fixedly connected to the lower parts of the above-mentioned laser emitter and laser receiver. The insertion rods are slidably inserted into the sleeves. The bottoms of the sleeves are fixedly connected to the tops of the switch magnetic bases. The insertion rods and the sleeves are in damping sliding connection.

[0021] Preferably, the above-mentioned device further includes a magnetic right-angled triangular ruler, which is used to assist the connection frame of the aircraft fuselage skeleton and the wing joint to maintain a vertical relative position; three pairs of aligned positioning holes are respectively formed in the connection frame of the aircraft fuselage skeleton and the wing joint, and the positioning holes can be penetrated by the laser generated by the laser emitter.

[0022] The present invention also provides a method for drilling holes in two directions between the connection frame of the aircraft fuselage skeleton and the wing joint. Using the above-mentioned device for drilling holes in two directions between the connection frame of the aircraft fuselage skeleton and the wing joint, the method specifically includes the following steps:

[0023] S1. Align and clamp the connection frame of the aircraft fuselage skeleton and the wing joint together, and select three positions not on the same straight line to process positioning holes;

[0024] S2. Then place the connection frame of the aircraft fuselage skeleton and the wing joint on two support seats respectively, and then adjust the verticality through the right-angled triangular ruler;

[0025] S3. Then adjust and align the positions through three groups of laser emitters and laser receivers penetrating through the three positioning holes. After the positioning and alignment, fix the connection frame of the aircraft fuselage skeleton and the wing joint through a fixture;

[0026] S4. Start the servo motor, and the drill bit rotates;

[0027] S5. The two X-axis linear sliding tables drive the support seats to approach the drill bit;

[0028] S6. Adjust the corresponding drilling position of the drill bit through the Y-axis linear sliding table and the Z-axis linear sliding table;

[0029] S7. Set the feed speed through the PLC controller and start automatic drilling;

[0030] S8. After the first hole is drilled, the X-axis linear sliding table moves to control the support seat to return to the original position. Then, the Y-axis linear sliding table and the Z-axis linear sliding table automatically adjust to the next drilling position, and then start drilling again. By circulating in this way, automatic drilling can be realized;

[0031] S9. During the drilling process, the rotation direction of the drilling can be automatically switched through the reversing mechanism, so that the drill bit can be intermittently reversed to discharge the waste chips from the drilling.

[0032] Preferably, in S9 above, the same type of drill bits are installed at both ends of the drive shaft. During rotation, one end drills in the positive direction and the other end discharges chips in the reverse direction; when discharging chips at the chip-discharging end, no feeding is performed.

[0033] Implementing the embodiments of the present invention will have the following beneficial effects:

[0034] After adopting the above-mentioned bidirectional drilling device for the aircraft fuselage skeleton connection frame and the wing joint;

[0035] Through the three-point positioning mechanism, the aircraft fuselage skeleton connection frame and the wing joint can be fixedly separated at intervals, and then two coaxial drill bits are used to perform synchronous drilling between them; the drilling efficiency is relatively high, and due to synchronous drilling and coaxial drilling, the consistency of hole alignment is relatively high, and it is not easy to generate errors;

[0036] Through the three-point positioning mechanism, the PLC controller, the X-axis linear slide, the Y-axis linear slide, and the Z-axis linear slide can realize automatic positioning drilling after positioning, which is very convenient;

[0037] The present invention adopts a processing method of drilling at one end and discharging chips at the other end and being able to cycle alternately, with good processing stability, balanced load and not easy to overload, smooth processing, and improved drilling efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0039] Among them:

[0040] Figure 1 It is a schematic structural diagram of a bidirectional drilling device for an aircraft fuselage skeleton connection frame and a wing joint in an embodiment.

[0041] Figure 2 It is a schematic structural diagram of a bidirectional drilling mechanism in an embodiment;

[0042] Figure 3 It is a schematic structural diagram of a commutation mechanism in an embodiment;

[0043] Figure 4 It is a schematic structural diagram of a drive shaft in an embodiment;

[0044] Figure 5 It is a schematic split structure diagram of a drive shaft and a drill bit in an embodiment;

[0045] Figure 6 Schematic diagram of the split structure of the three-point positioning mechanism in an embodiment;

[0046] Figure 7 Schematic diagram of the structures of the laser emitter and the laser receiver in an embodiment;

[0047] Figure 8 Schematic diagram of the structure of the gear set in an embodiment.

[0048] Reference numerals:

[0049] 55. Connection frame of the aircraft fuselage skeleton; 66. Right-angled triangle ruler; 77. Wing joint; 88. Positioning hole; 99. Gear set;

[0050] 100. Linear guide rail; 200. Support base; 201. X-axis linear slide;

[0051] 300. Three-point positioning mechanism; 301. Laser emitter; 302. Laser receiver; 303. Switch magnetic base; 304. Plug rod; 305. Sleeve;

[0052] 400. Y-axis linear slide; 500. Z-axis linear slide;

[0053] 600. Two-way drilling mechanism; 601. Gear reduction box; 602. Servo motor; 603. Bevel gear C;

[0054] 701. Ball bearing; 702. Drive shaft; 703. Driven gear; 704. Regular hexagonal part; 705. Threaded hole; 706. Regular hexagonal hole; 707. Locking bolt;

[0055] 800. Reversing mechanism; 801. Movable shaft; 802. Linear bearing; 803. Cylindrical gear; 804. Bevel gear A; 805. Bevel gear B; 806. Support bearing; 807. Connecting rod; 808. Cylinder;

[0056] 900. Drill bit; 901. Regular hexagonal prism. Detailed implementation manners

[0057] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this application belongs; the terms used in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above drawings are intended to cover non-exclusive inclusion. The terms "first", "second", etc. in the specification and claims of this application or the above drawings are used to distinguish different objects and are not used to describe a specific order.

[0058] As used herein, the term "embodiment" means that the specific features, structures, or characteristics described in connection with the embodiments can be included in at least one embodiment of the present application. The phrase appears in various places in the specification and does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art will explicitly and implicitly understand that the embodiments described herein can be combined with other embodiments.

[0059] To enable those skilled in the art to better understand the solution of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings.

[0060] Embodiment 1:

[0061] Please refer to Figures 1-8 , a two-way drilling device for the connection frame of the aircraft fuselage skeleton and the wing joint, including a linear guide rail 100. A Y-axis linear slide table 400 is fixedly connected to the middle of the linear guide rail 100. A vertically arranged Z-axis linear slide table 500 is fixedly installed on the slide seat of the Y-axis linear slide table 400. A two-way drilling mechanism 600 is fixedly installed on the slide seat of the Z-axis linear slide table 500. Support seats 200 are respectively slidably installed at both ends of the linear guide rail 100, and the support seats 200 are driven by an X-axis linear slide table 201.

[0062] During implementation, a drill bit 900 extends outward from each of the two opposite side surfaces of the two-way drilling mechanism 600 and the support seat 200. Among them, the two drill bits 900 are coaxially arranged, and the two drill bits 900 can rotate synchronously.

[0063] Specifically, it further includes a three-point positioning mechanism 300. The three-point positioning mechanism 300 includes three groups of laser emitters 301 and laser receivers 302, and the laser emitters 301 and laser receivers 302 are respectively arranged opposite and aligned on the two support seats 200.

[0064] During implementation, it further includes a PLC controller (not shown in the figure). The Y-axis linear slide table 400, the Z-axis linear slide table 500, and the two groups of X-axis linear slide tables 201 are all controlled by the PLC controller. The signal input end of the laser receiver 302 is connected to the signal input end of the PLC controller.

[0065] During implementation, the three groups of laser emitters 301 are not arranged in a straight line. Three points determine a plane. Through three-point alignment and positioning, the precise alignment of the connection frame of the aircraft fuselage skeleton and the wing joint can be basically maintained.

[0066] As Figures 2-4As shown, the bidirectional drilling mechanism 600 includes a servo motor 602, a gear reduction box 601 and a drive shaft 702, wherein the drive shaft 702 is rotatably mounted in the gear reduction box 601 through a ball bearing 701, and a driven gear 703 is also mounted on the drive shaft 702, which is meshed with a gear set 99 inside the gear reduction box 601 (the gear set 99 can be flexibly set according to the gear ratio, relative position space or requirements when designing); wherein the gear set 99 and the driven gear 703 are meshed with each other. Meshing connection; the drive shaft 702 is installed in the gear reduction box 601 and is connected to the servo motor 602 through the gear set 99, and the two ends of the drive shaft 702 extend outward from the two sides of the gear reduction box 601, and the two ends of the drive shaft 702 are both set as regular hexagonal parts 704, and the regular hexagonal parts 704 are provided with regular hexagonal holes 706; one end of the drill bit 900 is set as a regular hexagonal prism 901, and the regular hexagonal prism 901 is inserted into the regular hexagonal hole 706 and locked by a locking bolt 707.

[0067] When implementing, Figure 3 As shown in the figure, it also includes a reversing mechanism 800, which is installed in the gear reduction box 601. The reversing mechanism 800 includes a linear bearing 802 fixedly installed in the gear reduction box 601, and a movable shaft 801 is slidably installed inside the linear bearing 802. Two relatively set bevel gears A804 and bevel gear B805 are fixedly installed on the upper part of the movable shaft 801. A bevel gear C603 is fixedly installed on the output shaft of the servo motor 602, and a column gear 803 is installed on the movable shaft 801. The column gear 803 is meshed and connected with the gear set 99 in the gear reduction box 601.

[0068] Among them, one end of the movable shaft 801 is fixedly sleeved with a support bearing 806, and a cylinder 808 is fixedly installed inside the gear reducer 601. One end of the cylinder 808 is fixedly connected to the support bearing 806 through a connecting rod 807; through the extension and retraction of the cylinder 808, it is possible to switch the bevel gear A804 to mesh with the bevel gear C603 or to mesh the bevel gear B805 to mesh with the bevel gear C603; thereby, the rotation direction of the movable shaft 801 can be adjusted.

[0069] In addition, each outer side surface of the regular hexagonal portion 704 is provided with a pair of threaded holes 705 , and locking bolts 707 are threadedly installed in the threaded holes 705 .

[0070] When implementing, Figure 7 As shown in FIG. 1 , the laser transmitter 301 and the laser receiver 302 are both fixed on the support base 200 by the switch magnetic base 303 . The support base 200 is made of ordinary steel or high carbon steel and can be attracted by the switch magnetic base 303 .

[0071] Specifically, insertion rods 304 are fixedly connected to the lower parts of the laser emitter 301 and the laser receiver 302. The insertion rods 304 are slidably inserted into the sleeves 305. The bottom of the sleeves 305 is fixedly connected to the top of the switch magnetic base 303. The insertion rods 304 and the sleeves 305 are in damped sliding connection. The heights of the laser emitter 301 and the laser receiver 302 can be adjusted by the insertion rods 304 and the sleeves 305.

[0072] During implementation, it also includes a magnetic right-angled triangle 66, which is used to assist the aircraft fuselage skeleton connection frame 55 and the wing joint 77 to maintain a vertical relative position; three pairs of aligned positioning holes 88 are respectively formed on the aircraft fuselage skeleton connection frame 55 and the wing joint 77, and the positioning holes 88 can be penetrated by the laser generated by the laser emitter 301.

[0073] Embodiment 2:

[0074] Different from Embodiment 1, this Embodiment 2 provides a method for drilling holes in both directions between the aircraft fuselage skeleton connection frame and the wing joint. The drilling device for drilling holes in both directions between the aircraft fuselage skeleton connection frame and the wing joint in Embodiment 1 is adopted, and specifically includes the following steps:

[0075] S1. Align and clamp the aircraft fuselage skeleton connection frame 55 and the wing joint 77 together, and select three positions not on the same straight line to process the positioning holes 88;

[0076] S2. Then place the aircraft fuselage skeleton connection frame 55 and the wing joint 77 on two support seats 200 respectively, and then adjust the verticality through the right-angled triangle 66;

[0077] S3. Then adjust and align the positions through three groups of laser emitters 301 and laser receivers 302 penetrating through the three positioning holes 88. After the positioning and alignment, fix the aircraft fuselage skeleton connection frame 55 and the wing joint 77 through a fixture (not shown in the figure);

[0078] S4. Start the servo motor 602, and the drill bit 900 rotates;

[0079] S5. Two X-axis linear slides 201 drive the support seats 200 to approach the drill bit 900;

[0080] S6. Adjust the corresponding drilling position of the drill bit 900 through the Y-axis linear slide 400 and the Z-axis linear slide 500;

[0081] S7. Set the feed speed through the PLC controller and start automatic drilling;

[0082] After the first hole is drilled, the X-axis linear slide 201 moves to control the support base 200 to return to its original position. Then, the Y-axis linear slide 400 and the Z-axis linear slide 500 are automatically adjusted to the next drilling position, and then drilling starts again. By cycling in this way, automatic drilling can be achieved;

[0083] S9. During the drilling process, the rotation direction of the drilling can also be automatically switched by the reversing mechanism 800, so that intermittent reverse feeding can be carried out to discharge the waste chips from the drilled holes.

[0084] It should be noted that in S9, the same type of drill bit 900 is installed at both ends of the drive shaft 702. During rotation, one end drills in the positive direction and the other end discharges chips; when discharging chips, the end that discharges chips does not feed.

[0085] Obviously, the embodiments described above are only a part of the embodiments of the present application, rather than all embodiments. The preferred embodiments of the present application are shown in the drawings, but do not limit the patent scope of the present application. The present application can be implemented in many different forms. On the contrary, the purpose of providing these embodiments is to make the understanding of the disclosed content of the present application more thorough and comprehensive. Although the present application has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions described in the foregoing specific embodiments, or perform equivalent replacements for some of the technical features. Any equivalent structure made by using the specification and drawings of the present application, directly or indirectly applied in other related technical fields, is similarly within the scope of patent protection of the present application.

Claims

1. A bidirectional drilling device for the connection frame of an aircraft fuselage frame and a wing joint, characterized in that: include: A linear guide rail (100), wherein a Y-axis linear slide (400) is fixedly connected to the middle of the linear guide rail (100), a vertically arranged Z-axis linear slide (500) is fixedly installed on the slide seat of the Y-axis linear slide (400), and a bidirectional drilling mechanism (600) is fixedly installed on the slide seat of the Z-axis linear slide (500), Support seats (200) are slidably mounted at both ends of the linear guide rail (100), and the support seats (200) are driven by an X-axis linear slide table (201); A drill bit (900) extends outward from each of the two side surfaces of the bidirectional drilling mechanism (600) opposite to the support seat (200); wherein the two drill bits (900) are coaxially arranged and can rotate synchronously; It also includes a three-point positioning mechanism (300), wherein the three-point positioning mechanism (300) includes three groups of laser transmitters (301) and laser receivers (302), wherein the laser transmitters (301) and the laser receivers (302) are respectively arranged on two support seats (200) in a relatively aligned manner; It also includes a PLC controller, the Y-axis linear slide (400), the Z-axis linear slide (500) and the two groups of X-axis linear slides (201) are all controlled by the PLC controller, and the signal input end of the laser receiver (302) is connected to the signal input end of the PLC controller; It also includes a magnetic right-angled triangle ruler (66) used to assist the aircraft fuselage frame connection frame (55) and the wing joint (77) in maintaining vertical opposition; the aircraft fuselage frame connection frame (55) and the wing joint (77) are also respectively provided with three pairs of aligned positioning holes (88), and the positioning holes (88) can be penetrated by the laser generated by the laser transmitter (301).

2. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage skeleton according to claim 1, characterized in that: The three groups of laser emitters (301) are not arranged on the same straight line.

3. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage frame according to claim 2, characterized in that: The bidirectional drilling mechanism (600) comprises a servo motor (602), a gear reduction box (601), and a drive shaft (702); the drive shaft (702) is rotatably mounted in the gear reduction box (601) via a ball bearing (701) and is transmission-connected to the servo motor (602) via a gear set (99); a driven gear (703) is mounted on the drive shaft (702), wherein the gear set (99) is meshingly connected to the driven gear (703); both ends of the drive shaft (702) extend outwardly from both sides of the gear reduction box (601), and both ends of the drive shaft (702) are arranged as regular hexagonal portions (704), and a regular hexagonal hole (706) is provided in the regular hexagonal portion (704); One end of the drill bit (900) is configured as a regular hexagonal prism (901), and the regular hexagonal prism (901) is inserted into the regular hexagonal hole (706) and is locked by a locking bolt (707).

4. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage skeleton according to claim 3, characterized in that: It also includes a reversing mechanism (800), the reversing mechanism (800) being installed in the gear reduction box (601), the reversing mechanism (800) comprising a linear bearing (802) fixedly installed in the gear reduction box (601), a movable shaft (801) being slidably installed inside the linear bearing (802), two bevel gears A (804) and a bevel gear B (805) being fixedly installed on the upper part of the movable shaft (801) being arranged opposite to each other, a bevel gear C (603) being fixedly installed on the output shaft of the servo motor (602), a column gear (803) being installed on the movable shaft (801), and the column gear (803) being meshingly connected with a gear set (99) in the gear reduction box (601); A support bearing (806) is fixedly sleeved on one end of the movable shaft (801), a cylinder (808) is fixedly installed inside the gear reduction box (601), and one end of the cylinder (808) is fixedly connected to the support bearing (806) via a connecting rod (807); By extending and retracting the cylinder (808), it is possible to switch between making the bevel gear A (804) mesh with the bevel gear C (603) or making the bevel gear B (805) mesh with the bevel gear C (603); thereby, the rotation direction of the movable shaft (801) can be adjusted.

5. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage skeleton according to claim 4, characterized in that: A pair of threaded holes (705) are provided on each outer side surface of the regular hexagonal portion (704), and the locking bolts (707) are threadedly installed in the threaded holes (705).

6. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage skeleton according to claim 5, characterized in that: The laser transmitter (301) and the laser receiver (302) are both fixed on the support base (200) by suction through a switch magnetic base (303); the support base (200) is made of ordinary steel or high-carbon steel and can be attracted by the switch magnetic base (303).

7. A bidirectional drilling device for the connection frame and wing joint of an aircraft fuselage skeleton according to claim 6, characterized in that: The lower parts of the laser transmitter (301) and the laser receiver (302) are both fixedly connected with an insertion rod (304), the insertion rod (304) is slidably inserted in a sleeve (305), the bottom of the sleeve (305) is fixedly connected to the top of the switch magnetic base (303), and the insertion rod (304) and the sleeve (305) are in a damping sliding connection.

8. A bidirectional drilling method for a connection frame of an aircraft fuselage skeleton and a wing joint, using the bidirectional drilling device for a connection frame of an aircraft fuselage skeleton and a wing joint as claimed in claim 7, characterized in that: The specific steps include: S1, aligning and clamping the aircraft fuselage frame connection frame (55) and the wing joint (77) together, and selecting three locations that are not in a straight line to process positioning holes (88); S2, then placing the aircraft fuselage skeleton connection frame (55) and the wing joint (77) on two support seats (200) respectively, and then adjusting the verticality by a right-angle set square (66); S3, three sets of laser transmitters (301) and laser receivers (302) are then used to penetrate three positioning holes (88) for adjustment and alignment. After alignment, the aircraft fuselage skeleton connection frame (55) and the wing joint (77) are fixed by a fixture; S4, starting the servo motor (602), and the drill bit (900) rotates; S5, two X-axis linear slides (201) drive the support seat (200) to move closer to the drill bit (900); S6. Adjust the drilling position corresponding to the drill bit (900) by using the Y-axis linear slide (400) and the Z-axis linear slide (500); S7, set the feed speed through the PLC controller and start automatic drilling; S8. After the first hole is drilled, the X-axis linear slide (201) moves the control support seat (200) back to the original position, and then the Y-axis linear slide (400) and the Z-axis linear slide (500) are automatically adjusted to the next drilling position, and then drilling is started again, and the cycle is repeated in sequence to realize automatic drilling; S9. During the drilling process, the rotation direction of the drilling can be automatically switched through the reversing mechanism (800), so that the material can be reversed and discharged intermittently to discharge the waste chips of the drilling.

9. A bidirectional drilling method for the aircraft fuselage frame connecting frame and wing joint according to claim 8, characterized in that: In S9, the same type of drill bits (900) are installed at both ends of the driving shaft (702). When rotating, one end drills in the positive direction and the other end removes chips in the reverse direction; the end that removes chips does not feed when removing chips.

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