Fuselage skin drilling equipment

Abstract

The invention provides fuselage skin drilling equipment, and relates to a skin drilling process. The number of the supporting rods is two, the supporting rods rotate around the rotating shaft, the distance between the supporting rods and the rotating shaft is adjustable and equal, and the supporting rods rotate around the center shafts of the supporting rods. The number of the lower pressing rods is two, the lower pressing rods and the supporting rods are arranged in a spaced mode, the distance between the lower pressing rods and the supporting rods is adjustable, the lower pressing rods rotate around the center shafts of the supporting rods, the lower pressing rods move and rotate along with the supporting rods, and the lower pressing rods rotate around the center shafts of the lower pressing rods; the two limiting plates are arranged between the supporting rods, move and rotate along with the supporting rods, and move in the length direction of the bottom plate; the drilling machine moves in the length direction of the bottom plate; the drilling die is movably arranged between the bottom plate and the drilling machine in the height direction of the bottom plate and moves in the length direction of the bottom plate. The drilling efficiency and the drilling positioning accuracy can be improved, skin deformation caused during drilling is avoided, and the drilling device can be suitable for fuselage skins of various different curvatures and has high practicability.

Description

Technical Field

[0001] The present application relates to the field of skin processing, in particular to a skin drilling process, and specifically to a fuselage skin drilling device. Background Art

[0002] The skin of an aircraft is a thin shell covering the surface of the aircraft structure, usually made of metal or composite materials. Its main functions include protecting the internal structure of the aircraft, reducing air resistance, improving flight efficiency, and providing structural support. The shape of the skin is generally divided into single-curvature skin, double-curvature skin, complex-shaped skin, etc., and the fuselage of the aircraft generally uses single-curvature skin, that is, it has curvature in only one direction, and can usually be formed by pressing and rolling. The formed fuselage skin is generally riveted when connected to each other and to the frame, and before riveting, rivet holes need to be drilled at designated positions on the fuselage skin.

[0003] At present, the method of drilling holes in the fuselage skin is generally to place the skin on a customized fixing frame, and then manually operate a drilling machine to drill holes. However, manual drilling is inefficient and difficult to accurately position. It is easy to cause deformation of the skin during drilling. At the same time, different fixing frames need to be customized when drilling holes in fuselage skins with different curvatures, which is relatively troublesome. The prior art also shows some mechanical devices for drilling holes in the fuselage skin, which can achieve drilling holes in different positions of the fuselage skin by driving the drilling machine and rotating it. However, these mechanical devices generally need to drive the drilling machine to move in multiple directions in space and rotate around multiple directions. A large and complex mechanical structure is required to drive the drilling machine, and the drilling machine has a heavy weight, which can easily affect the accuracy of drilling positioning under long-term operation. Summary of the invention

[0004] In order to solve the above-mentioned defects of the related prior art, the present application provides a fuselage skin drilling equipment, which can improve the drilling efficiency and drilling positioning accuracy, avoid skin deformation during drilling, and can be applied to fuselage skins with a variety of different curvatures, and has strong practicality.

[0005] In order to achieve the above object, the present invention adopts the following technologies: A fuselage skin drilling device, comprising: The bottom plate is in the shape of a rectangular plate; The support rods have two parallel to the length direction of the bottom plate, the support rods are arranged at intervals and the spacing is a predetermined value, the support rods are all rotatably arranged around the same rotation axis parallel to the length direction of the bottom plate, the spacing between the support rods and the rotation axis is adjustable and the spacing is equal, and the support rods are all rotatably arranged around their own central axis; The lower pressure rods have two parts parallel to the length direction of the bottom plate. The lower pressure rods are matched with different support rods respectively. The lower pressure rods and the support rods matched with them are arranged at intervals and the intervals are adjustable. The lower pressure rods are respectively arranged to rotate around the central axis of the support rods matched with them. The lower pressure rods move with the support rods matched with them, and rotate around the rotation axis with the support rods matched with them. The lower pressure rods are all arranged to rotate around their own central axes. There are two limit plates, both of which are arranged between the support rods. The limit plates move with the support rods and rotate around the rotation axis with the support rods. The limit plates are arranged to move along the length direction of the bottom plate. A drilling machine is arranged above the bottom plate and moves along the length direction of the bottom plate, the working axis of the drilling machine is arranged toward the bottom plate and perpendicular to the upper surface of the bottom plate, and the central axis of the working axis intersects with the rotating axis; The drilling die is arranged between the bottom plate and the drilling machine and is movable along the bottom plate height direction. The drilling die is provided with a die hole along the bottom plate height direction. The die hole is coaxial with the working axis and has matching size.

[0006] Furthermore, a rotating rod is provided above the base plate along its own length direction, and the rotating rod is rotatably arranged around its own central axis. One end of the rotating rod is connected to a mounting plate, and a first linear cylinder is provided on the mounting plate. The central axis of the first linear cylinder is perpendicularly intersected with the central axis of the rotating rod, and the driving shaft of the first linear cylinder is connected to the first driving plate. Two first working rods are rotatably connected on the same side of the first driving plate, and the first working rods are all parallel to the rotating rod. The plane where the first working rods coexist is perpendicular to the central axis of the first linear cylinder, and the vertical distance between the first working rod and the first linear cylinder is equal. The first working rod is coaxially connected to one end of the support rod respectively, and two first rotating cylinders are provided on the first driving plate. The driving shafts of the first rotating cylinders are coaxially connected to the first working rods respectively.

[0007] Furthermore, a rotating cylinder is coaxially sleeved on the circumference of the first working rod, bearings are installed between the inner wall of the rotating cylinder and the first working rod, one end of the rotating cylinder is coaxially connected to a driven gear, the driven gears are respectively sleeved on the circumference of the first working rod, two second rotating cylinders are arranged on the first driving plate, the driving shafts of the second rotating cylinders are coaxially connected to the active gears, the active gears are respectively meshed with the driven gears, the rotating cylinders are connected to the first driving frame, the first driving frame is provided with a second linear cylinder, the central axes of the second linear cylinders are respectively perpendicular to the central axes of the corresponding first working rods, the driving shafts of the second linear cylinders are respectively arranged toward the corresponding first working rods and are connected to a rotating seat, one end of the lower pressure rod is rotatably connected to the rotating seat, and the central axis of the lower pressure rod is perpendicular to the central axis of the second linear cylinder.

[0008] Furthermore, a third linear cylinder is provided along the axial direction of the other end of the rotating rod, and a driving shaft of the third linear cylinder is arranged toward the outside of the other end of the rotating rod and is connected to a driving block, a fourth linear cylinder is provided on the driving block, the fourth linear cylinder is parallel to the first linear cylinder, the center axis of the fourth linear cylinder is perpendicular to the center axis of the rotating rod, the driving shaft of the fourth linear cylinder is connected to a second driving plate, the second driving plate is rotatably connected to one side of the support rod with two second working rods, the second working rods are parallel to the rotating rod, the plane where the second working rods coexist is perpendicular to the center axis of the fourth linear cylinder, the vertical distance between the center axis of the second working rod and the fourth linear cylinder is equal to the vertical distance between the center axis of the first working rod and the first linear cylinder, and a first matching opening is coaxially opened at the other end of the support rod, and the size of the first matching opening matches the size of the second working rod.

[0009] Furthermore, two third rotating cylinders are provided on the second driving plate, and the driving shafts of the third rotating cylinders are coaxially connected to the second working rods, and the second working rods are coaxially installed with fixing cylinders, and the fixing cylinders are connected to the second driving frame. The second driving frame is provided with a fifth linear cylinder, and the central axes of the fifth linear cylinders are perpendicularly intersected with the central axes of the corresponding second working rods, respectively. The driving shafts of the fifth linear cylinders are respectively arranged toward the corresponding second working rods and are connected to fixed seats, and the sides of the fixed seats facing the downward pressure rod are parallel to the axial direction of the second working rod and are connected to the third working rod, and the central axes of the third working rods are perpendicularly intersected with the central axes of the corresponding fifth linear cylinders, and the other end of the downward pressure rod is coaxially opened with a second matching opening, and the size of the second matching opening matches the size of the third working rod.

[0010] Furthermore, a sixth linear cylinder is provided on both the first driving plate and the second driving plate along the length direction of the bottom plate, and the driving shafts of the sixth linear cylinder are arranged opposite to each other and are respectively connected to the limit plates.

[0011] Furthermore, a support column is provided on the base plate, the upper end of the support column is connected to a support frame, a triangular block is provided on the support frame, the triangular block is connected to a first suspension rod, the first suspension rod is connected to a mounting frame, a fourth rotating cylinder is provided on the mounting frame, and a driving shaft of the fourth rotating cylinder is coaxially connected to the rotating rod.

[0012] Furthermore, the triangular block is connected to a second hanging rod, the second hanging rod is connected to a hanging plate, a first electric screw is provided on the hanging plate along the length direction of the base plate, a first matching block is threadedly matched on the first electric screw, the first matching block is connected to a first moving block, a moving opening is passed through the hanging plate, and the first moving block is connected to the drilling machine through the moving opening.

[0013] Furthermore, a loading plate is provided on the base plate, a second electric screw is provided on the loading plate along the length direction of the base plate, a second matching block is threadedly matched on the second electric screw, the second matching block is connected to a second moving block, a seventh linear cylinder is provided on the second moving block along the height direction of the base plate, and the driving shaft of the seventh linear cylinder is connected to the drilling mold.

[0014] Furthermore, the second matching block is also connected to a vertical rod, the vertical rod is connected to a receiving tray, and the receiving tray is located directly below the drilling mold.

[0015] The beneficial effects of the present invention are: 1. Use the bottom plate support rod and the lower pressure rod to fix the skin, and use the drilling machine and drilling mold to drill holes in the fuselage skin. There is no need to manually operate the drilling machine to drill holes, which improves the drilling efficiency and drilling accuracy.

[0016] 2. Use a drilling mold and a drilling machine to drill holes to avoid deformation of the skin during drilling.

[0017] 3. The support rod is movable, and the pressure rod can rotate around the support rod, so that fuselage skins with various curvatures can be fixed and holes can be drilled in fuselage skins with various curvatures.

[0018] 4. By moving the drilling machine and the drilling mold in one direction, drilling holes in different positions of the fuselage skin with different curvatures can be achieved, which simplifies the driving structure of the drilling machine and further improves the accuracy of drilling positioning. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a three-dimensional schematic diagram of the fuselage skin drilling equipment according to an embodiment of the present application.

[0020] Figure 2 It is a plan view schematic diagram of the fuselage skin drilling equipment in a working state according to an embodiment of the present application.

[0021] Figure 3 It is a plan schematic diagram of the fuselage skin drilling equipment of an embodiment of the present application in another working state.

[0022] Figure 4 It is a three-dimensional schematic diagram of the support rod and its driving structure according to an embodiment of the present application.

[0023] Figure 5 It is a partial three-dimensional schematic diagram of the downward pressure rod and its driving structure in an embodiment of the present application.

[0024] Figure 6 This application Figure 5 A local enlarged schematic diagram of point A in the middle.

[0025] Figure 7It is a three-dimensional schematic diagram of a second working rod and its driving structure, a limiting plate and its driving structure in an embodiment of the present application.

[0026] Figure 8 It is a partial three-dimensional schematic diagram of the third working rod and its driving structure in the embodiment of the present application.

[0027] Fig. 9 It is a three-dimensional schematic diagram of a rotating rod and its driving structure according to an embodiment of the present application.

[0028] Fig.10 It is a three-dimensional schematic diagram of a drilling machine and its driving mechanism, a drilling mold and its driving mechanism according to an embodiment of the present application.

[0029] Markings in the figure: 1-base plate, 11-support column, 12-support frame, 13-triangle block, 14-first suspension rod, 15-mounting frame, 16-fourth rotating cylinder, 17-second suspension rod, 2-support rod, 21-rotating rod, 22-mounting plate, 23-first linear cylinder, 24-first driving plate, 25-first working rod, 26-first rotating cylinder, 27-third linear cylinder, 28-driving block, 29-fourth linear cylinder, 210-second driving plate, 211-second working rod, 212-first matching port, 213-third rotating cylinder, 3-down pressure rod, 31-rotating cylinder, 32-bearing, 33-driven gear, 34-second rotating cylinder, 35-active Gear, 36-first drive frame, 37-second linear cylinder, 38-rotating seat, 39-fixed cylinder, 310-second drive frame, 311-fifth linear cylinder, 312-fixed seat, 313-third working rod, 314-second matching port, 4-limiting plate, 41-sixth linear cylinder, 5-drilling machine, 51-hanging plate, 52-first electric screw, 53-first matching block, 54-first moving block, 55-moving port, 6-drilling mold, 61-mold hole, 62-loading plate, 63-second electric screw, 64-second matching block, 65-second moving block, 66-seventh linear cylinder, 67-vertical rod, 68-receiving tray, 7-camera, 8-fuselage skin. DETAILED DESCRIPTION

[0030] To make the objectives, technical solutions and advantages of the embodiments of the present invention more clear, the implementation modes of the present invention are described in detail below with reference to the accompanying drawings. However, the embodiments described in the present invention are only part of the embodiments of the present invention, rather than all the embodiments.

[0031] like Figure 1 As shown, this embodiment provides a fuselage skin drilling device, including a base plate 1, a support rod 2, a lower pressure rod 3, a limit plate 4, a drilling machine 5, and a drilling mold 6.

[0032] Specifically, Figure 1As shown, the bottom plate 1 is in the shape of a rectangular plate and is used to carry the device.

[0033] Specifically, Figure 1 As shown, there are two support rods 2 arranged parallel to the length direction of the base plate 1, the support rods 2 are arranged at intervals and the spacing is a predetermined value, the support rods 2 are all rotatably arranged around the same rotation axis parallel to the length direction of the base plate 1, the spacing between the support rods 2 and the rotation axis is adjustable and the spacing is equal, and the support rods 2 are all rotatably arranged around their own central axes.

[0034] Specifically, Figure 1 As shown, the lower pressure rod 3 has two sections arranged parallel to the length direction of the base plate 1, and the lower pressure rods 3 are matched with different support rods 2 respectively. The lower pressure rods 3 and the support rods 2 matched with them are arranged at intervals and the intervals are adjustable. The lower pressure rods 3 are respectively rotated around the central axis of the support rods 2 matched with them, and the lower pressure rods 3 move following the support rods 2 matched with them, that is, when the support rods 2 and the rotating axis change and move, the lower pressure rods 3 can move synchronously with the support rods 2 matched with them; the lower pressure rods 3 rotate around the rotating axis following the support rods 2 matched with them, and the lower pressure rods 3 are all rotated around their own central axes.

[0035] Specifically, Figure 1 As shown, there are two limit plates 4, both of which are arranged between the support rods 2, and the limit plates 4 move with the support rods 2, that is, when the distance between the support rods 2 and the rotating axis changes and moves, the limit plates 4 can move synchronously with the matched support rods 2; the limit plates 4 rotate around the rotating axis with the support rods 2, and the limit plates 4 are moved along the length direction of the base plate 1. More specifically, in this example, the plate surface of the limit plates 4 is parallel to the two end surfaces of the base plate 1.

[0036] Specifically, Figure 1 As shown, the drilling machine 5 is movable along the length direction of the base plate 1 and is arranged above the base plate 1. The working axis of the drilling machine 5 faces the base plate 1 and is arranged perpendicular to the upper surface of the base plate 1. The central axis of the working axis intersects with the rotating axis. The working principle of the drilling machine 5 and its working axis belongs to the prior art and will not be elaborated here.

[0037] Specifically, Figure 1 and Figure 2 As shown, the drilling mold 6 is moved along the height direction of the base plate 1 and is arranged between the base plate 1 and the drilling machine 5, and is moved along the length direction of the base plate 1. The drilling mold 6 has a mold hole 61 passing through it along the height direction of the base plate 1. The mold hole 61 is coaxial with the working axis and has matching sizes. The mold hole 61 being coaxial with the working axis here means that the mold hole 61 is always coaxial with the working axis during the movement of the drilling machine 5 and the drilling mold 6, and the working axis is used to cooperate with the mold hole 61 for drilling.

[0038] When working, combine Figure 1 and Figure 2 As shown, the fuselage skin 8 processed by the device is a single-curved arc plate. The fuselage skin 8 to be processed is placed on the support rod 2 and located between the limit plates 4, so that the central axis of the fuselage skin 8 is parallel to the support rod 2, and the outer arc surface of the fuselage skin 8 is in contact with the support rod 2; the distance between the support rod 2 and the rotating shaft is adjusted. Since the distance between the support rod 2 is a predetermined value and the distance between the support rod 2 and the rotating shaft is equal, the distance between the support rod 2 and the rotating shaft is adjusted to Figure 2 The performance in the figure is to move up and down, at this time the support rod 2 drives the fuselage skin 8 to move up and down together, and stops moving when the central axis of the fuselage skin 8 coincides with the rotation axis. Such a design can make the central axis of the fuselage skin 8 of different curvatures coincide with the rotation axis; the lower pressure rod 3 is rotated around the central axis of the supporting rod 2 it matches, so that the central axis of the lower pressure rod 3, the central axis of the supporting rod 2 it matches and the rotation axis are coplanar, and the spacing between the lower pressure rod 3 and the supporting rod 2 it matches is adjusted so that the lower pressure rod 3 contacts the inner arc surface of the fuselage skin 8. At this time, the lower pressure rod 3 and the supporting rod 2 will clamp and fix the fuselage skin 8, and the lower pressure rod 3 and the supporting rod 2 it matches are on the fuselage The contact points on the skin 8 are parallel to the cross-section, and the fuselage skin 8 will not be deformed when clamped; the limit plate 4 is moved to make it contact with the two ends of the fuselage skin 8, and the drilling machine 5 and the drilling mold 6 are moved synchronously. The support rod 2 and the down-press rod 3 are rotated around their own central axes to drive the fuselage skin 8 to rotate around its own central axis, so that drilling positioning can be achieved at any position in the middle of the fuselage skin 8. The limit plate 4 is used to prevent axial displacement when the support rod 2 and the down-press rod 3 drive the fuselage skin 8 to rotate around its own central axis; the drilling machine 5 is operated so that its working axis extends downward into the mold hole 61 of the drilling mold 6 to complete the drilling; preferably, the surface material of the support rod 2 and the down-press rod 3 adopts an anti-slip material.

[0039] Combination Figure 1 and Figure 3 As shown, when it is necessary to drill a hole at the edge of the fuselage skin 8, the support rod 2 is rotated around the rotation axis so that the support rod 2 is located on the same side of the drilling point. At this time, the support rod 2 and the down-pressing rod 3 are rotated around their own central axes to achieve drilling at the edge of the fuselage skin 8; since the central axis of the fuselage skin 8 coincides with the rotation axis, the fuselage skin 8 also rotates around the rotation axis when following the rotation of the support rod 2. Such a design enables the working axis of the drilling machine 5 to always be perpendicular to the cross-section of the drilling point, thereby avoiding deformation of the fuselage skin 8 during drilling; preferably, the upper surface of the drilling mold 6 can be customized as an arc surface of different curvatures according to the curvature of the fuselage skin 8, and the corresponding drilling mold 6 is replaced when drilling holes in different fuselage skins 8. Such a design enables the upper surface of the drilling mold 6 to fit closely with the outer arc surface of the fuselage skin 8 during drilling, thereby further avoiding deformation of the fuselage skin 8 during drilling.

[0040] With such a design, it is possible to drill holes at any position on the fuselage skin 8; when drilling holes in the fuselage skin 8 with different curvatures, by adjusting the distance between the support rod 2 and the rotating axis, the central axis of the fuselage skin 8 can always be made to coincide with the rotating axis, thereby achieving clamping and fixing of the fuselage skin with different curvatures, and it can also ensure that the working axis of the drilling machine 5 is always perpendicular to the cross-section of the drilling point, thereby avoiding deformation of the fuselage skin 8 during drilling; at the same time, the drilling machine 5 and the drilling mold 6 only move in one direction for drilling positioning, which simplifies the driving structure of the drilling machine 5 and the drilling mold 6 and further improves the drilling positioning accuracy.

[0041] Preferably, Figure 1 and Figure 4 As shown, a rotating rod 21 is provided above the bottom plate 1 along its length direction, and the rotating rod 21 is rotatably arranged around its own central axis. A mounting plate 22 is connected to one end of the rotating rod 21, and a first linear cylinder 23 is provided on the mounting plate 22. The central axis of the first linear cylinder 23 is perpendicularly intersected with the central axis of the rotating rod 21, and a first driving plate 24 is connected to the driving shaft of the first linear cylinder 23. Two first working rods 25 are rotatably connected on the same side of the first driving plate 24, and the first working rods 25 are parallel to the rotating rod 21, and the plane where the first working rods 25 are located is perpendicular to the central axis of the first linear cylinder 23. The vertical distance between the first working rod 25 and the first linear cylinder 23 is equal, and the first working rods 25 are respectively One end of the support rod 2 is coaxially connected, and two first rotating cylinders 26 are provided on the first driving plate 24. The driving shafts of the first rotating cylinders 26 are coaxially connected to the first working rod 25, respectively. The first rotating cylinders 26 are used to drive the support rod 2 to rotate through the first working rod 25; with such a design, the rotating rod 21 is used to drive the support rod 2 to rotate around the central axis of the rotating rod 21 by rotating around its own central axis. The central axis of the rotating rod 21 is regarded as the rotating axis, so that the support rod 2 can be rotated around the rotating axis; the first linear cylinder 23 is used to drive the support rod 2 to move, thereby adjusting the distance between the support rod 2 and the rotating axis; the first rotating cylinder 26 is used to drive the support rod 2 to rotate around its own central axis.

[0042] Preferably, Figure 4~Figure 6As shown, a rotating cylinder 31 is coaxially sleeved on the circumference of the first working rod 25, and a bearing 32 is installed between the inner wall of the rotating cylinder 31 and the first working rod 25, and the bearing 32 is used to enable the rotating cylinder 31 and the first working rod 25 to rotate separately; one end of the rotating cylinder 31 is coaxially connected to a driven gear 33, and the driven gears 33 are respectively sleeved on the circumference of the first working rod 25. Two second rotating cylinders 34 are provided on the first driving plate 24, and the driving shafts of the second rotating cylinders 34 are coaxially connected to driving gears 35, and the driving gears 35 are respectively meshed with the driven gears 33. The rotating cylinders 31 are connected to a first driving frame 36, and the first driving frame 36 is provided with a first driving frame 36. A second linear cylinder 37 is provided, and the central axis of the second linear cylinder 37 is perpendicularly intersected with the central axis of the corresponding first working rod 25. The driving axes of the second linear cylinders 37 are respectively arranged toward the corresponding first working rods 25 and are connected to a rotating seat 38. One end of the lower pressure rod 3 is rotatably connected to the rotating seat 38, and the central axis of the lower pressure rod 3 is perpendicularly intersected with the central axis of the second linear cylinder 37. With this design, the second rotating cylinder 34 is used to drive the lower pressure rod 3 to rotate around the supporting rod 2 matched with it through the engagement of the driving gear 35 and the driven gear 33, and the second linear cylinder 37 is used to adjust the distance between the lower pressure rod 3 and the supporting rod 2 matched with it.

[0043] Preferably, Figure 7 As shown, the other end of the rotating rod 21 is provided with a third linear cylinder 27 along its own axial direction, and the driving shaft of the third linear cylinder 27 is arranged outside the other end of the rotating rod 21 and is connected to a driving block 28, and a fourth linear cylinder 29 is provided on the driving block 28, and the fourth linear cylinder 29 is parallel to the first linear cylinder 23, and the central axis of the fourth linear cylinder 29 is perpendicular to the central axis of the rotating rod 21, and the driving shaft of the fourth linear cylinder 29 is connected to a second driving plate 210, and the second driving plate 210 is rotatably connected to one side of the support rod 2 with two second working rods 211, and the second working rods 211 are all parallel to the rotating rod 21, and the plane where the second working rods 211 are located is perpendicular to the central axis of the fourth linear cylinder 29. The vertical distance of the central axis of the linear cylinder 29 is equal to the vertical distance of the central axis of the first working rod 25 and the first linear cylinder 23. The other end of the support rod 2 is coaxially provided with a first matching opening 212. The size of the first matching opening 212 matches the size of the second working rod 211. The matching here means that when the second working rod 211 extends into the first matching opening 212, the second working rod 211 is in rotational contact with the inner wall surface of the first matching opening 212. Such a design can support both ends of the support rod 2 to avoid displacement or bending of the support rod 2 caused by supporting the support rod 2 from one end. The third linear cylinder 27 and the fourth linear cylinder 29 can drive the second working rod 211 to leave the other end of the support rod 2, thereby facilitating loading and unloading.

[0044] Preferably, Figure 8As shown, two third rotating cylinders 213 are provided on the second driving plate 210, and the driving shafts of the third rotating cylinders 213 are respectively coaxially connected to the second working rods 211, and the second working rods 211 are coaxially installed with fixing cylinders 39, and the fixing cylinders 39 are connected to the second driving frame 310, and the second driving frame 310 is provided with fifth linear cylinders 311, and the central axes of the fifth linear cylinders 311 are respectively perpendicularly intersected with the central axes of the corresponding second working rods 211, and the driving shafts of the fifth linear cylinders 311 are respectively arranged toward the corresponding second working rods 211 and are respectively connected to the fixing seats 312, and the fixed seats 312 are respectively parallel to the second working rod 211 and axially connected to the third working rod 313 on one side facing the lower pressing rod 3, and the third working rod 313 is axially connected to the second working rod 211. The central axes of 13 are respectively perpendicular to the central axes of the corresponding fifth linear cylinders 311, and the other end of the lower pressure rod 3 is coaxially provided with a second matching opening 314, and the size of the second matching opening 314 matches the size of the third working rod 313. The matching here means that when the third working rod 313 extends into the second matching opening 314, the third working rod 313 rotates and contacts with the inner wall surface of the second matching opening 314; such a design can support both ends of the lower pressure rod 3 to avoid displacement or bending of the support rod 2 caused by supporting the lower pressure rod 3 from one end; and when the second working rod 211 leaves the other end of the support rod 2, the third working rod 313 can follow the second working rod 211 to leave the other end of the lower pressure rod 3, thereby facilitating loading and unloading.

[0045] Preferably, Figure 7 As shown, the first driving plate 24 and the second driving plate 210 are both provided with a sixth linear cylinder 41 along the length direction of the base plate 1, and the driving shafts of the sixth linear cylinder 41 are relatively arranged and respectively connected to the limit plates 4, and the sixth linear cylinder 41 is used to drive the limit plates 4 to move.

[0046] Preferably, Fig. 9 As shown, four support columns 11 are provided on the base plate 1, and the upper ends of the support columns 11 are connected to support frames 12, and the support frames 12 are provided with two triangular blocks 13, and the triangular blocks 13 are connected to first suspension rods 14, and the first suspension rods 14 are connected to the same mounting frame 15, and the mounting frame 15 is provided with two fourth rotating cylinders 16, and the driving shafts of the fourth rotating cylinders 16 are coaxially connected to the rotating rod 21, and the fourth rotating cylinder 16 is used to drive the rotating rod 21 to rotate around its own central axis.

[0047] Preferably, Fig.10As shown, the triangular blocks 13 are connected to two second suspension rods 17, and the second suspension rods 17 are connected to the same suspension plate 51. Two first electric screws 52 are provided on the suspension plate 51 along the length direction of the base plate 1. The first electric screws 52 are threadedly fitted with first matching blocks 53, and the first matching blocks 53 are connected to the same first moving block 54. A moving opening 55 is passed through the suspension plate 51, and the first moving block 54 is connected to the drilling machine 5 through the moving opening 55; the first electric screw 52 is used to drive the drilling machine 5 to move through the first matching blocks 53 and the first moving blocks 54.

[0048] Preferably, Fig.10 As shown, a loading plate 62 is provided on the base plate 1, and two second electric screws 63 are provided on the loading plate 62 along the length direction of the base plate 1, and the second electric screws 63 are threadedly matched with second matching blocks 64, and the second matching blocks 64 are connected to the same second moving block 65, and two seventh linear cylinders 66 are provided on the second moving block 65 along the height direction of the base plate 1, and the driving shafts of the seventh linear cylinders 66 are connected to the drilling mold 6, and the second electric screw 63 is used to drive the drilling mold 6 to move along the length direction of the base plate 1 through the second matching blocks 64 and the second moving blocks 65, and the seventh linear cylinder 66 is used to drive the drilling mold 6 to move along the height direction of the base plate 1.

[0049] Preferably, Fig.10 As shown, the second matching blocks 64 are all connected to vertical rods 67 , and the vertical rods 67 are all connected to the same receiving tray 68 . The receiving tray 68 is located directly below the drilling mold 6 and is used to receive the drilling waste falling from the drilling mold 6 .

[0050] Further preferably, Figure 1 and Figure 2 As shown, a camera 7 can be arranged outside the side and end of the device, and the camera 7 is used to capture the real-time position of the fuselage skin 8, thereby more accurately locating the drilling position.

[0051] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Obviously, those skilled in the art can make various modifications and variations to the present application without departing from the spirit and scope of the present application.

Claims

1. A fuselage skin drilling device, characterized in that: include: The bottom plate (1) is in the shape of a rectangular plate; The support rods (2) have two members arranged parallel to the length direction of the bottom plate (1), the support rods (2) are arranged at intervals and the interval is a predetermined value, the support rods (2) are all arranged to rotate around the same rotation axis parallel to the length direction of the bottom plate (1), the intervals between the support rods (2) and the rotation axis are adjustable and equal, and the support rods (2) are all arranged to rotate around their own central axes; The lower pressure rod (3) has two sections arranged parallel to the length direction of the bottom plate (1), the lower pressure rods (3) are matched with different support rods (2), the lower pressure rods (3) are spaced apart from the support rods (2) they match, and the spacing is adjustable, the lower pressure rods (3) are respectively rotatably arranged around the central axis of the support rods (2) they match, the lower pressure rods (3) move with the support rods (2) they match, and rotate with the support rods (2) they match around the rotation axis, and the lower pressure rods (3) are all rotatably arranged around their own central axes; There are two limit plates (4), both of which are arranged between the support rods (2). The limit plates (4) move with the support rods (2) and rotate around the rotation axis with the support rods (2). The limit plates (4) are arranged to move along the length direction of the bottom plate (1); A drilling machine (5) is arranged above the bottom plate (1) and moves along the length direction of the bottom plate (1). The working axis of the drilling machine (5) faces the bottom plate (1) and is arranged perpendicular to the upper surface of the bottom plate (1). The central axis of the working axis intersects with the rotation axis. The drilling die (6) is arranged between the bottom plate (1) and the drilling machine (5) so as to be movable along the height direction of the bottom plate (1), and is arranged to be movable along the length direction of the bottom plate (1). The drilling die (6) is provided with a die hole (61) penetrating along the height direction of the bottom plate (1). The die hole (61) is coaxial with the working axis and has matching dimensions.

2. The fuselage skin drilling equipment according to claim 1, characterized in that: A rotating rod (21) is provided above the bottom plate (1) along its length direction. The rotating rod (21) is rotatably arranged around its own central axis. One end of the rotating rod (21) is connected to a mounting plate (22). A first linear cylinder (23) is provided on the mounting plate (22). The central axis of the first linear cylinder (23) intersects the central axis of the rotating rod (21) perpendicularly. The driving shaft of the first linear cylinder (23) is connected to a first driving plate (24). Two first working rods are rotatably connected to the same side of the first driving plate (24). (25), the first working rods (25) are parallel to the rotating rod (21), the plane on which the first working rods (25) are located is perpendicular to the central axis of the first linear cylinder (23), the vertical distance between the first working rod (25) and the first linear cylinder (23) is equal, the first working rods (25) are coaxially connected to one end of the support rod (2), the first driving plate (24) is provided with two first rotating cylinders (26), and the driving shafts of the first rotating cylinders (26) are coaxially connected to the first working rods (25).

3. The fuselage skin drilling equipment according to claim 2, characterized in that: A rotating cylinder (31) is coaxially sleeved on the circumference of the first working rod (25), a bearing (32) is installed between the inner wall of the rotating cylinder (31) and the first working rod (25), one end of the rotating cylinder (31) is coaxially connected to a driven gear (33), the driven gears (33) are sleeved on the circumference of the first working rod (25), two second rotating cylinders (34) are provided on the first driving plate (24), the driving shafts of the second rotating cylinders (34) are coaxially connected to driving gears (35), the driving gears (35) are meshed with the driven gears (33) respectively. The rotating cylinder (31) is connected to a first driving frame (36), and a second linear cylinder (37) is provided on the first driving frame (36). The central axis of the second linear cylinder (37) is perpendicularly intersected with the central axis of the corresponding first working rod (25). The driving axes of the second linear cylinders (37) are respectively arranged toward the corresponding first working rod (25) and are connected to a rotating seat (38). One end of the lower pressing rod (3) is rotatably connected to the rotating seat (38), and the central axis of the lower pressing rod (3) is perpendicularly intersected with the central axis of the second linear cylinder (37).

4. The fuselage skin drilling equipment according to claim 2 or 3, characterized in that: A third linear cylinder (27) is provided at the other end of the rotating rod (21) along its own axial direction, and a driving shaft of the third linear cylinder (27) is arranged outside the other end of the rotating rod (21) and is connected to a driving block (28), and a fourth linear cylinder (29) is provided on the driving block (28), and the fourth linear cylinder (29) is parallel to the first linear cylinder (23), and a central axis of the fourth linear cylinder (29) intersects perpendicularly with the central axis of the rotating rod (21), and a second driving plate (210) is connected to the driving shaft of the fourth linear cylinder (29), and the second driving plate (210) is arranged toward one end of the supporting rod (2). Two second working rods (211) are rotatably connected to the side, the second working rods (211) are parallel to the rotating rod (21), the plane on which the second working rods (211) are located is perpendicular to the central axis of the fourth linear cylinder (29), the vertical distance between the second working rod (211) and the central axis of the fourth linear cylinder (29) is equal to the vertical distance between the central axis of the first working rod (25) and the central axis of the first linear cylinder (23), and the other end of the support rod (2) is coaxially provided with a first matching opening (212), the size of the first matching opening (212) matches the size of the second working rod (211).

5. The fuselage skin drilling equipment according to claim 4, characterized in that: Two third rotating cylinders (213) are provided on the second driving plate (210), and the driving shafts of the third rotating cylinders (213) are respectively coaxially connected to the second working rods (211). The second working rods (211) are coaxially mounted with fixed cylinders (39), and the fixed cylinders (39) are respectively connected to the second driving frame (310). The second driving frame (310) is respectively provided with a fifth linear cylinder (311), and the central axis of the fifth linear cylinder (311) is respectively perpendicularly intersected with the central axis of the corresponding second working rod (211). The fifth linear cylinder (311) ) are respectively arranged toward the corresponding second working rod (211) and are connected to a fixed seat (312); one side of the fixed seat (312) facing the lower pressure rod (3) is parallel to the second working rod (211) and is axially connected to a third working rod (313); the central axis of the third working rod (313) is perpendicularly intersected with the central axis of the corresponding fifth linear cylinder (311); the other end of the lower pressure rod (3) is coaxially provided with a second matching opening (314); the size of the second matching opening (314) matches the size of the third working rod (313).

6. The fuselage skin drilling equipment according to claim 4, characterized in that: A sixth linear cylinder (41) is provided on both the first driving plate (24) and the second driving plate (210) along the length direction of the bottom plate (1), and the driving shafts of the sixth linear cylinder (41) are arranged opposite to each other and are respectively connected to the limit plates (4).

7. The fuselage skin drilling equipment according to claim 2, characterized in that: A support column (11) is provided on the bottom plate (1), the upper end of the support column (11) is connected to a support frame (12), a triangular block (13) is provided on the support frame (12), the triangular block (13) is connected to a first suspension rod (14), the first suspension rod (14) is connected to a mounting frame (15), a fourth rotating cylinder (16) is provided on the mounting frame (15), and a driving shaft of the fourth rotating cylinder (16) is coaxially connected to the rotating rod (21).

8. The fuselage skin drilling equipment according to claim 7, characterized in that: The triangular block (13) is connected to a second suspension rod (17), the second suspension rod (17) is connected to a suspension plate (51), a first electric screw (52) is provided on the suspension plate (51) along the length direction of the bottom plate (1), a first matching block (53) is threadedly matched on the first electric screw (52), the first matching block (53) is connected to a first moving block (54), a moving opening (55) is passed through the suspension plate (51), and the first moving block (54) passes through the moving opening (55) to connect to the drilling machine (5).

9. The fuselage skin drilling equipment according to claim 1, characterized in that: A loading plate (62) is provided on the bottom plate (1); a second electric screw (63) is provided on the loading plate (62) along the length direction of the bottom plate (1); a second matching block (64) is threadedly matched on the second electric screw (63); the second matching block (64) is connected to a second moving block (65); a seventh linear cylinder (66) is provided on the second moving block (65) along the height direction of the bottom plate (1); and a driving shaft of the seventh linear cylinder (66) is connected to the drilling die (6).

10. The fuselage skin drilling equipment according to claim 9, characterized in that: The second matching block (64) is also connected to a vertical rod (67), and the vertical rod (67) is connected to a material receiving tray (68). The material receiving tray (68) is located directly below the drilling mold (6).

Images