Aircraft part welding workbench

Abstract

The utility model discloses an aircraft part welding workbench which comprises a workbench body unit which comprises a base and a balancing weight fixedly installed on one side of the upper end of the base. The positioning unit comprises a lifting assembly fixedly installed on the base, a driving motor is fixedly installed at the upper end of the side, close to the center of the base, of the lifting assembly, a rotating column is fixedly connected to an output shaft of the driving motor, and a fixing block is fixedly installed at the end, away from the driving motor, of the rotating column; and a corresponding fixing block is also arranged on one side, far away from the rotating column, of the fixing block. By rotating and clamping the small aircraft part, a worker only needs to rotate the aircraft part to a proper angle when welding one surface and the other welding surface are at the bottom end of the part, so that the damage rate of the aircraft part in the overturning process is reduced, and the welding efficiency of the aircraft part is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft component welding, in particular to an aircraft component welding workbench. Background Art

[0002] In recent years, in aircraft manufacturing, welding production has many advantages such as large batch size, fast production speed, and high assembly welding precision requirements for welded parts. At the same time, different parts require different welding methods. One of the aircraft parts welding workbenches can help operators weld small aircraft parts.

[0003] In the prior art, when welding small aircraft parts, workers need to place the parts to be welded on a workbench and then weld the parts with a welding gun. After welding one side, if the side to be welded is at the bottom of the part, the part needs to be turned over before welding can be performed. This can easily cause the parts to be damaged during the turning process, and repeated clamping during the turning process also wastes a lot of time, reducing the efficiency of welding aircraft parts. Utility Model Content

[0004] The purpose of this section is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and utility model name of this application to avoid blurring the purpose of this section, specification abstract and utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0005] In view of the above problems existing in the existing welding workbench for aircraft parts, the utility model is proposed.

[0006] Therefore, the utility model aims to provide an aircraft component welding workbench, which is suitable for solving the problem that after welding one side, if the side to be welded is at the bottom of the aircraft component, the aircraft component needs to be turned over before welding.

[0007] In order to solve the above technical problems, the utility model provides the following technical solutions: an aircraft parts welding workbench, comprising:

[0008] The workbench main unit includes a base and a counterweight fixedly mounted on one side of the upper end of the base;

[0009] The positioning unit includes a lifting component fixedly installed on the base, a driving motor is fixedly installed on the upper end of the lifting component near the center of the base, a rotating column is fixedly connected to the output shaft of the driving motor, a fixed block is fixedly installed on the end of the rotating column away from the driving motor, a corresponding fixed block is also provided on the side of the fixed block away from the rotating column, a plurality of telescopic rods are connected between two of the fixed blocks, a corresponding clamping component is installed on each of the fixed blocks, and a plurality of fixed blocks are fixedly installed on one end away from the telescopic rod with a limiting component.

[0010] As a preferred solution of the aircraft parts welding workbench described in the utility model, the lifting assembly includes a first servo motor fixedly mounted on a base, a first screw rod is fixedly mounted on the output shaft of the first servo motor, a movable sleeve is threadedly connected to the first screw rod, the movable sleeve is fixedly connected to the base by a plurality of telescopic rods, and one side of the movable sleeve is fixedly connected to the driving motor.

[0011] As a preferred solution of an aircraft parts welding workbench described in the utility model, each of the clamping assemblies comprises two racks slidably connected to a fixed block, each of the fixed blocks is rotatably mounted with a rotating rod, one end of the rotating rod passes through the fixed block and is fixedly connected to a corresponding gear, a plurality of the racks are meshed with corresponding gears, an aircraft parts clamping plate is fixedly mounted on the end of each rack away from the gear, the other end of the rotating rod is fixedly connected to a limiting gear, a handle is fixedly mounted on the limiting gear, a protective frame is wrapped around the outside of the limiting gear, the protective frame is fixedly mounted on a side of the fixed block away from the gear, a pull rod is slidably mounted on the protective frame, a limiting rack is fixedly mounted on one end of the pull rod close to the limiting gear, the limiting rack is meshed with the limiting gear, and the limiting rack and the protective frame are connected by a plurality of springs.

[0012] As a preferred solution of the aircraft parts welding workbench described in the utility model, the limiting assembly includes two fixing ears fixedly installed on the two fixing blocks at one end away from the telescopic rod, a second servo motor is fixedly installed on one side of one of the fixing ears, the output shaft of the second servo motor passes through the fixing ear and is fixedly connected to the second screw rod, the end of the second screw rod away from the output shaft of the second servo motor passes through another fixing ear, and the second screw rod is threadedly connected to the fixing ear away from the end of the second servo motor.

[0013] As a preferred solution of the aircraft parts welding workbench described in the utility model, a tool placement groove is fixedly installed on the base, and an anti-corrosion layer is laid around the upper end opening of the tool placement groove.

[0014] As a preferred solution of the aircraft parts welding workbench described in the utility model, wherein: a limit plate is fixedly installed on one end of the second screw rod away from the second servo motor, and the center of the limit plate is consistent with the center of the second screw rod.

[0015] The beneficial effects of the utility model include placing small aircraft parts on the clamping assembly, clamping the small aircraft parts horizontally by starting the second servo motor, clamping the small aircraft parts longitudinally by turning the handle, and then adjusting the lifting assembly to move the small aircraft parts to a suitable position, and adjusting the angle of the surface of the small aircraft parts to be welded by rotation. By rotating and clamping the small aircraft parts, when the staff has welded one side and the other welding surface is at the bottom of the part, they only need to rotate the aircraft parts to a suitable angle, thereby reducing the breakage rate of the aircraft parts during repeated clamping and manual flipping, and improving the efficiency of welding aircraft parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following briefly introduces the drawings required for the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. Among them:

[0017] Figure 1 This is a schematic diagram of the overall structure of an aircraft parts welding workbench proposed by the utility model;

[0018] Figure 2 This is a schematic diagram of the working unit structure of an aircraft parts welding workbench proposed by the utility model;

[0019] Figure 3 This is a schematic diagram of the structure of a clamping assembly of an aircraft parts welding workbench proposed by the utility model;

[0020] Figure 4 The utility model is a schematic diagram of the structure of a limit assembly of an aircraft component welding workbench.

[0021] Description of the drawings: 100 workbench main unit, 101 base, 102 counterweight block, 103 tool placement slot, 200 positioning unit, 201A lifting assembly, 2011 first servo motor, 2012 first screw rod, 2013 movable sleeve, 202 drive motor, 203 rotating column, 204 fixed block, 205A clamping assembly, 2051 rack, 2052 gear, 2053 aircraft parts clamping plate, 2054 limiting gear, 2055 handle, 2056 protection frame, 2057 pull rod, 2058 limiting rack, 206 telescopic rod, 207A limiting assembly, 2071 fixing ear, 2072 second servo motor, 2073 second screw rod, 2074 limiting plate. DETAILED DESCRIPTION

[0022] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0023] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0024] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0025] Secondly, the present invention is described in detail with reference to the schematic diagram. When describing the embodiments of the present invention, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0026] Reference Figure 1-Figure 3 , which is an embodiment of the utility model, provides an aircraft parts welding workbench, which includes a workbench main unit 100 and a positioning unit 200.

[0027] The workbench main unit 100 includes a base 101 and a counterweight 102 fixedly mounted on one side of the upper end of the base 101. The counterweight 102 is arranged to make the force on the base 101 more uniform. A tool placement slot 103 is fixedly mounted on the base 101. An anti-corrosion layer is laid around the upper opening of the tool placement slot 103. The material of the anti-corrosion layer is chrome. The service life of the tool placement slot 103 is extended by the arrangement of the anti-corrosion layer.

[0028] The positioning unit 200 includes a lifting component 201A fixedly mounted on the base 101, the lifting component 201A includes a first servo motor 2011 fixedly mounted on the base 101, a first screw rod 2012 is fixedly mounted on the output shaft of the first servo motor 2011, a movable sleeve 2013 is threadedly connected to the first screw rod 2012, the movable sleeve 2013 is fixedly connected to the base 101 through a plurality of telescopic rods 206, one side of the movable sleeve 2013 is fixedly connected to the driving motor 202, the upper end of the lifting component 201A near the center of the base 101 is fixedly mounted with the driving motor 202, a rotating column 203 is fixedly connected to the output shaft of the driving motor 202, a fixed block 204 is fixedly mounted on one end of the rotating column 203 away from the driving motor 202, a corresponding fixed block 204 is also provided on the side of the fixed block 204 away from the rotating column 203, a plurality of telescopic rods 206 are connected between the two fixed blocks 204, and a corresponding clamping component 205A is installed on each fixed block 204;

[0029] Each clamping assembly 205A includes two racks 2051 slidably connected to the fixed block 204, each fixed block 204 is rotatably mounted with a rotating rod, one end of the rotating rod passes through the fixed block 204 and is fixedly connected to a corresponding gear 2052, multiple racks 2051 are meshed with the corresponding gears 2052, and one end of each rack 2051 away from the gear 2052 is fixedly mounted with an aircraft component clamping plate 2053, the other end of the rotating rod is fixedly connected to a limited position gear 2054, and a handle 2055 is fixedly mounted on the limited position gear 2054. The outer side of the wheel 2054 is wrapped with a protection frame 2056, which is fixedly installed on the side of the fixed block 204 away from the gear 2052. A pull rod 2057 is slidably installed on the protection frame 2056. A limit rack 2058 is fixedly installed on one end of the pull rod 2057 close to the limit gear 2054. The limit rack 2058 is meshed with the limit gear 2054. The limit rack 2058 and the protection frame 2056 are connected by multiple springs. A limit assembly 207A is fixedly installed on one end of the multiple fixed blocks 204 away from the telescopic rod 206.

[0030] The limiting assembly 207A includes two fixing ears 2071 fixedly installed on one end of the two fixing blocks 204 away from the telescopic rod 206, wherein a second servo motor 2072 is fixedly installed on one side of one of the fixing ears 2071, and the output shaft of the second servo motor 2072 passes through the fixing ear 2071 and is fixedly connected to a second screw rod 2073, and the end of the second screw rod 2073 away from the output shaft of the second servo motor 2072 passes through another fixing ear 2071, and the second screw rod 2073 is threadedly connected to the fixing ear 2071 away from the end of the second servo motor 2072, and a limiting plate 2074 is fixedly installed on the end of the second screw rod 2073 away from the second servo motor 2072, and the center of the limiting plate 2074 is consistent with the center of the second screw rod 2073. The setting of the limiting plate 2074 prevents the second screw rod 2073 from separating and falling off from the fixing ear 2071.

[0031] During use, first place the small aircraft parts on the aircraft parts clamping plate 2053, start the second servo motor 2072, the second servo motor 2072 rotates forward to drive the second screw rod 2073 to rotate, the fixing ear 2071 threadedly connected to the second screw rod 2073 moves toward the direction of the second servo motor 2072 towards the rotation of the second screw rod 2073, then lift the pull rod 2057, turn the handle 2055, the handle 2055 drives the limit gear 2054 to rotate, at this time the gear 2052 connected to the limit gear 2054 rotates to make the two racks 2051 approach each other until the aircraft parts are clamped, after clamping, release the pull rod 2057, the limit rack 2058 connected to the pull rod 2057 clamps the limit gear 2054, so that the limit gear 2054 is clamped;

[0032] At this time, the first servo motor 2011 is started, and the first servo motor 2011 drives the first screw rod 2012 to rotate accordingly. The movable sleeve 2013 threadably connected to the first screw rod 2012 moves up and down through the multiple telescopic rods 206. When it is adjusted to a suitable angle, the first servo motor 2011 is stopped and welding begins. When it is necessary to weld the bottom surface of the aircraft component, the drive motor 202 is started, and the drive motor 202 rotates to make the aircraft component rotate as well. After rotating to a suitable angle, the drive motor 202 is stopped and welding can continue. By rotating and clamping the small aircraft components, the staff only needs to rotate the aircraft components to a suitable angle when one side is welded and the other welding surface is at the bottom of the part, thereby reducing the breakage rate of the aircraft components during repeated clamping and manual flipping, and improving the efficiency of welding aircraft components.

[0033] It should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the utility model, which should be included in the scope of the claims of the utility model.

Claims

1. An aircraft parts welding workbench, characterized in that: include: A workbench main unit (100) comprises a base (101) and a counterweight (102) fixedly mounted on one side of the upper end of the base (101); The positioning unit (200) comprises a lifting component (201A) fixedly mounted on a base (101); a driving motor (202) is fixedly mounted on the upper end of one side of the lifting component (201A) close to the center of the base (101); a rotating column (203) is fixedly connected to the output shaft of the driving motor (202); a fixed block (204) is fixedly mounted on one end of the rotating column (203) away from the driving motor (202); a corresponding fixed block (204) is also arranged on the side of the fixed block (204) away from the rotating column (203); a plurality of telescopic rods (206) are connected between two of the fixed blocks (204); a corresponding clamping component (205A) is mounted on each of the fixed blocks (204); and a limiting component (207A) is fixedly mounted on one end of the plurality of fixed blocks (204) away from the telescopic rods (206).

2. The aircraft parts welding workbench according to claim 1, characterized in that: The lifting assembly (201A) comprises a first servo motor (2011) fixedly mounted on a base (101); a first screw rod (2012) is fixedly mounted on an output shaft of the first servo motor (2011); a movable sleeve (2013) is threadedly connected to the first screw rod (2012); the movable sleeve (2013) is fixedly connected to the base (101) via a plurality of telescopic rods (206); and one side of the movable sleeve (2013) is fixedly connected to a driving motor (202).

3. The aircraft parts welding workbench according to claim 1, characterized in that: Each of the clamping assemblies (205A) comprises two racks (2051) slidably connected to a fixed block (204); a rotating rod is rotatably mounted on each of the fixed blocks (204); one end of the rotating rod passes through the fixed block (204) and is fixedly connected to a corresponding gear (2052); a plurality of the racks (2051) are meshed with corresponding gears (2052); an aircraft component clamping plate (2053) is fixedly mounted on one end of each of the racks (2051) away from the gear (2052); the other end of the rotating rod is fixedly connected to a limit gear (2054); the limit gear (2054) A handle (2055) is fixedly installed on the upper portion, a protective frame (2056) is wrapped around the outer side of the limit gear (2054), the protective frame (2056) is fixedly installed on the side of the fixed block (204) away from the gear (2052), a pull rod (2057) is slidably installed on the protective frame (2056), a limit rack (2058) is fixedly installed on one end of the pull rod (2057) close to the limit gear (2054), the limit rack (2058) is meshed with the limit gear (2054), and the limit rack (2058) and the protective frame (2056) are connected via a plurality of springs.

4. The aircraft parts welding workbench according to claim 1, characterized in that: The limiting assembly (207A) comprises two fixing ears (2071) fixedly mounted on the two fixing blocks (204) at one end away from the telescopic rod (206); a second servo motor (2072) is fixedly mounted on one side of one of the fixing ears (2071); an output shaft of the second servo motor (2072) passes through the fixing ear (2071) and is fixedly connected to a second screw rod (2073); an end of the second screw rod (2073) away from the output shaft of the second servo motor (2072) passes through another fixing ear (2071), and the second screw rod (2073) is threadedly connected to the fixing ear (2071) at one end away from the second servo motor (2072).

5. The aircraft parts welding workbench according to claim 1, characterized in that: A tool placement groove (103) is fixedly mounted on the base (101), and an anti-corrosion layer is laid around the upper opening of the tool placement groove (103).

6. The aircraft parts welding workbench according to claim 4, characterized in that: A limit plate (2074) is fixedly mounted on one end of the second screw rod (2073) away from the second servo motor (2072), and the center of the limit plate (2074) is consistent with the center of the second screw rod (2073).

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