CN113451861A - Automatic assembly mechanism and assembly method for aviation connector of engine accessory - Google Patents

Abstract

The invention discloses an automatic assembly mechanism and an assembly method for an aviation connector of an engine accessory, which comprise a workpiece positioning jig which moves forwards and backwards, a first supporting plate which moves horizontally and leftwards, a fixed-length cutting unit, a laser wire stripping unit, a peeling wire twisting unit, a needle shortening detection unit, a plastic terminal insertion unit, a short wire clamping and carrying unit, a short wire feeding unit and a plastic terminal feeding unit, wherein the fixed-length cutting unit, the laser wire stripping unit, the peeling wire twisting unit, the needle shortening detection unit and the plastic terminal insertion unit are sequentially and fixedly arranged on the first supporting plate from left to right, the short wire clamping and carrying unit is arranged corresponding to the workpiece positioning jig, the short wire feeding unit is matched and butted with the plastic terminal insertion unit, and the plastic terminal feeding unit is butted with the plastic terminal insertion unit. The invention realizes the wire stripping of the end part of the self-contained wire rod of the engine accessory, the wire stripping and terminal punching of one end of the short-circuit wire, the wire doubling and twisting and terminal punching of the other end of the short-circuit wire and the automatic needle retracting detection after the assembly of the aviation connector, and greatly improves the assembly efficiency and the assembly quality.

Description

Automatic assembly mechanism and assembly method for aviation connector of engine accessory

[ technical field ] A method for producing a semiconductor device

The invention belongs to the technical field of automation equipment, and particularly relates to an automatic assembly mechanism and an assembly method for an aviation connector of an engine accessory.

[ background of the invention ]

At present, an aerospace engine product comprises a regulator component, and the regulator component comprises a plurality of parts, so that the regulator component is mostly assembled manually at present, the assembly efficiency is low, the assembly precision and quality are difficult to guarantee, and for the aerospace engine, the assembly method cannot meet the high-precision requirement.

In the assembly of regulator part, need be in the aviation joint of pegging graft with the one end of each electronic components's the wire above, then fix aviation joint on regulator casing body, because the electronic components of regulator self is more in quantity, and still need merge into the wire rod of equal quantity from the external world, then peg graft the plastic terminal with the one end of these wire rods, then insert the aviation joint together again and go. In the prior art, the process adopts manual doubling, the plastic terminals are manually inserted and connected into the aviation connector and then fixed on the regulator, the efficiency is low, and the assembly quality cannot be guaranteed.

Therefore, there is a need to provide a new automatic assembly mechanism and method for aviation connectors of engine accessories to solve the above problems.

[ summary of the invention ]

One of the main purposes of the invention is to provide an automatic assembly mechanism for an aviation connector of an engine accessory, which realizes wire stripping of the end part of a self-contained wire of the engine accessory, wire stripping and terminal punching of one end of a short-circuit wire, wire doubling and twisting and terminal punching of the other end of the short-circuit wire and automatic needle retracting detection after the aviation connector is assembled, and greatly improves the assembly efficiency and the assembly quality.

The invention realizes the purpose through the following technical scheme: the utility model provides an aviation of engine accessory connects automatic assembly devices, its includes the work piece location tool that carries out the back-and-forth movement, carries out the level and removes the first backup pad that removes, from a left side to right side fixed setting in proper order is in fixed length on the first backup pad cuts the unit, laser wire stripping unit, peels off the twist thread unit, contracts needle detecting element and plastic terminal grafting unit, with the short-circuit wire centre gripping transport unit, short-circuit wire feed unit that work piece location tool corresponds the setting and with plastic terminal grafting unit cooperation butt joint's plastic terminal feed unit.

Furthermore, the workpiece positioning jig comprises a first motor, a second support plate driven by the first motor to move back and forth, a pair of hinged seats fixed on the second support plate, a rotary support plate hinged on the hinged seats on one side, a plurality of support positioning columns fixed on the rotary support plate, a pressing clamp, a mounting frame fixed on the second support plate, and a wire clamp jig or aviation connector fixing jig arranged on the mounting frame in a quick-change mode.

Furthermore, the mounting bracket has two support ends, the tip of supporting the end is provided with spacing support groove, the fastener tool with the both ends of aviation connector fixed tool are fixed through the bolt on spacing support groove.

Furthermore, the wire clamp jig comprises a first supporting rod and an elastic wire clamp, wherein two ends of the first supporting rod are clamped in the limiting supporting groove, and the elastic wire clamp is fixed on the first supporting rod; the aviation connector fixing jig comprises a second supporting rod and an aviation connector fixing clamp, wherein the two ends of the second supporting rod are clamped in the limiting supporting grooves, and the aviation connector fixing clamp is fixed on the second supporting rod.

Further, the fixed-length cutting unit comprises a support, a first air cylinder fixed on the support, a driving block driven by the first air cylinder to move back and forth, and an upper cutting die assembly and a lower cutting die assembly driven by the driving block to move up and down relatively; go up cutting die subassembly with lower cutting die subassembly structure is the same and include the movable block, cut sword, lever and connecting rod, the activity sets up on a slide rail about the movable block, it fixes to cut the sword the one end of movable block, the other end of movable block with lever one end is articulated together, the middle part of lever articulates on the support and the other end with the connecting rod is articulated together, the other end of connecting rod with the drive block is articulated together.

Furthermore, the needle retracting detection unit comprises a third motor, a third support plate driven by the third motor to move up and down, a pressure sensor fixed on the third support plate, and a thimble fixed at the sensing end of the pressure sensor, wherein the thimble is arranged in a horizontal state.

Furthermore, the plastic terminal feeding unit comprises a vibrating disc, a flow channel butted with the vibrating disc, and a material control assembly arranged above the tail end of the flow channel, the plastic terminal inserting unit comprises a fourth air cylinder, a material receiving clamping unit driven by the fourth air cylinder to move back and forth to realize butt joint with the tail end of the flow channel, an inserting and transferring unit for clamping the plastic terminal on the material receiving clamping unit and inserting the plastic terminal on the wire end part, a terminal riveting unit for riveting the plastic terminal and the wire end part together, and a wire fixing unit for keeping the wire straight and straight inserted when riveting the terminal.

Furthermore, the short-circuit wire clamping and carrying unit comprises a fifth motor, a sixth motor driven by the fifth motor to move back and forth, a fifth support plate driven by the sixth motor to move up and down, a seventh cylinder fixed on the fifth support plate, a rack driven by the seventh cylinder to move horizontally, a rotating shaft rotatably arranged on the fifth support plate, a gear fixed on the top of the rotating shaft and meshed with the rack, a third wire clamping jaw fixed at the bottom of the rotating shaft, and a wire pressing sheet fixed on the third wire clamping jaw and pressing wires downwards.

Furthermore, the device also comprises a resistance tester, wherein a connecting joint which is oppositely inserted with the aviation joint is led out of the resistance tester.

Another main object of the present invention is to provide an automatic assembly method of an aircraft joint of an engine fitting, comprising the following steps:

1) placing an engine regulator on a rotary supporting plate of a workpiece positioning jig, positioning the engine regulator through a supporting positioning column, and pressing and fixing the engine regulator through a pressing clamp;

2) installing a wire clamp jig on the workpiece positioning jig;

3) cutting all wires led out by the regulator to a set length by using a ruler and a pair of scissors according to the process requirement; turning the rotary supporting plate by 90 degrees to be in a vertical state, enabling the surface of one side, from which the regulator wire is led out, to face backwards, and moving the rotary supporting plate backwards to a first set position;

4) straightening one wire in the wire rods led out of the regulator, putting the wire into a wire clamp jig for clamping, and pressing a start button; meanwhile, the short-circuit wire clamping and carrying unit clamps a short-circuit wire to a second set position, the first supporting plate moves leftwards, and the fixed-length cutting, laser peeling, peeling and twisting and terminal punching operations are completed sequentially through the fixed-length cutting unit, the laser wire stripping unit, the peeling and twisting unit and the plastic terminal inserting unit; then the short-circuit wire is rotated by 180 degrees to replace the other end, the laser wire stripping unit is used for carrying out laser wire stripping, the short-circuit wire stays at a second set position, and the first supporting plate returns;

5) the first supporting plate moves leftwards, and the end part of the wire on the wire jig is cut at fixed length, peeled by laser and peeled and twisted;

6) the short-circuit wire clamping and carrying unit is used for merging the processed short-circuit wires into the wire jig, doubling the wires with the wire jig, and twisting the end parts of the two wires together through the peeling and twisting unit;

7) punching a terminal on one end of the combined two wires through the plastic terminal inserting unit;

8) repeating the steps 4) to 7) until all the wires are subjected to terminal crimping;

9) replacing an aviation connector fixing jig on the workpiece positioning jig, placing the aviation connector on the aviation connector fixing jig for fixing, inserting the pressed terminal into an insertion pin hole of the aviation connector according to a preset position by means of a magnifying lens, and pressing a starting button after the insertion;

10) the pin shrinkage detection unit moves to the position of the aviation connector and performs pin shrinkage detection on the plug terminal in the aviation connector;

11) after the needle retracting detection is OK, the workpiece positioning jig is forwards withdrawn from the machining position, then an operator turns the rotary supporting plate to be in a horizontal state, and a connecting joint of the resistance tester is inserted into the aviation joint to carry out resistance measurement detection;

12) after the resistance detection is OK, an operator binds the wire harness, and then fills the arc-resistant enamel into the threading hole for sealing;

13) locking and installing the aviation connector by using a screw locking mechanism;

14) the operator scans the workpiece information and the identity information of the operator by using the code scanning gun, the binding is realized, and then the binding is transferred to the next work station.

Compared with the prior art, the automatic assembly mechanism and the assembly method for the aviation connector of the engine accessory have the beneficial effects that: the automatic fixed-length cutting, laser peeling and peeling twisting of the wire rods of the workpiece are realized by arranging the integrally movable fixed-length cutting unit, the laser wire stripping unit, the peeling twisting unit, the needle retracting detection unit and the plastic terminal inserting unit and matching with the short-circuit wire clamping and carrying unit and the workpiece positioning jig; laser peeling, wire twisting and terminal punching at one end of the short-circuit wire rod are realized; laser peeling at the other end of the short-circuit wire rod is realized, and the short-circuit wire rod is connected with a workpiece with the wire rod in parallel and twisted and is used for punching a terminal; the production efficiency is greatly improved; by arranging the needle retracting detection unit, the automatic detection of whether the insertion of the plastic terminal on the aviation connector is in place is realized, and the assembly quality and the assembly reliability of the aviation connector are improved; the wire clamp jig structure and the quick-change structure of the aviation connector fixing jig are arranged on the workpiece positioning jig, so that the clamping requirement during wire rod machining and the fixing requirement of the aviation connector during needle retracting detection are met, and the efficiency is improved.

[ description of the drawings ]

FIG. 1 is a schematic perspective view of an embodiment of the present invention;

FIG. 2 is a schematic top view of an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a workpiece positioning fixture according to an embodiment of the present disclosure;

FIG. 4 is a schematic structural view of a mounting frame and a wire clamp fixture according to an embodiment of the invention;

FIG. 5 is a schematic structural diagram of a fixed-length cutting unit according to an embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a peeling and twisting unit according to an embodiment of the present invention;

FIG. 7 is a schematic structural diagram of a needle retracting detection unit according to an embodiment of the present invention;

FIG. 8 is a schematic structural diagram of a plastic terminal plugging unit and a plastic terminal feeding unit according to an embodiment of the present invention;

FIG. 9 is a schematic view showing a part of the structure of the short-wire holding and conveying unit according to the embodiment of the present invention;

the figures in the drawings represent:

100 aviation connector automatic assembly mechanisms of engine accessories;

1, a workpiece positioning jig, 11 a first motor, 12 a second support plate, 13 a hinged seat, 14 a rotating support plate, 15 a supporting positioning column, 16 a pressing clamp, 17 a mounting frame, 171 a supporting end, 172 a limiting supporting groove, 173 bolts, 18 a wire clamp jig, 181 a first supporting rod, 182 an elastic wire clamp and 19 a supporting column;

2 a first support plate;

3 fixed-length cutting units, 31 supports, 32 first cylinders, 33 driving blocks, 34 upper cutter die assemblies, 341 movable blocks, 342 cutting knives, 343 levers, 344 connecting rods and 35 lower cutter die assemblies;

4, a laser wire stripping unit is arranged,

5 a stripping and twisting unit, 51 a wire harness blocking mechanism, 511 a second air cylinder, 512 a third air cylinder, 513 a blocking fork plate;

a needle retraction detection unit, a third motor 61, a third support plate 62, a pressure sensor 63 and a thimble 64;

7 plastic terminal plug-in unit, 71 fourth cylinder, 72 wire fixing unit, 721 sixth cylinder, 722 second wire clamping jaw, 73 material receiving clamping unit, 74 plug-in transfer unit, 741 fourth motor, 742 fifth cylinder, 743 fourth supporting plate, 744 first wire clamping jaw, 75 terminal riveting unit;

8 short-circuit wire clamping and conveying units, 81 a fifth motor, 82 a sixth motor, 83 a fifth supporting plate, 84 a seventh cylinder, 85 racks, 86 a rotating shaft, 87 gears, 88 a third wire clamping jaw and 89 wire pressing sheets;

9 a short-circuit wire feeding unit;

10 plastic terminal feeding units, 101 vibrating discs, 102 flow channels and 103 material control assemblies;

20 resistance tester.

[ detailed description ] embodiments

The first embodiment is as follows:

referring to fig. 1 to 9, the present embodiment is an automatic assembly mechanism 100 for an aircraft joint of an engine accessory, which includes a workpiece positioning jig 1 moving forward and backward, a first support plate 2 moving horizontally and leftward, a fixed length cutting unit 3 fixedly disposed on the first support plate 2 from left to right, a laser wire stripping unit 4, a wire stripping and twisting unit 5, a pin shrinkage detection unit 6, a plastic terminal insertion unit 7, a short wire clamping and carrying unit 8 disposed corresponding to the workpiece positioning jig 1, a short wire feeding unit 9, and a plastic terminal feeding unit 10 in butt joint with the plastic terminal insertion unit 7.

The workpiece positioning jig 1 comprises a first motor 11, a second support plate 12 driven by the first motor 11 to move back and forth, a pair of hinge seats 13 fixed on the second support plate 12, a rotating support plate 14 hinged on the hinge seats 13 at one side, a plurality of support positioning columns 15 and a pressing clamp 16 fixed on the rotating support plate 14, a mounting frame 17 fixed on the second support plate 12, and a wire clamp jig 18 or an aviation connector fixing jig (not shown) arranged on the mounting frame 17 in a quick-change manner.

The second support plate 12 is provided with a support column 19 for supporting the bottom of the rotation support plate 14 in a horizontal state.

In order to realize the quick switching of the wire clamp jig 18 and the aviation connector fixing jig on the mounting frame 17, the mounting frame 17 is provided with two supporting ends 171, the end parts of the supporting ends 171 are provided with limiting supporting grooves 172, and the wire clamp jig 18 and the aviation connector fixing jig are fixed on the limiting supporting grooves 172 through bolts 173. The wire clamp jig 18 includes a first supporting rod 181 with both ends clamped in the limiting supporting grooves 172, and an elastic wire clamp 182 fixed on the first supporting rod 181. The aviation connector fixing jig is the same as the wire clamp jig 18 in structural principle and comprises a second supporting rod and an aviation connector fixing clamp, wherein the two ends of the second supporting rod are clamped in the limiting supporting grooves 172, and the aviation connector fixing clamp is fixed on the second supporting rod.

In order to improve the positional stability of the rotation support plate 14 after being turned over by 90 °, a reverse support structure may be provided on the back surface of the rotation support plate 14 to maintain the rotation support plate 14 in a vertical state.

The rotary supporting plates 14 are arranged on the pair of hinged seats 13 and can turn around the hinged seat shafts, an operator or a mechanical hand carries a workpiece onto the rotary supporting plates 14 in a horizontal state, the workpiece is positioned through the supporting positioning columns 15 and is pressed and fixed through the pressing clamps 16; then the rotating support plate 14 is manually turned by 90 degrees, so that the surface of one side of the workpiece with the wiring harness faces the rear, and the subsequent operation on the wiring harness is facilitated.

Before the aviation connector is assembled, a short-circuit wire needs to be in short circuit with each wire led out of a workpiece, a plastic terminal is assembled at the short-circuit position, then a plastic terminal is assembled at the other end of the short-circuit wire, and finally, after the plastic terminals corresponding to all the wires are installed, one of the plastic terminals is inserted into an insertion pin hole of the aviation connector; after the aviation connector is inserted, the insertion quality needs to be detected, so that the aviation connector needs to be fixed and moved to the position of the corresponding needle retracting detection unit 6 for detection. Therefore, this embodiment through set up fastener tool 18 with the quick change formula structure of the fixed tool of aviation connector, can be convenient, quick change between them, satisfy the fixed demand of wire rod and aviation connector.

The first support plate 2 is driven by a second motor (not shown) to move horizontally.

The fixed-length cutting unit 3 comprises a bracket 31, a first air cylinder 32 fixed on the bracket 31, a driving block 33 driven by the first air cylinder 32 to move back and forth, and an upper cutting die assembly 34 and a lower cutting die assembly 35 driven by the driving block 33 to move up and down relatively. The upper cutting die assembly 34 and the lower cutting die assembly 35 have the same structure and comprise a movable block 341, a cutting knife 342, a lever 343 and a connecting rod 344, the movable block 341 is movably arranged on a sliding rail up and down, the cutting knife 342 is fixed at one end of the movable block 341, the other end of the movable block 341 is hinged with one end of the lever 343, the middle part of the lever 343 is hinged on the bracket 31, the other end of the lever 343 is hinged with the connecting rod 344, and the other end of the connecting rod 344 is hinged with the driving block 33.

The first cylinder 32 drives the driving block 33 to move back and forth, the driving block 33 drives the connecting rod 343 to drive the lever 343 to turn around the lever shaft in the middle, and further drives the other end of the lever 343 to move up and down, so that the movable block 341 is driven to move up and down on the sliding rail, and the cutting knife 342 in the upper knife mold assembly 34 and the cutting knife 342 in the lower knife mold assembly 35 are cut.

The laser wire stripping unit 4 can be directly purchased from the market by adopting the existing mechanism.

The peeling and twisting unit 5 is commercially available, and is mainly used for peeling off the lacquer skin after the lacquer skin on the surface layer of the wire is separated by the laser wire stripping unit 4 on the end part of the wire, and then clamping, rotating and twisting the peeled part into one strand to twist the wire. In order to prevent the wire from being wound to interfere with the operating wire harness, the wire harness blocking mechanism 51 is further disposed on the peeling and twisting unit 5 in this embodiment, and the wire harness blocking mechanism 51 includes a second cylinder 511, a third cylinder 512 driven by the second cylinder 511 to move forward and backward, and a blocking fork 513 driven by the third cylinder 512 to move up and down.

The needle retracting detection unit 6 comprises a third motor 61, a third support plate 62 driven by the third motor 61 to move up and down, a pressure sensor 63 fixed on the third support plate 62, and a thimble 64 fixed at the sensing end of the pressure sensor 63, wherein the thimble 64 is arranged in a horizontal state. After all the wires with the plastic terminals are inserted into the aviation connectors, the aviation connectors are placed in the workpiece positioning jig 1 and fixed on the aviation connector fixing jig, then the needle retracting detection unit 6 moves to a specified position, the ejector pins 64 are firstly aligned to the first needle inserting holes according to a set detection sequence, the workpiece positioning jig 1 drives the aviation connectors to lean against the needle retracting detection unit 6 backwards, the ejector pins 64 are ejected into the needle inserting holes to set the depth, the pressure values of the ejector pins are sensed through the pressure sensors 63, and then whether the plastic terminals are inserted in place or not is judged.

The plastic terminal feeding unit 10 includes a vibration disc 101, a flow channel 102 butted with the vibration disc 101, and a material control assembly 103 disposed above the end of the flow channel 102, the plastic terminal inserting unit 7 includes a fourth cylinder 71, a material receiving clamping unit 73 driven by the fourth cylinder 71 to move back and forth to realize the butt joint with the end of the flow channel 102, an inserting and transferring unit 74 for clamping the plastic terminal on the material receiving clamping unit 73 and inserting the plastic terminal on the end of the wire rod, a terminal riveting unit 75 for riveting the plastic terminal and the end of the wire rod together, and a wire rod fixing unit 72 for keeping the wire rod straight and inserted when riveting the terminal.

The material control component 103 includes an electromagnet and a material pressing rod driven by the electromagnet to move up and down, and the last but one plastic terminal at the end of the flow channel 102 is pressed and held by the up and down movement of the material pressing rod, so as to prevent the plastic terminal from moving forward. The material receiving clamping unit 73 is of a clamping jaw structure, when a plastic terminal at the tail end of the runner 102 enters the material receiving clamping unit 73, the plastic terminal is clamped, then the plastic terminal is moved to a specified position through the fourth air cylinder 71, and then the inserting transfer unit 74 takes the plastic terminal away and moves the plastic terminal to an inserting position. The insertion transfer unit 74 includes a fourth motor 741, a fifth cylinder 742 driven by the fourth motor 741 to move forward and backward, a fourth support plate 743 driven by the fifth cylinder 742 to move up and down, and a first wire clamping jaw 744 fixed to the fourth support plate 743. The terminal crimping unit 75 may be configured as in the prior art, such as that disclosed in patent No. CN 202011143723.3. The first wire clamping jaw 744 clamps the plastic terminal and inserts from one side of the terminal riveting unit 75, and the wire fixing unit 72 wraps the wire inserted into the terminal riveting unit 75 from the other side, so that the wire can be smoothly inserted into the plastic terminal. The wire fixing unit 72 includes a sixth cylinder 721 and a second wire gripping jaw 722 that is driven by the sixth cylinder 721 to move left and right.

After the plastic terminal inserting unit 7 moves to the position of the workpiece positioning jig 1, the inserting and transferring unit 74 clamps the plastic terminal and stretches into the terminal riveting unit 75 to wait for the insertion of the wire, then the wire fixing unit 72 clamps one side, then the workpiece integrally moves backwards, so that the free end of the wire stretches into the plastic terminal, then the inserting and transferring unit 74 withdraws, and the terminal riveting unit 75 rivets the plastic terminal and the end part of the wire together to complete the assembly of the plastic terminal.

The short-wire holding/conveying unit 8 includes a fifth motor 81, a sixth motor 82 driven by the fifth motor 81 to move forward and backward, a fifth support plate 83 driven by the sixth motor 82 to move up and down, a seventh air cylinder 84 fixed to the fifth support plate 83, a rack 85 driven by the seventh air cylinder 84 to move horizontally, a rotary shaft 86 rotatably provided on the fifth support plate 83, a gear 87 fixed to the top of the rotary shaft 86 and engaged with the rack 85, a third wire gripper 88 fixed to the bottom of the rotary shaft 86, and a wire pressing piece 89 fixed to the third wire gripper 88 and pressing a wire downward.

The embodiment further comprises a resistance tester 20, and a connection joint which is inserted into the aviation joint is led out of the resistance tester 20.

The present embodiment further includes a code scanning gun, a display and a camera (not shown).

The embodiment also provides an assembling method of the automatic aviation connector assembling mechanism based on the engine fittings, which comprises the following steps:

1) placing an engine regulator on a rotary supporting plate 14 of the workpiece positioning jig 1, positioning the engine regulator through a supporting positioning column 15, and pressing and fixing the engine regulator through a pressing clamp 16;

2) installing a wire clamp jig 18 on the workpiece positioning jig 1;

3) cutting all wires led out by the regulator to a set length, such as 100mm, by using a ruler and a pair of scissors according to the process requirement; the rotary support plate 14 is turned over by 90 ° to be in a vertical state so that the surface of the side from which the regulator wire is led out faces backward, and is moved backward to a first set position;

4) an operator straightens one of the wires led out from the regulator, puts the wire into the wire clamp jig 18 and clamps the wire, and presses a start button; meanwhile, the short-circuit wire clamping and carrying unit 8 clamps a short-circuit wire to a second set position, the first supporting plate 2 moves leftwards, and the operations of fixed-length cutting, laser peeling, peeling and twisting and terminal punching are completed sequentially through the fixed-length cutting unit 3, the laser wire stripping unit 4, the peeling and twisting unit 5 and the plastic terminal inserting unit 7; then the short-circuit wire is rotated by 180 degrees to change the other end, and laser peeling is carried out by using the laser wire stripping unit 4; then, the first supporting plate 2 is stopped at a second set position and returns;

5) the first supporting plate 2 moves leftwards, and the end part of the wire on the wire jig 18 is cut at fixed length, peeled by laser and peeled and twisted;

6) the short-circuit wire clamping and carrying unit 8 merges the processed short-circuit wires into the wire jig 18, and the short-circuit wires are combined with the wires on the wire jig 18, and then the end parts of the two wires are twisted together through the peeling and twisting unit 5;

7) punching a terminal on one end of the combined two wires through the plastic terminal inserting unit 7;

8) repeating the steps 4) to 7) until all the wires are subjected to terminal crimping;

9) replacing the aviation connector fixing jig on the workpiece positioning jig 1, placing the aviation connector on the aviation connector fixing jig for fixing, inserting the pressed terminal into an insertion pin hole of the aviation connector according to a preset position by means of a magnifying lens, and pressing a starting button after the insertion;

10) the needle retracting detection unit 6 moves to the position of the aviation connector to perform needle retracting detection on the plug terminal in the aviation connector;

11) after the needle retracting detection is OK, the workpiece positioning jig 1 is retreated from the machining position forwards, then an operator turns the rotary supporting plate 14 to be in a horizontal state, and the operator inserts the connecting joint of the resistance tester 20 and the aviation joint in a butting way to carry out resistance measurement detection;

12) after the resistance detection is OK, an operator binds the wiring harness, and then injects anti-arc enamel into the threading hole (namely the insertion pin hole on the aviation connector) for sealing;

13) locking and installing the aviation connector by using a screw locking mechanism;

14) the operator scans the workpiece information and the identity information of the operator by using the code scanning gun, the binding is realized, and then the binding is transferred to the next work station.

In the steps 3) and 4), the first setting position and the second setting position can be distributed left and right, and the first setting position is positioned on the left side of the second setting position, so that when the first supporting plate 2 moves left and right, the short-circuit wire clamped on the short-circuit wire clamping and transporting unit 8 and the wire rod on the wire clamp jig 18 can be operated and processed in a flowing water mode, and the processing efficiency is improved; for better doubling, a left-right displacement mechanism may be provided on the short-wiring clamping and conveying unit 8 to move the short-wiring left and right, thereby achieving the position of the wire rod on the wire rod jig 18 and the doubling.

In the operation process, the operation process of an operator is recorded through the full-range video of the camera, and the operation process is stored, bound with the workpiece information scanned by the scanning gun and the identity information of the operator, so that the follow-up tracing is facilitated.

The aviation connector automatic assembly mechanism 100 of the engine fitting of the embodiment realizes automatic fixed-length cutting, laser peeling and peeling twisted wire of a self-contained wire of a workpiece by arranging an integrally movable fixed-length cutting unit, a laser wire stripping unit, a peeling twisted wire unit, a needle retracting detection unit and a plastic terminal insertion unit, and matching with a short-circuit wire clamping and carrying unit and a workpiece positioning jig; laser peeling, wire twisting and terminal punching at one end of the short-circuit wire rod are realized; laser peeling at the other end of the short-circuit wire rod is realized, and the short-circuit wire rod is connected with a workpiece with the wire rod in parallel and twisted and is used for punching a terminal; the production efficiency is greatly improved; by arranging the needle retracting detection unit, the automatic detection of whether the insertion of the plastic terminal on the aviation connector is in place is realized, and the assembly quality and the assembly reliability of the aviation connector are improved; the wire clamp jig structure and the quick-change structure of the aviation connector fixing jig are arranged on the workpiece positioning jig, so that the clamping requirement during wire rod machining and the fixing requirement of the aviation connector during needle retracting detection are met, and the efficiency is improved.

What has been described above are merely some embodiments of the present invention. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the inventive concept thereof, and these changes and modifications can be made without departing from the spirit and scope of the invention.

Claims (10)

1. The utility model provides an engine accessories's aviation connector automatic assembly mechanism which characterized in that: the device comprises a workpiece positioning jig which moves back and forth, a first supporting plate which moves horizontally and left and right, a fixed-length cutting unit, a laser wire stripping unit, a peeling wire twisting unit, a needle shrinking detection unit, a plastic terminal inserting unit, a short wire clamping and carrying unit, a short wire feeding unit and a plastic terminal feeding unit, wherein the fixed-length cutting unit, the laser wire stripping unit, the peeling wire twisting unit, the needle shrinking detection unit and the plastic terminal inserting unit are sequentially and fixedly arranged on the first supporting plate from left to right, the short wire clamping and carrying unit is correspondingly arranged on the workpiece positioning jig, and the plastic terminal feeding unit is in matched butt joint with the plastic terminal inserting unit.

2. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the workpiece positioning jig comprises a first motor, a second supporting plate driven by the first motor to move back and forth, a pair of hinged seats fixed on the second supporting plate, a rotary supporting plate hinged on the hinged seats on one side, a plurality of supporting positioning columns fixed on the rotary supporting plate, a pressing clamp, a mounting frame fixed on the second supporting plate, and a wire clamp jig or aviation connector fixing jig arranged on the mounting frame in a quick-change mode.

3. The automatic assembly mechanism for an aircraft joint of an engine accessory as set forth in claim 2, wherein: the mounting bracket is provided with two supporting ends, the end parts of the supporting ends are provided with limiting supporting grooves, and the wire clamp jig and the two ends of the aviation connector fixing jig are fixed on the limiting supporting grooves through bolts.

4. An automatic assembly mechanism for aviation connectors of engine accessories according to claim 3, wherein: the wire clamp jig comprises a first supporting rod and an elastic wire clamp, wherein two ends of the first supporting rod are clamped in the limiting supporting groove; the aviation connector fixing jig comprises a second supporting rod and an aviation connector fixing clamp, wherein the two ends of the second supporting rod are clamped in the limiting supporting grooves, and the aviation connector fixing clamp is fixed on the second supporting rod.

5. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the fixed-length cutting unit comprises a support, a first air cylinder fixed on the support, a driving block driven by the first air cylinder to move back and forth, an upper cutting die assembly and a lower cutting die assembly driven by the driving block to move up and down relatively; go up cutting die subassembly with lower cutting die subassembly structure is the same and include the movable block, cut sword, lever and connecting rod, the activity sets up on a slide rail about the movable block, it fixes to cut the sword the one end of movable block, the other end of movable block with lever one end is articulated together, the middle part of lever articulates on the support and the other end with the connecting rod is articulated together, the other end of connecting rod with the drive block is articulated together.

6. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the needle retracting detection unit comprises a third motor, a third supporting plate driven by the third motor to move up and down, a pressure sensor fixed on the third supporting plate, and a thimble fixed at the sensing end of the pressure sensor, wherein the thimble is arranged in a horizontal state.

7. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the plastic terminal feeding unit comprises a vibrating disc, a flow channel in butt joint with the vibrating disc and a material control assembly arranged above the tail end of the flow channel, the plastic terminal inserting unit comprises a fourth air cylinder, a material receiving clamping unit driven by the fourth air cylinder to move back and forth to realize butt joint with the tail end of the flow channel, an inserting and transferring unit for clamping the plastic terminal on the material receiving clamping unit and inserting the plastic terminal on the wire end part, a terminal riveting unit for riveting the plastic terminal and the wire end part together and a wire fixing unit for keeping the wire straight and inserted when the terminal is riveted.

8. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the short-wiring clamping and carrying unit comprises a fifth motor, a sixth motor driven by the fifth motor to move back and forth, a fifth support plate driven by the sixth motor to move up and down, a seventh air cylinder fixed on the fifth support plate, a rack driven by the seventh air cylinder to move horizontally, a rotating shaft rotatably arranged on the fifth support plate, a gear fixed on the top of the rotating shaft and meshed with the rack, a third wire clamping jaw fixed at the bottom of the rotating shaft, and a wire pressing sheet fixed on the third wire clamping jaw and pressing wires downwards.

9. The automatic aviation connector assembling mechanism for engine accessories according to claim 1, wherein: the resistance tester is provided with a connecting joint which is oppositely inserted with the aviation joint.

10. An automatic assembly method for an aviation connector of an engine accessory is characterized by comprising the following steps: the automatic aviation connector assembling mechanism is realized based on the automatic aviation connector assembling mechanism as claimed in claim 1, and comprises the following steps:

1) placing an engine regulator on a rotary supporting plate of a workpiece positioning jig, positioning the engine regulator through a supporting positioning column, and pressing and fixing the engine regulator through a pressing clamp;

2) installing a wire clamp jig on the workpiece positioning jig;

3) cutting all wires led out by the regulator to a set length by using a ruler and a pair of scissors according to the process requirement; turning the rotary supporting plate by 90 degrees to be in a vertical state, enabling the surface of one side, from which the regulator wire is led out, to face backwards, and moving the rotary supporting plate backwards to a first set position;

4) straightening one wire in the wire rods led out of the regulator, putting the wire into a wire clamp jig for clamping, and pressing a start button; meanwhile, the short-circuit wire clamping and carrying unit clamps a short-circuit wire to a second set position, the first supporting plate moves leftwards, and the fixed-length cutting, laser peeling, peeling and twisting and terminal punching operations are completed sequentially through the fixed-length cutting unit, the laser wire stripping unit, the peeling and twisting unit and the plastic terminal inserting unit; then the short-circuit wire is rotated by 180 degrees to replace the other end, the laser wire stripping unit is used for carrying out laser wire stripping, the short-circuit wire stays at a second set position, and the first supporting plate returns;

5) the first supporting plate moves leftwards, and the end part of the wire on the wire jig is cut at fixed length, peeled by laser and peeled and twisted;

6) the short-circuit wire clamping and carrying unit is used for merging the processed short-circuit wires into the wire jig, doubling the wires with the wire jig, and twisting the end parts of the two wires together through the peeling and twisting unit;

7) punching a terminal on one end of the combined two wires through the plastic terminal inserting unit;

8) repeating the step 4) to the step 7) until all the wires are subjected to terminal crimping;

9) replacing an aviation connector fixing jig on the workpiece positioning jig, placing the aviation connector on the aviation connector fixing jig for fixing, inserting the pressed terminal into an insertion pin hole of the aviation connector according to a preset position by means of a magnifying lens, and pressing a starting button after the insertion;

10) the pin shrinkage detection unit moves to the position of the aviation connector and performs pin shrinkage detection on the plug terminal in the aviation connector;

11) after the needle retracting detection is OK, the workpiece positioning jig is forwards withdrawn from the machining position, then an operator turns the rotary supporting plate to be in a horizontal state, and a connecting joint of the resistance tester is inserted into the aviation joint to carry out resistance measurement detection;

12) after the resistance detection is OK, an operator binds the wire harness, and then fills the arc-resistant enamel into the threading hole for sealing;

13) locking and installing the aviation connector by using a screw locking mechanism;

14) the operator scans the workpiece information and the identity information of the operator by using the code scanning gun, the binding is realized, and then the binding is transferred to the next work station.

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