CN116572092B - Duplex position of automatic change processing aircraft spare part grinds platform - Google Patents

Duplex position of automatic change processing aircraft spare part grinds platform Download PDF

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Publication number
CN116572092B
CN116572092B CN202310647742.2A CN202310647742A CN116572092B CN 116572092 B CN116572092 B CN 116572092B CN 202310647742 A CN202310647742 A CN 202310647742A CN 116572092 B CN116572092 B CN 116572092B
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CN
China
Prior art keywords
polishing
frame
placing
aircraft
aircraft part
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CN202310647742.2A
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Chinese (zh)
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CN116572092A (en
Inventor
张海
张梓煊
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Sheyang Feitianxiang Aviation Equipment Co ltd
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Sheyang Feitianxiang Aviation Equipment Co ltd
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Priority to CN202310647742.2A priority Critical patent/CN116572092B/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B5/00—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor
    • B24B5/02—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor involving centres or chucks for holding work
    • B24B5/04—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor involving centres or chucks for holding work for grinding cylindrical surfaces externally
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B27/00—Other grinding machines or devices
    • B24B27/0023—Other grinding machines or devices grinding machines with a plurality of working posts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B27/00—Other grinding machines or devices
    • B24B27/02—Bench grinders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B41/00—Component parts such as frames, beds, carriages, headstocks
    • B24B41/02—Frames; Beds; Carriages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B41/00—Component parts such as frames, beds, carriages, headstocks
    • B24B41/06—Work supports, e.g. adjustable steadies
    • B24B41/067—Work supports, e.g. adjustable steadies radially supporting workpieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B47/00—Drives or gearings; Equipment therefor
    • B24B47/20—Drives or gearings; Equipment therefor relating to feed movement
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/10—Greenhouse gas [GHG] capture, material saving, heat recovery or other energy efficient measures, e.g. motor control, characterised by manufacturing processes, e.g. for rolling metal or metal working

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Grinding Of Cylindrical And Plane Surfaces (AREA)
  • Constituent Portions Of Griding Lathes, Driving, Sensing And Control (AREA)
  • Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)

Abstract

The invention discloses a double-station polishing table for automatically processing airplane parts, which comprises a bottom frame, wherein two placing frames are oppositely arranged on the inner side of the bottom frame. According to the invention, by adjusting the relative distance between the bottom surface of the placing rack and the top surface of the limiting frame, aircraft parts with different diameters can be placed inside the placing grooves of the two placing racks, the bottom surfaces of the polishing plates of the two polishing structures are adjusted to be in the same horizontal plane, and the placing racks and the polishing plates of the two stations are matched to polish the aircraft parts with different diameters; through adjusting the relative distance between rack and the limit frame top surface, place the same aircraft part in two standing groove inboards, when the structure of polishing moves down and makes the board of polishing polish two aircraft parts, the board pressure of polishing that is in two aircraft part tops is different each other, thereby can carry out the processing of polishing of different degree to the same aircraft part according to the demand of polishing of difference, improves the efficiency of processing aircraft part of polishing in batches.

Description

Duplex position of automatic change processing aircraft spare part grinds platform
Technical Field
The invention belongs to the technical field of part polishing, and particularly relates to a double-station polishing table for automatically processing airplane parts.
Background
Work piece polishing is one of the common operations in the course of working, and at present polishing operation is usually accomplished by manual work, and though polishing effect is good, inefficiency, and the metal dust that the course of polishing produced is unfavorable to the health of operating personnel.
When polishing cylindrical parts of an aircraft, a specific clamping structure is required to limit the cylindrical parts of the aircraft, and when batch processing is performed on the workpieces, the efficiency is further reduced and the operation intensity is increased if a traditional manual polishing mode is still adopted.
Therefore, it is necessary to invent a double station grinding table for automatically processing aircraft parts to solve the above problems.
Disclosure of Invention
In order to solve the problems, the invention provides a double-station grinding table for automatically processing airplane parts, which solves the problems in the prior art.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides an automatic change duplex position of processing aircraft spare part and polish platform, includes the chassis, the chassis inboard is provided with two racks relatively, rack bottom both sides all utilize connection structure and chassis inboard bottom surface to be connected, rack top surface center department is provided with the standing groove of placing the aircraft part, and the standing groove top of two racks all is provided with the structure of polishing, and the structure of polishing rotates and cup joints in the lifter surface, and the structure bottom of polishing connects the board of polishing, the board of polishing corresponds in aircraft part top, both sides face center department around the chassis is run through respectively at the lifter both ends, the cylinder is all installed to side bottom around the chassis, cylinder top output corresponds to paste in the lifter tip, the inboard symmetry of chassis is provided with two limiting frames, and the lifter runs through the logical groove that limiting frame center department, and the montant of logical inslot corresponds and runs through the lifter.
Further, the connection structure includes the limit frame that corresponds to install at the inboard bottom surface top of chassis, limit frame inboard corresponds the grafting has the cover frame, cover frame circumference lateral surface is provided with two side pieces relatively, and two side pieces all utilize the spring to be connected with the inboard bottom surface of chassis, and two springs all cup joint in limit frame surface, limit frame lateral surface is provided with the perpendicular groove that corresponds with two side pieces, and cover frame utilizes side piece and perpendicular groove sliding fit from top to bottom.
Further, the screw rods are vertically arranged on two sides of the bottom surface of the placement frame, the bottom ends of the screw rods are correspondingly inserted into the top of the sleeve frame, the top end of the sleeve frame is connected with the swivel by utilizing the annular edge in a rotating mode, and the swivel is spirally sleeved on the surface of the screw rods.
Further, the rack both sides face center department all is provided with the cross slot, and the rack utilizes the cross slot to correspond the joint and have interior pole, interior pole both ends all utilize the curb plate to be connected with square round bar, and two square round bars run through two cross slots respectively, and square round bar outside end screw cup joints the nut, and the nut medial surface corresponds the laminating with the rack lateral surface.
Further, the inner rod surface rotates and is sleeved with the rotating plates, the two rotating plates are symmetrically arranged by taking the central line of the underframe as an axis, the inner side ends of the two rotating plates are relatively arranged in parallel, the front side and the rear side of the outer side end of the rotating plate are connected with the two side plates by using torsion springs, and the rotating plates are positioned at the inner side of the placing groove.
Further, the structure of polishing includes two revolving racks that set up relatively, and two revolving racks top correspond to cup joint in lifter surface, and the board of polishing that two revolving racks bottom are connected corresponds and be in the standing groove inboard, and two revolving racks center departments all run through there is the arc pole, and arc pole both ends all utilize the elastic component to be connected with two revolving racks lateral surfaces respectively.
Further, the revolving rack bottom is provided with the breach, the lug of polishing board top surface center department corresponds the buckle inboard at the breach, the revolving rack bottom runs through and is provided with the draw-in lever, the draw-in lever corresponds the lug that runs through polishing board top surface, and polishing board utilizes draw-in lever and breach rotation to be connected.
Further, the circle center of the arc-shaped rod coincides with the central line of the lifting rod, and both ends of the arc-shaped rod are connected with limiting sheets.
The invention has the technical effects and advantages that:
1. according to the invention, by adjusting the relative distance between the bottom surface of the placing rack and the top surface of the limiting frame, aircraft parts with different diameters can be placed inside the placing grooves of the two placing racks, the bottom surfaces of the polishing plates of the two polishing structures are adjusted to be in the same horizontal plane, and the placing racks and the polishing plates of the two stations are matched to polish the aircraft parts with different diameters; through adjusting the relative distance between rack and the limit frame top surface, place the same aircraft part in two standing groove inboards, when the structure of polishing moves down and makes the board of polishing polish two aircraft parts, the board pressure of polishing that is in two aircraft part tops is different each other, thereby can carry out the processing of polishing of different degree to the same aircraft part according to the demand of polishing of difference, improves the efficiency of processing aircraft part of polishing in batches.
2. According to the invention, the square round rod is in sliding fit with the transverse groove, at the moment, the square round rod cannot rotate at the inner side of the transverse groove, when the aircraft part is correspondingly placed at the inner side of the placing groove, the relative distance between the two inner rods is adjusted, so that the placing frame is suitable for the aircraft parts with different lengths, when the two ends of the aircraft part are pressed down on the top surfaces of the two rotating plates, the outer ends of the rotating plates rotate on the surfaces of the inner rods due to the pressure of the aircraft part, the rotating plates twist the torsion springs in the rotating process, the torsion forces of the torsion springs are utilized to lift the two ends of the aircraft part, then the polishing plates at the bottom of the polishing structure are correspondingly pressed on the top surfaces of the aircraft part, the aircraft part is prevented from moving out of the inner side of the placing groove due to the pressure of the polishing plates, and the torsion forces of the two torsion springs are convenient to squeeze and limit the two ends of the aircraft part, so that the stability of the aircraft part at the inner side of the placing groove is further improved.
3. According to the invention, the rotating frames are pulled to rotate on the surface of the lifting rod, the angle between the two rotating frames is changed until the bottom surface of the polishing plate is attached to the top surface of the aircraft part, and the elastic force of the two elastic pieces enables the bottom ends of the two rotating frames to extrude the top surface of the aircraft part, so that the polishing plate connected with the aircraft part is tightly pressed on the top surface of the aircraft part; when the cylinder work makes two structures of polishing of lifter pulling move down in step, the board of polishing is at aircraft part top surface slip this moment, and the removal of board of polishing makes two revolving racks all slide at the arc pole surface, and the angle between two revolving racks increases gradually, and two revolving racks also increase gradually to the pressure of two elastic component respectively, and the elasticity of two elastic component makes the board of polishing also increase gradually to the pressure of aircraft part top surface, has improved the effect of polishing of board to the aircraft part.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the overall structure of a double-station grinding table for automatically processing aircraft parts according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a connection structure according to an embodiment of the present invention;
FIG. 3 is a schematic view of the overall structure of a rack according to an embodiment of the present invention;
FIG. 4 is a schematic illustration of the internal components of a carrier defining aircraft parts according to an embodiment of the invention;
FIG. 5 is an overall schematic of a sanding structure in accordance with embodiments of the present invention;
in the figure: 1. a chassis; 2. a placing rack; 3. a placement groove; 4. a lifting rod; 5. polishing the plate; 6. a cylinder; 7. a defining rack; 8. a vertical rod; 9. defining a frame; 10. a sleeve frame; 11. a side block; 12. a spring; 13. a vertical groove; 14. a screw; 15. a swivel; 16. a transverse groove; 17. an inner rod; 18. a side plate; 19. a square round bar; 20. a screw cap; 21. a rotating plate; 22. a torsion spring; 23. a rotating frame; 24. an arc-shaped rod; 25. an elastic member; 26. and (5) clamping the rod.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides a double-station grinding table for automatically processing airplane parts, which is shown in fig. 1 and comprises a bottom frame 1, wherein two placing frames 2 are oppositely arranged on the inner side of the bottom frame 1, two sides of the bottom surface of each placing frame 2 are connected with the bottom surface of the inner side of the bottom frame 1 by a connecting structure, and a placing groove 3 for placing airplane parts is arranged in the center of the top surface of each placing frame 2. Proper placing frame 2 is selected according to the length of the aircraft parts to be polished, placing the placing frame 2 on the inner side of the underframe 1 correspondingly, connecting the placing frame 2 with the underframe 1 correspondingly by utilizing a connecting structure, completing the installation of the placing frame 2, and then placing the aircraft parts on the inner side of the placing groove 3.
And the standing groove 3 tops of two racks 2 all are provided with the structure of polishing, and the structure of polishing rotates and cup joints in lifter 4 surface, and the structure of polishing bottom is connected and is polished board 5, and the board 5 of polishing corresponds and be located aircraft part top, both sides face center department around chassis 1 is run through respectively at lifter 4 both ends, cylinder 6 is all installed to side bottom around chassis 1, cylinder 6 top output corresponds and pastes in lifter 4 tip, chassis 1 inboard symmetry is provided with two and prescribes a limit to frame 7, and lifter 4 runs through the logical groove of prescribing a limit to frame 7 center department, and the montant 8 of logical inslot corresponds and run through lifter 4. The cylindric aircraft part corresponds and places at the inside back of standing groove 3, adjust the position of polishing structure bottom polishing board 5 for polishing board 5 bottom surface corresponds the laminating with the top surface of aircraft part, utilize the pressure of polishing board 5 and the circular recess of standing groove 3 to conveniently prescribe a limit to the aircraft part, start cylinder 6, when cylinder 6 output pulling lifter 4 reciprocates, lifter 4 utilizes montant 8 to reciprocate in prescribing a limit to the inboard of frame 7, utilize two montants 8 to guarantee lifter 4 vertical movement, avoid lifter 4 to rotate at the removal in-process, and avoid lifter 4 to produce the situation of skew in-process that reciprocates.
In fig. 1 and fig. 2, the connection structure includes a limiting frame 9 correspondingly installed at the top of the bottom surface of the inner side of the chassis 1, a sleeve frame 10 is correspondingly inserted in the inner side of the limiting frame 9, two side blocks 11 are oppositely arranged on the outer side surface of the circumference of the sleeve frame 10, the two side blocks 11 are connected with the bottom surface of the inner side of the chassis 1 by using springs 12, the two springs 12 are sleeved on the surface of the limiting frame 9, vertical grooves 13 corresponding to the two side blocks 11 are arranged on the outer side surface of the limiting frame 9, and the sleeve frame 10 is in up-down sliding fit with the vertical grooves 13 by using the side blocks 11. After the rack 2 is connected to the top of the connecting structure, the weight of the rack 2 and the pressure applied to the top of the aircraft part by the polishing plate 5 enable the rack 10 to move downwards on the inner side of the limiting frame 9, the rack 10 drives the side block 11 to move downwards on the inner side of the vertical groove 13 in the downward moving process, the side block 11 is used for extruding the spring 12, at the moment, the bottom of the rack 2 is under the action of the elastic force of the spring 12, the limiting frame 9 and the rack 10 are vertically connected, at the moment, the rack 2 is in a vertically downward moving state in the downward moving process, the elastic force of the spring 12 is used for guaranteeing that the polishing plate 5 and the top surface of the aircraft part generate pressure, and meanwhile, the lifting rod 4 moves downwards to enable the polishing plate 5 of the polishing structure to slide on the surface of the aircraft part, so that the polishing plate 5 can conveniently polish the top surface of the aircraft part, the aircraft part can rotate on the inner side of the placing groove 3, the contact surface of the cylindrical part and the bottom surface of the polishing plate 5 is changed, and the aircraft part can be comprehensively polished.
In fig. 1 to 3, screws 14 are vertically installed on two sides of the bottom surface of the placement frame 2, the bottom ends of the screws 14 are correspondingly inserted into the top of the sleeve frame 10, a swivel 15 is rotatably connected to the top end of the sleeve frame 10 by using a ring edge, and the swivel 15 is spirally sleeved on the surface of the screws 14. After the placing frames 2 are correspondingly inserted into the inner sides of the two sleeve frames 10 by the aid of the screws 14, the swivel 15 is rotated, the relative distance between the bottom surfaces of the placing frames 2 and the top surfaces of the limiting frames 9 can be conveniently adjusted by the spiral effect of the swivel 15 and the screws 14, aircraft parts with different diameters can be placed in the inner sides of the placing grooves 3 of the two placing frames 2, the bottom surfaces of the polishing plates 5 of the two polishing structures are adjusted to be in the same horizontal plane, and the two-station placing frames 2 and the polishing plates 5 are matched to polish the aircraft parts with different diameters.
Through adjusting the relative distance between rack 2 and the top surface of inject frame 9, place the same aircraft part in two standing grooves 3 inboard, adjust two polishing structure's polishing board 5 and correspond the suppression at aircraft part top, when polishing structure moves down and makes polishing board 5 polish two aircraft parts this moment, be in the polishing board 5 pressure each other different at two aircraft part tops, thereby can carry out the processing of polishing of different degree to the same aircraft part according to the demand of polishing of difference, improve the efficiency of processing aircraft part of polishing in batches.
In fig. 3 and fig. 4, the center of two side surfaces of the rack 2 is provided with a transverse groove 16, the rack 2 is correspondingly clamped with an inner rod 17 by using the transverse groove 16, two ends of the inner rod 17 are respectively connected with square round rods 19 by using side plates 18, the two square round rods 19 respectively penetrate through the two transverse grooves 16, the outer side ends of the square round rods 19 are spirally sleeved with nuts 20, and the inner side surfaces of the nuts 20 are correspondingly attached to the outer side surfaces of the rack 2. After the aircraft parts are correspondingly placed inside the placing groove 3, friction force between the polishing plate 5 and the top surface of the aircraft parts easily causes the aircraft parts to slide inside the placing groove 3, the screw cap 20 is unscrewed, when the inner rod 17 is pushed to move inside the placing groove 3, the inner rod 17 drives the square round rod 19 to move inside the transverse groove 16 by using the side plate 18 until the two inner rods 17 are respectively positioned at two ends of the aircraft parts, the screw cap 20 is screwed, and the limitation of the inner rods 17 is completed. When the polishing plate 5 polishes the top surface of the aircraft part, the two inner rods 17 are utilized to limit the aircraft part, the two inner rods 17 are used for limiting the two ends of the aircraft part respectively, friction between the polishing plate 5 and the aircraft part is avoided, the aircraft part moves inside the placing groove 3, and stability of the aircraft part in the polishing process is guaranteed.
In fig. 1, 3 and 4, the surface of the inner rod 17 is rotatably sleeved with two rotating plates 21, the two rotating plates 21 are symmetrically arranged with the central line of the chassis 1 as an axis, the inner ends of the two rotating plates 21 are relatively parallel, the front side and the rear side of the outer end of the rotating plate 21 are connected with the two side plates 18 by torsion springs 22, and the rotating plates 21 are positioned at the inner side of the placing groove 3. Because square round bar 19 and transverse groove 16 sliding fit, square round bar 19 can't rotate in transverse groove 16 inboard this moment, when correspondingly placing the aircraft part in the standing groove 3 inboard, adjust the relative distance between two interior poles 17 and make rack 2 adapter in the aircraft part of different length, when two rotor plate 21 tops surfaces are all pressed down at the aircraft part both ends, the pressure of aircraft part makes rotor plate 21 outside end rotate on interior pole 17 surfaces, rotor plate 21 is to torsion spring 22 in the rotation in-process, utilize torsion spring 22's torsional force so to carry out the lifting to aircraft part both ends, then will polish the board 5 of structure bottom and correspond the suppression in aircraft part top surface, utilize the pressure of polishing board 5 to avoid the aircraft part to follow the standing groove 3 inboard and shift out, and the torsional force of two torsion springs 22 conveniently extrudees the aircraft part both ends and prescribe a limit, further improve the stability of aircraft part in the standing groove 3 inboard.
In fig. 1 and 5, the polishing structure includes two revolving racks 23 that set up relatively, and two revolving racks 23 top corresponds to cup joint in lifter 4 surface, and the polishing board 5 that two revolving racks 23 bottom are connected is corresponding to be in standing groove 3 inboard, and two revolving racks 23 center department all runs through has arc pole 24, and arc pole 24 both ends all utilize elastic component 25 to be connected with two revolving racks 23 lateral surfaces respectively. The center of the arc-shaped rod 24 coincides with the center line of the lifting rod 4, and both ends of the arc-shaped rod 24 are connected with limited pieces. When the polishing plate 5 is correspondingly pressed at the top of the aircraft part, the rotating frames 23 are pulled to rotate on the surface of the lifting rod 4, the angle between the two rotating frames 23 is changed until the bottom surface of the polishing plate 5 is attached to the top surface of the aircraft part, the elastic force of the two elastic pieces 25 enables the bottom ends of the two rotating frames 23 to extrude the top surface of the aircraft part, and then the polishing plate 5 connected with the aircraft part is tightly pressed on the top surface of the aircraft part. When the cylinder 6 works so that the lifting rod 4 pulls the two polishing structures to move downwards synchronously, the polishing plate 5 slides on the top surface of the aircraft part at the moment, the two rotating frames 23 slide on the surface of the arc-shaped rod 24 due to the movement of the polishing plate 5, the angle between the two rotating frames 23 is gradually increased, the pressure of the two rotating frames 23 to the two elastic pieces 25 is also gradually increased, the pressure of the polishing plate 5 to the top surface of the aircraft part is also gradually increased due to the elastic force of the two elastic pieces 25, and the polishing effect of the polishing plate 5 to the aircraft part is improved.
In fig. 1 and 5, a notch is provided at the bottom end of the rotating frame 23, a bump at the center of the top surface of the polishing plate 5 is correspondingly buckled at the inner side of the notch, a clamping rod 26 is provided at the bottom end of the rotating frame 23 in a penetrating manner, the clamping rod 26 correspondingly penetrates through the bump at the top surface of the polishing plate 5, and the polishing plate 5 is rotationally connected with the notch by using the clamping rod 26. When the polishing plate 5 slides on the top surface of the aircraft part, as the rotating frame 23 rotates, the protruding blocks at the top of the polishing plate 5 also rotate on the inner sides of the gaps by using the clamping rods 26, and at the moment, the elastic force of the elastic piece 25 always presses on the top surface of the aircraft part vertically through the polishing plate 5 at the bottom of the rotating frame 23, so that the situation that the bottom surface of the polishing plate 5 is separated from the aircraft part or deviates due to the rotation of the rotating frame 23 is avoided, and the polishing plate 5 is ensured to continuously polish the aircraft part.
The working principle of the invention is as follows:
referring to fig. 1 to 5 of the drawings, after the placing frames 2 are correspondingly inserted into the inner sides of the two sleeve frames 10 by using the screw rods 14, the rotating ring 15 is rotated, the spiral effect of the rotating ring 15 and the screw rods 14 is convenient for adjusting the relative distance between the bottom surface of the placing frame 2 and the top surface of the limiting frame 9, aircraft parts with different diameters can be placed in the inner sides of the placing grooves 3 of the two placing frames 2, the bottom surfaces of the polishing plates 5 with two polishing structures are adjusted to be in the same horizontal plane, and the placing frames 2 and the polishing plates 5 with two stations are matched to polish the aircraft parts with different diameters.
Through adjusting the relative distance between rack 2 and the top surface of prescribing a limit to frame 9, place the same aircraft part in two standing grooves 3 inboard, adjust two polishing structure's polishing board 5 and correspond the suppression at aircraft part top, when polishing structure moves down so that polishing board 5 polishes two aircraft parts this moment, the polishing board 5 pressure at two aircraft part tops is mutually different, thereby can carry out the processing of polishing of different degree to same aircraft part according to the demand of polishing of difference.
The cylindric aircraft part corresponds and places at the inside back of standing groove 3, adjust the position of polishing structure bottom polishing board 5 for polishing board 5 bottom surface corresponds the laminating with the top surface of aircraft part, utilize the pressure of polishing board 5 and the circular recess of standing groove 3 to conveniently prescribe a limit to the aircraft part, start cylinder 6, when cylinder 6 output pulling lifter 4 reciprocates, lifter 4 utilizes montant 8 to reciprocate in prescribing a limit to the inboard of frame 7, utilize two montants 8 to guarantee lifter 4 vertical movement, avoid lifter 4 to rotate at the removal in-process, and avoid lifter 4 to produce the situation of skew in-process that reciprocates.
When the position of the polishing plate 5 is adjusted, the rotating frames 23 are pulled to rotate on the surface of the lifting rod 4, the angle between the two rotating frames 23 is changed until the bottom surface of the polishing plate 5 is attached to the top surface of the aircraft part, the elastic force of the two elastic pieces 25 enables the bottom ends of the two rotating frames 23 to extrude the top surface of the aircraft part, and then the polishing plate 5 connected with the aircraft part is tightly pressed on the top surface of the aircraft part. When the cylinder 6 works so that the lifting rod 4 pulls the two polishing structures to move downwards synchronously, the polishing plate 5 slides on the top surface of the aircraft part at the moment, the two rotating frames 23 slide on the surface of the arc-shaped rod 24 due to the movement of the polishing plate 5, the angle between the two rotating frames 23 is gradually increased, the pressure of the two rotating frames 23 to the two elastic pieces 25 is also gradually increased, the pressure of the polishing plate 5 to the top surface of the aircraft part is also gradually increased due to the elastic force of the two elastic pieces 25, and the polishing effect of the polishing plate 5 to the aircraft part is improved.
Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims (5)

1. Double-station grinding table for automatically processing airplane parts, comprising an underframe (1), and is characterized in that: the device is characterized in that two placing racks (2) are oppositely arranged on the inner side of the bottom surface of the bottom frame (1), two sides of the bottom surface of the placing racks (2) are connected with the inner bottom surface of the bottom frame (1) through connecting structures, placing grooves (3) for placing aircraft parts are formed in the centers of the top surfaces of the placing racks (2), polishing structures are arranged on the tops of the placing grooves (3) of the two placing racks (2), the polishing structures are rotationally sleeved on the surfaces of lifting rods (4), polishing plates (5) are connected to the bottoms of the polishing structures, the polishing plates (5) are correspondingly arranged on the tops of the aircraft parts, two ends of the lifting rods (4) respectively penetrate through the centers of the front side surface and the rear side surface of the bottom frame (1), air cylinders (6) are respectively arranged at the bottoms of the front side surface and the rear side surface of the bottom frame (1), two limiting frames (7) are symmetrically arranged on the inner sides of the bottom frame (1), the lifting rods (4) penetrate through the through grooves in the centers of the limiting frames (7), and vertical rods (8) on the inner sides of the through grooves correspondingly penetrate through the lifting rods (4);
the connecting structure comprises a limiting frame (9) correspondingly arranged at the top of the bottom surface of the inner side of the underframe (1), a sleeve frame (10) is correspondingly inserted into the inner side of the limiting frame (9), two side blocks (11) are oppositely arranged on the outer side surface of the circumference of the sleeve frame (10), the two side blocks (11) are connected with the bottom surface of the inner side of the underframe (1) by using springs (12), the two springs (12) are sleeved on the surface of the limiting frame (9), vertical grooves (13) corresponding to the two side blocks (11) are formed in the outer side surface of the limiting frame (9), and the sleeve frame (10) is in vertical sliding fit with the vertical grooves (13) by using the side blocks (11);
screw rods (14) are vertically arranged on two sides of the bottom surface of the placement frame (2), the bottom ends of the screw rods (14) are correspondingly inserted into the top of the sleeve frame (10), the top end of the sleeve frame (10) is rotationally connected with a swivel (15) by using a ring edge, and the swivel (15) is spirally sleeved on the surface of the screw rods (14);
the structure of polishing includes two revolving racks (23) that set up relatively, and two revolving racks (23) top corresponds to cup joint in lifter (4) surface, and the board of polishing (5) that two revolving racks (23) bottom are connected is corresponding to be in standing groove (3) inboard, and arc pole (24) have all been run through in two revolving racks (23) center department, and arc pole (24) both ends all utilize elastic component (25) to be connected with two revolving racks (23) lateral surface respectively.
2. The duplex sanding station for automated processing of aircraft parts according to claim 1, wherein:
the utility model discloses a rack, including rack (2), lateral surface center department all is provided with transverse groove (16), and rack (2) utilize transverse groove (16) to correspond the joint has interior pole (17), interior pole (17) both ends all utilize curb plate (18) to be connected with square round bar (19), and two square round bar (19) run through two transverse groove (16) respectively, and nut (20) have been cup jointed to square round bar (19) outside end spiral, and nut (20) medial surface and rack (2) lateral surface face are laminated.
3. The duplex sanding station for automated processing of aircraft parts according to claim 2, wherein:
the surface of the inner rod (17) is rotatably sleeved with rotating plates (21), the two rotating plates (21) are symmetrically arranged by taking the central line of the underframe (1) as an axis, the inner side ends of the two rotating plates (21) are relatively arranged in parallel, the front side and the rear side of the outer side end of each rotating plate (21) are connected with the two side plates (18) by torsion springs (22), and the rotating plates (21) are positioned at the inner side of the placing groove (3).
4. A duplex sanding station for automated processing of aircraft parts according to claim 3, wherein:
the polishing device is characterized in that a notch is formed in the bottom end of the rotating frame (23), a bump at the center of the top surface of the polishing plate (5) is correspondingly buckled on the inner side of the notch, a clamping rod (26) is arranged at the bottom end of the rotating frame (23) in a penetrating mode, the clamping rod (26) correspondingly penetrates through the bump on the top surface of the polishing plate (5), and the polishing plate (5) is rotationally connected with the notch through the clamping rod (26).
5. A duplex sanding station for automated processing of aircraft parts according to claim 3, wherein:
the circle center of the arc-shaped rod (24) coincides with the central line of the lifting rod (4), and both ends of the arc-shaped rod (24) are connected with limiting sheets.
CN202310647742.2A 2023-06-02 2023-06-02 Duplex position of automatic change processing aircraft spare part grinds platform Active CN116572092B (en)

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