CN106001376A - Detaching device of loosened rivet on edge of aircraft laminate reinforcing structure - Google Patents
Detaching device of loosened rivet on edge of aircraft laminate reinforcing structure Download PDFInfo
- Publication number
- CN106001376A CN106001376A CN201610663862.1A CN201610663862A CN106001376A CN 106001376 A CN106001376 A CN 106001376A CN 201610663862 A CN201610663862 A CN 201610663862A CN 106001376 A CN106001376 A CN 106001376A
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- Prior art keywords
- rivet
- aircraft
- loosens
- lock lever
- reinforcement structure
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
- B21J15/50—Removing or cutting devices for rivets
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Press Drives And Press Lines (AREA)
- Automatic Assembly (AREA)
Abstract
A detaching device of a loosened rivet on the edge of an aircraft laminate reinforcing structure comprises a lower support, an upper support, a rivet supporting device and a locking rod, wherein the lower support is provided with an upper clamping device, the upper support is provided with a lower clamping device which is matched with the upper clamping device and used for horizontally clamping a panel, the rivet supporting device is vertically arranged on the lower support, the upper end of the rivet supporting device is provided with an anvil making contact with a pier head at the lower end of the rivet, and the locking rod is vertically arranged on the upper support, is coaxial with the rivet supporting device, and is internally and coaxially provided with a drill hole matched with a drill bit. In the use process, the anvil on the rivet supporting device abuts against the lower portion of the pier head of the loosened rivet, the locking rod is aligned with the upper portion of a process head of the loosened rivet, and then the panel of the aircraft laminate reinforcing structure is clamped by the upper clamping device and the lower clamping device. The drill bit drills the rivet along the drill hole till the rivet is completely detached. The rivet detaching efficiency is improved, the aperture of a rivet installation hole can not become larger, and no potential hazards are brought to subsequence rivet installation.
Description
Technical field
The present invention relates to a kind of aircraft stacking reinforcement structure edge and loosen rivet removal device.
Background technology
There are many stacking reinforcement structures on Boeing 737 airplane, typically formed by two-layer or multilamellar aluminium sheet, composite board riveting.Awing there is the duties such as vibrations, rain erosion so that loosening and then causing structure to be peeled off often occur in this region rivet, and affects flight safety due to this region.Not yet there are special tooling device and technique at present to process the situation that loosening occurs in this region rivet, how to be removed by its working experience and skill by worker, owing in drilling process, drill edge drives rivet to rotate around installing hole, often make rivet installing hole aperture become big, install for follow-up rivet and airborne vehicle brings safely hidden danger.
Summary of the invention
The present invention is in order to overcome the deficiency of above technology, it is provided that a kind of aircraft stacking reinforcement structure edge that improves loosens the machine stacking reinforcement structure edge of rivet removal work efficiency and precision and loosens rivet removal device.
The present invention overcomes its technical problem be the technical scheme is that
A kind of aircraft stacking reinforcement structure edge loosens rivet removal device, including:
Lower carriage, it is provided with clamping device；
Upper bracket, is arranged at the upper end of lower carriage, and it is provided with and matches for the lower fixture by sheet material horizontal-clamping with upper clamping device；
Rivet support device, it is vertically arranged on lower carriage, and its upper end is provided with the anvil block contacted with pier nose portion, rivet lower end；And
Check lock lever, it is vertically arranged on upper bracket, and with rivet support device same axis, described check lock lever is axially inside provided with the boring matched with drill bit.
Above-mentioned upper clamping device includes vertically being combined on the clamping screw I of four edges of upper bracket, is arranged at the rubber blanket I of clamping screw I lower end and is arranged at the clamping knob wheel I on clamping screw I top, and described lower fixture includes vertically being combined on the clamping screw II of four edges of lower carriage, is arranged at the rubber blanket II on clamping screw II top and is arranged at clamping screw II and pushes up the clamping knob wheel II of lower end.
Above-mentioned check lock lever lower end edge circumferencial direction is arranged at intervals with some locking tooth sheets, and the internal diameter between each described locking tooth sheet is more than the bolt diameter of rivet, and is less than the technique head diameter of rivet.
In order to easy to operate, the head end of above-mentioned check lock lever is provided with check lock lever handwheel.
For the ease of centering, above-mentioned anvil block is provided with the cross recess that the pier nose with rivet matches.
For the ease of being adjusted at the rivet loosened of response, along front and back and some check lock lever chutes being crisscross arranged of left and right directions on above-mentioned upper bracket, along front and back and some bulb chutes being crisscross arranged of left and right directions on described lower carriage, described check lock lever chute is arranged at intervals with some screws, described check lock lever is combined in corresponding screw by the end of thread, the bottom of described rivet support device is provided with bulb, and described bulb is placed in bulb chute.
For the ease of movement, above-mentioned rivet support device includes the interior bar that outer loop bar and activity are plugged in outer loop bar, it is provided with spring between described interior bar and outer loop bar, described interior bar lower end is provided with and prevents its limit baffle ring departed from from outer loop bar, the head end of described interior bar is connected with anvil block, and the lower end of described outer loop bar is connected with bulb.
For the ease of being adjusted at the rivet loosened of response, also include for driving the upper bracket carriage drive mechanism relative to lower carriage slide anteroposterior.
Above-mentioned carriage drive mechanism is included being arranged at the dovetail groove of lower carriage upper end, is arranged at the dovetail guide of upper bracket lower end, is arranged at the tooth bar of dovetail guide lower end along the length direction of dovetail guide, is rotated the gear being installed on lower carriage by gear drive rod, the head end of described gear drive rod is provided with gear and drives handwheel, upper bracket is slided by dovetail guide in the dovetail groove being plugged in lower carriage, and rack and pinion is meshed.
In order to increase adjustment stroke, said gear has two groups, and two gears are rotated by gear drive rod respectively and are installed on two ends before and after lower carriage, and two gears are meshed with tooth bar respectively.
The invention has the beneficial effects as follows: during use, the anvil block on rivet support device is made to withstand on below the pier nose of loosening rivet, check lock lever is also directed at the top of the technique head of loosening rivet, afterwards the sheet material of aircraft stacking reinforcement structure is clamped by upper clamping device and lower fixture.Drill bit is along holing rivet drilling, until it is removed completely.Improve the dismounting efficiency of rivet, rivet installing hole aperture will not become big, installs to follow-up rivet and bring hidden danger.
Accompanying drawing explanation
Fig. 1 is the stereochemical structure explosive view of the present invention；
Fig. 2 is the stereoscopic mechanism schematic diagram of the present invention；
Fig. 3 is the structural representation of the locking tooth sheet of the present invention；
Fig. 4 is the structural representation of the anvil block of the present invention；
In figure, 1. lower carriage
2. upper bracket 3. dovetail guide 4. dovetail groove 5. clamping screw I 6. rubber blanket I 7. clamping knob wheel I 8. clamping screw II 9. clamping knob wheel II
10. rubber blanket II 11. tooth bar 12. gear 13. gear drive rod 14. gear drives handwheel
In the 15. check lock lever chute 16. screw 17. bulb chute 18. outer loop bars 22. of check lock lever 19. check lock lever handwheel 20. drill bit 21., bar 23. bulb 24. limit baffle ring 25. anvil block 26. cross recess 27. locks tooth sheet 28. sheet material.
Detailed description of the invention
Below in conjunction with the accompanying drawings 1, accompanying drawing 2, accompanying drawing 3, the present invention will be further described for accompanying drawing 4.
As shown in Figures 1 and 2, a kind of aircraft stacking reinforcement structure edge loosens rivet removal device, including: lower carriage 1, it is provided with clamping device；Upper bracket 2, is arranged at the upper end of lower carriage 1, and it is provided with and matches for the lower fixture by sheet material 28 horizontal-clamping with upper clamping device；Rivet support device, it is vertically arranged on lower carriage 1, and its upper end is provided with the anvil block 25 contacted with pier nose portion, rivet lower end；And check lock lever 18, it is vertically arranged on upper bracket 2, and with rivet support device same axis, check lock lever 18 is axially inside provided with the boring matched with drill bit 20.During use, make the anvil block 25 on rivet support device withstand on below the pier nose of loosening rivet, check lock lever 18 is also directed at the top of the technique head of loosening rivet, afterwards the sheet material 28 of aircraft stacking reinforcement structure is clamped by upper clamping device and lower fixture.Drill bit 20 is along holing rivet drilling, until it is removed completely.Improve the dismounting efficiency of rivet, rivet installing hole aperture will not become big, installs to follow-up rivet and bring hidden danger.
Further, upper clamping device includes vertically being combined on the clamping screw I 5 of 2 four edges of upper bracket, being arranged at the rubber blanket I 6 of clamping screw I 5 lower end and be arranged at the clamping knob wheel I 7 on clamping screw I 5 top, and lower fixture includes vertically being combined on the clamping screw II 8 of 1 four edges of lower carriage, being arranged at the rubber blanket II on clamping screw II 8 top
10 and be arranged at clamping screw II 8 top lower end clamping knob wheel II 9.Clamping screw I 5 and clamping screw II 8 is driven to rotate respectively by rotating clamping knob wheel I 7 and clamping knob wheel II 9, finally realize rubber blanket I 6 to contact with upper plane and the lower plane of sheet material 28 respectively with rubber blanket II 10, it is achieved fixed by sheet material 28 horizontal-clamping.Check lock lever 18 lower end edge circumferencial direction can be arranged at intervals with some locking tooth sheets 27, and the internal diameter between each locking tooth sheet 27 is more than the bolt diameter of rivet, and is less than the technique head diameter of rivet.Therefore the technique head that each locking tooth sheet 27 can be wrapped in rivet is peripheral, it is achieved fixing of circumferencial direction, prevents drill bit 20 when boring, and loosening rivet is followed drill bit 20 and rotated.The head end of check lock lever 18 can be provided with check lock lever handwheel 19.Drive check lock lever 18 to rotate by check lock lever handwheel 19 the most convenient, improve the convenience of operation.Anvil block 25 can be provided with the cross recess 26 that the pier nose with rivet matches, need the pier nose of the rivet loosened removed to be placed in the cross recess 26 of anvil block 25, can preferably realize centering, improve the convenience of use.
Further, along front and back and some check lock lever chutes 15 being crisscross arranged of left and right directions on upper bracket 2, along front and back and some bulb chutes 17 being crisscross arranged of left and right directions on lower carriage 1, check lock lever chute 15 is arranged at intervals with some screws 16, check lock lever 18 is combined in corresponding screw 16 by the end of thread, the bottom of rivet support device is provided with bulb 23, and bulb 23 is placed in bulb chute 17.Rivet support device can slide at the rivet quickly navigating to need drilling to remove by bulb 23 in bulb chute 17, and check lock lever 18 can realize in corresponding screw 16 quickly positioning by screwing in, and improve efficiency.Rivet support device includes the interior bar 22 that outer loop bar 21 and activity are plugged in outer loop bar 21, it is provided with spring between interior bar 22 and outer loop bar 21, interior bar 22 lower end is provided with and prevents its limit baffle ring 24 departed from from outer loop bar 21, the head end of interior bar 22 is connected with anvil block 25, and the lower end of outer loop bar 21 is connected with bulb 23.When needs are mobile, being pulled downward on by interior bar 22, make spring-compressed, anvil block 25 does not contacts with the pier nose of rivet simultaneously, can be moved easily, and when moving to specify position, unclamps interior bar 22, and interior bar 22 is pushed to anvil block 25 and contacts with the pier nose of rivet by spring.Also include the carriage drive mechanism for driving relative lower carriage 1 slide anteroposterior of upper bracket 2, position before and after upper bracket 2 and lower carriage 1, the progressive convenience that improve regulation can be adjusted by carriage drive mechanism.Further, carriage drive mechanism can be following structure, it is included being arranged at the dovetail groove 4 of lower carriage 1 upper end, is arranged at the dovetail guide 3 of upper bracket 2 lower end, is arranged at the tooth bar 11 of dovetail guide 3 lower end along the length direction of dovetail guide 3, is rotated the gear 12 being installed on lower carriage 1 by gear drive rod 13, the head end of gear drive rod 13 is provided with gear and drives handwheel 14, upper bracket 2 is slided by dovetail guide 3 in the dovetail groove 4 being plugged in lower carriage 1, and tooth bar 11 is meshed with gear 12.Driving handwheel 14 driving gear drives bar 13 to rotate by gear, so that gear 12 rotates, gear 12 is rotated and makes upper bracket 2 be slided along the dovetail groove 4 of lower carriage 1 by dovetail guide 3.Gear 12 can have two groups, and two gears 12 are rotated by gear drive rod 13 respectively and are installed on two ends before and after lower carriage 1, and two gears 12 are meshed with tooth bar 11 respectively.So can improve the stroke of the slip of tooth bar 11, it is to avoid gear 12 departs from tooth bar 11.
Claims (10)
1. an aircraft stacking reinforcement structure edge loosens rivet removal device, it is characterised in that including:
Lower carriage (1), it is provided with clamping device；
Upper bracket (2), is arranged at the upper end of lower carriage (1), and it is provided with and matches for the lower fixture by sheet material (28) horizontal-clamping with upper clamping device；
Rivet support device, it is vertically arranged on lower carriage (1), and its upper end is provided with the anvil block (25) contacted with pier nose portion, rivet lower end；And
Check lock lever (18), it is vertically arranged on upper bracket (2), and with rivet support device same axis, described check lock lever (18) is axially inside provided with the boring matched with drill bit (20).
Aircraft stacking reinforcement structure edge the most according to claim 1 loosens rivet removal device, it is characterized in that: described upper clamping device includes vertically being combined on the clamping screw I (5) of (2) four edges of upper bracket, the rubber blanket I (6) being arranged at clamping screw I (5) lower end and the clamping knob being arranged at clamping screw I (5) top wheel I (7), described lower fixture includes the clamping screw II (8) being vertically combined on (1) four edge of lower carriage, it is arranged at the rubber blanket II (10) on clamping screw II (8) top and is arranged at the clamping knob wheel II (9) of lower end, clamping screw II (8) top.
Aircraft stacking reinforcement structure edge the most according to claim 1 loosens rivet removal device, it is characterized in that: described check lock lever (18) lower end edge circumferencial direction is arranged at intervals with some lockings tooth sheet (27), internal diameter between each described locking tooth sheet (27) is more than the bolt diameter of rivet, and is less than the technique head diameter of rivet.
Aircraft stacking reinforcement structure edge the most according to claim 1 loosens rivet removal device, it is characterised in that: the head end of described check lock lever (18) is provided with check lock lever handwheel (19).
Aircraft stacking reinforcement structure edge the most according to claim 1 loosens rivet removal device, it is characterised in that: described anvil block (25) is provided with the cross recess (26) that the pier nose with rivet matches.
Aircraft stacking reinforcement structure edge the most as claimed in any of claims 1 to 5 loosens rivet removal device, it is characterized in that: described upper bracket (2) is upper along front and back and some check lock lever chutes (15) being crisscross arranged of left and right directions, described lower carriage (1) is upper along front and back and some bulb chutes (17) being crisscross arranged of left and right directions, described check lock lever chute (15) is arranged at intervals with some screws (16), described check lock lever (18) is combined in corresponding screw (16) by the end of thread, the bottom of described rivet support device is provided with bulb (23), described bulb (23) is placed in bulb chute (17).
Aircraft stacking reinforcement structure edge the most according to claim 6 loosens rivet removal device, it is characterized in that: described rivet support device includes the interior bar (22) that outer loop bar (21) and activity are plugged in outer loop bar (21), it is provided with spring between described interior bar (22) and outer loop bar (21), described interior bar (22) lower end is provided with and prevents its limit baffle ring (24) departed from from outer loop bar (21), the head end of described interior bar (22) is connected with anvil block (25), and the lower end of described outer loop bar (21) is connected with bulb (23).
Aircraft stacking reinforcement structure edge the most as claimed in any of claims 1 to 5 loosens rivet removal device, it is characterised in that: also include the carriage drive mechanism for driving upper bracket (2) lower carriage (1) slide anteroposterior relatively.
Aircraft stacking reinforcement structure edge the most according to claim 8 loosens rivet removal device, it is characterized in that: described carriage drive mechanism includes being arranged at the dovetail groove (4) of lower carriage (1) upper end, it is arranged at the dovetail guide (3) of upper bracket (2) lower end, length direction along dovetail guide (3) is arranged at the tooth bar (11) of dovetail guide (3) lower end, the gear (12) being installed on lower carriage (1) is rotated by gear drive rod (13), the head end of described gear drive rod (13) is provided with gear and drives handwheel (14), upper bracket (2) slides in the dovetail groove (4) being plugged in lower carriage (1) by dovetail guide (3), and tooth bar (11) is meshed with gear (12).
Aircraft stacking reinforcement structure edge the most according to claim 9 loosens rivet removal device, it is characterized in that: described gear (12) has two groups, two gears (12) are rotated by gear drive rod (13) respectively and are installed on two ends before and after lower carriage (1), and two gears (12) are meshed with tooth bar (11) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663862.1A CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663862.1A CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
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| Publication Number | Publication Date |
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| CN106001376A true CN106001376A (en) | 2016-10-12 |
| CN106001376B CN106001376B (en) | 2017-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610663862.1A Active CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
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| CN (1) | CN106001376B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107321898A (en) * | 2017-09-01 | 2017-11-07 | 山东太古飞机工程有限公司 | A kind of aircraft loosens tubular rivet and removes device |
| CN107377691A (en) * | 2017-09-01 | 2017-11-24 | 山东太古飞机工程有限公司 | A kind of quick bending line-plotting device for aircraft sheet metal |
| CN107738223A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing |
| CN107738759A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | Aircraft engine radome fairing is removed and installation assistor |
| CN108941428A (en) * | 2018-07-28 | 2018-12-07 | 江西省东龙实业股份有限公司 | A kind of fast-dialing wheel rivet punching |
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| CN103878287A (en) * | 2014-02-21 | 2014-06-25 | 山东太古飞机工程有限公司 | Auxiliary remover for rivet with head |
| CN205111336U (en) * | 2015-11-11 | 2016-03-30 | 湖北大运汽车有限公司 | Drilling frock clamp assembly of rotatory many orientation locking |
| CN205851778U (en) * | 2016-08-15 | 2017-01-04 | 山东太古飞机工程有限公司 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
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| EP1072338A1 (en) * | 1999-07-19 | 2001-01-31 | Alstom | Rivet removing tool and process |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107321898A (en) * | 2017-09-01 | 2017-11-07 | 山东太古飞机工程有限公司 | A kind of aircraft loosens tubular rivet and removes device |
| CN107377691A (en) * | 2017-09-01 | 2017-11-24 | 山东太古飞机工程有限公司 | A kind of quick bending line-plotting device for aircraft sheet metal |
| CN107738223A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing |
| CN107738759A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | Aircraft engine radome fairing is removed and installation assistor |
| CN107738223B (en) * | 2017-11-13 | 2023-11-10 | 山东太古飞机工程有限公司 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
| CN107738759B (en) * | 2017-11-13 | 2023-12-01 | 山东太古飞机工程有限公司 | Booster for dismounting and mounting aircraft engine fairing |
| CN108941428A (en) * | 2018-07-28 | 2018-12-07 | 江西省东龙实业股份有限公司 | A kind of fast-dialing wheel rivet punching |
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|---|---|
| CN106001376B (en) | 2017-10-24 |
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