CN210996856U - Bolt hole damage removing mechanism - Google Patents
Bolt hole damage removing mechanism Download PDFInfo
- Publication number
- CN210996856U CN210996856U CN201921598534.3U CN201921598534U CN210996856U CN 210996856 U CN210996856 U CN 210996856U CN 201921598534 U CN201921598534 U CN 201921598534U CN 210996856 U CN210996856 U CN 210996856U
- Authority
- CN
- China
- Prior art keywords
- hole
- guide
- bolt hole
- damage
- bolt
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000000149 penetrating effect Effects 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 abstract description 8
- 238000003780 insertion Methods 0.000 abstract description 3
- 230000037431 insertion Effects 0.000 abstract description 3
- 230000010405 clearance mechanism Effects 0.000 description 15
- 238000012545 processing Methods 0.000 description 6
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
Images
Landscapes
- Connection Of Plates (AREA)
Abstract
The utility model relates to the technical field of airplanes, and provides a bolt hole damage clearing mechanism which is used for clearing bolt hole damage of an airplane structural member and comprises a fixing member, a guiding member and a reamer, wherein the fixing member is used for being fixed on the airplane structural member, the fixing member is provided with a guiding hole, and the guiding hole is arranged opposite to a damaged bolt hole of the airplane structural member; the guide piece is arranged on the fixing piece, a guide hole is formed in the guide piece, the guide hole and the guide hole are coaxially arranged, and the diameter of the guide hole is smaller than or equal to that of the guide hole; the reamer is rotatably arranged in the guide hole in a penetrating mode so as to perform reaming treatment on the damaged bolt hole by the part of the reamer arranged in the damaged bolt hole in the penetrating mode. Because the setting of mounting and guide piece can guarantee that the reamer can not take place the skew in the position that the reaming in-process removed, and the disect insertion just can begin the reaming and handle in the guiding hole, need not too much artificial adjustment to the damage has been accelerated and has been clear away efficiency.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to a bolt hole damage clearance mechanism.
Background
The integral structure of the airplane is assembled by structural components in various shapes, and most of the structural components are connected by bolts. The bolts pass through the bolt holes on a plurality of structural components at the same time, and then the nuts are screwed down, so that the structural components are tightly connected together. These structural members and bolts are subjected to various stresses during the operation of the aircraft to cause damage, and therefore various damages such as corrosion, deformation, cracks and the like of the bolt holes are often found during the maintenance of the aircraft. If the damage of the bolt hole is not processed in time, the damage can be further enlarged, and the damage or the failure of a structural part can be caused by serious damage of the bolt hole, so that the performance and the operation safety of the airplane are influenced.
According to the maintenance scheme provided by the aircraft manufacturer, after finding out the damage of the bolt hole, the high-frequency eddy current instrument is required to determine the damage conditions such as the position of the damage, the depth of the damage and the like. And then, eccentrically reaming the bolt hole by using a reamer with the diameter larger than the diameter of the bolt by 1/32 inches, wherein the eccentric cutting position of the reamer is the damaged position of the bolt hole. And (4) after eccentric reaming of the reamer, determining the damage removal condition by using a high-frequency eddy meter, and checking whether the damage of the bolt hole is removed completely. If not, a further 1/32 inch larger reamer than the previous reamer is required to re-eccentrically ream the bolt hole until the bolt hole damage is completely removed or the limit of the allowable eccentric reaming diameter of the bolt hole is reached. But when the reamer is used for reaming, the efficiency is low because no corresponding auxiliary tool is arranged, and deviation is easy to occur in reaming.
Disclosure of Invention
It is a primary object of the present disclosure to overcome at least one of the above-mentioned deficiencies of the prior art and to provide a bolt hole damage clearing mechanism.
The utility model provides a bolt hole damage clearance mechanism for clear away the bolt hole damage of aircraft structure, bolt hole damage clearance mechanism includes:
the fixing piece is used for being fixed on the aircraft structural part, a guide hole is formed in the fixing piece, and the guide hole is arranged opposite to the damaged bolt hole of the aircraft structural part;
the guide piece is arranged on the fixing piece, a guide hole is formed in the guide piece, the guide hole and the guide hole are coaxially arranged, and the diameter of the guide hole is smaller than or equal to that of the guide hole;
the reamer is rotatably arranged in the guide hole in a penetrating mode and used for carrying out reaming treatment on the damaged bolt hole through the part of the reamer arranged in the damaged bolt hole in a penetrating mode.
In an embodiment of the present invention, the diameter of the guide hole is equal to the diameter of the reamer, and the diameter of the guide hole is larger than the original diameter of the damaged bolt hole.
In an embodiment of the present invention, a preset distance is provided between the center line of the guide hole and the center line of the damaged bolt hole, and the center line of the guide hole is located on one side of the center line of the damaged bolt hole close to the damaged position of the damaged bolt hole.
The utility model discloses an in the embodiment, be provided with the fixed orifices on the mounting, the bolt hole on fixed orifices and the aircraft structure sets up relatively, and the bolt hole sets up with damaging the bolt hole is adjacent, and bolt hole damage clearance mechanism still includes:
and the fastener penetrates through the fixing hole and the bolt hole in sequence and then is locked on the aircraft structural part.
The utility model discloses an embodiment, the fastener is the bolt, and bolt hole damage clearance mechanism still includes:
the gasket is sleeved on the fastener;
the nut is locked on the fastener;
the gasket is clamped between the aircraft structural part and the nut, and/or between the bolt head of the bolt and the fixing part.
In an embodiment of the invention, the fastening hole is a bar-shaped hole, and the fastening member is movably arranged relative to the bar-shaped hole to adjust a distance between the fastening member and the guide member.
In one embodiment of the invention, the guide is arranged in the guide hole.
In an embodiment of the present invention, the outer diameter of the guiding member is adapted to the diameter of the guiding hole, and one end of the guiding member abuts against the aircraft structural member and is located on the plane of the hole opening of the damaged bolt hole.
The utility model discloses an in one embodiment, the guiding hole includes first hole section and second hole section, and the external diameter of guide spare and the diameter looks adaptation of first hole section, the diameter of second hole section are less than the diameter of first hole section, and the one end of guide spare is located the drill way place plane of second hole section, and the reamer is worn to establish in the damage bolt hole after passing guide hole and second hole section in proper order.
In one embodiment of the invention, the portion of the guide member is located outside the guide hole.
The utility model discloses a bolt hole damage clearance mechanism can accomplish the reaming processing to damaging the bolt hole fast through mounting, guide and reamer. In the damage treatment process is cleared away at concrete bolt hole, fix the mounting on aircraft structure to make the guiding hole on the mounting and the damage bolt hole of aircraft structure set up relatively, wear to establish in the damage bolt hole behind the guiding hole that the reamer passed the guiding piece, thereby realized the reaming processing to the damage bolt hole through rotating the reamer, eliminated the inside damage of bolt hole promptly. The utility model discloses a mechanism is clear away to bolt hole damage because the setting of mounting and guide piece can guarantee that the reamer can not take place the skew in the position that reaming in-process removed, and just can begin the reaming processing in the disect insertion guiding hole, need not too much artificial adjustment to the damage has been accelerated and has been clear away efficiency.
Drawings
Various objects, features and advantages of the present disclosure will become more apparent from the following detailed description of preferred embodiments thereof, which is to be read in connection with the accompanying drawings. The drawings are merely exemplary illustrations of the disclosure and are not necessarily drawn to scale. In the drawings, like reference characters designate the same or similar parts throughout the different views. Wherein:
FIG. 1 is a first perspective structural view of a bolt hole damage clearing mechanism according to an exemplary embodiment;
FIG. 2 is a structural schematic diagram illustrating a second perspective of a bolt hole damage removal mechanism according to an exemplary embodiment;
FIG. 3 is a third perspective structural view of a bolt hole damage removal mechanism according to an exemplary embodiment.
The reference numerals are explained below:
10. an aircraft structural member; 20. a fixing member; 21. a fixing hole; 30. a guide; 31. a guide hole; 40. a reamer; 50. a fastener; 51. a gasket; 52. and a nut.
Detailed Description
Exemplary embodiments that embody features and advantages of the present disclosure are described in detail below in the specification. It is to be understood that the disclosure is capable of various modifications in various embodiments without departing from the scope of the disclosure, and that the description and drawings are to be regarded as illustrative in nature, and not as restrictive.
In the following description of various exemplary embodiments of the disclosure, reference is made to the accompanying drawings, which form a part hereof, and in which is shown by way of illustration various exemplary structures in which aspects of the disclosure may be practiced. Other specific arrangements of systems and steps, and structural and functional modifications may be made without departing from the scope of the present disclosure. Moreover, although the terms "over", "between", "within", and the like may be used in this specification to describe various example features and elements of the disclosure, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples in the drawings. Nothing in this specification should be construed as requiring a specific three dimensional orientation of structures in order to fall within the scope of this disclosure.
An embodiment of the utility model provides a bolt hole damage clearance mechanism, as shown in fig. 1 to fig. 3, bolt hole damage clearance mechanism is used for cleaing away the bolt hole damage of aircraft structure 10, and bolt hole damage clearance mechanism includes: the fixing part 20 is used for being fixed on the aircraft structural part 10, and a guide hole is formed in the fixing part 20 and is opposite to a damaged bolt hole of the aircraft structural part 10; the guide piece 30 is arranged on the fixing piece 20, a guide hole 31 is arranged on the guide piece 30, the guide hole 31 is coaxially arranged with the guide hole, and the diameter of the guide hole 31 is smaller than or equal to that of the guide hole; and the reamer 40 is rotatably arranged in the guide hole 31 in a penetrating mode, so that the damaged bolt hole can be subjected to reaming treatment by the part of the reamer 40 penetrating in the damaged bolt hole.
The utility model discloses a bolt hole damage clearance mechanism of an embodiment can accomplish the reaming processing to damaging the bolt hole fast through mounting 20, guide piece 30 and reamer 40. In the specific bolt hole damage removing process, the fixing piece 20 is fixed on the aircraft structural piece 10, the guide hole in the fixing piece 20 is arranged opposite to the damaged bolt hole in the aircraft structural piece 10, the reamer 40 penetrates through the guide hole 31 of the guide piece 30 and then is arranged in the damaged bolt hole in a penetrating mode, and the reamer 40 is rotated to achieve reaming processing of the damaged bolt hole, namely damage inside the bolt hole is eliminated. The utility model discloses a bolt hole damage clearance mechanism of an embodiment because mounting 20 and guide 30's setting, can guarantee that the position that reamer 40 removed can not take place the skew at the reaming in-process, and the disect insertion just can begin the reaming processing in the bullport 31, need not too much artificial adjustment to the damage clearance efficiency has been accelerated.
In one embodiment, the diameter of the guide hole 31 is equal to the diameter of the reamer 40, and the diameter of the guide hole 31 is larger than the original diameter of the damaged bolt hole. Wherein, the diameter of reamer 40 is greater than the original diameter of damage bolt hole, and what carried out damage bolt hole promptly is the reaming treatment to this damage of elimination damage bolt hole.
In one embodiment, the reamers 40 may be selected differently depending on the original diameter of the damaged bolt hole, and the corresponding guides 30 are also replaced so that the diameter of the guide holes 31 is equal to the diameter of the reamers 40.
In one embodiment, the bolt hole damage removal mechanism includes 8 reamers 40 of different sizes, the diameter of the reamers 40 increasing progressively from 7/16 inches by 1/32 inches, and 8 guides 30, the inner diameter of the guides 30 also increasing progressively from 7/16 inches by 1/32 inches.
In one embodiment, the center line of the guide hole 31 has a predetermined distance from the center line of the damaged bolt hole, and the center line of the guide hole 31 is located on the side of the center line of the damaged bolt hole close to the damaged position of the damaged bolt hole. In order to remove the damage of the damaged bolt hole, it is necessary to shift the reamer 40 to the damaged position of the damaged bolt hole so as to ensure that the damage can be removed.
As shown in fig. 1, the fixing member 20 is provided with a fixing hole 21, the fixing hole 21 is arranged opposite to the bolt hole on the aircraft structural member 10, the bolt hole and the damaged bolt hole are adjacently arranged, and the bolt hole damage removing mechanism further includes: and the fastener 50, wherein the fastener 50 passes through the fixing hole 21 and the bolt hole in sequence and then is locked on the aircraft structural part 10.
In one embodiment, the fastener 20 is mounted on the aircraft structure 10 by a fastener 50, and the fastener 50 is fastened by means of a bolt hole on the aircraft structure 10, that is, when a specific damage is cleared, the fastener 50 is used to lock the fastener 20 on the aircraft structure 10 by means of a bolt hole on the aircraft structure 10 disposed adjacent to the damaged bolt hole, and then a reaming process is performed by using the reamer 40.
As shown in fig. 2 and 3, the fastener 50 is a bolt, and the bolt hole damage removing mechanism further includes: the gasket 51 is sleeved on the fastener 50; a nut 52, the nut 52 being locked on the fastener 50; the shim 51 is clamped between the aircraft structural member 10 and the nut 52, and/or the shim 51 is clamped between the bolt head of the bolt and the fixing member 20.
In one embodiment, the fastener 20 is secured to the aircraft structural member 10 by bolts, washers 51, and nuts 52. Wherein a washer 51 is arranged between the bolt head and the fixing element 20, and a washer 51 is arranged between the nut 52 and the aircraft structural element 10.
In one embodiment, the fixing hole 21 is a strip-shaped hole, and the fastener 50 is movably disposed with respect to the strip-shaped hole to adjust a distance between the fastener 50 and the guide 30. The setting in bar hole is mainly for adjusting the position relation of guide hole 31 and the damage bolt hole of guide piece 30, at specific reaming in-process, because the setting in bar hole can make mounting 20 drive guide piece 30 and remove for the bar hole, and the hole enlargement demand is satisfied with the position relation of damage bolt hole to guide hole 31, namely makes reamer 40 can clear away the damage position of damage bolt hole completely.
In one embodiment, the guide 30 is disposed within the guide hole. The guide 30 is of the type that is mounted directly in the guide hole of the fixture 20, i.e. it can be understood in use as a part of the fixture 20, but the guide 30 and the fixture 20 are of two detachable configurations, requiring the replacement of the guide 30 with a guide hole 31 of a different size.
In one embodiment, the guide 30 has an outer diameter adapted to the diameter of the pilot hole, and one end of the guide 30 abuts the aircraft structure 10 in the plane of the orifice of the damaged bolt hole. Wherein, the reamer 40 enters the damaged bolt hole after passing through the guide hole 31.
In one embodiment, the guide 30 is composed of a first cylindrical section having an outer diameter larger than an outer diameter of a second cylindrical section, which is inserted into the guide hole, and a second cylindrical section, which stops on the orifice of the guide hole.
In one embodiment, the guide hole includes a first hole section and a second hole section, the outer diameter of the guide member 30 is matched with the diameter of the first hole section, the diameter of the second hole section is smaller than the diameter of the first hole section, one end of the guide member 30 is located on the plane of the hole of the second hole section, and the reamer 40 passes through the guide hole 31 and the second hole section in sequence and then is arranged in the damaged bolt hole.
In one embodiment, portions of the guide 30 are located outside of the guide holes.
The utility model discloses a bolt hole damage clearance mechanism, it includes 8 reamers 40 of different sizes, reamer 40 diameter is started to increase gradually according to 1/32 inches by 7/16 inches, 8 guide bush (guide piece 30), the internal diameter of guide bush (the internal diameter of bullport 31) also starts to increase gradually according to 1/32 inches from 7/16 inches, 2 fixed blocks (mounting 20), 1 bolt (fastener 50) and 1 corresponding nut 52 and gasket 51 of 3/8 inches diameter are a plurality of. To the utility model discloses a bolt hole damage clearance mechanism can use on the bolt hole that the aperture is 3/8 inches and 1/2 inches, and the scope of reaming diameter is 13/32 inches ~ 5/8 inches.
The basic method is as follows: a guide bush of appropriate diameter is first fitted to the fixing block, and the fixing block is then fixed to the bolt hole adjacent to the damaged bolt hole using the bolt and 1 corresponding nut 52 and washer 51. And moving the fixing block so that the bolt detached from the damaged bolt hole can pass through the guide bush and the damaged bolt hole. And then adjusting the fixed block to enable the gap between the guide bush and the bolt detached from the damaged bolt hole to move towards the damaged position as much as possible so as to ensure that the damaged bolt hole can be completely removed at the eccentric hole expanding position. Finally, a reamer 40 with a proper size is used to pass through the guide bushing to complete the via hole of the eccentric hole, so that the purpose of removing the damage of the bolt hole is achieved.
Use the bolt hole that the diameter is 3/8 inches as an example, use the utility model discloses a bolt hole damage clearance mechanism's step:
1. a bolt adjacent to the damaged bolt hole is removed to obtain a bolt hole, and an 5/16-inch diameter bolt is used to pass through the removed bolt hole and the U-shaped groove (fixing hole 21) in the fixing block, and then the fixing block is preliminarily fixed by attaching the corresponding nut 52 and washer 51.
2. The U-shaped groove on the fixed block can enable the fixed block to move within a small range. A guide bushing having an inner bore diameter 1/32 inches greater than the original diameter of the damaged bolt hole was fitted at the circular hole (pilot hole) of the anchor block.
3. The bolt detached from the damaged bolt hole penetrates through the hole in the guide bushing and the damaged bolt hole, the fixing block is adjusted, and the gap between the guide bushing and the bolt detached from the damaged bolt hole moves towards the damaged position as far as possible, so that the damage of the bolt hole can be completely removed at the eccentric hole-expanding position.
4. The nut secured to the anchor block is locked to tightly secure the anchor block to the surface of the aircraft structure 10.
5. A reamer 40 with a proper size is used to pass through the guide bushing to complete the via hole of the eccentric hole, so that the purpose of removing the damage of the bolt hole is achieved.
The utility model discloses a function that bolt hole damage clearance mechanism can realize:
1. the position of the eccentric hole can be quickly and accurately positioned, and the damage of the bolt hole can be accurately removed.
2. The utility model discloses set up reamer guide bush, can make reamer perpendicular to structure surface feed, the condition that can not appear boring partially and bore askew.
3. The utility model discloses the reamer diameter size that sets up begins to increase gradually according to 1/32 inches from 7/16 inches, satisfies on the bolt hole that the aperture is 3/8 inches and 1/2 inches, demand that reaming diameter range 13/32 inches ~ 5/8 inches, application range is wide.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. The present invention is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and exemplary embodiments be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.
Claims (10)
1. A bolt hole damage clearing mechanism for clearing bolt hole damage to an aircraft structure (10), the bolt hole damage clearing mechanism comprising:
the fixing part (20) is used for being fixed on the aircraft structural part (10), a guide hole is formed in the fixing part (20), and the guide hole is opposite to a damaged bolt hole of the aircraft structural part (10);
a guide part (30), wherein the guide part (30) is arranged on the fixing part (20), a guide hole (31) is arranged on the guide part (30), the guide hole (31) is coaxially arranged with the guide hole, and the diameter of the guide hole (31) is smaller than or equal to that of the guide hole;
the reamer (40) is rotatably arranged in the guide hole (31) in a penetrating mode, and the damaged bolt hole is subjected to reaming treatment by the aid of the reamer (40) which is arranged in the damaged bolt hole in a penetrating mode.
2. The mechanism of claim 1, wherein the guide hole (31) has a diameter equal to the diameter of the reamer (40), the guide hole (31) having a diameter greater than the original diameter of the damaged bolt hole.
3. The mechanism of claim 1, wherein the center line of the guide hole (31) has a predetermined distance from the center line of the damaged bolt hole, and the center line of the guide hole (31) is located on the side of the center line of the damaged bolt hole close to the damaged position of the damaged bolt hole.
4. The bolt hole damage removing mechanism according to any one of claims 1 to 3, wherein a fixing hole (21) is provided in the fixing member (20), the fixing hole (21) being disposed opposite to a bolt hole in the aircraft structural member (10), the bolt hole being disposed adjacent to the damaged bolt hole, the bolt hole damage removing mechanism further comprising:
and the fastener (50) passes through the fixing hole (21) and the bolt hole in sequence and then is locked on the aircraft structural part (10).
5. The bolt hole damage removal mechanism of claim 4, wherein the fastener (50) is a bolt, the bolt hole damage removal mechanism further comprising:
a gasket (51), wherein the gasket (51) is sleeved on the fastener (50);
a nut (52), said nut (52) being locked on said fastener (50);
wherein the shim (51) is clamped between the aircraft structural part (10) and the nut (52) and/or the shim (51) is clamped between a bolt head of the bolt and the fixing part (20).
6. The bolt hole damage clearing mechanism according to claim 4, characterized in that the fixing hole (21) is a strip-shaped hole, the fastener (50) being movably arranged relative to the strip-shaped hole to adjust a distance between the fastener (50) and the guide (30).
7. The bolt hole damage clearing mechanism according to any one of claims 1 to 3, wherein the guide (30) is disposed within the guide hole.
8. The bolt hole damage clearing mechanism according to claim 7, characterized in that the guide piece (30) has an outer diameter adapted to the diameter of the pilot hole, one end of the guide piece (30) abutting the aircraft structure (10) and lying in the plane of the orifice of the damaged bolt hole.
9. The mechanism for removing the damage to the bolt hole according to claim 7, wherein the guide hole comprises a first hole section and a second hole section, the outer diameter of the guide piece (30) is matched with the diameter of the first hole section, the diameter of the second hole section is smaller than that of the first hole section, one end of the guide piece (30) is located on the plane of the orifice of the second hole section, and the reamer (40) penetrates through the damaged bolt hole after sequentially passing through the guide hole (31) and the second hole section.
10. The bolt hole damage clearing mechanism of claim 8 or 9, wherein a portion of the guide (30) is located outside the guide hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921598534.3U CN210996856U (en) | 2019-09-24 | 2019-09-24 | Bolt hole damage removing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921598534.3U CN210996856U (en) | 2019-09-24 | 2019-09-24 | Bolt hole damage removing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210996856U true CN210996856U (en) | 2020-07-14 |
Family
ID=71473239
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921598534.3U Expired - Fee Related CN210996856U (en) | 2019-09-24 | 2019-09-24 | Bolt hole damage removing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210996856U (en) |
-
2019
- 2019-09-24 CN CN201921598534.3U patent/CN210996856U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10752377B2 (en) | Method and apparatus for preventing lightning strike damage to a structural component | |
| US8292551B2 (en) | System, method and apparatus for removing failed fasteners | |
| US20110232072A1 (en) | Riveting screw tack and use thereof for temporarily fixing a boring grid to elements to be assembled | |
| CN210996856U (en) | Bolt hole damage removing mechanism | |
| DE102014224920A1 (en) | Device for recontouring a gas turbine blade | |
| CN210848371U (en) | Adjustable boring machine tool | |
| CN112894708A (en) | Gun dismantling reamer device and method | |
| US8430627B2 (en) | Gas turbine exhaust strut refurbishment | |
| US9770765B2 (en) | Match drilling tool, system and method | |
| CN211915816U (en) | Adjustable friction stir welding stirring head | |
| CN211438183U (en) | Turning device for workpiece with ultra-long hole | |
| CN209272629U (en) | It is a kind of for processing the cutting apparatus of inner hole symmetrical key | |
| US5125774A (en) | Boring bar cutter tool | |
| CN112705903B (en) | Lathe tailstock repairing method | |
| CN218253223U (en) | Combined cutter | |
| CN211803937U (en) | Safety valve seat machining tool | |
| CN220445680U (en) | High-precision small-diameter deep hole machining tool | |
| CN205362711U (en) | Cutting instrument | |
| US7435040B1 (en) | Apparatus and method for the reaming of a hole in a work surface | |
| CN220030481U (en) | Graphite hard felt drilling tool | |
| US11919133B2 (en) | Quick-release captive clamping pin systems and methods | |
| CN220739499U (en) | Inner and outer diameter integrated adjustable boring cutter | |
| CN217193058U (en) | Lug hole bush end face deburring tool | |
| CN207043358U (en) | Adjustable fine boring cutter | |
| CN219254168U (en) | Special cutter for boring taper hole |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200714 Termination date: 20210924 |