CN208879724U - It is a kind of for repairing the boring cutter of aircraft crossing point holes - Google Patents
It is a kind of for repairing the boring cutter of aircraft crossing point holes Download PDFInfo
- Publication number
- CN208879724U CN208879724U CN201821441461.2U CN201821441461U CN208879724U CN 208879724 U CN208879724 U CN 208879724U CN 201821441461 U CN201821441461 U CN 201821441461U CN 208879724 U CN208879724 U CN 208879724U
- Authority
- CN
- China
- Prior art keywords
- cutter hub
- cutter
- guiding
- guide pad
- boring cutter
- 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.)
- Active
Links
Landscapes
- Drilling And Boring (AREA)
Abstract
The utility model provides a kind of for repairing the boring cutter of aircraft crossing point holes, belongs to aircraft assembly and working service field.The boring cutter includes cutter hub and pilot bushing；The pilot bushing is set in the guiding location external of cutter hub, unspoiled crossing point holes apertures on outer diameter and same group intersection point, internal diameter and the position cooperation of cutter hub guiding, the guiding for boring cutter, guarantee that cutter hub is fed along correct axis in process, eliminates cutter hub caused by air drill is swung and swing.Boring cutter power device is changed to air drill, hand feed feeds path and determined by pilot bushing, and method is easy flexibly, is highly suitable for hands- operation, and energy high degree simplifies aircraft intersection point repair process, saves vast resources.
Description
Technical field
The utility model belongs to aircraft assembly and working service field, and in particular to a kind of for repairing aircraft crossing point holes
Boring cutter.
Background technique
Multiple movable parts are installed on aircraft outer wing, the crossing point holes that movable part is docked with airframe components all install bushing,
The effect of bushing is: 1) when movable part deflects, preventing abrasion of the connection pin shaft to body；2) it in component docking operation, prevents
Body is damaged when pin shaft is installed.These bushings and body are all interference installation, bushing inner hole (component crossing point holes) axis
Position is to be guaranteed in dress component assembling by tool positioner, or guaranteed by finishing after assembly.If made in aircraft
With in the process, bush hole is damaged, and must just be replaced.For the bushing finished after assembly, bushing inner hole is deposited with outer circle
In eccentricity, after more renewing bushing, it is necessary to bushing inner hole is re-worked, and for the aircraft in using, if by aircraft components
It removes and returns to assembly shop more resleeve and lay equal stress on new finishing, it may be desirable to a large amount of time and expense.If there is a kind of easy
Machining tool can finish the bushing of replacement on machine and can guarantee intersection point axial location required precision, it will save a large amount of
Manpower, financial resources and time.
Utility model content
The boring cutter that the utility model aims at the problems existing in the prior art, and provides a kind of for repairing aircraft crossing point holes and
Application method, the boring cutter be one kind can air drill clamping, the combination boring cutter with pilot bushing and guide pad.
The technical solution of the utility model includes:
It is a kind of for repairing the boring cutter of aircraft crossing point holes, which includes cutter hub 1 and pilot bushing 2；
The cutter hub 1 is in second order stepped cylinder, including retaining part, guiding position and cutting parts；After cutter hub 1
Portion is retaining part, is in triangular prism shape, provides power for the clamping and guiding of air drill, and in processing；The middle part of cutter hub 1 is
Guiding position guarantees that processing backsight sets of holes and same group crossing point holes are coaxial for cooperating with pilot bushing；The front of cutter hub is cutting
Position, cutting parts include the blade 3 and guide pad for being embedded in guide part bit port, and blade 3 and guide pad are set as needed
Size, blade 3 will ensure to process back aperture and meet the requirements, for cutting；Guide pad includes the first guide pad 4, the second guide pad 5
It is circumferentially uniformly distributed at guide part bit port with 6,3 guide pads of third guide pad, the outer of guide pad and blade 3 is constituted
Diameter of a circle with processing the diameter of metapore it is consistent, for self- steering and boring cutter is avoided to beat, guarantee machining accuracy；
The pilot bushing 2 is set in the guiding location external of cutter hub 1, unspoiled intersection point on outer diameter and same group intersection point
Hole apertures, internal diameter and cutter hub 1 are oriented to position cooperation, for the guiding of boring cutter, guarantee that cutter hub 1 is along correct in process
Axis feeding is eliminated cutter hub caused by air drill is swung and is swung.
Boring cutter power device is air drill, and hand feed feeds path and determined by pilot bushing, and method is easy flexibly, very
Suitable for hands- operation, energy high degree simplifies aircraft intersection point repair process, saves vast resources.
It is a kind of for repairing the application method of the boring cutter of aircraft crossing point holes, steps are as follows:
(1) bushing being damaged on aircraft is removed, reinstalls bushing of the internal diameter with 1mm machining allowance；
(2) pilot bushing 2 is installed on cutter hub 1, and the retaining part of cutter hub 1 is loaded onto air drill；
(3) pilot bushing 2 is installed in same group of crossing point holes undamaged on aircraft, is pushed into cutter hub 1 along pilot bushing 2,
Until blade 3 is contacted with processed bushing；
(4) according to bushing and processing aperture setting air drill revolving speed is processed, air drill is opened, is slowly pushed along pilot bushing 2
Cutter hub 1 is fed, and manually controls feed speed, when the blade 3 of boring cutter cutting produces processed bushing, closes air drill.
Working principle of the utility model is: processing initial stage, boring cutter is swung by the limitation of pilot bushing 2；After blade incision,
First guide pad 4, the second guide pad 5, third guide pad 6 and the hole after being processed cooperate, and play self- steering and limitation bounce,
To guarantee the precision and axis direction in hole.
The utility model has the beneficial effects that this boring cutter structure is simple, manufacturing cost is low, can be loaded on air drill, guiding lining
Set and guide pad combine guiding, it is ensured that cutter is stablized when processing, and jerk value is minimum.Finishing is replaced because impaired on machine
The bushing crossed guarantees that processing back aperture meets drawing requirement, and guarantees that axially bored line meets aircraft original intersection point in processing back bush
Axis, therefore can simplify aircraft crossing point holes bushing injury repair process, save a large amount of manpower, financial resources and time.
Detailed description of the invention
Fig. 1 is the structure chart of boring cutter.
Fig. 2 is the sectional view of retaining part.
Fig. 3 is the structure chart of cutting parts.
Fig. 4 is the processing method schematic diagram of boring cutter.
In figure: 1 cutter hub；2 pilot bushings；3 blades；4 first guide pads；5 second guide pads；6 third guide pads.
Specific embodiment
The technical solution of the utility model is further detailed below in conjunction with specific embodiments and the drawings.
It is a kind of that for repairing the boring cutter of aircraft crossing point holes, the boring cutter includes cutter hub 1 and pilot bushing 2,
The cutter hub 1 is in second order stepped cylinder, including retaining part, guiding position and cutting parts；After cutter hub 1
Portion is retaining part, is in triangular prism shape, provides power for the clamping and guiding of air drill, and in processing；The middle part of cutter hub 1 is
Guiding position guarantees that processing backsight sets of holes and same group crossing point holes are coaxial for cooperating with pilot bushing；The front of cutter hub is cutting
Position, cutting parts include the blade 3 and guide pad for being embedded in guide part bit port, and blade 3 and guide pad are set as needed
Size, blade 3 will ensure to process back aperture and meet the requirements, for cutting；Guide pad includes the first guide pad 4, the second guide pad 5
It is circumferentially uniformly distributed at guide part bit port with 6,3 guide pads of third guide pad, the outer of guide pad and blade 3 is constituted
Diameter of a circle and processing metapore one guide pad of diameter cause, for self- steering and boring cutter is avoided to beat, guarantee machining accuracy；
The pilot bushing 2 is set in the guiding location external of cutter hub 1, unspoiled intersection point on outer diameter and same group intersection point
Hole apertures, internal diameter and cutter hub 1 are oriented to position cooperation, for the guiding of boring cutter, guarantee that cutter hub 1 is along correct in process
Axis feeding is eliminated cutter hub caused by air drill is swung and is swung.
Boring cutter power device is air drill, and hand feed feeds path and determined by pilot bushing, and method is easy flexibly, very
Suitable for hands- operation, energy high degree simplifies aircraft intersection point repair process, saves vast resources.
It is a kind of for repairing the application method of the boring cutter of aircraft crossing point holes, steps are as follows:
(1) bushing being damaged on aircraft is removed, reinstalls bushing of the internal diameter with 1mm machining allowance；
(2) pilot bushing 2 is installed on cutter hub 1, and the retaining part of cutter hub 1 is loaded onto air drill；
(3) pilot bushing 2 is installed in same group of crossing point holes undamaged on aircraft, is pushed into cutter hub 1 along pilot bushing 2,
Until blade 3 is contacted with processed bushing；
(4) according to bushing and processing aperture setting air drill revolving speed is processed, air drill is opened, is slowly pushed along pilot bushing 2
Cutter hub 1 is fed, and manually controls feed speed, when the blade 3 of boring cutter cutting produces processed bushing, closes air drill.
Claims (1)
1. a kind of for repairing the boring cutter of aircraft crossing point holes, which is characterized in that the boring cutter includes cutter hub (1) and pilot bushing (2)；
The cutter hub (1) is in second order stepped cylinder, including retaining part, guiding position and cutting parts；After cutter hub (1)
Portion is retaining part, is in triangular prism shape, provides power for the clamping and guiding of air drill, and in processing；The middle part of cutter hub (1)
Guarantee that processing backsight sets of holes and same group crossing point holes are coaxial for cooperating with pilot bushing for guiding position；The front of cutter hub is to cut
Position is cut, cutting parts include the blade (3) and guide pad for being embedded in guide part bit port, and blade (3) and guide pad are according to need
Size is set, and blade (3) will ensure to process back aperture and meet the requirements, for cutting；Guide pad include the first guide pad (4),
Second guide pad (5) and third guide pad (6), 3 guide pads are circumferentially uniformly distributed at guide part bit port, guide pad and knife
The diameter of a circle that the outer of piece (3) is constituted is consistent with the processing diameter of metapore, for self- steering and boring cutter is avoided to beat, and guarantees
Machining accuracy；
The pilot bushing (2) is set in the guiding location external of cutter hub (1), unspoiled intersection point on outer diameter and same group intersection point
Hole apertures, internal diameter and the position cooperation of cutter hub (1) guiding guarantee that cutter hub (1) is along just in process for the guiding of boring cutter
True axis feeding is eliminated cutter hub caused by air drill is swung and is swung.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821441461.2U CN208879724U (en) | 2018-09-04 | 2018-09-04 | It is a kind of for repairing the boring cutter of aircraft crossing point holes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821441461.2U CN208879724U (en) | 2018-09-04 | 2018-09-04 | It is a kind of for repairing the boring cutter of aircraft crossing point holes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208879724U true CN208879724U (en) | 2019-05-21 |
Family
ID=66511048
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821441461.2U Active CN208879724U (en) | 2018-09-04 | 2018-09-04 | It is a kind of for repairing the boring cutter of aircraft crossing point holes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208879724U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109014256A (en) * | 2018-09-04 | 2018-12-18 | 沈阳飞机工业（集团）有限公司 | It is a kind of for repairing the boring cutter and application method of aircraft crossing point holes |
-
2018
- 2018-09-04 CN CN201821441461.2U patent/CN208879724U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109014256A (en) * | 2018-09-04 | 2018-12-18 | 沈阳飞机工业（集团）有限公司 | It is a kind of for repairing the boring cutter and application method of aircraft crossing point holes |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105252224A (en) | Machining method of outer duct outlet guide vane of aero-engine | |
| CN208879724U (en) | It is a kind of for repairing the boring cutter of aircraft crossing point holes | |
| CN101450407A (en) | Electro-hydraulic servo valve sleeve throttling square-hole processing tool | |
| CN106736332B (en) | A kind of numerical-control processing method of the High Pressure Turbine Rotor combination with brill tapered hole | |
| CN109014256A (en) | It is a kind of for repairing the boring cutter and application method of aircraft crossing point holes | |
| CN200974145Y (en) | Reaming and extruding cutter for hole machining | |
| CN206047249U (en) | A kind of floating handle of a knife | |
| CN208853744U (en) | A kind of dedicated boring head for processing pregnant hole on lathe | |
| CN203484723U (en) | Combined numerical control milling cutter | |
| CN103817366A (en) | Combined chambering cutter | |
| CN204603417U (en) | A kind of dual output milling head | |
| CN105081372A (en) | Telescopic boring cutter for processing internal conical surface | |
| CN203853566U (en) | Assembled deep hole boring cutter for sleeve inner hole processing | |
| CN105458311B (en) | For the correction compound tool of diesel engine frame camshaft hole processing | |
| CN212734376U (en) | Auxiliary limiting stopper for milling step difference | |
| CN111015388A (en) | Closed groove cutter body ejector rod type cutting tool for grinding fiber inner diameter shaft sleeve | |
| CN204075247U (en) | A kind of positioner of automatic displacement | |
| CN110293237A (en) | A kind of coaxial high accurate hole processing boring cutter and processing method | |
| CN104439945A (en) | Numerical control machining method for aero-engine main nozzle parts | |
| CN205702502U (en) | A kind of aluminum alloy conduit end face high-efficiency cutting tool for processing | |
| CN210819058U (en) | Single-blade honing cutter | |
| CN111002121A (en) | Open groove cutter type cutting tool for grinding fiber inner diameter shaft sleeve | |
| CN216632736U (en) | Side milling head for boring side surface of flap slide rail | |
| CN203900515U (en) | Telescopic inner conical surface machining boring cutter | |
| CN219900281U (en) | Motor casing composite boring cutter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |