CN107471082A - The lapping device and Ginding process of aircraft check valve - Google Patents
The lapping device and Ginding process of aircraft check valve Download PDFInfo
- Publication number
- CN107471082A CN107471082A CN201710820626.0A CN201710820626A CN107471082A CN 107471082 A CN107471082 A CN 107471082A CN 201710820626 A CN201710820626 A CN 201710820626A CN 107471082 A CN107471082 A CN 107471082A
- Authority
- CN
- China
- Prior art keywords
- boss
- check valve
- abrasive disk
- aircraft
- aircraft check
- 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.)
- Pending
Links
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
- B24B37/00—Lapping machines or devices; Accessories
-
- 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
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
Abstract
The invention discloses a kind of lapping device and Ginding process of aircraft check valve, wherein, the lapping device includes：The boss abrasive disk (2) at least partly mutually agreed with the groove (101) on the aircraft check valve (1), and the drag link mechanism (3) of axial direction sliding of the aircraft check valve (1) along the boss abrasive disk (2) can be driven, and the drag link mechanism (3) and at least partly described boss abrasive disk (2) can be using the axis of the boss abrasive disk (2) as axle rotation.By above-mentioned design, realizing can be ground in the method for simplicity to the sealing concave of aircraft check valve, greatly improve the effect of the quality of production and production efficiency.
Description
Technical field
The present invention relates to the process equipment of aircraft check valve and method field, in particular it relates to the grinding of aircraft check valve
Device and Ginding process.
Background technology
In daily production process, conventional grinder can only ground flat, concave surface is often because shape of contact surface etc. is asked
Topic so that the grinding of concave surface tends not to be ground by the grinder of routine.And the structure of aircraft check valve is often recessed
Face is as sealing surface, typically based on import, the domestic solution that temporarily processing to its concave surface etc. has not had.Cause
This, the problems such as general import aircraft check valve leaks, then aircraft system shop be substantially using being manually ground, and one
As underhand polish generally require the bimestrial time could be ground one, and effect is also not ideal.
Therefore it provides a kind of can be ground in the method for simplicity to the sealing concave of aircraft check valve, life is greatly improved
The problem of lapping device and Ginding process of yield and quality and the aircraft check valve of production efficiency are urgent need to resolve of the present invention.
The content of the invention
For above-mentioned prior art, it is an object of the invention to overcome general import aircraft check valve appearance in the prior art
The problems such as leakage, then aircraft system shop is substantially to use and is manually ground, and in general underhand polish generally requires two
Month time could ground one, and the problem of effect is also not ideal, so as to provide it is a kind of can be in easy method pair
The sealing concave of aircraft check valve is ground, and greatly improves the lapping device of the aircraft check valve of the quality of production and production efficiency
And Ginding process.
To achieve these goals, the invention provides a kind of lapping device of aircraft check valve, wherein, the grinding dress
Put including：The boss abrasive disk at least partly mutually agreed with the groove on the aircraft check valve, and described fly can be driven
The drag link mechanism of axial direction sliding of the machine check valve along the boss abrasive disk, and described in the drag link mechanism and at least part
Boss abrasive disk can be using the axis of the boss abrasive disk as axle rotation.
Preferably, the drag link mechanism comprises at least the connecting rod that can be fixedly connected with the aircraft check valve and can
The rotating unit for driving the connecting rod to rotate.
Preferably, the rotating unit includes the rotary electric machine being connected with the connecting rod.
Preferably, the boss abrasive disk includes base frame and the pivot protrusion platform that can be arranged to rotation on the base frame,
And the pivot protrusion platform mutually agrees with the groove.
Preferably, at least two through holes are additionally provided with the boss abrasive disk.
Present invention also offers a kind of Ginding process of aircraft check valve, wherein, the Ginding process use is according to above-mentioned
Described lapping device, the Ginding process include：
1) aircraft check valve is placed on boss abrasive disk, and the groove on the aircraft check valve is ground with the boss
Disk at least partly mutually agrees with setting；
2) drag link mechanism and the aircraft check valve are fixedly installed, and drive the aircraft check valve to be ground along the boss
The axial direction movement of mill, simultaneously so that the aircraft check valve and at least partly described boss abrasive disk rotation, and it is described
Aircraft check valve is opposite with the sense of rotation of the boss abrasive disk.
Preferably, also include adding lapping liquid into one of through hole of boss abrasive disk in step 2) and flow to grinding
It is ground on face, and grinding waste material is flowed out by another through hole being arranged on boss abrasive disk.
Preferably, the lapping liquid comprises at least silicon carbide micro-powder and cod-liver oil.
Preferably, in step 2), axial direction of the aircraft check valve along the boss abrasive disk is moved as reciprocal fortune
It is dynamic, and the face to be ground of the aircraft check valve is at least partly in contact with the abradant surface of the boss abrasive disk.
According to above-mentioned technical proposal, the present invention is ground by the way that the lapping device to be arranged to have with the boss that groove mutually agrees with
Mill so that the groove on the boss abrasive disk and aircraft check valve agrees with and enables the boss abrasive disk and the groove
Inwall is in contact, meanwhile, a drag link mechanism that can be slid along the axial direction of boss abrasive disk is set so that the draw-bar machine
Structure can drive axial direction of the aircraft check valve along boss abrasive disk to move, and further, the drag link mechanism can drive winged
Machine check valve using the axis of boss abrasive disk as axle rotation, and boss abrasive disk also can using its axis as axle rotation, and two
The sense of rotation of person is opposite so that and the two can effectively realize the effect of friction, meanwhile, because drag link mechanism can drive aircraft
Check valve moves, so that the grinding track of the groove of aircraft check valve is formed as a light belt, not only avoid and manually grinds
The efficiency of mill is low and poor quality, meanwhile, improve operating time of integral grinding etc..
Other features and advantages of the present invention will be described in detail in subsequent specific embodiment part.
Brief description of the drawings
Accompanying drawing is for providing a further understanding of the present invention, and a part for constitution instruction, with following tool
Body embodiment is used to explain the present invention together, but is not construed as limiting the invention.In the accompanying drawings：
Fig. 1 is a kind of structural representation of the lapping device of aircraft check valve；
Fig. 2 is a kind of front view of the structure of aircraft check valve.
Description of reference numerals
1- aircraft check valve 2- boss abrasive disks
3- drag link mechanism 101- grooves
102- inner ring 103- outer shrouds
201- base frame 202- pivot protrusion platforms.
Embodiment
The embodiment of the present invention is described in detail below in conjunction with accompanying drawing.It should be appreciated that this place is retouched
The embodiment stated is merely to illustrate and explain the present invention, and is not intended to limit the invention.
In the present invention, in the case where not making opposite explanation, " upper and lower and axial " etc. is included in the noun of locality in term
Only represent orientation of the term under normal service condition, or be skilled artisan understands that be commonly called as, and be not construed as pair
The limitation of the term.
The invention provides a kind of lapping device of aircraft check valve, wherein, as depicted in figs. 1 and 2, the lapping device
Including：The boss abrasive disk 2 at least partly agreed with the phase of groove 101 on the aircraft check valve 1, and can drive described
The drag link mechanism 3 of axial direction sliding of the aircraft check valve 1 along the boss abrasive disk 2, and the drag link mechanism 3 and at least portion
Divide the boss abrasive disk 2 can be using the axis of the boss abrasive disk 2 as axle rotation.
The present invention is by the way that the lapping device is arranged to the boss abrasive disk 2 agreed with the phase of groove 101 so that this is convex
Groove 101 on platform abrasive disk 2 and aircraft check valve 1 agrees with and enables the inwall of the boss abrasive disk 2 and the groove 101
It is in contact, meanwhile, a drag link mechanism 3 that can be slid along the axial direction of boss abrasive disk 2 is set so that the drag link mechanism
3 can drive axial direction of the aircraft check valve 1 along boss abrasive disk 2 to move, and further, the drag link mechanism 3 can drive
Aircraft check valve 1 using the axis of boss abrasive disk 2 as axle rotation, and boss abrasive disk 2 also can using its axis as axle rotation, and
And the sense of rotation of the two is opposite so that the two can effectively realize the effect of friction, meanwhile, because drag link mechanism 3 being capable of band
Dynamic aircraft check valve 1 moves, so that the grinding track of the groove 101 of aircraft check valve 1 is formed as a light belt, not only keeps away
Exempted from underhand polish efficiency is low and poor quality, meanwhile, improve operating time of integral grinding etc..Here aircraft list
Can be conventional architecture style to the structure of valve 1, for example, can be with as shown in Fig. 2 being the inner ring 102 and outer shroud that include fit
103, and plate body is connected between inner ring 102 and one of end face of outer shroud 103, to cause between inner ring 102 and outer shroud 103
Be formed as the cell body of one end closing, i.e. groove 101 in the present invention.At least part structure in boss abrasive disk 2 is with being somebody's turn to do
The phase of groove 101 is agreed with, i.e., it comprises at least an annulated column structure for being inserted into the groove 101.Certainly, have similar to this kind of
The workpiece to be added of inner groove surface herein can, also, the structure of boss abrasive disk 2 here can be entered according to actual workpiece to be added
Row regulation and selection, are seldom repeated herein.
In a kind of preferred embodiment of the present invention, the drag link mechanism 3 comprises at least can be with the aircraft list
The connecting rod being fixedly connected to valve 1 and the rotating unit that the connecting rod can be driven to rotate.
In further preferred embodiment, the rotating unit includes the rotary electric machine being connected with the connecting rod.From
And make it possible to drive connecting rod to rotate by the rotary electric machine, and and then drive aircraft check valve 1 to rotate, meanwhile, the connection
Bar can move along the axial direction of boss abrasive disk 2, and be further driven to aircraft check valve 1 and move, and similar structure is herein
Can, seldom repeat herein.
For example, in a kind of embodiment being more highly preferred to of the present invention, the boss abrasive disk 2 could be arranged to include
Base frame 201 and the pivot protrusion platform 202 that can be arranged to rotation on the base frame 201, and the pivot protrusion platform 202 with it is described
The phase of groove 101 is agreed with.Certainly, pivot protrusion platform 202 can rotates here, to realize the grinding effect with groove 101.
In a kind of preferred embodiment of the present invention, at least two are also provided with the boss abrasive disk 2
Through hole, and the through hole is extended on the abradant surface of the boss abrasive disk 2 and the aircraft check valve 1, is enable to lead to
The through hole is crossed to add lapping liquid or discharge grinding waste material.
Present invention also offers a kind of Ginding process of aircraft check valve, wherein, the Ginding process uses described above
Lapping device, the Ginding process includes：
1) aircraft check valve 1 is placed on boss abrasive disk 2, and the groove 101 on the aircraft check valve 1 with it is described convex
Platform abrasive disk 2 at least partly mutually agrees with setting；
2) drag link mechanism 3 and the aircraft check valve 1 are fixedly installed, and drive the aircraft check valve 1 along described convex
The axial direction movement of platform abrasive disk 2, simultaneously so that the aircraft check valve 1 and at least partly described boss abrasive disk 2 are certainly
Turn, and the aircraft check valve 1 is opposite with the sense of rotation of the boss abrasive disk 2.
In a kind of embodiment being more highly preferred to of the present invention, also include in step 2) to boss abrasive disk 2 wherein
Lapping liquid is added in one through hole and is flow on abradant surface and is ground, and causes grinding waste material by being arranged at boss abrasive disk
Another through hole outflow on 2.
In further preferred embodiment, the lapping liquid comprises at least silicon carbide micro-powder and cod-liver oil.Certainly, here
Silicon carbide micro-powder and the usage ratio of cod-liver oil can be adjusted according to being actually needed, seldom repeat herein.
In another preferred embodiment of the present invention, in step 2), the aircraft check valve 1 is ground along the boss
The axial direction movement of disk 2 is moves back and forth, and the face to be ground of the aircraft check valve 1 and the boss abrasive disk 2 are ground
Flour milling is at least partly in contact.So as to avoid the aircraft check valve 1 from directly departing from the boss abrasive disk 2, and then avoid nothing
The problem of method is ground.
By this lapping mode, now grinding an aircraft check valve 1 only needs 1/6 hour, i.e., can grind within one hour
Six aircraft check valves 1 so that operating efficiency improves thousands of times, and the better quality of aircraft check valve 1 after grinding, effectively
Raising quality is realized, improves efficiency, reduces the effect of cost.
The preferred embodiment of the present invention is described in detail above in association with accompanying drawing, still, the present invention is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the present invention, a variety of letters can be carried out to technical scheme
Monotropic type, these simple variants belong to protection scope of the present invention.
It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the present invention to it is various can
The combination of energy no longer separately illustrates.
In addition, various embodiments of the present invention can be combined randomly, as long as it is without prejudice to originally
The thought of invention, it should equally be considered as content disclosed in this invention.
Claims (9)
1. a kind of lapping device of aircraft check valve, it is characterised in that the lapping device includes：At least part and the aircraft
The boss abrasive disk (2) that groove (101) on check valve (1) mutually agrees with, and the aircraft check valve (1) can be driven along institute
The drag link mechanism (3) of the axial direction sliding of boss abrasive disk (2) is stated, and the drag link mechanism (3) and at least part are described convex
Platform abrasive disk (2) can be using the axis of the boss abrasive disk (2) as axle rotation.
2. lapping device according to claim 1, it is characterised in that the drag link mechanism (3) comprises at least can be with institute
State the connecting rod that aircraft check valve (1) is fixedly connected and the rotating unit that the connecting rod can be driven to rotate.
3. lapping device according to claim 2, it is characterised in that the rotating unit includes being connected with the connecting rod
Rotary electric machine.
4. according to the lapping device described in any one in claim 1-3, it is characterised in that boss abrasive disk (2) bag
The pivot protrusion platform (202) that includes base frame (201) and can be arranged to rotation on the base frame (201), and the pivot protrusion platform
(202) mutually agree with the groove (101).
5. according to the lapping device described in any one in claim 1-3, it is characterised in that on the boss abrasive disk (2)
It is additionally provided with least two through holes.
6. a kind of Ginding process of aircraft check valve, it is characterised in that the Ginding process use is appointed according in claim 1-5
Lapping device described in meaning one, the Ginding process include：
1) aircraft check valve (1) is placed on boss abrasive disk (2), and the groove (101) on the aircraft check valve (1) and institute
State boss abrasive disk (2) and at least partly mutually agree with setting；
2) drag link mechanism (3) and the aircraft check valve (1) are fixedly installed, and drive the aircraft check valve (1) along described
The axial direction movement of boss abrasive disk (2), simultaneously so that the aircraft check valve (1) is ground with least partly described boss
Disk (2) rotation, and the aircraft check valve (1) is opposite with the sense of rotation of the boss abrasive disk (2).
7. Ginding process according to claim 6, it is characterised in that also include to boss abrasive disk (2) in step 2)
Lapping liquid is added in one of through hole and is flow on abradant surface and is ground, and grinding waste material is ground by being arranged at boss
Another through hole outflow on mill (2).
8. Ginding process according to claim 6, it is characterised in that the lapping liquid comprises at least silicon carbide micro-powder and fish
Liver oil.
9. according to the Ginding process described in any one in claim 6-8, it is characterised in that in step 2), the aircraft list
Axial direction movement to valve (1) along the boss abrasive disk (2) is moves back and forth, and the aircraft check valve (1) is waited to grind
Flour milling is at least partly in contact with the abradant surface of the boss abrasive disk (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710820626.0A CN107471082A (en) | 2017-09-13 | 2017-09-13 | The lapping device and Ginding process of aircraft check valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710820626.0A CN107471082A (en) | 2017-09-13 | 2017-09-13 | The lapping device and Ginding process of aircraft check valve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107471082A true CN107471082A (en) | 2017-12-15 |
Family
ID=60583859
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710820626.0A Pending CN107471082A (en) | 2017-09-13 | 2017-09-13 | The lapping device and Ginding process of aircraft check valve |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107471082A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110076638A (en) * | 2019-06-05 | 2019-08-02 | 北京首钢冷轧薄板有限公司 | A kind of circle shear precision restorative procedure |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR200445915Y1 (en) * | 2009-02-13 | 2009-09-10 | 주식회사 아이제이피에스 | Lapping apparatus |
| CN102975111A (en) * | 2012-08-20 | 2013-03-20 | 广东肇庆微硕电子有限公司 | Grinding method and special device for soft magnetic ferrite magnetic cores |
| CN103100960A (en) * | 2012-12-28 | 2013-05-15 | 贵州航天控制技术有限公司 | Grinding device for shell body part |
| CN203156547U (en) * | 2012-12-28 | 2013-08-28 | 贵州航天控制技术有限公司 | Grinding device for casing part |
| CN203853873U (en) * | 2014-05-14 | 2014-10-01 | 河北大唐国际唐山热电有限责任公司 | Grinding device of steam inlet valve spool and grinding device of steam inlet valve seat |
| CN204248575U (en) * | 2014-09-23 | 2015-04-08 | 山西汤荣机械制造股份有限公司 | A kind of mandrel device for grinding positioning sleeve |
| CN204366698U (en) * | 2014-12-11 | 2015-06-03 | 沭阳康顺磁性器材有限公司 | E shape core grinding clamp fixture |
| CN205817574U (en) * | 2016-04-11 | 2016-12-21 | 中电华元核电工程技术有限公司 | Nuclear power station piston check valve polishing jig holds positioner |
| CN206200732U (en) * | 2016-09-27 | 2017-05-31 | 上海宝钢工业技术服务有限公司 | For the specific purpose tool that valve element and sealing surface of seat grind |
-
2017
- 2017-09-13 CN CN201710820626.0A patent/CN107471082A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR200445915Y1 (en) * | 2009-02-13 | 2009-09-10 | 주식회사 아이제이피에스 | Lapping apparatus |
| CN102975111A (en) * | 2012-08-20 | 2013-03-20 | 广东肇庆微硕电子有限公司 | Grinding method and special device for soft magnetic ferrite magnetic cores |
| CN103100960A (en) * | 2012-12-28 | 2013-05-15 | 贵州航天控制技术有限公司 | Grinding device for shell body part |
| CN203156547U (en) * | 2012-12-28 | 2013-08-28 | 贵州航天控制技术有限公司 | Grinding device for casing part |
| CN203853873U (en) * | 2014-05-14 | 2014-10-01 | 河北大唐国际唐山热电有限责任公司 | Grinding device of steam inlet valve spool and grinding device of steam inlet valve seat |
| CN204248575U (en) * | 2014-09-23 | 2015-04-08 | 山西汤荣机械制造股份有限公司 | A kind of mandrel device for grinding positioning sleeve |
| CN204366698U (en) * | 2014-12-11 | 2015-06-03 | 沭阳康顺磁性器材有限公司 | E shape core grinding clamp fixture |
| CN205817574U (en) * | 2016-04-11 | 2016-12-21 | 中电华元核电工程技术有限公司 | Nuclear power station piston check valve polishing jig holds positioner |
| CN206200732U (en) * | 2016-09-27 | 2017-05-31 | 上海宝钢工业技术服务有限公司 | For the specific purpose tool that valve element and sealing surface of seat grind |
Non-Patent Citations (4)
| Title |
|---|
| "精密轴套研磨自动化 ", 《仪表技术与传感器》 * |
| 吕济柱等: "《机械设计与制造实训教程》", 31 August 2010 * |
| 方亚龙等: "圆柱轴、孔配合面的研磨工艺与研磨具 ", 《仪表技术与传感器》 * |
| 胡亚中: "莫氏锥体套规的内孔磨削和研磨 ", 《航空制造技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110076638A (en) * | 2019-06-05 | 2019-08-02 | 北京首钢冷轧薄板有限公司 | A kind of circle shear precision restorative procedure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108789060B (en) | Bilateral double-station power control belt sander and its polishing work station | |
| CN206296792U (en) | Mill ball core apparatus | |
| CN204602328U (en) | A kind of modified coating basket-type grinder | |
| CN106239346B (en) | A kind of valve clack of safety valve Magnetic-Fluid Grinding polishing machine and polishing method | |
| CN103769984B (en) | Abrasive belt grinder | |
| CN107471082A (en) | The lapping device and Ginding process of aircraft check valve | |
| CN206474988U (en) | A kind of two-sided polishing plank process equipment | |
| CN2930972Y (en) | Inner-cooling-type high speed thin film grinding head | |
| KR101265070B1 (en) | Polishing apparatus of ball | |
| CN108942700A (en) | A kind of hydraulic cylinder abrasive Flow Machining fixture | |
| CN208084106U (en) | A kind of finishing ring for polishing grinding equipment | |
| CN206982446U (en) | A kind of segment difference grinding machine processes auxiliary clamping device | |
| CN102729133A (en) | Wafer grinding device and wafer grinding method | |
| CN209190545U (en) | A kind of durable sanding and polishing flap wheel | |
| CN203566431U (en) | Multi-section simultaneous centerless grinding structure for same workpiece | |
| CN112676962A (en) | Grinding machine device for machining radiator | |
| CN205438040U (en) | Novel cone crusher welt is polished device | |
| CN206982440U (en) | Robot polishing start of adaptive spindle | |
| CN109848773A (en) | A kind of polissoir for bearing mnanufacture | |
| CN210147777U (en) | Desk-top case grinds machine | |
| CN217453331U (en) | Sealing surface grinding tool for valve core and valve seat in ball valve | |
| KR20160054120A (en) | Polishing device using magneto-rheological fluid | |
| CN206200729U (en) | A kind of valve clack of safety valve Magnetic-Fluid Grinding polishing machine | |
| CN201183218Y (en) | Rapid metallographic section grinding-polishing integrated equipment | |
| CN109452883A (en) | A kind of soybean refiner |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171215 |