CN104760020A - Detachment and installation device for close fit part and detachment and installation method - Google Patents
Detachment and installation device for close fit part and detachment and installation method Download PDFInfo
- Publication number
- CN104760020A CN104760020A CN201510172701.8A CN201510172701A CN104760020A CN 104760020 A CN104760020 A CN 104760020A CN 201510172701 A CN201510172701 A CN 201510172701A CN 104760020 A CN104760020 A CN 104760020A
- Authority
- CN
- China
- Prior art keywords
- fit part
- tight fit
- bolt
- nut
- installing hole
- 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
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
- B25B27/023—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same using screws
Abstract
The invention relates to the technical field of aircraft component manufacturing, discloses a detachment and installation device for a close fit part and a detachment and installation method and aims at solving the problems that at present, when the close fit part is installed in or taken out, time and labor are wasted, and an aircraft body and the part are prone to being damaged. The detachment and installation device for the close fit part comprises a circular supporting plate, an annular gasket and a bolt and a nut which are matched with each other, wherein a through hole is formed in the center of the circular supporting plate, the outer diameter of the annular gasket is less than the diameter of the supporting plate, the inner diameter of the annular gasket is not less than the diameter of an installing hole of the aircraft body, and the height of the annular gasket is not less than that of the close fit part. According to the device, the bolt and the nut are adopted, no vibration or knocking noise occurs, the observation is facilitated in the operation process, the controllability is good, and the aircraft body and the part can not be damaged by knocking.
Description
Technical field
The present invention relates to aircraft components manufacturing technology field, relate to a kind of attaching/detaching apparatus and assembly and disassembly methods of tight fit part.
Background technology
On airframe, a lot of place needs to use tight fit part, such as sleeve, packing ring etc.At present, the loading of tight fit part or taking-up, when not having or be inconvenient to use press device, often taking the mode of knocking to carry out, not only wasting time and energy, and easily cause the damage of body and part, also may produce injury to operating personnel.
Summary of the invention
The object of the present invention is to provide a kind of attaching/detaching apparatus and assembly and disassembly methods of tight fit part, solving current tight fit part when loading or take out, wasting time and energy and easily causing the problem of body and part injury.
A kind of tight fit part attaching/detaching apparatus provided by the invention, for the described tight fit part removed on airframe in installing hole or install in described installing hole by described tight fit part, described tight fit part is circular, and described attaching/detaching apparatus comprises:
Circular base slab, center position offers through hole;
Circular packing ring, external diameter is less than the diameter of described gripper shoe, and internal diameter is not less than the diameter of described installing hole, and is highly not less than the height of described tight fit part;
Bolt, the screw diameter of described bolt is not more than the diameter of through hole in described gripper shoe and the internal diameter of described tight fit part;
Nut, matches with described bolt, and the external diameter of described nut is greater than the diameter of through hole in described gripper shoe and the internal diameter of described tight fit part.
Alternatively, described gripper shoe and described packing ring are formed in one structure, and described gripper shoe is positioned at the axial end portion of described packing ring.
Present invention also offers a kind of method for dismounting of tight fit part, for the described tight fit part that will remove on airframe in installing hole, adopt the tight fit part attaching/detaching apparatus described in above-mentioned any one, described method for dismounting comprises the steps:
Step one, by described bolt from described body side through the endoporus of described tight fit part, and to pass from opposite side;
Step 2, pass the described bolt of described body opposite side, more successively through the endoporus of described packing ring and the through hole of described gripper shoe, be finally connected with described nut, wherein, described packing ring and described tight fit part are coaxially arranged;
Step 3, the nut rotating described bolt or described nut, until described tight fit part exits completely by described bolt in installing hole described body.
Present invention also offers a kind of installation method of tight fit part, for described tight fit part is installed on airframe in installing hole, adopt described in above-mentioned any one tight fit part attaching/detaching apparatus, described installation method comprises the steps:
Step one, described bolt is penetrated the endoporus of described tight fit part from side, and pass from opposite side;
Step 2, pass the described bolt of described tight fit part opposite side, again successively through installing hole, the endoporus of described packing ring and the through hole of described gripper shoe on described body, finally be connected with described nut, wherein, described tight fit part is coaxial with installing hole on described body;
Step 3, the nut rotating described bolt or described nut, until described tight fit part to be press fit on described body in installing hole by described bolt completely.
Beneficial effect of the present invention:
The attaching/detaching apparatus of tight fit part provided by the invention and assembly and disassembly methods, the mode of employing bolts and nuts, friction and knocking noise, be convenient to limit observation in operating process and controllability is good, can not cause knock damage to body and part.In addition, owing to not needing to make electrical installation, therefore there is not dependent loss, the dry sound of equipment and safety problem, and low to the skill set requirements of personnel, cost is low.
Accompanying drawing explanation
Fig. 1 is the attaching/detaching apparatus using state schematic diagram of tight fit part of the present invention.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As shown in Figure 1, tight fit part attaching/detaching apparatus of the present invention, for the described tight fit part 5 removed on airframe 6 in installing hole or install in described installing hole by described tight fit part 5, tight fit part 5 is usually in circular.
Tight fit part attaching/detaching apparatus comprises gripper shoe 1, packing ring 2, bolt 3 and nut 4 etc.
Particularly, gripper shoe 1 is rounded, and can adopt how many material be applicable to, and such as steel or timber etc., its center position offers through hole.Packing ring 2 is in circular, and external diameter is less than the diameter of gripper shoe 1, and internal diameter is not less than the diameter of installing hole, and is highly not less than the height of tight fit part 5.Further, gripper shoe 1 and packing ring 2 can be integrated formed structures, and wherein, gripper shoe 1 is positioned at the axial end portion of packing ring 2, to save manufacturing procedure and cost.
The screw diameter of bolt 3 is not more than the diameter of through hole in gripper shoe 1 and the internal diameter of tight fit part 5.Nut 4 and bolt 3 match, and the external diameter of nut 4 is greater than the diameter of through hole in gripper shoe 1 and the internal diameter of tight fit part 5.
Present invention also offers a kind of method for dismounting of tight fit part, adopt above-mentioned tight fit part attaching/detaching apparatus, for the described tight fit part 5 that will remove on airframe 6 in installing hole, concrete method for dismounting comprises the steps:
Step one, by bolt 3 from body 6 side through the endoporus of tight fit part 5, and to pass from opposite side;
Step 2, pass the described bolt 3 of body 6 opposite side, more successively through the endoporus of packing ring 2 and the through hole of gripper shoe 1, finally be connected with nut 4, wherein, packing ring 2 and described tight fit part 5 are coaxially arranged;
The nut of step 3, swivel bolt 3 or nut 4, until tight fit part 5 exits completely by bolt 3 in installing hole body 6.
Present invention also offers a kind of installation method of tight fit part, adopt above-mentioned tight fit part attaching/detaching apparatus, for being installed on airframe 6 in installing hole by tight fit part 5, concrete installation method comprises the steps:
Step one, bolt 3 is penetrated the endoporus of tight fit part 5 from side, and pass from opposite side;
Step 2, pass the bolt 3 of tight fit part 5 opposite side, more successively through installing hole, the endoporus of packing ring 2 and the through hole of gripper shoe 1 on body 6, be finally connected with nut 4, wherein, tight fit part 5 is coaxial with installing hole on body 6;
The nut of step 3, swivel bolt 3 or nut 4, until tight fit part 5 to be press fit on body 6 in installing hole by bolt 3 completely.
The attaching/detaching apparatus of tight fit part provided by the invention and assembly and disassembly methods, the mode of employing bolt 3 and nut 4, friction and knocking noise, be convenient to limit observation in operating process and controllability is good, pinpoint the problems and can stop immediately, can not cause body and part and knock damage.Further, do not need to make electrical installation, there is not dependent loss, the dry sound of equipment and safety problem, low to the skill set requirements of personnel, cost is also low.In addition, the structure of attaching/detaching apparatus is simple, be convenient to take and operate, and the restriction by place and operating space is little, especially uses with the obvious advantage on outfield or machine
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (4)
1. a tight fit part attaching/detaching apparatus, go up the described tight fit part (5) in installing hole for removing airframe (6) or described tight fit part (5) is installed in described installing hole, described tight fit part (5) is in circular, it is characterized in that, described attaching/detaching apparatus comprises:
Circular base slab (1), center position offers through hole;
Circular packing ring (2), external diameter is less than the diameter of described gripper shoe (1), and internal diameter is not less than the diameter of the upper installing hole of described body (6), and is highly not less than the height of described tight fit part (5);
Bolt (3), the screw diameter of described bolt (3) is not more than the upper diameter of through hole of described gripper shoe (1) and the internal diameter of described tight fit part (5);
Nut (4), matches with described bolt (3), and the external diameter of described nut (4) is greater than the upper diameter of through hole of described gripper shoe (1) and the internal diameter of described tight fit part (5).
2. tight fit part attaching/detaching apparatus according to claim 1, it is characterized in that, described gripper shoe (1) and described packing ring (2) are formed in one structure, and described gripper shoe (1) is positioned at the axial end portion of described packing ring (2).
3. the method for dismounting of a tight fit part, for the described tight fit part (5) in the upper installing hole of airframe (6) will be removed, it is characterized in that, adopt the tight fit part attaching/detaching apparatus described in claim 1 or 2, described method for dismounting comprises the steps:
Step one, by described bolt (3) from described body (6) side through the endoporus of described tight fit part (5), and to pass from opposite side;
Step 2, pass the described bolt (3) of described body (6) opposite side, again successively through the endoporus of described packing ring (2) and the through hole of described gripper shoe (1), finally be connected with described nut (4), wherein, described packing ring (2) and described tight fit part (5) are coaxially arranged;
Step 3, the nut rotating described bolt (3) or described nut (4), until described tight fit part (5) is exited completely by described bolt (3) in installing hole described body (6).
4. the installation method of a tight fit part, for described tight fit part (5) being installed in the upper installing hole of airframe (6), it is characterized in that, adopt the tight fit part attaching/detaching apparatus described in claim 1 or 2, described installation method comprises the steps:
Step one, described bolt (3) is penetrated the endoporus of described tight fit part (5) from side, and pass from opposite side;
Step 2, pass the described bolt (3) of described tight fit part (5) opposite side, again successively through described body (6) upper installing hole, the endoporus of described packing ring (2) and the through hole of described gripper shoe (1), finally be connected with described nut (4), wherein, described tight fit part (5) is coaxial with the upper installing hole of described body (6);
Step 3, the nut rotating described bolt (3) or described nut (4), until described tight fit part (5) is press fit in the upper installing hole of described body (6) by described bolt (3) completely.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510172701.8A CN104760020A (en) | 2015-04-13 | 2015-04-13 | Detachment and installation device for close fit part and detachment and installation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510172701.8A CN104760020A (en) | 2015-04-13 | 2015-04-13 | Detachment and installation device for close fit part and detachment and installation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104760020A true CN104760020A (en) | 2015-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510172701.8A Pending CN104760020A (en) | 2015-04-13 | 2015-04-13 | Detachment and installation device for close fit part and detachment and installation method |
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| CN (1) | CN104760020A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3443249A1 (en) * | 1984-11-23 | 1986-06-05 | Franc 1000 Berlin Kroselj | Device for removing and fitting rolling-contact bearings |
| JPH0890445A (en) * | 1994-09-28 | 1996-04-09 | Hitachi Building Syst Eng & Service Co Ltd | Bearing member press fitting device |
| CN202592311U (en) * | 2012-04-13 | 2012-12-12 | 哈尔滨飞机工业集团有限责任公司 | Bush dismounting device |
| CN202862137U (en) * | 2012-10-02 | 2013-04-10 | 中国石油化工股份有限公司胜利油田分公司孤岛采油厂 | Crank pin lining extractor |
| CN103317475A (en) * | 2013-06-27 | 2013-09-25 | 开平市盈光机电科技有限公司 | Mechanism for assembling and disassembling bearing of injection molding machine |
| CN203357381U (en) * | 2013-06-27 | 2013-12-25 | 开平市盈光机电科技有限公司 | Mechanism for assembling and disassembling bearing of injection molding machine |
| CN203696917U (en) * | 2014-01-08 | 2014-07-09 | 哈尔滨飞机工业集团有限责任公司 | Lining press-fitting tool |
-
2015
- 2015-04-13 CN CN201510172701.8A patent/CN104760020A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3443249A1 (en) * | 1984-11-23 | 1986-06-05 | Franc 1000 Berlin Kroselj | Device for removing and fitting rolling-contact bearings |
| JPH0890445A (en) * | 1994-09-28 | 1996-04-09 | Hitachi Building Syst Eng & Service Co Ltd | Bearing member press fitting device |
| CN202592311U (en) * | 2012-04-13 | 2012-12-12 | 哈尔滨飞机工业集团有限责任公司 | Bush dismounting device |
| CN202862137U (en) * | 2012-10-02 | 2013-04-10 | 中国石油化工股份有限公司胜利油田分公司孤岛采油厂 | Crank pin lining extractor |
| CN103317475A (en) * | 2013-06-27 | 2013-09-25 | 开平市盈光机电科技有限公司 | Mechanism for assembling and disassembling bearing of injection molding machine |
| CN203357381U (en) * | 2013-06-27 | 2013-12-25 | 开平市盈光机电科技有限公司 | Mechanism for assembling and disassembling bearing of injection molding machine |
| CN203696917U (en) * | 2014-01-08 | 2014-07-09 | 哈尔滨飞机工业集团有限责任公司 | Lining press-fitting tool |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20150708 |