CN104260051A - Bushing compression tool for aircraft control surface butting tab - Google Patents
Bushing compression tool for aircraft control surface butting tab Download PDFInfo
- Publication number
- CN104260051A CN104260051A CN201410471093.6A CN201410471093A CN104260051A CN 104260051 A CN104260051 A CN 104260051A CN 201410471093 A CN201410471093 A CN 201410471093A CN 104260051 A CN104260051 A CN 104260051A
- Authority
- CN
- China
- Prior art keywords
- guide
- axis
- pin
- lining
- pressing plate
- 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.)
- Granted
Links
Classifications
-
- 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
- B25B27/06—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 inserting or withdrawing sleeves or bearing races
-
- 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
Abstract
The invention relates to a bushing compression tool for an aircraft control surface butting tab, and belongs to aircraft manufacture and assembly tools. The bushing compression tool comprises a guide shaft I, a positioning nut I, a bottom plate, a return spring I, a pressing plate, a pin I, an eccentric handle, a pin II, a return spring II, a positioning nut II and a guide shaft II, wherein the guide shaft I and the guide shaft II are fixed onto the eccentric handle through the pin I and the pin II respectively, and the pressing plate, the return spring I, the return spring II and the bottom plate penetrate the guide shaft I and the guide shaft II. The special tool replaces manual operation, the labor amount of workers is reduced, the probability of bumping aircraft parts and damaging a bushing is decreased, and bushing assembly quality and production efficiency are improved.
Description
Technical field
The present invention relates to a kind of lining compaction tool for aircraft rudder surface docking auricle place, belong to aircraft manufacturing and assembly tool.
Background technology
Aircraft wing connects the auricle place of connecing at wing flap, aileron etc. and all have employed a large amount of linings, and the locational space of lining installation place is narrow and small, and the convenience that therefore lining is installed must solve.Current wing flap, aileron place auricle mounting bush adopts workman to beat installation by hand, does not have special erecting tools, and manual installation method inconvenient operation is lost time, and also easily causes piece surface to scratch, causes harmful effect to product quality.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide a kind of lining compaction tool for aircraft rudder surface docking auricle place, facilitate the lining of small space to compress, and instrument using simply, conveniently, operating effect is good.
To achieve these goals, the present invention adopts following technical scheme:
For the lining compaction tool at aircraft rudder surface docking auricle place, it comprises the axis of guide I, setscrew nut I, base plate, back-moving spring I, pressing plate, pin I, eccentric handle, pin II, back-moving spring II, setscrew nut II, the axis of guide II;
The axis of guide I, the axis of guide II are fixed in eccentric handle respectively by pin I and pin II;
By pressing plate, back-moving spring I, back-moving spring II and base plate through the axis of guide I and the axis of guide II.
Setscrew nut I, setscrew nut II are arranged on the junction of the axis of guide I, the axis of guide II and base plate bottom surface respectively.
Substrate has pilot hole and a dismounting hole larger than Outer Diameter of lining.
Pressing plate middle section thickness be less than lining put into auricle open grade place after surplus and width is greater than auricle width, there is the locating shaft being slightly less than bushing inner diameter at center, and pressing plate surrounding is boss, and has pilot hole on boss.
The eccentric cylinder that during this tool assemble, the axis of guide is fixed on eccentric handle by pin can freely rotate, pressing plate and base plate pass the axis of guide by the pilot hole of self, back-moving spring is housed between the two, adjusts spacing between pressing plate and base plate to adapt to the auricle of the different-thickness in certain limit finally by setscrew nut.
Beneficial effect of the present invention
The present invention replaces manual operations by specific purpose tool, decrease the amount of labour of workman, decrease the probability of damage airplane parts and damage lining, improve quality and the production efficiency of lining assembling, and the lining that instrument can meet different-thickness auricle in certain limit is installed, decrease the quantity of specific purpose tool, and when old lining changed by needs, can directly by new lining press-in hole, old lining be discharged from the dismounting hole below floor by this instrument.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the facade structures schematic diagram of center platen of the present invention;
Fig. 3 is the facade structures schematic diagram of base plate in the present invention;
Fig. 4 is that the present invention prepares using state schematic diagram;
Fig. 5 is that completion status of the present invention uses schematic diagram.
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing 1 ~ 5:
For the lining compaction tool at aircraft rudder surface docking auricle place, it comprises the axis of guide I 1, setscrew nut I 2, base plate 3, back-moving spring I 4, pressing plate 5, pin I 6, eccentric handle 7, pin II 8, back-moving spring II 9, setscrew nut II 10, the axis of guide II 11;
The axis of guide I 1, the axis of guide II 11 are fixed in eccentric handle 7 respectively by pin I 6 and pin II 8;
By pressing plate 5, back-moving spring I 4, back-moving spring II 9 and base plate 3 through the axis of guide I (1) and the axis of guide II 11.
Setscrew nut I 2, setscrew nut II 10 are arranged on the junction of the axis of guide I 1, the axis of guide II 11 and base plate 3 bottom surface respectively.
Base plate 3 has above pilot hole 31 and a dismounting hole 32 larger than Outer Diameter of lining.
Pressing plate 5 middle section thickness be less than lining put into auricle open grade place after surplus and width is greater than auricle width, there is the locating shaft 51 being slightly less than bushing inner diameter at center, and pressing plate surrounding is boss 52, and has pilot hole 53 on boss 52.
When using this compactor, first lining is fixed on the locating shaft 51 on pressing plate (as Fig. 2), compactor is stretched into (as Fig. 4) in auricle afterwards, lining is aimed at behind pressure hole, eccentric handle hand propelled band dynamic pressure plate is moved down, completes the compression work (as Fig. 5) of lining, after release lever, pressing plate has been lifted reset by back-moving spring, now compactor can be shifted out and prepare lower task.As repeated above-mentioned work when more need renew lining, new lining can by old lining from the dismounting hole 32(base plate as Fig. 3), complete more changing jobs of lining.
Claims (4)
1. for aircraft rudder surface docking auricle place a lining compaction tool, it is characterized in that: it comprise the axis of guide I (1), setscrew nut I (2), base plate (3), back-moving spring I (4),
Pressing plate (5), pin I (6), eccentric handle (7), pin II (8), back-moving spring II (9),
Setscrew nut II (10), the axis of guide II (11);
The axis of guide I (1), the axis of guide II (11) are fixed in eccentric handle (7) respectively by pin I (6) and pin II (8);
By pressing plate (5), back-moving spring I (4), back-moving spring II (9) and base plate (3) through the axis of guide I (1) and the axis of guide II (11).
2. the lining compaction tool for aircraft rudder surface docking auricle place according to claim 1, is characterized in that: setscrew nut I (2), setscrew nut II (10) are arranged on the junction of the axis of guide I (1), the axis of guide II (11) and base plate (3) bottom surface respectively.
3. the lining compaction tool for aircraft rudder surface docking auricle place according to claim 1, is characterized in that: base plate (3) has above pilot hole (31) and a dismounting hole (32) larger than Outer Diameter of lining.
4. the lining compaction tool for aircraft rudder surface docking auricle place according to claim 1, it is characterized in that: pressing plate (5) middle section thickness be less than lining put into auricle open grade place after surplus and width is greater than auricle width, there is the locating shaft (51) being slightly less than bushing inner diameter at center, pressing plate surrounding is boss (52), and has pilot hole (53) on boss (52).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471093.6A CN104260051B (en) | 2014-09-17 | 2014-09-17 | A kind of lining compaction tool for aircraft rudder surface docking auricle place |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471093.6A CN104260051B (en) | 2014-09-17 | 2014-09-17 | A kind of lining compaction tool for aircraft rudder surface docking auricle place |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104260051A true CN104260051A (en) | 2015-01-07 |
| CN104260051B CN104260051B (en) | 2016-02-10 |
Family
ID=52151695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410471093.6A Active CN104260051B (en) | 2014-09-17 | 2014-09-17 | A kind of lining compaction tool for aircraft rudder surface docking auricle place |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104260051B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112621648A (en) * | 2020-12-15 | 2021-04-09 | 中建八局第三建设有限公司 | Building aluminum membrane plate pin plate dismantling tool |
| GB2588658A (en) * | 2019-10-31 | 2021-05-05 | Airbus Operations Ltd | Aircraft assembly tool |
| CN114833743A (en) * | 2022-04-26 | 2022-08-02 | 南京合信自动化有限公司 | Bottom plate assembly turnover mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2244980Y (en) * | 1995-04-13 | 1997-01-15 | 邓坚 | Blind hole bearing draw-off gear |
| CN2251467Y (en) * | 1994-09-14 | 1997-04-09 | 南昌铁路分局南昌车辆段 | Device for automatic withdrawing rolling bearing internal race for rolling stock |
| US5653011A (en) * | 1995-09-05 | 1997-08-05 | Collins; Brian Edward | Fixture for replacing a bearing |
| US5664328A (en) * | 1994-02-28 | 1997-09-09 | Westinghouse Electric Corporation | Tool for removing a metallic plug from a tube |
| US6182353B1 (en) * | 1996-03-11 | 2001-02-06 | Rexnord Corporation | Swaging tool for bearing installation |
| CN204076178U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of lining compaction tool for aircraft rudder surface docking auricle place |
-
2014
- 2014-09-17 CN CN201410471093.6A patent/CN104260051B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5664328A (en) * | 1994-02-28 | 1997-09-09 | Westinghouse Electric Corporation | Tool for removing a metallic plug from a tube |
| CN2251467Y (en) * | 1994-09-14 | 1997-04-09 | 南昌铁路分局南昌车辆段 | Device for automatic withdrawing rolling bearing internal race for rolling stock |
| CN2244980Y (en) * | 1995-04-13 | 1997-01-15 | 邓坚 | Blind hole bearing draw-off gear |
| US5653011A (en) * | 1995-09-05 | 1997-08-05 | Collins; Brian Edward | Fixture for replacing a bearing |
| US6182353B1 (en) * | 1996-03-11 | 2001-02-06 | Rexnord Corporation | Swaging tool for bearing installation |
| CN204076178U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of lining compaction tool for aircraft rudder surface docking auricle place |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2588658A (en) * | 2019-10-31 | 2021-05-05 | Airbus Operations Ltd | Aircraft assembly tool |
| GB2588658B (en) * | 2019-10-31 | 2022-04-20 | Airbus Operations Ltd | Aircraft flight control surface guide assembly tool |
| CN112621648A (en) * | 2020-12-15 | 2021-04-09 | 中建八局第三建设有限公司 | Building aluminum membrane plate pin plate dismantling tool |
| CN112621648B (en) * | 2020-12-15 | 2022-04-19 | 中建八局第三建设有限公司 | Building aluminum membrane plate pin plate dismantling tool |
| CN114833743A (en) * | 2022-04-26 | 2022-08-02 | 南京合信自动化有限公司 | Bottom plate assembly turnover mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104260051B (en) | 2016-02-10 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |