CN200999095Y - Local expansion sample plate for airplane production - Google Patents
Local expansion sample plate for airplane production Download PDFInfo
- Publication number
- CN200999095Y CN200999095Y CNU2007200311256U CN200720031125U CN200999095Y CN 200999095 Y CN200999095 Y CN 200999095Y CN U2007200311256 U CNU2007200311256 U CN U2007200311256U CN 200720031125 U CN200720031125 U CN 200720031125U CN 200999095 Y CN200999095 Y CN 200999095Y
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- aircraft production
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Abstract
The utility model discloses a partial flat template used for the aircraft production, comprising a rectangular template body and four edges along the fringes of the template body. The template body is arranged with at least two location holes used for localizing the template body and a plurality of carrier holes used to ascertain the well location. This utility model has the advantages of simple structure and usableness. So, it can fully replace the existing shaping plate, hole guiding device and the threader so as to improve the production efficiency and ensure the working quality.
Description
Technical field
The utility model relates to the model that uses in a kind of Aircraft Production, and model is launched in particularly a kind of part that is used for Aircraft Production.
Background technology
At present, in home-built aircraft production, still adopt Muscovite manufacturing process, also continue to use and cut the brill model, perhaps when covering is cut edge with the casting die that falls, draw a line, wipe out surplus by the mould tire; When parts assemble, press figure paper size described point line, wipe out methods such as covering surplus.Not only setting-out work capacity of above-mentioned process is big, and production efficiency is low, and the product left and right sides of assembling out is asymmetric.In fitting process because the workman uses instruments such as hole guiding device, down-lead device, occur through regular meeting overproof, even the phenomenon that occurs scrapping.Cut bore model make complicated, cost is high, people seldom adopt in the production.
The utility model content
The purpose of this utility model is the deficiency that exists at prior art, provide a kind of simple in structure, easy to use, can guarantee that workmanship, the part that is used for Aircraft Production of enhancing productivity launch model.
The technical solution of the utility model is: model is launched in a kind of part that is used for Aircraft Production, it comprises rectangular plate body 1 and is positioned at four peripheries 4 at plate body 1 edge, it is characterized in that: be provided with two knock hole 2 and a plurality of guide holes 3 that are used for determining bore position that are used for plate body 1 location on the plate body 1 at least.
The utility model compared with prior art has the following advantages:
(1) the utility model is reasonable in design, simple in structure, easy to use, with low cost, can replace fully to cut to bore model, hole guiding device and down-lead device;
(2) realize that the aircraft assembling left and right sides is same, assembling is same with the side cut of skin part mould tire, and same type frame frame is same, has improved the presentation quality of product;
(3) make in aircraft assembling and the panel beating work and no longer get line ready, improved production efficiency, guaranteed product design;
(4) the utility model can replace the curved part of woollen sample making metal plate fully, therefore can save to cut and bore model and standard full pattern, thereby reduce frock cost 90%, part material 20%, save shaping time 50%, mill with panel beating and to bore guide hole in groups, the milling periphery bores the guide hole effect than assembler setting-out and improves 10 times.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
The specific embodiment
The utility model will be further described below in conjunction with accompanying drawing.
As shown in Figure 1, the utility model comprises rectangular plate body 1 and is positioned at four peripheries 4 at plate body 1 edge, is provided with two knock hole 2 and a plurality of guide holes 3 that are used for determining bore position that are used for plate body 1 location on the plate body 1 at least.
Described four peripheries 4 wherein one be covering cutting setting-out limit, its excess-three bar is skeleton part applying limit.
Described four peripheries 4 are skeleton part applying limit.
The diameter of knock hole 2 is 3.1mm, and the diameter of guide hole 3 is 2.1mm.
Plate body 1 is made by the quenching natrual ageing duralumin lath of thickness 1mm.
Principle of work of the present utility model is as follows: in present Aircraft Production, solution boring and side cut problem are the global shapes from aircraft, because double curved surface can not launch, must use in the production and cut the brill model, make Aircraft Production complicated.If local shape from aircraft, can find when cutting the covering fillet according to the skeleton in length and breadth of aircraft, these fillet coverings all are the single degree, the curvature of its Width can be ignored fully, the fillet covering of these single degree all can launch so, so invented the local model that launches of the utility model according to above-mentioned principle.
(1) when boring guide hole, can locate the local model that launches of the utility model by profile for the airframe part.Can't lead the hole of brill behind the covering can not bore when part is made assembling, during covering to be assembled, by leading the local model that launches of knock hole location the utility model that is drilled on the covering, bores by guide hole 3 then and makes remaining hole.
(2) the curved part of hyperbolic metal plate is realized launching model boring: because the curved part surface of the metal plate that cooperates with covering can be opened up, another joint face can be used as simple bending face, and is also deployable.Therefore, no matter be vertically or all available expansion model boring of the curved part of horizontal skeleton metal plate, cut edge, needn't use and cut the brill model.
(3) needn't draw dotted line by the mould bead wire for the covering or the casting die that falls, only need according to launching a model that model duplicate and be positioned at that setting-out gets final product on the mould tire by the utility model of assembling usefulness is local.Can guarantee the crash consistency that part is cut edge and assembling is cut edge thus.
(4) be used for parts assembling, setting-out: establishing adjacent two coverings is A and B, and A is dress earlier, adorns behind the B, and then the local model that launches of the utility model should be selected on the B.
When part was made, the decal that launches model according to the part of B was pruned the mating edge of A, not made allowance; Prune the mating edge of B and answer made allowance (optional surplus 20mm).
When parts assembled, model was launched in the utility model part of equipped covering A and B on the type frame earlier, and the local model that launches is by the knock hole location of having bored on the skeleton, and gap clearance is not more than 0.5mm.When dress covering B, take off the local model that launches of the utility model, behind the covering location, get out knock hole, by knock hole on the covering and 2 alignment of the knock hole on the model model is located on covering B, by the opposite joint sideline of drawing, the setting-out limit 4 of model, prune surplus then, guarantee to be not more than 1mm with the gap clearance of covering A.
Claims (5)
1, model is launched in a kind of part that is used for Aircraft Production, it comprises rectangular plate body (1) and is positioned at four peripheries (4) at plate body (1) edge, it is characterized in that: be provided with two knock hole (2) and a plurality of guide holes (3) that are used for determining bore position that are used for plate body (1) location on the plate body (1) at least.
2, model is launched in the part that is used for Aircraft Production according to claim 1, it is characterized in that: described four peripheries (4) wherein one for covering cuts the setting-out limit, its excess-three bar is skeleton part applying limit.
3, model is launched in the part that is used for Aircraft Production according to claim 1, and it is characterized in that: described four peripheries (4) are skeleton part applying limit.
4, model is launched in the part that is used for Aircraft Production according to claim 1, and it is characterized in that: the diameter of knock hole (2) is 3.1mm, and the diameter of guide hole (3) is 2.1mm.
5, model is launched in the part that is used for Aircraft Production according to claim 1, and it is characterized in that: plate body (1) is made by the rubber-like thin plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200311256U CN200999095Y (en) | 2007-01-30 | 2007-01-30 | Local expansion sample plate for airplane production |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200311256U CN200999095Y (en) | 2007-01-30 | 2007-01-30 | Local expansion sample plate for airplane production |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200999095Y true CN200999095Y (en) | 2008-01-02 |
Family
ID=39013502
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200311256U Expired - Fee Related CN200999095Y (en) | 2007-01-30 | 2007-01-30 | Local expansion sample plate for airplane production |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200999095Y (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102555240A (en) * | 2011-12-27 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Method for refining skin assembly positioning hole on composite material member |
| CN102658481A (en) * | 2012-04-17 | 2012-09-12 | 三一矿机有限公司 | Rivet welding device for vehicle frame accessories of mining dump truck and use method |
| CN102658378A (en) * | 2012-05-22 | 2012-09-12 | 西安飞机工业（集团）有限责任公司 | Drilling method for wall plate skin of airplane |
| CN103203733A (en) * | 2013-03-20 | 2013-07-17 | 沈阳飞机工业（集团）有限公司 | Design method of adding detachable templates |
| CN103203735A (en) * | 2013-04-24 | 2013-07-17 | 哈尔滨飞机工业集团有限责任公司 | Curved aluminum skin contour line-drawing method |
| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN107088868A (en) * | 2017-06-19 | 2017-08-25 | 江西洪都航空工业集团有限责任公司 | It is a kind of be used for from nacelle ecto-entad draw the frock in hole and its draw hole method |
| CN108422016A (en) * | 2018-03-02 | 2018-08-21 | 沈阳飞机工业（集团）有限公司 | A kind of design method of curved surface part drilling model |
| CN109591334A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | A kind of localization method of pair of honeycomb parts punching |
| CN110355819A (en) * | 2019-06-18 | 2019-10-22 | 成都飞机工业（集团）有限责任公司 | A kind of method for drilling of covering and skeleton connection structure |
-
2007
- 2007-01-30 CN CNU2007200311256U patent/CN200999095Y/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102555240A (en) * | 2011-12-27 | 2012-07-11 | 成都飞机工业（集团）有限责任公司 | Method for refining skin assembly positioning hole on composite material member |
| CN102658481A (en) * | 2012-04-17 | 2012-09-12 | 三一矿机有限公司 | Rivet welding device for vehicle frame accessories of mining dump truck and use method |
| CN102658481B (en) * | 2012-04-17 | 2016-04-13 | 三一矿机有限公司 | A kind of carriage of mining self-unloading vehicle annex rivet welding device and using method |
| CN102658378A (en) * | 2012-05-22 | 2012-09-12 | 西安飞机工业（集团）有限责任公司 | Drilling method for wall plate skin of airplane |
| CN103203733A (en) * | 2013-03-20 | 2013-07-17 | 沈阳飞机工业（集团）有限公司 | Design method of adding detachable templates |
| CN103203735B (en) * | 2013-04-24 | 2015-08-26 | 哈尔滨飞机工业集团有限责任公司 | A kind of scribble method of curved surface lead-covering profile |
| CN103203735A (en) * | 2013-04-24 | 2013-07-17 | 哈尔滨飞机工业集团有限责任公司 | Curved aluminum skin contour line-drawing method |
| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN103286767B (en) * | 2013-06-13 | 2015-09-09 | 沈阳飞机工业（集团）有限公司 | A kind of layout for drilling method of skin part |
| CN107088868A (en) * | 2017-06-19 | 2017-08-25 | 江西洪都航空工业集团有限责任公司 | It is a kind of be used for from nacelle ecto-entad draw the frock in hole and its draw hole method |
| CN108422016A (en) * | 2018-03-02 | 2018-08-21 | 沈阳飞机工业（集团）有限公司 | A kind of design method of curved surface part drilling model |
| CN109591334A (en) * | 2018-10-12 | 2019-04-09 | 江西昌河航空工业有限公司 | A kind of localization method of pair of honeycomb parts punching |
| CN109591334B (en) * | 2018-10-12 | 2021-04-30 | 江西昌河航空工业有限公司 | Positioning method for punching honeycomb part |
| CN110355819A (en) * | 2019-06-18 | 2019-10-22 | 成都飞机工业（集团）有限责任公司 | A kind of method for drilling of covering and skeleton connection structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080102 Termination date: 20110130 |