CN208070046U - A kind of assembling jig of carbon fibre composite aircraft door - Google Patents
A kind of assembling jig of carbon fibre composite aircraft door Download PDFInfo
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- CN208070046U CN208070046U CN201820301784.5U CN201820301784U CN208070046U CN 208070046 U CN208070046 U CN 208070046U CN 201820301784 U CN201820301784 U CN 201820301784U CN 208070046 U CN208070046 U CN 208070046U
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Abstract
The utility model provides a kind of assembling jig of carbon fibre composite aircraft door, it is to assemble 5 metal joints on composite material hatch door by the form of glue riveting, and ensure relative position degree and concentricity of the castellated edge between the form accuracy and nipple orifice of 5 nipple orifices that it, which is acted on,.Pass through the assembling jig of the utility model, the high-precision that carbon fibre composite hatch door and metal joint may be implemented is assembled, avoid the relative position deviation caused by positioning and clamping form are unreasonable, or product caused by product state and state deviation after undercarriage are larger is sprung back when assembly and precision is overproof, meanwhile the form of tower structure combination positioning component has enough opening characters, can either ensure operating space, again so that structure simplifies as far as possible, manufacturing cost is reduced.
Description
Technical field
The utility model is related to a kind of assembling jigs of carbon fibre composite aircraft door.
Background technology
Carbon fibre composite is not only far above steel and aluminium because of its performance (specific strength, specific modulus, heat resistance and toughness etc.)
Etc. common structural material, also superior to fiberglass reinforced plastics, also it is widely used in aviation field, such as aircraft door,
Radome fairing, central wing box section etc., wherein aircraft door is usually complex-curved, and more with body matching part, and is general assembly
It is last assembly precision is often far above other component together, so, rationally designing carbon fibre composite assembling jig is
Determine the most important thing of entire door members manufacture.Currently, such assembling jig form mainly continues to use virgin metal door members
Assembling form, the problems such as having ignored the rebound of carbon fibre composite product, so that precision often occurs in the product after assembly
It is overproof, the problem of general assembly is difficult to coordinate.This not only adds development costs, also drastically influence project process.
Utility model content
The purpose of this utility model is to provide a kind of existing skill of assembling jig solution of carbon fibre composite aircraft door
The relative position deviation caused by positioning and clamping form are unreasonable present in art, or when because of assembly after product state and undercarriage
Product rebound and precision sideslip caused by state deviation is larger, meanwhile, and operation convenient for assembly, worker's working efficiency is improved,
And structure relative simplicity, reduce manufacturing cost.
The technical solution of utility model is：
A kind of assembling jig of carbon fibre composite aircraft door, including frame and positioning component one, positioning component two,
Positioning component three, positioning component four, positioning component five, positioning component six, positioning component seven, positioning component eight, positioning component nine,
Fabrication hole positioning component one, locating clamp plate component, compresses snap-gauge component at fabrication hole positioning component two, and frame is equipped with 4 benchmark
Hole fills each positioning component to adjust, and there are operating space, positioning component one, positioning component five, works between frame both sides and product
Skill hole positioning component one, fabrication hole positioning component two are all made of locator and handle positioning bolt, and position is fixed, can not
Dismounting, positioning component two, positioning component three, positioning component four are made of locating rack, locator and positioning bolt, bolt, wherein
Bolt, locator are detachable, and positioning component six, positioning component seven, positioning component eight, positioning component nine are all by positioning plate, spiral shell
Revolve locating rod, limiter, key, bearing, bolt, handwheel composition, dismantle after bolt can by rotation hand wheel by spiral positioning bar and
Positioning plate moves, and when product positions, reversely rotates handwheel after pin hole reaches designated position, is inserted into bolt, realizes that positioning plate is fixed
Bit function, locating clamp plate component and compression snap-gauge component are made of bearing, snap-gauge, dumpling drilling bolt, handle positioning bolt,
And snap-gauge can be rotated around top dumpling spot hole.
Further, positioning component one, positioning component two, positioning component three, positioning component four, positioning component five, technique
Hole positioning component one, fabrication hole positioning component two are all using face, hole positioning form, positioning component six, positioning component seven, positioning
Component eight, positioning component nine all use line, face positioning form, locating clamp plate component to use face positioning form.
Further, the location hole in locating component two is kidney slot, to solve because of carbon fibre composite system
The problem of product can not position in tooling caused by part technology hole position deviation.
Further, positioning component six, positioning component seven, there are 3mm uniform gaps, are padded with product tooth profile using 3mm
Piece detects.
Further, compressing snap-gauge, there are 4.5mm uniform gaps with product theory appearance profile, paste 5mm thickness silicon rubber
To compress while protect multiple material product injury-free.
Further, locating clamp plate and product type face contact position use zigzag, reduce contact area, avoid because of part or
Integral position deviates caused by single salient point.
When assembly, first, opens and compress snap-gauge, composite material hatch door is fixed by fabrication hole positioning component one, fabrication hole
Hyte part two, positioning component six, positioning component seven, positioning component eight, positioning component nine and snap-gauge positioning component are positioned,
It is secondary, product is fixed using compression snap-gauge component and C-type clamp, then, uses positioning component one, positioning component two, positioning component
Three, positioning component four, positioning component five position 5 metal joints, and carry out glue riveting operation, and finally, dismounting is fixed successively
The locator and bolt of hyte part one, positioning component five screw out positioning component six, positioning component seven, positioning component eight, positioning group
The spiral positioning bar of part nine dismantles the bolt of fabrication hole positioning component, opens and compresses snap-gauge and locating clamp plate and by product undercarriage.
The utility model has the beneficial effects that：By the assembling jig of the utility model, carbon fiber composite may be implemented
Expect that the high-precision of hatch door and metal joint is assembled, avoid the relative position deviation caused by positioning and clamping form are unreasonable,
Or product caused by product state and state deviation after undercarriage are larger is sprung back when assembly and precision is overproof.Meanwhile this assembly type
The operating space of frame form is open, and positioning and clamping device are simple to operate, can greatly improve the work effect of assembler
Rate reduces cost.
Description of the drawings
Fig. 1 is the structural schematic diagram of the utility model embodiment；
Fig. 2 is assembling jig structural schematic diagram when snap-gauge is opened；
Wherein：1- frames, 2- positioning components one, 3- positioning components two, 4- positioning components three, 5- positioning components four, 6- is fixed
Hyte part five, 7- positioning components six, 8- positioning components seven, 9- positioning components eight, 10 positioning components nine, 11- fabrication hole positioning groups
Part one, 12- fabrication holes positioning component two, 13- compress snap-gauge component, 14- locating clamp plate components.
Specific implementation mode
Further to illustrate that the utility model is to realize the predetermined purpose technological means and effect taken, please refer to
Under the detailed description and accompanying drawings in relation to utility model, it is believed that thus the purpose of this utility model, feature and feature can should obtain
Understand deeply and specifically, however, the drawings only provide reference and explanation, is not used for limiting the utility model.
Embodiment provides a kind of assembling jig of carbon fibre composite aircraft door, in very large range can be general,
Even if assembling the carbon fibre composite hatch door product of different model aircraft, as long as its basic structure is similar, this can be used
Utility model can not only ensure opposite position of the castellated edge between the form accuracy and nipple orifice of 5 nipple orifices
Precision and concentricity are set, and structure can be simplified to greatest extent, open working space reduces life to improve efficiency of assembling
Produce cost.
Embodiment
A kind of assembling jig of carbon fibre composite aircraft door：
As shown in Figure 1, Figure 2, including frame 1 and positioning component 1, positioning component 23, positioning component 34, positioning component 45,
Positioning component 56, positioning component 67, positioning component 78, positioning component 89, positioning component 9 10, fabrication hole positioning component one
11, fabrication hole positioning component 2 12, compression snap-gauge component 13, locating clamp plate component 14.
Frame 1 is equipped with 4 datum holes, and each positioning component is filled to adjust, and frame is welded by square type material and bloom, and two
There are the operating spaces 500mm between side and product, space is open.Positioning component 1, positioning component 56, fabrication hole positioning component
One 11, fabrication hole positioning component 2 12 is all made of locator and handle positioning bolt, and position is fixed, non-dismountable.It is fixed
Hyte part 23, positioning component 34, positioning component 45 are made of locating rack, locator and positioning bolt, bolt, wherein bolt,
Locator is detachable, facilitates product undercarriage.Locating clamp plate component 14 and compression snap-gauge component 13 are by bearing, snap-gauge, dumpling drilling
It is formed with bolt, handle positioning bolt, and snap-gauge can be rotated around top dumpling spot hole, and product is facilitated to load and unload.Positioning component 67 is determined
Hyte part 78, positioning component 89, positioning component 9 10 are by positioning plate, spiral positioning bar, limiter, key, bearing, bolt, hand
Spiral positioning bar and positioning plate can be moved 150mm by rotation hand wheel after dismantling bolt, facilitate product undercarriage, make by wheel composition
When part positions, handwheel also need to be only reversely rotated after pin hole reaches designated position, is inserted into bolt, realize positioning plate positioning function.
Positioning component 1, positioning component 23, positioning component 34, positioning component 45, positioning component 56, fabrication hole positioning component one
11, fabrication hole positioning component 2 12 be using face, hole positioning form, positioning component 67, positioning component 78, positioning component 89,
Positioning component 9 10 uses face positioning form using line, face positioning form, locating clamp plate component 14.In locating component 2 12
Location hole be kidney slot, to solve caused by carbon fibre composite product technology hole position deviation product without
The problem of method positions in tooling.Positioning component 67, positioning component 78, there are 3mm uniform gaps, make with product tooth profile
It is detected with 3mm gaskets.Compressing snap-gauge 13, there are 4.5mm uniform gaps with product theory appearance profile, paste 5mm thickness silicon rubber and use
To compress while protect multiple material product injury-free.Locating clamp plate 14 uses zigzag with product type face contact position, reduces contact
Area avoids the integral position caused by part or single salient point from deviating.Locating clamp plate 14 and compression snap-gauge 13 are all made of ZL104
Material, light weight, and do not damage product.
When assembly, first, opens and compress snap-gauge 13, composite material hatch door is passed through into fabrication hole positioning component 1, technique
Hole positioning component 2 12, positioning component 67, positioning component 78, positioning component 89, positioning component 9 10 and snap-gauge positioning component
14 are positioned, and secondly, are fixed product using compression snap-gauge component 13 and C-type clamp, then, use positioning component 1, positioning
56 pairs of component 23, positioning component 34, positioning component 45, positioning component 5 metal joints position, and carry out glue riveting behaviour
Make, finally, dismantles the locator and bolt of positioning component 1, positioning component 56 successively, screw out positioning component 67, positioning group
The spiral positioning bar of part 78, positioning component 89, positioning component 9 10, dismounting fabrication hole positioning component 1, fabrication hole positioning
The bolt of component 2 12 is opened and compresses snap-gauge 13 and locating clamp plate 14 and by product undercarriage.
The above, for those of ordinary skill in the art, can with technical solution according to the present utility model and
Technical concept makes other various corresponding change and deformations, and after all these change and distortions should all belong to the utility model
Attached scope of the claims.
Claims (6)
1. a kind of assembling jig of carbon fibre composite aircraft door, it is characterised in that：Including frame and positioning component one, determine
Hyte part two, positioning component four, positioning component five, positioning component six, positioning component seven, positioning component eight, is determined positioning component three
Hyte part nine, fabrication hole positioning component two, locating clamp plate component, compresses snap-gauge component at fabrication hole positioning component one, is set on frame
There are 4 datum holes, each positioning component is filled to adjust, there are operating space, positioning component one, positioning between frame both sides and product
Component five, fabrication hole positioning component one, fabrication hole positioning component two are all made of locator and handle positioning bolt, position
Fixed, non-dismountable, positioning component two, positioning component three, positioning component four are by locating rack, locator and positioning bolt, bolt
Composition, wherein bolt, locator are detachable, positioning component six, positioning component seven, positioning component eight, positioning component nine be all by
Positioning plate, spiral positioning bar, limiter, key, bearing, bolt, handwheel composition, dismantling can be by rotation hand wheel by spiral after bolt
Locating rod and positioning plate movement when product positions, reversely rotate handwheel after pin hole reaches designated position, are inserted into bolt, realize
Positioning plate positioning function, locating clamp plate component and compression snap-gauge component are positioned by bearing, snap-gauge, dumpling drilling bolt, handle
Bolt forms, and snap-gauge can be rotated around top dumpling spot hole.
2. the assembling jig of carbon fibre composite aircraft door as described in claim 1, it is characterised in that：Positioning component
One, positioning component two, positioning component three, positioning component four, positioning component five, fabrication hole positioning component one, fabrication hole positioning group
Part two is all using face, hole positioning form, and positioning component six, positioning component seven, positioning component eight, positioning component nine all use
Line, face positioning form, locating clamp plate component use face positioning form.
3. the assembling jig of carbon fibre composite aircraft door as described in claim 1, it is characterised in that：Locating group
Location hole in part two is kidney slot.
4. the assembling jig of carbon fibre composite aircraft door as described in claim 1, it is characterised in that：Positioning component
Six, there are uniform gaps with product tooth profile for positioning component seven.
5. the assembling jig of carbon fibre composite aircraft door as described in claim 1, it is characterised in that：Compress snap-gauge with
Product theory appearance profile pastes silicon rubber to compress the multiple material product of protection there are uniform gap.
6. the assembling jig of carbon fibre composite aircraft door as described in claim 1, it is characterised in that：Locating clamp plate with
Product type face contact position uses zigzag.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820301784.5U CN208070046U (en) | 2018-03-05 | 2018-03-05 | A kind of assembling jig of carbon fibre composite aircraft door |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820301784.5U CN208070046U (en) | 2018-03-05 | 2018-03-05 | A kind of assembling jig of carbon fibre composite aircraft door |
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| Publication Number | Publication Date |
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| CN208070046U true CN208070046U (en) | 2018-11-09 |
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| CN201820301784.5U Active CN208070046U (en) | 2018-03-05 | 2018-03-05 | A kind of assembling jig of carbon fibre composite aircraft door |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108382605A (en) * | 2018-03-05 | 2018-08-10 | 江苏恒神股份有限公司 | A kind of assembling jig of carbon fibre composite aircraft door |
| CN111251227A (en) * | 2020-03-16 | 2020-06-09 | 沈阳飞机工业（集团）有限公司 | Multi-hole coaxial assembling tool and assembling method for superhard beam parts |
| CN112340055A (en) * | 2020-09-30 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Column cardboard location assembly type frame |
-
2018
- 2018-03-05 CN CN201820301784.5U patent/CN208070046U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108382605A (en) * | 2018-03-05 | 2018-08-10 | 江苏恒神股份有限公司 | A kind of assembling jig of carbon fibre composite aircraft door |
| CN111251227A (en) * | 2020-03-16 | 2020-06-09 | 沈阳飞机工业（集团）有限公司 | Multi-hole coaxial assembling tool and assembling method for superhard beam parts |
| CN111251227B (en) * | 2020-03-16 | 2023-08-01 | 沈阳飞机工业（集团）有限公司 | Multi-hole coaxial assembly tool and assembly method for superhard beam parts |
| CN112340055A (en) * | 2020-09-30 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Column cardboard location assembly type frame |
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