CN109774194A - A kind of integrally formed tooling of composite material fuselage covering and its moulding process - Google Patents
A kind of integrally formed tooling of composite material fuselage covering and its moulding process Download PDFInfo
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- CN109774194A CN109774194A CN201910249693.0A CN201910249693A CN109774194A CN 109774194 A CN109774194 A CN 109774194A CN 201910249693 A CN201910249693 A CN 201910249693A CN 109774194 A CN109774194 A CN 109774194A
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- 239000002131 composite material Substances 0.000 title claims abstract description 91
- 238000000034 method Methods 0.000 title claims abstract description 33
- 230000008569 process Effects 0.000 title claims abstract description 21
- 238000000465 moulding Methods 0.000 title abstract description 14
- 238000007711 solidification Methods 0.000 claims abstract description 35
- 230000008023 solidification Effects 0.000 claims abstract description 33
- 238000004519 manufacturing process Methods 0.000 claims abstract description 18
- 230000030570 cellular localization Effects 0.000 claims description 65
- 230000006835 compression Effects 0.000 claims description 12
- 238000007906 compression Methods 0.000 claims description 12
- 238000005056 compaction Methods 0.000 claims description 9
- 238000010792 warming Methods 0.000 claims description 9
- 239000011230 binding agent Substances 0.000 claims description 8
- 239000004744 fabric Substances 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 4
- 238000007731 hot pressing Methods 0.000 claims description 4
- 230000001680 brushing effect Effects 0.000 claims description 3
- 230000008859 change Effects 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 description 14
- 239000007767 bonding agent Substances 0.000 description 10
- 238000009434 installation Methods 0.000 description 6
- 230000001413 cellular effect Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 239000002023 wood Substances 0.000 description 3
- 239000011157 advanced composite material Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013036 cure process Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000003698 laser cutting Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a kind of integrally formed tooling of composite material fuselage covering and its moulding process, are related to unmanned plane technical field of composite material manufacturing, including frame and tooling template；The both ends fixation that mounting groove, two mounting groove arranged relatives, and tooling template are offered on two opposite faces of the frame is fastened on two mounting grooves；Two groups of detachable loose pieces are also equipped in the frame upper surface, two groups of detachable loose pieces are located at the two sides of tooling template, the medial surface of two groups of detachable loose pieces and the working face of tooling template form a continuous surface, and two groups of detachable loose pieces and tooling template constitute solidification chamber.The present invention realizes the molding of deep camber composite material unmanned aerial vehicle body covering entirety with special process in conjunction with special tooling.
Description
Technical field
The present invention relates to unmanned plane technical field of composite material manufacturing, cover in particular to a kind of composite material fuselage
The integrally formed tooling of skin and its moulding process.
Background technique
Advanced composite material is with light-weight, intensity is high, specific stiffness is high, designability is strong, fatigue crack-resistant is good, corrosion resistant
The advantages that erosion, good stability of the dimension；Meanwhile part and fastener quantity can be greatly reduced using integration manufacturing technology,
Construction weight is reduced, production cost is reduced, therefore, current most unmanned aerial vehicle body covering is all made of advanced composite material system
At.
Currently, the mold used during fuselage skin is integrally formed is more complex, for integration honeycomb sandwich construction technique side
Method has co-curing and second bonding；But in co-curing reaction, Resin Flow is very good, which to will cause gummosis excessively, causes panel poor
Glue, and briquetting pressure is excessive will cause the smaller panel defect and weak of will lead to of top panel recess, honeycomb unstability, sliding, and pressure
It is glued, is difficult to be controlled so as to cause the yield rate of fuselage skin.
Therefore, it is proposed that a kind of integrally formed tooling of composite material fuselage covering that can solve the above problem and its molding work
Skill.
Summary of the invention
The purpose of the present invention is to provide a kind of integrally formed tooling of composite material fuselage covering and its moulding process, with solution
The certainly above problem.
Purpose to realize the present invention, the technical solution of use are as follows: a kind of integrally formed tooling of composite material fuselage covering, packet
Include frame and tooling template；Mounting groove, two mounting groove arranged relatives, and work are offered on two opposite faces of the frame
The both ends fixation of dress template is fastened on two mounting grooves；It is also equipped with two groups of detachable loose pieces in the frame upper surface, two
The detachable loose piece of group is located at the two sides of tooling template, the medial surface of two groups of detachable loose pieces and the working face shape of tooling template
At a continuous surface, two groups of detachable loose pieces and tooling template constitute solidification chamber.
Further, detachable loose piece described in every group includes multiple detachable loose pieces successively closely arranged.
Further, the two sides of the tooling template are provided with along platform, and two are each attached to the top surface of frame along platform.
Further, the tooling template is integrally formed with Yan Tai.
Further, detachable loose piece described in two groups is separately mounted to two along platform.
Further, the bottom of the frame is also equipped with the wheel of multiple rotations.
Further, multiple hanging rings are additionally provided on the frame.
Further, the both ends of the tooling template are also equipped with dismountable locator.
A kind of composite material fuselage covering integral forming technique, specifically comprises the following steps:
(1) prepreg laying cellular localization sample making: is being solidified into composite material intracavitary, and that laying is had to prepreg
The integrally formed tooling of fuselage skin is sent in autoclave, solidifies the prepreg of laying；After prepreg solidification, by composite wood
The material integrally formed tooling of fuselage skin is taken out out of autoclave, and the prepreg after solidification is whole from composite material fuselage covering
Forming frock is removed, and cellular localization template is formed；
(2) prepare before part production: solidifying intracavitary brushing release agent, cutting exterior skin tablet, inside panel tablet；It will step
Cellular localization template obtained is cut in rapid 1, forms cellular localization plate；And cellular localization plate surface is pasted into release cloth；
(3) exterior skin forms: exterior skin tablet laying obtained in step 2 is intracavitary in solidification, will and laying be had outer
The integrally formed tooling of composite material fuselage covering of covering tablet is sent in autoclave, solidifies the exterior skin tablet of laying；
Exterior skin tablet after solidification is removed from the integrally formed tooling of composite material fuselage covering, exterior skin is made；
(4) honeycomb laying: attached first layer binder is brushed on exterior skin inner surface obtained in step 3；It will be made in step 2
The cellular localization plate obtained is placed on exterior skin, and projects honeycomb using laser-projector, and it is accurately fixed to carry out to cellular localization plate
Position；At this point, passing through the positioning of cellular localization plate, honeycomb is laid on exterior skin, the composite machine after last laying honeycomb
The integrally formed tooling of body covering is sent into hot compaction in autoclave；By the integrally formed tooling of composite material fuselage covering after hot compaction
It takes out, and cellular localization plate is removed from the integrally formed tooling of composite material fuselage covering, and in cell out of autoclave
With attached second layer binder is brushed in non-cellular area；The integrally formed tooling of composite material fuselage covering is finally fed again into autoclave
Interior pre-compacted；
(5) integrally formed: the integrally formed tooling of composite material fuselage covering in step 4 is taken out from autoclave,
It is laid with inside panel tablet on honeycomb, and has the integrally formed tooling of composite material fuselage covering of inside panel tablet to be sent to laying
Solidified in autoclave, is finally taken out the integrally formed tooling of composite material fuselage covering from autoclave, and by composite material
Covering is formed in the integrally formed tooling of fuselage skin to remove.
Further, integrally formed in the composite material fuselage covering that will be placed with exterior skin tablet in the step 3
Tooling is being sent into autoclave in solidification process, first to be evacuated to -0.7Bar in autoclave hereinafter, and with less than 1.5 DEG C/
The speed of min is warming up to 80 DEG C ± 5 DEG C；And while heating, autoclave is forced into the compression rate of 0.5Bar/min
It is passed through atmosphere when 1.0Bar, and continues to be forced into 5.0Bar ± 0.2Bar with the compression rate of 0.5Bar/min.
Further, in the step 5, laying is had to the integrally formed work of composite material fuselage covering of inside panel tablet
Dress, which is sent in autoclave, to carry out first being evacuated to -0.28Bar~-0.34Bar to autoclave, and to be less than in solidification process
The speed of 1.5 DEG C/min is warming up to 80 DEG C ± 5 DEG C；While heating, autoclave is added with the compression rate of 0.5Bar/min
It is passed through atmosphere when being depressed into 1.0Bar, and continues to be forced into 3.0Bar ± 0.2Bar with the compression rate of 0.5Bar/min.
Further, in the step 3 and step 5, exterior skin tablet and inside panel tablet in the curing process, first will
Temperature rises to 80 DEG C ± 5 DEG C in autoclave, and makes to keep first time constant temperature in autoclave, and first time constant temperature time is 20min
~25min；After first time constant temperature, 130 DEG C ± 5 DEG C are warming up to the speed less than 1.5 DEG C/min, starts second of perseverance
Temperature is 100min~120min when second of constant temperature；After second of constant temperature, to be not more than 1.5 DEG C/min speed to heat
Cool down in pressure tank, finally, carrying out release to autoclave after being cooled to 60 DEG C or less.
Further, in the step 4, the integrally formed tooling of composite material fuselage covering after laying honeycomb is sent into
In autoclave when hot compaction, the temperature in autoclave is 60 DEG C ± 5 DEG C, and keeps 30 ± 5min constant temperature.
The beneficial effects of the invention are as follows,
1. reducing manufacture difficulty, the technique for realizing deep camber tooling shape with the form design type face of composite structure
It is required that and after product curing molding, by dismantling detachable loose piece one by one, realize the technique requirement that product can demould；
Meanwhile the integrally formed tooling of composite material fuselage covering can not only manufacture product, can also manufacture cellular localization plate, reduce
The individually cost of die sinking manufacture cellular localization plate.
2. according to the special structure form of fuselage skin, using the integrally formed tooling of composite material fuselage covering and technique phase
Combination realizes product manufacturing；Meanwhile using cure process, it is integrally formed after product be with honeycomb sandwich construction
Fuselage skin, keep the structure of fuselage skin stronger；Because first molding exterior skin is free of honeycomb, therefore can be used compared with great achievement
Type pressure is solidified, and ensure that the Forming Quality of exterior skin.
3. forming cellular localization plate and exterior skin using same set of tooling, there is cellular localization plate and exterior skin identical
Thermal expansion amount；Using cellular localization plate positioning honeycomb, it is ensured that honeycomb puts the accuracy of position on exterior skin upper berth；Guaranteeing
In the case where honeycomb quality, the Forming Quality of fuselage skin can guarantee using the cure parameter of optimization.
Detailed description of the invention
Fig. 1 is the main view of the integrally formed tooling of composite material fuselage covering provided by the invention；
Fig. 2 is the left view of the integrally formed tooling of composite material fuselage covering provided by the invention；
Fig. 3 is the top view of the integrally formed tooling of composite material fuselage covering provided by the invention；
Fig. 4 is the explosive view of the integrally formed tooling of composite material fuselage covering provided by the invention.
Label and corresponding parts title in attached drawing:
1, frame, 2, tooling template, 3, mounting groove, 4, detachable loose piece, 5, solidification chamber, 6, Yan Tai, 7, wheel, 8, hang
Ring, 9, locator；
41, horizontal part, 42, curved portion, 43, location hole.
Specific embodiment
The present invention is described in further detail below through specific implementation examples and in conjunction with the accompanying drawings.
A kind of shown integrally formed tooling of composite material fuselage covering provided by the invention of Fig. 1 to Fig. 4, including frame
1 and tooling template 2；Mounting groove 3, two 3 arranged relatives of mounting groove, and work are offered on two opposite faces of the frame 1
The both ends fixation of dress template 2 is fastened on two mounting grooves 3；Two groups of detachable loose pieces are also equipped on 1 upper surface of frame
4, two groups of detachable loose pieces 4 are located at the two sides of tooling template 2, medial surface and the tooling template 2 of two groups of detachable loose pieces 4
Working face forms a continuous surface, and two groups of detachable loose pieces 4 constitute solidification chamber 5 with tooling template 2.
The frame 1 is rectangular frame 1, and mounting groove 3 is U-shaped, and the cross section of tooling template 2 is also U-shaped, makes tooling template
2 cooperate with mounting groove 3, to enable what the both ends of tooling template 2 consolidated to be supported in two mounting grooves 3；The tooling template 2
It is welded and fixed with frame 1, keeps the installation of tooling template 2 more firm, and the either flush of the high-end and frame 1 of tooling template 2.
Two groups of detachable loose pieces 4 are fixed by screws on frame 1, and two groups of detachable loose piece 4 symmetry arrangements on frame 1, are made
Two groups of detachable loose pieces 4 are located at the two sides of tooling template 2, and the lower end of two groups of detachable 4 inner surfaces of loose piece and tooling type
Two sides of plate 2 are docked, and two groups of detachable loose pieces 4 is made to collectively form the solidification chamber 5 an of spill with tooling template 2, and are consolidated
Change gap of the upper end opening of chamber 5 between two groups of detachable 4 upper ends of loose piece.
When needing to produce fuselage skin or cellular localization plate, two groups of detachable loose pieces 4 first can be separately fixed at frame 1
On, then solidifying the material that production fuselage skin or cellular localization plate are laid in chamber 5, and after material-paving, will answer
The integrally formed tooling of condensation material fuselage skin is sent to hot pressing in-tank-solidification, to make to be laid on the material progress solidified in chamber 5
Solidification makes to solidify the material in chamber 5 and is shaped to fuselage skin or cellular localization template, and by composite material fuselage covering integral into
Type tooling is taken out out of autoclave, finally removes two groups of detachable loose pieces 4 from frame 1, the body covering that curing molding is generated
Or the cellular localization template that cellular localization template takes out out of solidification chamber 5, and takes out forms cellular localization by secondary operation
Plate.
Detachable loose piece 4 described in every group includes multiple detachable loose pieces 4 successively closely arranged, and makes fuselage skin or bee
Nest positioning plate in process of production, solidifies material in chamber 5 in the curing process, the tension of material can pass through multiple detachable work
Block 4 carry out it is evenly dispersed, to prevent body covering or cellular localization plate from generating deformation in process of production；The detachable loose piece
4 include horizontal part 41 and the curved portion 42 being vertically fixed on horizontal part 41, and horizontal part 41 is wholely set with curved portion 42, and arc
The inner surface in shape portion 42 and the inner surface of tooling template 2 are spliced to form a continuous surface；The vertical component effect is fixed by screws in
On frame 1, make the easier for installation of detachable loose piece 4, and keeps the installation of detachable loose piece 4 more firm.
The curved portion 42 of each detachable loose piece 4 offers location hole 43, and it is convenient in placement exterior skin material to make
Positioning when piece, inside panel tablet and cellular localization plate, keeps the size for the fuselage skin produced more accurate.
The two sides of the tooling template 2 are provided with along platform 6, and two are each attached to the top surface of frame 1, the edge along platform 6
Platform 6 is in long strip, and the equal length of the length along platform 6 and tooling template 2, make along the both ends of platform 6 respectively with tooling template 2
Both ends alignment；In to 2 installation process of tooling template, the two sides for installing template can be fixed by along the fixation of platform 6, to make
The installation of tooling template 2 is more firm.The tooling template 2 is integrally formed with along platform 6, makes tooling template 2 and the company along platform 6
It connects stronger, not only plus the conveniently installation to tooling template 2, and enables the two sides of tooling template 2 and along the fixation of platform 6
It is more firm, to keep the deformation quantity of the fuselage skin produced and cellular localization plate smaller.
Detachable loose piece 4 described in two groups is separately mounted to two along platform 6, not only makes the installation of detachable loose piece 4 more
It is convenient, and make the inner surface of detachable loose piece 4 and tooling template 2 docks that place gap is smaller, makes the product finally processed essence
Du Genggao.
The bottom of the frame 1 is also equipped with the wheel 7 of multiple rotations；The wheel 7 is at least 4, and to a wheel 7
It is evenly distributed on the bottom surface of frame 1, it, can be quickly by composite material fuselage covering when making to solidify the material in chamber 5 and needing to solidify
Integrally formed tooling is sent to autoclave, and makes to solidify the material in chamber 5 after solidification, can be quickly by composite machine
The integrally formed tooling of body covering is released out of hydraulic tank.Multiple hanging rings 8 are additionally provided on the frame 1, multiple hanging rings 8 distinguish position
In in two opposing sidewalls of frame 1, facilitate the carrying to the integrally formed tooling of composite material fuselage covering.
The both ends of the tooling template 2 are also equipped with dismountable locator 9, and the locator 9 can be fixed for infrared ray
Position device 9 directlys adopt pin positioning, makes during producing fuselage skin, can carry out to exterior skin tablet and inside panel tablet
Positioning, keeps the size of the fuselage skin of production department more accurate.
It is also carved with cellular line on the tooling template 2, is enable when being processed into cellular localization plate to cellular localization template
It is cut according to cellular line, keeps the cellular localization board size processed more accurate.
The present invention also provides a kind of composite material fuselage covering integral forming techniques, specifically comprise the following steps:
(1) cellular localization sample making: prepreg laying is being solidified in chamber 5, and laying is had to the composite wood of prepreg
The material integrally formed tooling of fuselage skin is sent in autoclave, solidifies the prepreg of laying；It, will be compound after prepreg solidification
The integrally formed tooling of material fuselage skin is taken out out of autoclave, and the prepreg after solidification is whole from composite material fuselage covering
Body formed tooling is removed, and cellular localization template is formed.
First multiple detachable loose pieces 4 are fixed by screws in two along platform 6 respectively, make multiple detachable loose pieces 4
The inner surface of inner surface and tooling template 2 collectively forms solidification chamber 5, while locator 9 being mounted on to the both ends of tooling template 2；
Then by prepreg laying in solidification chamber 5, and prepreg is no less than 5 layers, to guarantee the cellular localization template formed after solidifying
With there is certain rigidity；And after prepreg laying, by laying have the composite material fuselage covering of prepreg integral into
Type tooling is sent in autoclave, and the prepreg for solidifying laying in chamber 5 is made to be cured, to form cellular localization template；When pre-
After leaching material is fully cured, the integrally formed tooling of composite material fuselage covering is taken out out of autoclave, and passes through two locators 9
Location hole 43 is marked on cellular localization template；Finally, multiple detachable loose pieces 4 are removed from along platform 6, and by molding bee
Nest positioning templet is removed out of solidification chamber 5.
(2) prepare before part production: the brushing release agent in solidification chamber 5 cuts exterior skin tablet, inside panel tablet；It will
Cellular localization template obtained is cut in step 1, forms cellular localization plate；And cellular localization plate surface is pasted and is demoulded
Cloth.
Exterior skin tablet is cut with inside panel tablet all in accordance with blanking typesetting figure, and honeycomb obtained is fixed in step 1
Position template is cut using laser cutting machine according to the cellular line on cellular localization template, in cutting process, according to positioning
The location hole 43 that device 9 marks on cellular localization plate, while location hole 43 is cut on cellular localization plate；In cellular localization template
It after cutting, polishes cellular localization template, keeps the cellular localization plate appearance to be formed more smooth, size is more smart
It is quasi-；It is described by cellular localization plate surface paste release cloth, facilitate the later period to cellular localization plate take out；The release cloth may be used also
It is directly substituted using release agent；The cellular localization plate as made from step 1 and step 2 only need to be when producing fuselage skin first time
It is processed, in following process production process, cellular localization plate is reusable.
(3) exterior skin forms: by exterior skin tablet laying obtained in step 2 in solidification chamber 5, will and have laying outer
The integrally formed tooling of composite material fuselage covering of covering tablet is sent in autoclave, solidifies the exterior skin tablet of laying；
Exterior skin tablet after solidification is removed from the integrally formed tooling of composite material fuselage covering, exterior skin is made.
It is complete in exterior skin tablet laying by the exterior skin tablet laying in step 2 in the solidification chamber 5 that brush has release agent
Laying is had the integrally formed tooling of composite material fuselage covering of exterior skin tablet to be sent in autoclave and solidified by Cheng Hou,
Make exterior skin tablet in hot pressing in-tank-solidification in exterior skin；It will include the composite wood of exterior skin after exterior skin curing molding
The material integrally formed tooling of fuselage skin is taken out out of autoclave, after the integrally formed tooling of composite material fuselage covering is taken out, outside
Covering is stored in solidification chamber 5.
(4) honeycomb laying: attached first layer binder of exterior skin inner surface brush obtained in step 3；It will be made in step 2
Cellular localization plate be placed on exterior skin, and using laser-projector project honeycomb, cellular localization plate is accurately positioned；
At this point, passing through the positioning of cellular localization plate, honeycomb is laid on exterior skin, the composite material fuselage after last laying honeycomb covers
The integrally formed tooling of skin is sent into hot compaction in autoclave；By the integrally formed tooling of composite material fuselage covering after hot compaction from heat
It presses in tank and takes out, and cellular localization plate is removed from the integrally formed tooling of composite material fuselage covering, and in cell and non-
Attached second layer binder is brushed on cell；Finally the integrally formed tooling of composite material fuselage covering is fed again into autoclave in advance
Compacting.
First binder and second bonding agents in the step 4 are core rubber film, and in the attached process of first bonding agents brush
In, first bonding agents are evenly distributed on the surface of exterior skin, after first bonding agents brush is attached, will be made in step 2
Cellular localization plate be placed on brush with first bonding agents exterior skin on, in cellular localization plate placement process, pass through two
Locator 9 positions the location hole 43 on cellular localization plate, and the position for placing cellular localization plate is more accurate；In honeycomb
After positioning plate is placed, by the positioning of cellular localization plate, honeycomb is placed on one by one on exterior skin of the brush with first bonding agents,
And after honeycomb is placed, the integrally formed tooling of composite material fuselage covering is sent in autoclave and carries out hot compaction, is made
Honeycomb is adhesively fixed on exterior skin.
After honeycomb and exterior skin are adhesively fixed, the integrally formed tooling of composite material fuselage covering is taken out of autoclave
Out, due to the surface mount release cloth of cellular localization plate, cellular localization plate is made not to be adhesively fixed with exterior skin, so that honeycomb be made to determine
Position plate can be removed quickly from exterior skin；First binder table after cellular localization plate is removed, after honeycomb and hot compaction
It brushes attached second bonding agents and is sent to the integrally formed tooling of composite material fuselage covering after second bonding agents brush is attached in face
Pre-compacted is carried out in autoclave, the temperature of pre-compacted is 60 DEG C ± 5 DEG C, and during pre-compacted and keeps 30min ± 5min
Constant temperature, so that second bonding agents be made to solidify, to keep honeycomb Nian Jie with exterior skin securely.
(5) integrally formed: the integrally formed tooling of composite material fuselage covering in step 4 is taken out from autoclave,
It is laid with inside panel tablet on honeycomb, and has the integrally formed tooling of composite material fuselage covering of inside panel tablet to be sent to laying
Solidified in autoclave, is finally taken out the integrally formed tooling of composite material fuselage covering from autoclave, and by composite material
Covering is formed in the integrally formed tooling of fuselage skin to remove.
After it will carry out pre-compacted in step 4, the integrally formed tooling of composite material fuselage covering is taken out out of autoclave,
After the integrally formed tooling of composite material fuselage covering is taken out, it is laid with inside panel tablet on honeycomb, is laid in inside panel tablet
After outer wall, the integrally formed tooling of composite material fuselage covering is again fed in autoclave and is solidified, to make inside panel
Tablet is bonded and fixed on honeycomb by second bonding agents, so that exterior skin be made to chat piece, honeycomb, the co-curing shape of inside panel tablet
At fuselage skin, after fuselage skin curing molding, the integrally formed tooling of composite material fuselage covering is taken out out of autoclave,
At this point, detachable loose piece 4 is removed from along platform 6, the fuselage skin of curing molding is taken out out of solidification chamber 5 finally, is completed
The production of fuselage skin.
In the step 3, sent by the integrally formed tooling of composite material fuselage covering for being placed with exterior skin tablet
Enter in autoclave in solidification process, first to being evacuated to -0.7Bar in autoclave hereinafter, and with the speed less than 1.5 DEG C/min
It is warming up to 80 DEG C ± 5 DEG C；And while heating, lead to when being forced into 1.0Bar to autoclave with the compression rate of 0.5Bar/min
Enter atmosphere, and continues to be forced into 5.0Bar ± 0.2Bar with the compression rate of 0.5Bar/min.In the step 5, by laying
There is the integrally formed tooling of composite material fuselage covering of inside panel tablet to be sent in autoclave to carry out in solidification process, first to heat
Pressure tank is evacuated to -0.28Bar~-0.34Bar, and is warming up to 80 DEG C ± 5 DEG C with the speed less than 1.5 DEG C/min；It is heating up
While, atmosphere is passed through when being forced into 1.0Bar to autoclave with the compression rate of 0.5Bar/min, and continue with 0.5Bar/
The compression rate of min is forced into 3.0Bar ± 0.2Bar.
In the step 3 and step 5, exterior skin tablet and inside panel tablet in the curing process, first will be in autoclaves
Temperature rises to 80 DEG C ± 5 DEG C, and makes to keep first time constant temperature in autoclave, and first time constant temperature time is 20min~25min；
After first time constant temperature, 130 DEG C ± 5 DEG C are warming up to the speed less than 1.5 DEG C/min, start second of constant temperature, second
It is 100min~120min when secondary constant temperature；After second of constant temperature, with no more than 1.5 DEG C/min speed in autoclave into
Row cooling, finally, carrying out release to autoclave after being cooled to 60 DEG C or less.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of integrally formed tooling of composite material fuselage covering, which is characterized in that including frame and tooling template；The frame
Two opposite faces on offer mounting groove, two mounting groove arranged relatives, and tooling template both ends fixation be fastened on two
On a mounting groove；Two groups of detachable loose pieces are also equipped in the frame upper surface, two groups of detachable loose pieces are located at tooling
The two sides of template, the medial surface of two groups of detachable loose pieces and the working face of tooling template form a continuous surface, and two groups detachable
Loose piece and tooling template constitute solidification chamber.
2. the integrally formed tooling of composite material fuselage covering according to claim 1, which is characterized in that removable described in every group
Unloading loose piece includes multiple detachable loose pieces successively closely arranged.
3. the integrally formed tooling of composite material fuselage covering according to claim 1, which is characterized in that the tooling template
Two sides be provided with along platform, two are each attached to the top surface of frame along platform.
4. the integrally formed tooling of composite material fuselage covering according to claim 3, which is characterized in that removable described in two groups
It unloads loose piece and is separately mounted to two along platform.
5. the integrally formed tooling of composite material fuselage covering according to claim 1, which is characterized in that the tooling template
Both ends be also equipped with dismountable locator.
6. the integrally formed tooling of composite material fuselage covering according to claim 1, which is characterized in that the bottom of the frame
Portion is also equipped with the wheel of multiple rotations, and multiple hanging rings are additionally provided on frame.
7. a kind of composite material fuselage covering integral forming technique, which is characterized in that specifically comprise the following steps:
(1) prepreg laying cellular localization sample making: is being solidified into composite material fuselage intracavitary, and that laying is had to prepreg
The integrally formed tooling of covering is sent in autoclave, solidifies the prepreg of laying；After prepreg solidification, by composite machine
The integrally formed tooling of body covering is taken out out of autoclave, and the prepreg after solidification is integrally formed from composite material fuselage covering
Tooling is removed, and cellular localization template is formed；
(2) prepare before part production: solidifying intracavitary brushing release agent, cutting exterior skin tablet, inside panel tablet；By step 1
In cellular localization template obtained cut, form cellular localization plate；And cellular localization plate surface is pasted into release cloth；
(3) exterior skin forms: exterior skin tablet laying obtained in step 2 is intracavitary in solidification, will and laying there be into exterior skin
The integrally formed tooling of composite material fuselage covering of tablet is sent in autoclave, solidifies the exterior skin tablet of laying；It will consolidate
Exterior skin tablet after change is removed from the integrally formed tooling of composite material fuselage covering, and exterior skin is made；
(4) honeycomb laying: attached first layer binder is brushed on exterior skin inner surface obtained in step 3；It will be obtained in step 2
Cellular localization plate is placed on exterior skin, and projects honeycomb using laser-projector, is accurately positioned to cellular localization plate；This
When, by the positioning of cellular localization plate, honeycomb is laid on exterior skin, the composite material fuselage covering after last laying honeycomb
Integrally formed tooling is sent into hot compaction in autoclave；By the integrally formed tooling of composite material fuselage covering after hot compaction from hot pressing
It takes out, and cellular localization plate is removed from the integrally formed tooling of composite material fuselage covering, and in cell and non-bee in tank
Attached second layer binder is brushed in nest area；The integrally formed tooling of composite material fuselage covering is finally fed again into precompressed in autoclave
It is real；
(5) integrally formed: the integrally formed tooling of composite material fuselage covering in step 4 to be taken out from autoclave, in honeycomb
Upper laying inside panel tablet, and there is the integrally formed tooling of composite material fuselage covering of inside panel tablet to be sent to hot pressing laying
Solidified in tank, is finally taken out the integrally formed tooling of composite material fuselage covering from autoclave, and by composite material fuselage
Covering is formed in the integrally formed tooling of covering to remove.
8. composite material fuselage covering integral forming technique according to claim 7, which is characterized in that in the step 3
In, solidification process in autoclave is being sent into the integrally formed tooling of composite material fuselage covering that will be placed with exterior skin tablet
In, first to being evacuated to -0.7Bar in autoclave hereinafter, and being warming up to 80 DEG C ± 5 DEG C with the speed less than 1.5 DEG C/min；And
While heating, be passed through atmosphere when being forced into 1.0Bar to autoclave with the compression rate of 0.5Bar/min, and continue with
The compression rate of 0.5Bar/min is forced into 5.0Bar ± 0.2Bar.
9. composite material fuselage covering integral forming technique according to claim 8, which is characterized in that in the step 5
In, there is the integrally formed tooling of composite material fuselage covering of inside panel tablet to be sent in autoclave laying and carries out solidification process
In, -0.28Bar~-0.34Bar first is evacuated to autoclave, and be warming up to 80 DEG C ± 5 with the speed less than 1.5 DEG C/min
℃；While heating, be passed through atmosphere when being forced into 1.0Bar to autoclave with the compression rate of 0.5Bar/min, and continue with
The compression rate of 0.5Bar/min is forced into 3.0Bar ± 0.2Bar.
10. composite material fuselage covering integral forming technique according to claim 9, which is characterized in that in the step 3
With in step 5, temperature in autoclave in the curing process, is first risen to 80 DEG C ± 5 DEG C by exterior skin tablet and inside panel tablet, and
Make to keep first time constant temperature in autoclave, and first time constant temperature time is 20min~25min；After first time constant temperature, with
Speed less than 1.5 DEG C/min is warming up to 130 DEG C ± 5 DEG C, starts second of constant temperature, when second of constant temperature for 100min~
120min；After second of constant temperature, to be not more than 1.5 DEG C/min speed to cooling down in autoclave, finally, cooling down
Release is carried out to autoclave after to 60 DEG C or less.
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| CN110682124A (en) * | 2019-09-12 | 2020-01-14 | 陕西飞机工业（集团）有限公司 | Milling fixture for fine cutting of large-scale double-curvature aircraft skin |
| CN111531202A (en) * | 2020-05-12 | 2020-08-14 | 航天特种材料及工艺技术研究所 | Positioning method and machining method of aircraft skin assembly hole |
| CN111706585A (en) * | 2020-05-15 | 2020-09-25 | 成都飞机工业（集团）有限责任公司 | Reverse gluing method for sheet aluminum alloy basin-shaped part |
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