CN110193957A - A kind of small drone composite aileron moulding technique - Google Patents

A kind of small drone composite aileron moulding technique Download PDF

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Publication number
CN110193957A
CN110193957A CN201910593016.0A CN201910593016A CN110193957A CN 110193957 A CN110193957 A CN 110193957A CN 201910593016 A CN201910593016 A CN 201910593016A CN 110193957 A CN110193957 A CN 110193957A
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CN
China
Prior art keywords
former
layer
shell
plate
prepreg
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CN201910593016.0A
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Chinese (zh)
Inventor
赵伟超
孙奇
赵景丽
何颖
段国晨
童话
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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Priority to CN201910593016.0A priority Critical patent/CN110193957A/en
Publication of CN110193957A publication Critical patent/CN110193957A/en
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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00Moulds or cores; Details thereof or accessories therefor
    • B29C33/38Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3835Designing moulds, e.g. using CAD-CAM
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00Moulds or cores; Details thereof or accessories therefor
    • B29C33/38Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3842Manufacturing moulds, e.g. shaping the mould surface by machining
    • B29C33/3857Manufacturing moulds, e.g. shaping the mould surface by machining by making impressions of one or more parts of models, e.g. shaped articles and including possible subsequent assembly of the parts
    • B29C33/3892Preparation of the model, e.g. by assembling parts
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/54Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing

Abstract

The present invention relates to a kind of small drone composite aileron moulding techniques, successively including the manufacture of special airbag molding die, the manufacture of air bag core model, prepare product integrally forming mould, paving prepreg obtains laying, each die assembly formed closed assembly, solidification demoulding again;The present invention solves vacuum and imports the limitation problem of liquid resin gradation curing molding and improve the homogeneity question of product quality, thickness, improve the problem that foam-formed pressure is small and construction weight is larger, it provides light-weight, high-performance, dimensional stability good integral forming technique method for small drone composite aileron, improves the structural behaviour and the scope of application of small drone composite aileron.

Description

A kind of small drone composite aileron moulding technique
Technical field
The invention belongs to unmanned plane composite material process planning technical fields, are related to a kind of small drone composite material pair Wing moulding technique.
Background technique
The aileron of aircraft refers to the movable aerofoil in wingtip rear outside for being mounted on wing, it is the main operation rudder of aircraft The lifting rolling maneuver of aircraft is realized in face by the aileron of operating aircraft.Traditional nonmetallic materials unmanned plane aileron is mainly adopted Glass reinforced plastic or liquid molding process are pasted with wet process hand, is usually composed of the structure of covering, cork wood rib or stringer, beam;With biography System aileron molding mode compares, the molding composite aileron of prepreg have gel content uniformly, it is lighter in weight, excellent comprehensive The advantages that closing mechanical property and high environmental suitability, it is also more and more extensive to be applied in High Performance Unmanned Aerial Vehicle housing construction.
The Chinese invention patent of 107160709 A of notification number CN discloses that " a kind of composite liquid molding microlight-type flies The method and rudder face of machine rudder face ", propose by vacuum import liquid resin method and gradation curing molding in the way of realize The manufacture of rudder face.This method needs gradation curing molding to assemble girder construction, then is filled behind gap in girder construction by fine sand Form the upper and lower covering of rudder face.This method high production cost and period are long, and the product weight of realization is larger, gel content and thickness Unevenly, and in forming process by way of fine sand or inflation filled-type face, complex process, and product quality is not easily-controllable System;Suitable for the gradation curing molding of relatively large composite aileron, it is not suitable for the whole of small drone composite aileron Body formed and lightweight requirements.
The Chinese invention patent of 106182801 A of notification number CN discloses a kind of " aircraft foam core filled composite material rudder Face forming method " proposes to realize the integrally formed of rudder face using foam thermal expansion itself.The full-height bubble contained in this method Foam sandwich weight is larger, and compared with thermal expansion of silicone rubber molding, vacuum assisted resin infusion, foam thermal expansion stresses itself are smaller, Therefore this method is suitable for the integrally formed of non-bearing structure low performance aileron, is not suitable for high performance mini unmanned plane composite wood Expect the integrally formed of aileron.
Summary of the invention
Technical problems to be solved
In order to avoid the shortcomings of the prior art, the present invention proposes a kind of small drone composite aileron molding work Process and equipment import the limitation problem and raising product quality, thickness of liquid resin gradation curing molding for solving vacuum The homogeneity question of degree improves the problem that foam-formed pressure is small and construction weight is larger, is small drone composite material pair The wing provides light-weight, high-performance, the good integral forming technique method of dimensional stability, improves small drone composite material pair The structural behaviour and the scope of application of the wing.
Technical solution
A kind of small drone composite material vertical tail moulding technique, it is characterised in that steps are as follows:
Step 1: the manufacture of special airbag molding die
The three-dimensional modeling and optimization design that special airbag molding die is carried out using CATIA software, by the number after optimization Model carries out mold processing;The special airbag molding die is divided into lower former and upper former two parts, lower former and upper yin Mould is by positioning pin and is bolted, intermediate after combination to form a cavity, the cavity and unmanned plane composite wood to be processed Expect that aileron product inner cavity is consistent;The left and right both ends of special airbag molding die are provided with the first right baffle-plate and the first right shell body, point It is not located by connecting by bolt and lower former and upper former end face, is used for closed above-mentioned cavity;The central region of right shell body It is provided with centre bore, is filled and deflated by connector for fixation balloon molding core model;
Step 2: the manufacture of air bag core model
Step 2a: break seal respectively lower former, upper former, the first right baffle-plate and the first right shell body, to its each inner surface according to Secondary smearing hole sealing agent and water-soluble mold-release agent dry 15min;Lower former, upper former inner surface on layer-by-layer paving silicon rubber Piece forms silastic-layer;The lower former of silicon rubber layer and upper former are molded again;In the first right baffle-plate and the first right gear The equally layer-by-layer paving silicone rubber plate of plate inner surface forms silastic-layer, wherein it is pre- to be filled and deflated by connector on right shell body inner surface It nuzzles in silastic-layer, and is embedded in central hole;The first right baffle-plate of upper silicon rubber layer and the first right shell body are pacified respectively again Loaded on lower former, upper former two sides, the closed assembly containing cavity is formed;Nitrogen is filled with cavity by being filled and deflated by connector, is protected 0.4MPa is pressed, intracavitary carry out air-leakage test is put assembly when the pressure revealed in 5 minutes is no more than 0.017MPa Enter and vulcanized in vacuum solidification furnace: first being heated up with the heating rate of 1-3 DEG C/min, until reach 180 DEG C of thermostat temperature, Heat preservation 2 hours;It is cooled down again with the rate of temperature fall of 3 DEG C/min, is come out of the stove when 55 DEG C or less;
Step 2b: dismantling the first right baffle-plate and the first right shell body, will be with the gas for being filled and deflated by connector in separation after former Capsule-core mould is separated from lower former inner surface, obtains air bag core model after side finishing more than silicon rubber;When air bag core model is unsatisfactory for It can repeat to manufacture using special airbag molding die when requirement;
Step 3: preparing product integrally forming mould
The three-dimensional modeling and optimization design that product integrally forming mould is carried out using CATIA software, by the number after optimization Model carries out mold processing;The product integrally forming mould along production breakdown interface to leading edge carry out block design after divided To form lower former and forming upper former two parts;Forming lower former includes entire rear type face, is made with upper former cooperation is formed With by positioning pin and bolt connecting mode formation entire combination mold, for the integrally formed of product;On this basis, together The second right baffle-plate of molding die, the second right shell body is arranged at product integrally forming mould both ends in sample, convenient for positioning fixation balloon core Mould is filled and deflated by connector, is connected through a screw thread to form closed assembly with product integrally forming mould;
Step 4: break seal respectively product integrally forming mould, the second right baffle-plate and the second right shell body, to its each inner surface It successively smears hole sealing agent and water-soluble mold-release agent, dry 15min;2 layers of 0 °/90 ° carbon fiber of layer-by-layer paving on former under molding Fabric prereg, edge reserve extra prepreg on the non-forming working face under forming on the left of former, and using non-porous Isolation film separates, and obtains the pre- laying of lower covering;Forming 2 layers of 0 °/90 ° carbon fibre fabrics preimpregnation of the upper layer-by-layer paving of female mold surfaces Material, obtains the pre- laying of covering;Be filled with nitrogen to 0.4MPa to air bag core model, after its constant pressure at rear 1 layer 0 ° of paving/ 90 ° of carbon fibre fabric prepregs obtain the pre- laying of beam;The prepreg is stored in -18 DEG C of deepfreeze environment, and is opened Evaporated condensation water is formed in packaging bag before sealing;The paving is carried out in Clean room, 22 ± 4 DEG C of temperature of holding in Clean room, relatively Humidity is not more than 65%;
Step 5: the second right baffle-plate, the second right shell body are installed in former both ends respectively under the molding containing prepreg, simultaneously will Air bag core model merging containing prepreg wherein, and is filled and deflated by the central hole that connector is fixed on molding die right shell body;By cork wood Part is placed against the pre- laying of beam;0 ° of Unidirectional band prepreg of 50mm wide is rolled into cylindrical type solid stripe object to be filled in Gap between cork wood part and the lower former of molding, forms the pre- laying of strip;2 layers will reserved at the non-forming working face in left side Extra prepreg is successively turned over respectively after removing non-porous release film in air bag core model upper surface;It again will be in the molding containing prepreg Former and the lower former of molding are combined, and form closed assembly;
Step 6: above-mentioned closed assembly being placed in vacuum solidification furnace and is solidified: first with the heating of 1-3 DEG C/min Rate heats up, until reaching 120 DEG C of thermostat temperature, keeps the temperature 1 hour;Cooling drop is carried out with the rate of temperature fall of 3 DEG C/min again Temperature is come out of the stove when 55 DEG C or less;
Step 7: second right baffle-plate at dismountable body both ends, the second right shell body will form upper former and be integrally detached from upwards, Product green body both ends burr is sanded clean, air bag core model (6) put after nitrogen treatment by it from cured product base It is extracted out in body, then product green body is detached from from forming on lower former, sharp processing is carried out to side more than product, and notch progress is sanded Finishing processing, obtains small drone composite aileron product.
Beneficial effect
A kind of small drone composite aileron moulding technique proposed by the present invention, has the beneficial effect that:
(1) it solves vacuum to import the limitation problem of liquid resin gradation curing molding and improve product quality, thickness Uniformity avoids the environmental pollution generated in chemicals preparation and use process and quality risk;Effectively improve foam at Type pressure is small and the larger problem of construction weight, improve small drone composite aileron structural behaviour and applicable model It encloses;
(2) moulding process and tooling are effectively simplified, technology difficulty is reduced, shortens the production cycle, avoids material The relatively lossy of material, not only realizes the integrally formed of composite aileron, it is integrally formed excellent greatly to have played composite material Gesture, and obtained product structure is light-weight, performance is high;
(3) integrally formed suitable for a variety of small drone composite ailerons, avoid because type chamber it is narrow caused by The problems such as vacuum assisted resin infusion is difficult or various product demoulding is difficult;
(4) by air bag mandrel molding, briquetting pressure can be effectively uniformly transferred, ensure that integrally formed product ruler Very little stabilization improves product inner and outer surfaces quality, also avoids the heat stagnation aftereffect of interiors of products, keeps properties of product reliable.
Detailed description of the invention
Fig. 1 is composite aileron structural schematic diagram of the embodiment of the present invention;
Fig. 2 is composite aileron structure schematic side view in embodiment
Fig. 3 is special airbag molding die and air bag core model schematic side view in embodiment;
Fig. 4 is special airbag molding die left side structure schematic diagram in embodiment;
Fig. 5 is special airbag molding die right side structure schematic diagram in embodiment;.
Fig. 6 is air bag core mold structure schematic diagram in embodiment;
Fig. 7 is embodiment middle berth schematic diagram of a layer structure;
Fig. 8 is equipment position schematic side view in embodiment;
Fig. 9 is lower covering forming schematic diagram in embodiment;
Figure 10 is upper covering forming schematic diagram in embodiment;
Figure 11 is status diagram before solidifying in embodiment.
Wherein former under 1-, the upper former of 2-, the first right baffle-plate of 3-, the first right shell body of 4-, 5- centre bore, 6- air bag core model, 7- forms lower former, former in 8- molding, the pre- laying of covering under 9-, the pre- laying of 10- beam, 11- cork wood part, and 12- strip is pre- Laying, the pre- laying of the upper covering of 13-, the non-forming working face of 14-, 15- molding die right baffle-plate, 16- molding die right shell body.
Specific embodiment
Now in conjunction with embodiment, attached drawing, the invention will be further described:
The first step, the design of special airbag molding die.
Referring to Fig.1, the product of the present embodiment is the structure special-shaped part of typical compact unmanned plane composite aileron, is about 600mm, about 80,75mm, leading edge radius of the radian about 6mm, trailing edge ends thickness about 1.5mm, product covering are whole respectively for both ends chord length Body thickness about 0.4mm.The product structure is complicated, light-weight;Both ends end face is open type, and one end is big, one end is small;Leading edge punishment It is furnished with invagination groove at 5, excellent rigidity is not only provided for product leading edge, but also bolt, fixation can be carried out with other connectors, it is real Existing aileron function;It is provided with cork wood built-in fitting and the pre- laying of strip at rear, not only effectively increases integrally formed rear product Total splicing between rigid support and covering, also effectively increase product rear with type and avoiding more defect at rear fillet Generation.
Referring to Fig. 2, according to product three-dimensional digital-to-analogue, Fixture Design is carried out using CATIA software, mold is carried out by digital-to-analogue and adds Work obtains special airbag molding die, the manufacture for air bag core model.
Referring to Fig. 3, special airbag molding die is mainly made of lower former 1 and upper former 2, and lower former 1 and upper former 2 are logical It crosses positioning pin and is bolted to form the entire combination mold containing cavity, the cavity and unmanned plane composite aileron to be processed Product inner cavity is consistent.Meanwhile front and rear edge apposition position is provided with sunken recess, convenient for being sealed to synthesis type, cavity for air bag core model 6 And remaining side finishing.
Referring to Fig. 4,5, on this basis, the special airbag molding die both ends after combination are provided with the first right baffle-plate 3, the One right shell body 4 is convenient for airtight cavity.Baffle is the metal plate with mold same material, and surface contains bolt hole, will by bolt It is cooperatively connected with the both sides of the face of lower former 1 and upper former 2 respectively, and wherein 4 central region of right shell body is provided with centre bore 5, Can be used for fixation balloon core model 6 is filled and deflated by connector, which uses quick-release connection type.
Special airbag molding die piecemeal is simple, reasonable, can effectively avoid the poor air-tightness caused by excessive block design The problems such as, the dismountable block plate being arranged by both ends had not only ensured the detachability of type intracavitary good airtightness and baffle, but also benefit In the positioning and demoulding of air bag core model;By the sagging design of apposition position, it can effectively ensure that the technique of silicone rubber plate paving is convenient Property and vulcanization rear gasbag overall tightness.
Second step manufactures air bag core model 6.
Referring to Fig. 6, break seal lower former 1, upper former 2 and right baffle-plate 3, right shell body 4 successively apply on each shaping work face It smears hole sealing agent and water-soluble mold-release agent, dry 15min.Paving silicone rubber plate is distinguished on each shaping work face, forms silicon rubber Glue-line.It requires air bag when shaped article that there is certain rigidity and rate of collapsing when paving, the prepreg of paving can be played very Support well and positioning action, and the adjustment to bag material thickness can be passed through, it is ensured that in sulfidation good air-tightness and Release property, specific method are the silastic-layers that paving is thicker on each turning and left and right baffle, can be effectively formed certain Rigidity forms effective supporting surface;Connector is nuzzled in silastic-layer in advance in right shell body 4, it is ensured that connector and silicon rubber vulcanization Leakproofness afterwards.After silicone rubber plate laying, contouring is carried out to silastic-layer, and place 5mm's to apposition position is reserved Silicon rubber bonding jumper improves the reliability to commissural air bag core model leakproofness and quality.
On this basis, the lower former 1 containing silastic-layer and upper former 2 are molded, then at composable mold both ends Right baffle-plate 3, right shell body 4 are installed respectively, ultimately form closed assembly.
It is filled with nitrogen into the cavity of closed assembly by being filled and deflated by connector, until intracavitary formation 0.4MPa pressure;It is right Intracavitary carry out air-leakage test, and when the pressure revealed in 5 minutes is no more than 0.017MPa, assembly is put into vacuum solidification Vulcanize in furnace, to the effect that first heated up with the heating rate of 1-3 DEG C/min, until reaching 180 DEG C of thermostat temperature, is protected Temperature 2 hours;It is cooled down, is come out of the stove when 55 DEG C or less, and demoulded with the rate of temperature fall of 3 DEG C/min again.Finally use Blade of cutting a sheet of paper modifies side more than the flake of air bag core model green body, obtains air bag core model 6.
Third step, the design of product integrally forming mould.
The three-dimensional modeling of product integrally forming mould is carried out using CATIA software according to product three-dimensional digital-to-analogue referring to Fig. 7 And optimization design, the mathematical model after optimization is subjected to mold processing, obtains product integrally forming mould, is used for composite material pair The wing it is integrally formed.
Referring to Fig. 8, the product integrally forming mould along production breakdown interface block design is carried out to leading edge after divided To form lower former 7 and forming upper 8 two parts of former;Wherein descending former 7 includes entire rear type face, is made with the cooperation of upper former 8 With by positioning pin and bolt connecting mode formation entire combination mold, for the integrally formed of product.On this basis, together Molding die right baffle-plate 15, molding die right shell body 16 is arranged at product integrally forming mould both ends in sample, convenient for positioning fixed gas Capsule-core mould 6 is filled and deflated by connector, and is connected through a screw thread to form closed assembly with product integrally forming mould.
By being used cooperatively for product integrally forming mould and air bag core model 6, before capable of substantially effectively solving product solidification, Total quality state afterwards, the uniformity of briquetting pressure transmitting, improves the releasability of product and the reliability of inside and outside quality.
4th step, preparation process.
Former 8 and molding die right baffle-plate 15, mold right shell body 16 on the lower former 7 of unpacking molding, molding, respectively each Hole sealing agent and water-soluble mold-release agent are successively smeared on shaping work face, dry 15min.
Referring to Fig. 7, prepare integrally formed prepreg and cork wood part 11;The prepreg used in the present embodiment is single layer The MTM28/CF0300-42%RW carbon fibre fabric prepreg of thickness δ 0.2mm and the MTM28-1/ of thickness in monolayer δ 0.125mm T700SC-125-33%RW Unidirectional band prepreg.
5th step, prepreg are cut out.
The expansion setting-out and process optimization that prepreg is carried out by product three-dimensional digital-to-analogue carry out prepreg using AutoCAD Optimal Layout design, to improve stock utilization, reduce cost;It reuses CNC cutting machine to be cut out, and to cutting out Prepreg be marked and lamination place.When prepreg is cut out allow the cut-parts deviation of directivity be ± 1 °, dimensional discrepancy for ± 1mm。
6th step, prepreg overlay.
Referring to Fig. 7,9, layer-by-layer 2 layers of paving (0 °/90 °) the carbon cloth Fabric prereg on former 7 under molding, edge is reserved Extra prepreg is separated on the non-forming working face 14 under forming on the left of former 7 using non-porous release film, and lower illiteracy is obtained The pre- laying 9 of skin.
Referring to Fig.1 0, upper 2 layers of 8 surface layer-by-layer paving of former (0 °/90 °) carbon cloth Fabric prereg is being formed, interlayer is formed The pre- laying 13 of covering is obtained after step-wise transition.
Nitrogen is filled with to 0.4MPa to air bag core model 6, and 1 layer of paving (0 °/90 °) carbon fiber is knitted at rear after its constant pressure Object prepreg obtains the pre- laying 10 of beam.
Referring to Fig.1 1,7 both ends installation forming mold right baffle-plate 15 of former, the right gear of molding die under the molding containing prepreg Plate 16, while wherein by the merging of air bag core model 6 containing prepreg, and be filled and deflated by connector and be fixed on molding die right shell body 16 Central hole;Pre- laying 10 by cork wood part 11 against beam is placed;0 ° of Unidirectional band prepreg of 50mm wide is rolled into circle Column type solid stripe object is filled in cork wood part 11 and forms the gap between lower former 7, forms the pre- laying 12 of strip.It will be left The 2 layers of extra prepreg reserved at the non-forming working face 14 in side are successively turned over respectively after removing non-porous release film in air bag core model 6 upper surfaces, and form step-wise transition;By former 8 in the molding containing prepreg and under forming, former 7 is combined again, is formed Closed assembly.
It is as follows that entire laying crosses range request: in order to exclude the air wrapped up between laying as far as possible, should carry out to prepreg overlay Vacuum preloading is real, and helps forming parts.In paving prepreg the 1st layer, before laying sandwich material with it is later and subsequent every Paving 1 to 3 layer of prepreg should all carry out vacuum preloading reality, the method for vacuum preloading reality be in pre- laying successively paving there are commonly Hole isolation film, airfelt, temporary vacuum bag pass through the Adhesion formation vacuum tightness of mold inoperative type face edge sealant tape System, then 0.08MPa or more vacuum degree at least 10 minutes in system are kept by way of persistently vacuumizing;Each vacuum preloading The temporary vacuum bag for being stained with sealant tape is opened after reality, is put together, entire mold work type face is exposed all, then Successively by overlay layer surface have hole isolation film, airfelt remove and completely retain, continued to use to next time.Carbon fibre fabric is pre- Overlap joint processing should be carried out when leaching material paving, and lap width is 25mm or so, and adjacent interlayer lap side seam should be staggered 25mm or so.
7th step, solidification.
Above-mentioned closed assembly is placed in vacuum solidification furnace and is solidified: first with the heating rate of 1-3 DEG C/min into Row heating keeps the temperature 1 hour until reaching 120 DEG C of thermostat temperature;It is cooled down again with the rate of temperature fall of 3 DEG C/min, until It comes out of the stove at 55 DEG C or less.
8th step, demoulding and sharp processing.
Dismountable body both ends metal baffle will form the whole disengaging upwards of upper former 8, by product green body both ends burr sand Mill is clean, put to air bag core model 6 and extract it from cured product green body out after nitrogen treatment, then by product green body from It forms and is detached from lower former 7, sharp processing is carried out to side more than product, and notch is sanded and carries out finishing processing.
So far, the integrally formed of small drone composite aileron product is completed.

Claims (1)

1. a kind of small drone composite aileron moulding technique, it is characterised in that steps are as follows:
Step 1: the manufacture of special airbag molding die
The three-dimensional modeling and optimization design that special airbag molding die is carried out using CATIA software, by the mathematical model after optimization Carry out mold processing;The special airbag molding die is divided into lower former (1) and upper former (2) two parts, lower former (1) and Upper former (2) is by positioning pin and is bolted, intermediate after combination to form a cavity, the cavity and unmanned plane to be processed Composite aileron product inner cavity is consistent;The left and right both ends of special airbag molding die are provided with the first right baffle-plate (3) and first Right shell body (4) is located by connecting by bolt and lower former (1) and upper former (2) end face respectively, is used for closed above-mentioned chamber Body;The central region of right shell body (4) is provided with centre bore (5), is filled and deflated by connector for fixation balloon molding core model (6);
Step 2: the manufacture of air bag core model (6)
Step 2a: break seal respectively lower former (1), upper former (2), the first right baffle-plate (3) and the first right shell body (4), it is each to its Inner surface successively smears hole sealing agent and water-soluble mold-release agent, dries 15min;Lower former (1), upper former (2) inner surface on Layer-by-layer paving silicone rubber plate, forms silastic-layer;The lower former (1) of silicon rubber layer and upper former (2) are molded again;? First right baffle-plate (3) and the equally layer-by-layer paving silicone rubber plate of the first right shell body (4) inner surface form silastic-layer, wherein in right gear Connector will be filled and deflated by plate (4) inner surface to nuzzle in silastic-layer in advance, and will be embedded at centre bore (5);Again by upper silicon rubber layer The first right baffle-plate (3) and the first right shell body (4) be respectively arranged in lower former (1), upper former (2) two sides, formed containing cavity Closed assembly;Nitrogen is filled with cavity, pressure maintaining 0.4MPa, to intracavitary carry out air-leakage test, when 5 by being filled and deflated by connector Minute in reveal pressure be no more than 0.017MPa when, assembly is put into vacuum solidification furnace and is vulcanized: first with 1-3 DEG C/ The heating rate of min heats up, until reaching 180 DEG C of thermostat temperature, keeps the temperature 2 hours;Again with the rate of temperature fall of 3 DEG C/min into Row cools, and comes out of the stove when 55 DEG C or less;
Step 2b: dismantling the first right baffle-plate (3) and the first right shell body (4), in separation after former (2), will have and be filled and deflated by connector Air bag core model (6) separated from lower former (1) inner surface, through more than silicon rubber side finishing after obtain air bag core model (6);Work as gas Capsule-core mould (6) can repeat to manufacture when being unsatisfactory for requirement using special airbag molding die;
Step 3: preparing product integrally forming mould
The three-dimensional modeling and optimization design that product integrally forming mould is carried out using CATIA software, by the mathematical model after optimization Carry out mold processing;The product integrally forming mould along production breakdown interface to leading edge carry out block design after be divided into Former (7) and upper former (8) two parts of molding under type;Forming lower former (7) includes entire rear type face, with the upper former of molding (8) it is used cooperatively, entire combination mold is formed by positioning pin and bolt connecting mode, for the integrally formed of product;Herein On the basis of, the second right baffle-plate of molding die (15), the second right shell body (16) equally are set at product integrally forming mould both ends, just It is filled and deflated by connector in positioning fixation balloon core model (6), is connected through a screw thread to form closed combination with product integrally forming mould Body;
Step 4: break seal respectively product integrally forming mould, the second right baffle-plate and the second right shell body, successively to its each inner surface It smears hole sealing agent and water-soluble mold-release agent, dry 15min;2 layers of 0 °/90 ° carbon fiber of layer-by-layer paving are knitted on former (7) under molding Object prepreg, edge reserves extra prepreg on the non-forming working face (14) under forming on the left of former (7), and uses Non-porous release film separates, and obtains the pre- laying of lower covering (9);Forming upper 2 layers of 0 °/90 ° carbon fiber of former (8) surface layer-by-layer paving Fabric prereg obtains the pre- laying of covering (13);Nitrogen is filled with to 0.4MPa, after its constant pressure after to air bag core model (6) 1 layer of 0 °/90 ° carbon fibre fabric prepreg of paving, obtain the pre- laying (10) of beam at edge;The prepreg is stored in -18 DEG C In deepfreeze environment, and evaporated condensation water is formed in preceding packaging bag of breaking seal;The paving is carried out in Clean room, is protected in Clean room 22 ± 4 DEG C of temperature are held, relative humidity is not more than 65%;
Step 5: the second right baffle-plate (15), the second right shell body (16) are installed in former (7) both ends respectively under the molding containing prepreg, Simultaneously wherein by air bag core model (6) merging containing prepreg, and it is filled and deflated by the centre bore that connector is fixed on molding die right shell body Place;Pre- laying (10) by cork wood part (11) against beam is placed;0 ° of Unidirectional band prepreg of 50mm wide is rolled into cylinder Type solid stripe object is filled in cork wood part (11) and forms the gap between lower former (7), is formed the pre- laying of strip (12); The 2 layers of extra prepreg reserved at the non-forming working face in left side (14) are successively turned in gas respectively after removing non-porous release film Capsule-core mould (6) upper surface;By former in the molding containing prepreg (8) and under forming, former (7) are combined again, form closed group It is fit;
Step 6: above-mentioned closed assembly being placed in vacuum solidification furnace and is solidified: first with the heating rate of 1-3 DEG C/min It heats up, until reaching 120 DEG C of thermostat temperature, keeps the temperature 1 hour;It is cooled down again with the rate of temperature fall of 3 DEG C/min, directly It comes out of the stove when to 55 DEG C or less;
Step 7: second right baffle-plate (15) at dismountable body both ends, the second right shell body (16), it is whole upwards by upper former (8) are formed Body is detached from, and product green body both ends burr is sanded clean, put after nitrogen treatment by it air bag core model (6) from cured It is extracted out in product green body, then product green body is detached from from forming on lower former (7), sharp processing, and sand are carried out to side more than product It grinds notch and carries out finishing processing, obtain small drone composite aileron product.
CN201910593016.0A 2019-07-03 2019-07-03 A kind of small drone composite aileron moulding technique Pending CN110193957A (en)

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CN111086128A (en) * 2019-12-27 2020-05-01 湖北航聚科技有限公司 Core mold for manufacturing solid rocket engine and forming method thereof
CN112092411A (en) * 2020-07-31 2020-12-18 北京卫星制造厂有限公司 Forming tool and method for small-caliber long-size non-uniform-thickness thin rectangular pipe fitting

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CN106273547A (en) * 2016-09-09 2017-01-04 西安爱生技术集团公司 One has cabin cover and Ω stringer deep camber unmanned plane wallboard manufacturing process
CN108943769A (en) * 2018-06-21 2018-12-07 西安爱生技术集团公司 The manufacturing method of the non-isometrical enclosed type square tube type carbon fiber girder construction product of unmanned plane
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FR1238462A (en) * 1958-07-10 1960-08-12 Fenner Co Ltd J H Drawing sleeve for spinning machines
CN106273547A (en) * 2016-09-09 2017-01-04 西安爱生技术集团公司 One has cabin cover and Ω stringer deep camber unmanned plane wallboard manufacturing process
CN108943769A (en) * 2018-06-21 2018-12-07 西安爱生技术集团公司 The manufacturing method of the non-isometrical enclosed type square tube type carbon fiber girder construction product of unmanned plane
CN108959744A (en) * 2018-06-21 2018-12-07 西安爱生技术集团公司 A kind of small and medium size unmanned aerial vehicles composite wing wing box manufacturing method

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* Cited by examiner, † Cited by third party
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CN111086128A (en) * 2019-12-27 2020-05-01 湖北航聚科技有限公司 Core mold for manufacturing solid rocket engine and forming method thereof
CN112092411A (en) * 2020-07-31 2020-12-18 北京卫星制造厂有限公司 Forming tool and method for small-caliber long-size non-uniform-thickness thin rectangular pipe fitting

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