CN104385624B - Forming method for composite material barrel shell employing horizontal installation - Google Patents

Forming method for composite material barrel shell employing horizontal installation Download PDF

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Publication number
CN104385624B
CN104385624B CN201410515854.3A CN201410515854A CN104385624B CN 104385624 B CN104385624 B CN 104385624B CN 201410515854 A CN201410515854 A CN 201410515854A CN 104385624 B CN104385624 B CN 104385624B
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CN
China
Prior art keywords
prepreg
cylinder
laying
diaphragm
barrel shell
Prior art date
Application number
CN201410515854.3A
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Chinese (zh)
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CN104385624A (en
Inventor
章令晖
陈萍
张志刚
靳利锋
王琦洁
李雨默
赵金涛
王众志
尚健
吕贤亮
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北京空间机电研究所
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Priority to CN201410515854.3A priority Critical patent/CN104385624B/en
Publication of CN104385624A publication Critical patent/CN104385624A/en
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    • 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
    • B29C70/30Shaping 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
    • B29C70/38Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • 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 invention relates to a forming method for a composite material barrel shell employing horizontal installation, and belongs to the field of composite material structure design and composite material processing technologies. The formed horizontally-installed composite material barrel shell is low in structure density, the common-resin composite material has the density less than 1.65 g/cm<3>, and the density is about 1/5 of that of steel and 1/3 of titanium alloy, the weight reduction effect is obvious, and the composite material accords with the spacecraft lightweighting development trend. The method realizes integral forming of the structure main part of the composite material barrel shell employing horizontal installation, the fiber continuity is good, the damping performance is excellent, the structural rigidity and the local strength are both relatively high, the stability is good, and special requirements of a spacecraft optical system are satisfied.

Description

A kind of manufacturing process using horizontally-mounted composite barrel shell
Technical field
The present invention relates to a kind of manufacturing process using horizontally-mounted composite barrel shell, belong to composite Structure design and composite processing technology field.
Background technology
Space Remote Sensors system is towards more wide spectrum scope, higher spectral resolution, more high spatial resolution, more High radiometric resolution, and multipolarization, from various visual angles, multi-direction, multidate, multimodal direction develop. Its version also becomes more complicated and diversified therewith.No matter from the performance of material or Technology For angle, traditional metal material is far from the demand meeting current Space Remote Sensors.Advanced composite material There is light weight, that specific strength and specific modulus height, endurance, damping characteristics are good, performance can design etc. is excellent Point, just progressively substituting original metal material becomes the critical material of Space Remote Sensors structure.
The barrel shell type component of Space Remote Sensors system, such as lens barrel, shade etc., traditionally how using vertical Straight mounting means is connected with main body, as depicted in figs. 1 and 2, that is, by the flange of end or outer surface, Auricle etc. is connected with main body, and joint face is orthogonal with the axis of lens barrel or shade.But right angle setting side Formula makes limited by remote sensor topology layout.And under many circumstances, the length of the part such as lens barrel or shade Long, this can make its own rigidly be deteriorated, and single order frequency of vibration reduces.Additionally, right angle setting mode Joint face is less, and bonding strength is relatively low.From the point of view of engineer applied effect, for this class barrel shell structure, adopt With horizontal installation, there is bigger advantage.On the one hand remote sensor topology layout is more optimized.On the other hand, Horizontal mounting means increased connection area, improves bonding strength;Muscle (rib) between barrel shell and joint face Improve the rigidity of structure, meet the requirement to frequency of vibration for the remote sensor systems.
The manufacturing technology of composite products totally different in metal material, the molding of composite generally will be in mould In complete.For using horizontally-mounted composite barrel shell, its version ratio adopts right angle setting Composite barrel shell complicated, thus its manufacturing process is a great problem in through engineering approaches application all the time.
Content of the invention
The purpose of the present invention is traditionally to adopt right angle setting mode for Space Remote Sensors barrel shell structure, exists Remote sensor topology layout is limited, poor, the more low deficiency of bonding strength of rigidity, proposes one kind and adopts horizontal peace The manufacturing process of the composite barrel shell of dress.
The purpose of the present invention is achieved through the following technical solutions.
A kind of manufacturing process using horizontally-mounted composite barrel shell of the present invention, this composite barrel shell Including cylinder, the ribs of more than two, joint face, the stud of more than two and diaphragm;Diaphragm is arranged on The inside of cylinder, the mid portion of joint face is fixedly connected with cylinder by stud, two rim portion of joint face It is fixedly connected with cylinder by ribs;In addition to diaphragm, other parts be cylinder, ribs, joint face and Stud is formed in one, this four parts assembly abbreviation cylinder;Form cavity between two adjacent studs; Form cavity between two adjacent ribs;
Steps of the method are:
The first step, Mould design and manufacturing
Two parts, cylinder shaping dies and light are comprised using the mould of horizontally-mounted composite drum shell structure Late shaping dies.
Cylinder shaping dies adopt assembling die, this assembling die include mandrel, base, panel, insert, Side plate, end cap and the equal pressing plate of technique;
Mandrel profile and size are consistent with cylinder bore;Base upper surface shape and size are consistent with joint face; The cavity being formed between panel profile and size and adjacent two studs is consistent;
The cavity being formed between insert profile and size and adjacent two ribs is consistent;
The number of cavities being formed between the quantity of insert and two ribs is identical;
Side plate is arranged on the outside of insert, fits with cylinder side, its fit shape and size and cylinder side Unanimously;
End cap amounts to two pieces, is separately mounted to the two ends of base, and in the middle part of end cap, the shape according to panel is slotted, Spacing for panel;
The equal pressing plate of technique is the profile thin plate consistent with cylinder upper surface shape.
Diaphragm shaping dies adopt former, and its cavity shape and size are consistent with diaphragm.
Second step, mould pretreatment
In one layer of releasing agent of external coating of cylinder shaping dies and diaphragm shaping dies, releasing agent tolerable temperature Typically it is not less than 140 DEG C, and dry;
3rd step, prepared by prepreg
The required prepreg of preparation, carries out prepreg b rankization according to the particular type of resin matrix and processes, that is, Heating makes resin soften but incomplete fusion, has certain viscosity, is easy to the paving of operation below;
4th step, prepreg cutting
The quantity of blank, cutting prepreg according to needed for the overall dimensions calculating of cylinder and diaphragm.
5th step, laying
Shell portion carries out laying as follows:
1) laying prepreg on base, forms joint face part.
2) laying t type prepreg above base, forms intermediate studs part.
3) in panel outer surface laying prepreg, form stud part;It is positioned over together with panel after laying is closely knit The 2nd above base) both sides of step institute laying t type prepreg;
4) along mandrel outer surface laying prepreg, form cylindrical portions, after compacting, be placed on the upper of panel Side;
5) along mandrel outer surface laying prepreg, both sides turn to downwards the lateral surface of panel.
6) in the outer surface laying prepreg of insert, form ribs part, put together with insert after laying is closely knit It is placed in the 5th) both sides of step institute laying prepreg;
7) the laying number of plies of above-mentioned each step prepreg is all not quite similar, and needs respectively according to product thickness and monolayer The thickness of prepreg determines.
Diaphragm part carries out laying as follows:
Along mould inner surface ecto-entad successively laying, repair the edge of pinch-off part along mould outer rim simultaneously.If Using full wafer prepreg, clip should be added by circumferentially spaced 30mm~60mm;If if each layer is divided into Dry tablet prepreg, can be using docking or overlap joint (lap width with layer adjacent two panels prepreg 5mm~10mm), the abutment joint of adjacent layer prepreg or overlap joint line should stagger 10mm in the same direction successively More than.
Should be according to practical situation in lay-up process, 3~5 layers of every laying carries out a pre-compacted.
6th step, pre-compacted
It is coated with politef isolating membrane, the equal pressing plate of technique, airfelt successively, adhesive seal adhesive tape simultaneously encapsulates Vacuum nylon film, evacuation carries out pre-compacted.
After the completion of pre-compacted, remove vacuum nylon film, airfelt, the equal pressing plate of technique, politef every From film, continue the laying step not completed.
7th step, solidification
Repair the flash cutting pre-compacted process, clean the glue of die surface.
Be coated with successively politef isolating membrane, inhale glue-line, politef isolating membrane, the equal pressing plate of technique, Airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film.
Complete to solidify using vacuum bag-autoclave method or vacuum bag-Oven Method.
8th step, the demoulding and finishing
Remove vacuum nylon film and airfelt, take off the equal pressing plate of technique on surface, remove end cap and side plate, Then remove the insert of both sides, then mandrel is deviate from from product, then panel is deviate from from product, Shell portion is deviate from afterwards from base.
Diaphragm is deviate from from diaphragm shaping dies.
The overlap of finishing cylinder and diaphragm and burr.
9th step, assembly trial assembly is joined
The above cylinder being obtained and each diaphragm are carried out trial assembly and join, fit clearance is generally 0.1mm~0.3mm.
Tenth step, bonding front surface is processed
Bonding region needed for labelling, periphery pastes isolating membrane.Equably polished cylinder and diaphragm using sand paper Bonding plane, with solvent clean, cleans and dries.
11st step, joins glue
Prepare the cold curing structural adhesive needed for bonding.
12nd step, assembly bonding
One layer of cold curing structural adhesive is equably smeared on the bonding plane of cylinder and diaphragm, successively respectively Each diaphragm is loaded in cylinder, cleans excessive glue, and fixed with pressure sensitive adhesive tape.
Under room temperature, standing certain time completes to solidify.
13rd step, assembly is repaired
Remove pressure sensitive adhesive tape etc., repair excessive glue and the burr on file surface.
The mold base both ends of the surface fluting of the described first step, well width is identical with endcap width, and groove depth is more than 2mm meets guiding and requires.
The equal pressing plate of technique of the described first step is the thick engineering plastic flitch of 0.3~2mm or aluminium alloy plate, and surface is put down Whole, bright and clean.
The prepreg of described 3rd step is aramid fiber, the fabric of glass fibre, carbon fiber and other fibers Or unidirectional pre-immersion material.
The prepreg of described 3rd step, such as controls 40 ± 5% using unidirectional pre-immersion material resin content, as adopted Fabric prereg resin content controls 42 ± 5%, and volatile content all requires less than 3%.
The ply parameter of described 5th step, depending on barrel shell version, after every one piece of prepreg of laying, is coated with One layer of polytetrafluoroethylene film, is then progressively rolled with rubber rollers and electric iron, make fine and close between layers but Corrugationless.More than the 10mm in addition, the splicing seams of adjacent prepreg require to stagger.
The process for pre-compacting of described 6th step is that evacuated pressure is not more than -0.09mpa, keeps 0.5~1 hour After shut down, while evacuation allow according to resin matrix particular type carry out heating makes resin soften.
The curing process of described 8th step according to the particular type of resin matrix, the material of mould, product big Depending on little and thickness, should be cooled to less than 60 DEG C after shutdown can come out of the stove.
Described 9th step can carry out process optimization according to fit clearance, if fit clearance is more than 0.3mm, can Add appropriate thickening agent when the 11st step prepares cold curing gluing agent, or in the 12nd step assembly bonding When filling layer of glass sand net.
The present invention compared with prior art has the beneficial effect that
(1) density using horizontal installation composite drum shell structure that the present invention shapes is low, general resin base Composite density is less than 1.65g/cm3, only about the 1/5 of steel, the 1/3 of titanium alloy, weight loss effect is obvious, Meet spacecraft lightweight development trend.
(2) present invention achieves adopting the horizontal monolithic molding installing composite drum shell structure main part, Fiber seriality is good, and damping capacity is excellent, and the rigidity of structure and local strength are all higher, good stability, meets The particular/special requirement of spacecraft optical system.
(3) forming die structure form of the present invention, simply it is easy to processing, is easily installed and the demoulding, product wall Thickness is uniform, dimensional accuracy is higher.
(4) forming process of the present invention is simple, reliable, is easy to laying operation, is set using conventional technique For completing to solidify, to similar labyrinth, there is the preferable suitability.
(5) forming process of the present invention is with short production cycle, and the opposing metallic material product production cycle can shorten More than half.
Brief description
Fig. 1 is the right angle setting barrel shell structural representation in prior art with auricle and flange;
Fig. 2 is the right angle setting barrel shell structural representation in prior art with flange;
Fig. 3 is the horizontal mounting cylinder shell structure schematic diagram of the present invention;
Fig. 4 is the structural representation of the cylinder of the present invention;
Fig. 5 is the structural representation of the diaphragm of the present invention;
Fig. 6 is the structural representation of the cylinder shaping dies of the present invention;
Fig. 7 is the structural representation of mandrel in the cylinder shaping dies of the present invention;
Fig. 8 is the structural representation of base in the cylinder shaping dies of the present invention;
Fig. 9 is the structural representation of panel in the cylinder shaping dies of the present invention;
Figure 10 is the structural representation of insert in the cylinder shaping dies of the present invention;
Figure 11 is the structural representation of the cylinder shaping dies latus inframedium of the present invention;
Figure 12 is the structural representation of end cap in the cylinder shaping dies of the present invention;
Figure 13 is the laying schematic diagram of the shell portion of the present invention;
Figure 14 is the process chart of the present invention.
Specific embodiment
The invention will be further described with reference to the accompanying drawings and examples.
Embodiment
Elaborate the present invention with reference to acquiring satellite camera cone (hereinafter referred to as cone).
Cone is using horizontally-mounted thin wall cylinder shell structure, as shown in figure 3, this composite barrel shell bag Include 15, ten ribs 14 of cylinder, 13, three studs 12 of joint face and six diaphragms 11;Six diaphragms , in the inside of cylinder 15, mechanism of diaphragm is as shown in Figure 5 for 11 non-uniform Distribution;The mid portion of joint face 13 It is fixedly connected with cylinder 15 by stud 12, two rim portion of joint face 13 pass through ribs 14 and cylinder 15 are fixedly connected;Article ten, ribs 14 is evenly distributed on the both sides of cylinder 15;In addition to diaphragm 11, other portions I.e. cylinder 15, ribs 14, joint face 13 and stud 12 is divided to be formed in one, this four parts assembly letter Claim cylinder, as shown in Figure 4;Form cavity between two adjacent studs 12;Two adjacent ribs 14 Between formed cavity.
Cone length is 1000mm, and highly for 277mm, cylinder 15 is a diameter ofCylinder 15 Wall thickness be 1mm, the wall thickness of diaphragm is 1mm, and the wall thickness of ten ribs 14 is 2mm, joint face 13 Wall thickness be 2mm, the wall thickness of three studs 12 is 2mm, and material is kevlar/8d-1 composite. Will be bonding integral with six diaphragms for shell portion using cold curing gluing agent.Finally adopt machining side Method processes installing hole and thermal control plug-in unit connecting hole with phase machine bottom board.
As shown in figure 14, steps of the method are:
The first step, Mould design and manufacturing
Mould using horizontally-mounted polymer matrix composites barrel shell structure comprises two parts, cylinder finishing die Tool and diaphragm shaping dies.
As shown in fig. 6, cylinder shaping dies adopt assembling die, this assembling die include mandrel 6, base 1, Panel 4, insert 3, side plate 2, end cap 5 and the equal pressing plate of technique 7;
Mandrel 6 is hollow cylinder, and profile and size are consistent with cylinder 15 inner chamber, as shown in Figure 7;
Base 1 is square cavity, and upper surface is slotted, and upper surface shape and size are consistent with joint face 13, such as Shown in Fig. 8;Base 1 both ends of the surface are slotted, and well width is identical with end cap 5 width, and groove depth is 5mm;
The cavity being formed between panel 4 profile and size and adjacent two studs 12 is consistent, as shown in Figure 9;
The cavity being formed between insert 3 profile and size and adjacent two ribs 14 is consistent, such as Figure 10 Shown;
The number of cavities being formed between the quantity of insert 3 and two ribs 14 is identical;
Side plate 2 is arranged on the outside of insert 3, fits with cylinder side, its fit shape and size and cylinder Side is consistent, as shown in figure 11;
End cap 5 amounts to two pieces, is separately mounted to the two ends of base 1, end cap 5 middle part is according to the shape of panel 4 Shape is slotted, spacing for panel 4, as shown in figure 12;
The equal pressing plate of technique 7 is the profile thin plate consistent with cylinder upper surface shape, using thickness for 0.5mm's Thin plate is made.
Diaphragm shaping dies adopt former, and its cavity shape and size are consistent with diaphragm;
Cylinder shaping dies and diaphragm shaping dies all adopt metal material;
Second step, mould pretreatment
In one layer of fluorocarbons releasing agent of external coating of cylinder shaping dies and diaphragm shaping dies, and dry in the air Dry, releasing agent tolerable temperature is typically not less than 140 DEG C;Surface smear one in securing members such as screw, alignment pins Layer silicone grease;
3rd step, prepared by prepreg
Using the kevlar49/8d-1 plain cloth prepreg of nominal thickness 0.1mm, prepare required prepreg, Prepreg resin content controls 42 ± 5%, and volatile content requires to be not more than 3%, then carries out prepreg b Rankization is processed, i.e. heating makes resin soften but incomplete fusion, has certain viscosity, is easy to work below The paving of sequence;B rank handling process is: enters baking oven, is warming up to 90~100 DEG C and keeps 45~60 minutes;
4th step, prepreg cutting
The quantity of blank, cutting prepreg according to needed for the overall dimensions calculating of cylinder and diaphragm.
5th step, laying
Shell portion carries out laying as follows, before laying, mould is preheating to 50 DEG C:
1) laying prepreg on base 1, forms joint face 13 part, as shown in chain-dotted line below Figure 13, Amount to 15 layers;
2) laying t type prepreg above base 1, forms intermediate studs 12 part, in the middle of such as Figure 13 Shown in solid, 5 layers of horizontal direction, 6 layers of vertical direction;
3) in panel 4 outer surface laying prepreg, form stud 12 part;As shown in Figure 13 dashed middle line, Amount to 5 layers;It is positioned over base 1 top the 2nd together with panel 4 after laying is closely knit) step institute laying t type prepreg Both sides;
4) along mandrel 6 outer surface laying prepreg, form cylinder 15 part, shown in solid above such as Figure 13, Amount to 5 layers;;It is placed on the top of panel 4 after compacting;
5) along mandrel 6 outer surface laying prepreg, both sides turn to downwards the lateral surface of panel 4, such as Figure 13 Shown in the chain-dotted line of top, 5 layers altogether;
6) in the outer surface laying prepreg of insert 3, formed ribs 14 part, after laying is closely knit together with Insert 3 is positioned over the 5th) both sides of step institute laying prepreg, as shown in solid in Figure 13 two sides, altogether 10 Layer;
7) the laying number of plies of above-mentioned each step prepreg is all not quite similar, and needs respectively according to product thickness and monolayer The thickness of prepreg determines.
7) the laying direction of above-mentioned each step prepreg replaces laying using (0/90) and (+45/-45).
Diaphragm part carries out laying as follows:
Along mould inner surface ecto-entad successively laying, repair the edge of pinch-off part along mould outer rim simultaneously.If Using full wafer prepreg, clip should be added by circumferentially spaced 30mm~60mm;If if each layer is divided into Dry tablet prepreg, can be using docking or overlap joint (lap width with layer adjacent two panels prepreg 5mm~10mm), the abutment joint of adjacent layer prepreg or overlap joint line should stagger 10mm in the same direction successively More than;Total laying number of plies is 10 layers, and prepreg laying direction is all (0/90);
Lay-up process should be according to practical situation, and 3~5 layers of every laying carries out a pre-compacted.
6th step, pre-compacted
It is coated with politef isolating membrane, the equal pressing plate of technique, airfelt successively, adhesive seal adhesive tape simultaneously encapsulates Vacuum nylon film, evacuation carries out pre-compacted;
Precompressed real parameter is: evacuated pressure is not more than -0.09mpa, keeps 0.5~1 hour under room temperature state;
After the completion of pre-compacted, remove vacuum nylon film, airfelt, the equal pressing plate of technique, politef every From film, continue the laying step not completed.
7th step, solidification
Repair the flash cutting pre-compacted process, clean the glue of die surface.
Be coated with successively politef isolating membrane, inhale glue-line, politef isolating membrane, the equal pressing plate of technique, Airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film.
Complete to solidify using vacuum bag-autoclave method or vacuum bag-Oven Method, curing process is: evacuation pressure Power is not more than -0.094mpa, be warming up to 70 ± 3 DEG C keep 1 hour after plus outer be depressed into 0.2mpa, continue to heat up To 120 ± 3 DEG C plus it is depressed into 0.5mpa outward, shut down after being continuously heating to 140 ± 3 DEG C of holdings 3 hours, treat temperature Tank is gone out after being down to less than 60 DEG C.
8th step, the demoulding and finishing
Remove vacuum nylon film and airfelt, take off the equal pressing plate 7 on surface, remove end cap 5 and side plate 2, Then remove the insert 4 of both sides, then mandrel 6 deviate from from product, then panel 3 is deviate from from product, Last abjection shell portion from base 1.
Diaphragm is deviate from from diaphragm shaping dies.
The overlap of finishing cylinder and diaphragm and burr.
9th step, assembly trial assembly is joined
The above cylinder being obtained and each diaphragm are carried out trial assembly and join, fit clearance is generally 0.1mm~0.3mm. If fit clearance is more than 0.3mm, appropriate thickening agent can be added when preparing cold curing gluing agent, or The filling layer of glass sand net in bonding.
Tenth step, bonding front surface is processed
Bonding region needed for labelling, periphery pastes isolating membrane.Equably polished cylinder and diaphragm using sand paper Bonding plane, is cleaned, cleans and is dried with acetone solvent.
11st step, joins glue
Prepare the cold curing structural adhesive needed for bonding: using hardener420 adhesive, it prepares work Skill is: according to first component: component B=100:40 (weight ratio) prepares hardener420 glue, fully stirs Mix and make its mix homogeneously.
12nd step, assembly bonding
One layer of hardener420 adhesive is equably smeared respectively on the bonding plane of cylinder and diaphragm, successively will Six diaphragms load in cylinder, clean excessive glue, and are fixed with pressure sensitive adhesive tape.
Under room temperature, standing certain time completes to solidify, and curing process is: keeps contact pressure, stands 7 at room temperature 3 hours are stood under the conditions of it or 60 DEG C.
13rd step, assembly is repaired
Remove pressure sensitive adhesive tape etc., repair excessive glue and the burr on file surface.

Claims (9)

1. a kind of manufacturing process using horizontally-mounted composite barrel shell, this composite barrel shell includes justifying Cylinder, the ribs of more than two, joint face, the stud of more than two and diaphragm;Diaphragm is arranged on cylinder Inside, the mid portion of joint face is fixedly connected with cylinder by stud, and two rim portion of joint face pass through to add Strong rib is fixedly connected with cylinder;Cylinder, ribs, joint face and stud are formed in one, cylinder, reinforcement The assembly abbreviation cylinder of rib, joint face and stud;Form cavity between two adjacent studs;Adjacent Article two, between ribs, form cavity;
It is characterized in that steps of the method are:
The first step, Mould design and manufacturing
Mould includes cylinder shaping dies and diaphragm shaping dies;
Cylinder shaping dies adopt assembling die, this assembling die include mandrel, base, panel, insert, Side plate, end cap and the equal pressing plate of technique;
Mandrel profile and size are consistent with cylinder bore;Base upper surface shape and size are consistent with joint face; The cavity being formed between panel profile and size and adjacent two studs is consistent;
The cavity being formed between insert profile and size and adjacent two ribs is consistent;
The number of cavities being formed between the quantity of insert and two ribs is identical;
Side plate is arranged on the outside of insert, fits with cylinder side, its fit shape and size and cylinder side Unanimously;
End cap two pieces altogether, is separately mounted to the two ends of base, according to the shape fluting of panel in the middle part of end cap, uses Spacing in panel;
The equal pressing plate of technique is the profile thin plate consistent with cylinder upper surface shape;
Diaphragm shaping dies adopt former, and its cavity shape and size are consistent with diaphragm;
Second step, mould pretreatment
In one layer of releasing agent of external coating of cylinder shaping dies and diaphragm shaping dies, releasing agent tolerable temperature It is not less than 140 DEG C, and dry;
3rd step, prepared by prepreg
The required prepreg of preparation, carries out prepreg b rankization according to the particular type of resin matrix and processes, that is, Heating makes resin soften but incomplete fusion;
4th step, prepreg cutting
Overall dimensions cutting prepreg according to cylinder and diaphragm;
5th step, laying
Shell portion carries out laying as follows:
1) laying prepreg on base, forms joint face part;
2) laying t type prepreg above base, forms intermediate studs part;
3) in panel outer surface laying prepreg, form stud part, be positioned over together with panel after laying is closely knit The 2nd above base) both sides of step institute laying t type prepreg;
4) along mandrel outer surface laying prepreg, form cylindrical portions, after compacting, be placed on the upper of panel Side;
5) along mandrel outer surface laying prepreg, both sides turn to downwards the lateral surface of panel;
6) in the outer surface laying prepreg of insert, form ribs part, put together with insert after laying is closely knit It is placed in the 5th) both sides of step institute laying prepreg;
Diaphragm part carries out laying as follows:
Along mould inner surface ecto-entad successively laying, and carry out pre-compacted, repair pinch-off along mould outer rim simultaneously The edge of part;
6th step, pre-compacted
It is coated with politef isolating membrane, the equal pressing plate of technique and airfelt successively, then adhesive seal adhesive tape is simultaneously Encapsulated vacuum nylon film, evacuation carries out pre-compacted;Pre-compacted is carried out in lay-up process, every laying 3~5 Layer carries out a pre-compacted;
After the completion of pre-compacted, remove vacuum nylon film, airfelt, the equal pressing plate of technique, politef every From film, continue the laying step not completed;
7th step, solidification
Repair the flash cutting pre-compacted process, clean the glue of die surface;
Be coated with successively politef isolating membrane, inhale glue-line, politef isolating membrane, the equal pressing plate of technique and Airfelt, then adhesive seal adhesive tape encapsulated vacuum nylon film;
Complete to solidify using vacuum bag-autoclave method or vacuum bag-Oven Method;
8th step, the demoulding and finishing
Remove vacuum nylon film and airfelt, take off the equal pressing plate of technique, remove end cap and side plate, then tear open Except the insert of both sides, then mandrel is deviate from from product, then panel is deviate from from product, finally the bottom of from Shell portion is deviate from seat;
Diaphragm is deviate from from diaphragm shaping dies;
The overlap of finishing cylinder and diaphragm and burr;
9th step, assembly trial assembly is joined
The above cylinder being obtained and each diaphragm are assembled;
Tenth step, bonding front surface is processed
Equably polished using sand paper the bonding plane of cylinder and diaphragm, with solvent clean, clean and dry;
11st step, assembly bonding
One layer of cold curing structural adhesive is equably smeared on the bonding plane of cylinder and diaphragm, successively respectively Each diaphragm is loaded in cylinder, cleans excessive glue, and fixed with pressure sensitive adhesive tape;Stand under room temperature, complete to solidify;
12nd step, assembly is repaired
Remove pressure sensitive adhesive tape, repair excessive glue and the burr on file surface.
2. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: when diaphragm part carries out laying, using full wafer prepreg, circumferentially spaced 30mm~60mm Add clip.
3. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: when diaphragm part carries out laying, if each layer is divided into dry tablet prepreg, with layer adjacent two Piece prepreg using docking or overlap, the abutment joint of adjacent layer prepreg or overlap joint line in the same direction according to Secondary more than the 10mm that staggers.
4. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 3, It is characterized in that: lap width 5mm~10mm.
5. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: the mold base both ends of the surface fluting of the first step, well width is identical with endcap width, groove depth More than 2mm.
6. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: the equal pressing plate of technique of the first step is the thick engineering plastic flitch of 0.3~2mm or aluminium alloy plate.
7. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: the prepreg of the 3rd step be aramid fabric prepreg, aramid fiber unidirectional pre-immersion material, Glass fiber cloth prepreg, glass fibre unidirectional pre-immersion material, carbon fibre fabric prepreg or carbon fiber one-way Prepreg.
8. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: the laying of the 5th step, after every one piece of prepreg of laying, it is coated with one layer of polytetrafluoroethylene film, Then progressively rolled with rubber rollers and electric iron, make densification between layers but corrugationless, adjacent prepreg Splicing seams require to stagger more than 10mm.
9. a kind of manufacturing process using horizontally-mounted composite barrel shell according to claim 1, It is characterized in that: the process for pre-compacting of the 6th step is that evacuated pressure is not more than -0.09mpa, keeps 0.5~1 Hour, carrying out heating according to the particular type of resin matrix while evacuation makes resin soften.
CN201410515854.3A 2014-09-29 2014-09-29 Forming method for composite material barrel shell employing horizontal installation CN104385624B (en)

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CN106700532A (en) * 2016-11-21 2017-05-24 泉州瀚能科技有限公司 Novel composite nanometer energy-saving heating device shell and preparation technology thereof
CN108274777B (en) * 2017-12-22 2020-08-14 北京卫星制造厂 Carbon fiber composite waveguide and preparation method thereof
CN109518824B (en) * 2019-01-07 2020-10-23 北京宇航系统工程研究所 Modular spherical crown-shaped turnover structure bearing large external pressure
CN110299598B (en) * 2019-05-24 2021-02-09 北京卫星制造厂有限公司 Aramid fiber skin-paper honeycomb sandwich cylindrical shell structure and preparation method thereof
CN110524923A (en) * 2019-08-30 2019-12-03 晋西工业集团有限责任公司 A kind of composite forming method of the nonmetallic tubular product of heavy caliber
CN110682559A (en) * 2019-09-19 2020-01-14 中航复合材料有限责任公司 Method for forming aramid fiber composite material central cylinder
CN110789150A (en) * 2019-10-23 2020-02-14 北京卫星制造厂有限公司 Forming method based on multi-profile light heat insulation material
CN111376389A (en) * 2020-03-20 2020-07-07 中国航发北京航空材料研究院 Forming die for cylindrical composite material component with flanging and preparation method

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