CN107199713A - A kind of high-quality forming method of composite material bracket - Google Patents

A kind of high-quality forming method of composite material bracket Download PDF

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Publication number
CN107199713A
CN107199713A CN201710307885.3A CN201710307885A CN107199713A CN 107199713 A CN107199713 A CN 107199713A CN 201710307885 A CN201710307885 A CN 201710307885A CN 107199713 A CN107199713 A CN 107199713A
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China
Prior art keywords
prepreg
lattice chamber
thickness
forming method
laying
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CN201710307885.3A
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Chinese (zh)
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CN107199713B (en
Inventor
孙文文
赵文宇
郭鸿俊
张蕾
郑红飞
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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Priority to CN201710307885.3A priority Critical patent/CN107199713B/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
    • 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
    • B29C70/34Shaping 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
    • B29C70/345Shaping 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 matched moulds
    • 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 high-quality forming method of composite material bracket, by using formpiston, metal silicon rubber (metal core) combination compression molding, outer former (upper cover plate, lower shoe, side shield) above and below metal laying, form closed cavity, silicon rubber soft mode, metal-cored collaboration pressurization, solve the problems, such as external pressure can not the gusset of plaid matching chamber apply pressure and gusset dimensional accuracy, it is ensured that gusset Forming Quality and dimensional accuracy;Designed by composite plys, solve composite material bracket fiber continuity problem to greatest extent, meet carrying demand;Substituted by middle temperature pre-compacted, core rod, cure process is controlled, solve the problems, such as lattice chamber assembly precision, overall co-curing, the once high-quality shaping of composite material bracket is realized, loss of weight about 30% 50%, meet space flight model lighting requirement compared with conventional metal member.

Description

A kind of high-quality forming method of composite material bracket
Technical field
The present invention relates to a kind of high-quality forming method of composite material bracket, particularly a kind of big thickness multi-cavity of large-size The high-quality forming method of flange reinforced structure composite material bracket, belongs to structural composite material and technology field.
Background technology
Currently, space industry is proposed to new model loss of weight, efficient require so that the composite of high-strength light should With increasingly extensively, parts in cabin are developed into from large scale structure bay section.At present, some domestic existing structure bay sections are with supporting zero Part has carried out composite, such as triangle fagging, bearing, operation lid, its regular shape, simple in construction, thickness is smaller, into Type technique is simple, mainly plays certain connection, supporting role.
Composite material bracket is the special-shaped multi-cavity component of the big thickness of large-size in cabin, except the supporting role certain to instrument Outside, while being subjected to the relatively big load produced under certain operating mode, and assembly relation is more, and design is to its bearing capacity, internal matter Amount, dimension precision requirement are higher.Therefore how by rational mold design, moulding process, the big thickness of large-size is solved many Cell method orchid reinforced structure composite material bracket fiber continuity and symmetry are laid, effective application of pressure and uniformly transfer etc. is asked Topic, realizes the overall co-curing shaping of the high-quality of composite material bracket, high dimensional accuracy, while meeting wanting for structural-load-carrying capacity The technical barrier of Seeking Truth urgent need to resolve.
The content of the invention
It is an object of the invention to provide a kind of high-quality forming method of composite material bracket, by optimize mold design, Composite plys design and middle temperature pre-compacted, core rod replacement, cure process control technology etc., realize composite material bracket High-quality overall co-curing shaping, meet model structure loss of weight requirement.
What the above-mentioned purpose of the present invention was mainly achieved by following technical solution:
A kind of high-quality forming method of composite material bracket, the mould of use is including under n upper lattice chamber formpistons, m Lattice chamber formpiston, n soft mode, side shield, upper cover plate and lower shoe, the n upper lattice chamber formpistons, the shapes of n soft mode are made with waiting The shape of n upper lattice chambers of standby support matches, the shape of the m lower lattice chamber formpistons and m of support to be prepared lower lattice chambers Shape match, specific forming method comprises the following steps:
The surfaces of step (1), the surface that prepreg is laid on to n upper lattice chamber formpistons respectively and m lower lattice chamber formpistons;
Step (2), the prepreg progress heating pre-compacted that laying will be completed;
N upper lattice chamber formpistons are removed after step (3), pre-compacted cooling, n upper lattice chamber prepreg overlays are formed, it is soft by n Mould is respectively put into the n upper lattice chamber prepreg overlays;
Step (4), the upper lattice chamber prepreg overlays of n and the m lower lattice chamber formpiston for laying prepreg assembled so that Upper lattice chamber prepreg overlay is contacted and compressed with lower lattice chamber prepreg overlay;
Step (5), lower shoe is fixedly connected with the lower lattice chamber formpistons of m and n soft mode respectively, side shield respectively with Upper cover plate, lower shoe are fixedly connected, and form closed cavity;
Step (6), it is heating and curing, side shield, upper cover plate, soft mode and lower shoe is removed after the completion of solidification, is answered Condensation material support;
Described n, m are positive integer, and n >=2, m >=1.
In above-mentioned forming method, prepreg is laid simultaneously in the upper surface of lattice chamber formpiston respectively on n in the step (1) Under turn to its side surface, lower lattice chamber formpiston is 1, laid in the upper surface of lower lattice chamber formpiston prepreg and under turn to its side table Face.
In above-mentioned forming method, in step (1) process of deployment, the laying for often laying 0.5-1mm thickness carries out one It is secondary to vacuumize compacting, the laying degree of packing is improved, unnecessary material side is removed after compacting.
In above-mentioned forming method, the specific method of pre-compacted is in the step (2):The prepreg for completing laying is adopted After being wrapped up successively with isolated material, suction glue material and vacuum bag, pre-compacted is carried out in baking oven, heating platform or autoclave, is protected Temperature is 70-90 DEG C, and soaking time is 30min-120min.
In above-mentioned forming method, the prepreg is carbon fiber epoxy sweat connecting material, and prepreg thickness is 0.125-0.20mm, resin quality degree is 30%-38%, and volatile content≤1%, fiber areal densities are 130- 220g/m2
In above-mentioned forming method, the soft mode is metal core in silicon rubber soft mode, silicon rubber soft mode, metal-cored with Bottom plate is connected.
In above-mentioned forming method, the upper lattice cavity volume V of the support to be prepared1With the volume V of silicon rubber soft mode2It Poor Δ V is met:5% < Δs V/V1< 12%.
In above-mentioned forming method, n upper lattice chamber prepreg overlays and 1 lower lattice chamber prepreg are spread in the step (4) When layer is assembled, n upper lattice chamber prepreg overlays of built-in n soft mode are placed sequentially in the lower lattice chamber of built-in lower lattice chamber formpiston Prepreg overlay top, and upper surfaces and the lower lattice chamber prepreg overlay of the upper lattice chamber prepreg overlay of n upper surface simultaneously Compress, form the web of support to be prepared, the outer surface of 2 upper lattice chamber prepreg overlays at two ends is spread with lower lattice chamber prepreg The outer surface of layer aligns respectively, the side surface formed between the listrium of support to be prepared, adjacent 2 upper lattice chamber prepreg overlays Laying forms the gusset of support to be prepared;N upper lattice chamber prepreg overlays of the built-in n soft mode be placed side by side on built under The lower lattice chamber prepreg overlay top of lattice chamber formpiston.
In above-mentioned forming method, if the web thickness of support to be prepared is H1, listrium thickness is H2, gusset thickness is H3, Then the overlay thickness of prepreg is H1, H2, H3The half of middle minimum value, i.e. overlay thickness are 1/2MIN { H1, H2, H3}。
In above-mentioned forming method, if web thickness H1, listrium thickness H2, gusset thickness H3Midfield plate thickness H1For maximum Value, that is, meet H1≥MAX{H2, H3, then increase laying web sandwich material is needed, is laid before assembly;If web thickness H1, listrium thickness H2, gusset thickness H3Midfield plate thickness H1For minimum value, that is, meet H1≤MIN{H2, H3, then need increase to spread If gusset sandwich material, is laid before assembly.
In above-mentioned forming method, the step (4) spreads n upper lattice chamber prepreg overlays and 1 lower lattice chamber prepreg After layer is assembled, if the outside table of the outer surface and lower lattice chamber prepreg overlay of the upper lattice chamber prepreg overlay of 2 of two ends Face align respectively after overlay thickness, less than listrium (11) thickness of support to be prepared, then increase the prepreg paving of outer surface Layer, with the thickness requirement for the listrium (11) for meeting support to be prepared.
In above-mentioned forming method, the side shield is two, is U-shape structure, is formed after the end face alignment of U-shape structure Annular housing.
In above-mentioned forming method, it is solidificated in baking oven or autoclave and carries out in the step (6), solidification heating rate is 10~40 DEG C/h, solidification temperature is 150 DEG C~185 DEG C, and hardening time is 3h~8h.
The present invention has the advantages that compared with prior art:
(1), the present invention carries out the preparation of composite material bracket using the mould of particular design, is spread by using metal Formpiston, metal-silicone rubber (metal core) combination compression molding, outer former (upper cover plate, lower shoe, side shield), are formed above and below layer Closed cavity, and being pressurizeed by silicon rubber soft mode, metal-cored collaboration, solve external pressure can not the gusset of plaid matching chamber apply pressure and muscle Board size precision problem, it is ensured that the quality and dimensional accuracy of support web, listrium, especially gusset shaping;
(2), the present invention is designed by prepreg overlay using formpiston above and below metal laying, is solved composite material bracket Fiber continuity problem to greatest extent, meets carrying demand;
(3), the present invention is controlled by middle temperature process for pre-compacting, core rod substitutes, cure process is controlled, and solves lattice chamber group Precision, overall co-curing problem are filled, the once high-quality shaping of composite material bracket is realized;
(4), the present invention is designed during laying according to the size relationship of the web, listrium and gusset of support to be prepared Increase web sandwich material or gusset sandwich material, meet the formed precision and quality of composite material bracket.
(5), the present invention to soft mode structural material by optimizing design, and soft mode uses silicon rubber, and soft mode includes gold Belong to core, it is metal-cored to be connected by screw or pin with lower shoe, and give the lattice cavity volume V of support to be prepared1With silicon rubber (metal core) volume V2Difference Δ V need meet condition, further ensure gusset shaping quality and dimensional accuracy.
(6), support of the present invention loss of weight about 30%-50% compared with conventional metal member, meeting the lighting of space flight model will Ask.
Brief description of the drawings
Fig. 1 is the high-quality forming method flow chart of composite material bracket of the present invention;
Fig. 2 is rack forming mould schematic diagram of the present invention;
Fig. 3 is side shield schematic diagram in mould of the present invention.
Fig. 4 is composite material bracket laying schematic diagram of the present invention;
Fig. 5 is rack forming mould assembling schematic diagram of the present invention.
Embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings:
It is the high-quality forming method flow chart of composite material bracket of the present invention, composite branch of the invention as shown in Figure 1 The forming method of frame specifically includes following steps:
1st, mould manufactures and designs
Composite material bracket relies on metal-silicone rubber assembling die, using integral shaping method, reaches that big thickness is special-shaped more Cavity (lattice chamber side by side, it is non-side by side and deposit) composite material bracket one-shot forming, solve the big thickness multi-cavity flange reinforcement of large-size Structural composite material scaffold fibers continuity and symmetry are laid, effective application of pressure and the problems such as uniformly transfer, and meet knot Structure bearing capacity, high-quality, high-precision design requirement.
Mold design is closing, combined type die, and in composite material bracket, lattice chamber or the non-intracavitary of lattice side by side place silicon side by side Metal core in rubber soft mode, silicon rubber soft mode, is pressurizeed by silicon rubber soft mode, metal-cored collaboration, solidified composite The uniform effectively stress in each side in journey, it is ensured that the high-quality shaping of product and dimensional homogeneity.Composite material bracket to be prepared includes Web, listrium, gusset and the lattice chamber up and down of formation.
Mould includes type metal hard die and silicon rubber soft mode (metal core):
(1) type metal hard die
According to product structure form, type metal hard die is designed, including upper lattice chamber formpiston 1 (is 3 in n point valves, the present embodiment Point valve), lower lattice chamber formpiston 2 (being overall in entirety or m point valves, the present embodiment), side shield 4 (p block side shields, side shield number Amount is designed according to product shape face demand and divide valve, is 2 in the present embodiment), upper cover plate 5, lower shoe 6, as shown in Figure 2 For rack forming mould schematic diagram of the present invention, wherein lower lattice chamber formpiston 2 can be the integrated design with lower shoe 6, upper cover plate 5, Lower shoe 6, side shield 4 are mechanically connected by bolt, and the housing depth that upper cover plate 5, lower shoe 6 are formed after connecting meets to be prepared The requirement of composite material bracket height dimension.
Upper lattice chamber formpiston 1 carries out symmetrical expression point valve with lower lattice chamber formpiston 2 with web thickness position of center line, then upper formpiston Divided valve again again with lattice chamber, point valve principle is to carry out symmetrical expression point valve with gusset mid-depth line position.Ensure gusset and abdomen The fiber continuity of plate is laid.Upper lattice chamber formpiston 1 is only used for laying, and lower lattice chamber formpiston 2 is used for laying and solidification.
If Fig. 3 is side shield schematic diagram in mould of the present invention, side shield 4 is two in the embodiment of the present invention, is U-shaped Structure, forms annular housing after the end face alignment of U-shape structure, upper cover plate 5 is located at the upper surface of annular housing with lower shoe 6 respectively With lower surface, the inner mold face of side shield 4, according to the configuration design of support to be prepared, can be curved baffle 4-1, waveform baffle plate 4-2 etc., as shown in Figure 3.
(2) silicon rubber soft mode (metal core)
The size design of silicon rubber soft mode 3 is according to lattice chamber size, shape, composite material bracket briquetting pressure and silicon rubber expansion Characteristic is carried out.According to lot of experiments and research, support lattice cavity volume V to be formed1With the volume of silicon rubber soft mode 3 (metal core) V2Difference Δ V meet:5% < Δs V/V1There is provided briquetting pressure P, 0.4MPa < P < 1.5MPa by < 12%.In silicon rubber soft mode 3 Metal core 3-1, metal-cored 3-1 are connected by screw or pin 3-2 with lower shoe 6.
The shape of the upper lattice chamber of n of the upper lattice chambers point valve formpiston 1 of n, the shape of n silicon rubber soft mode 3 and support to be prepared Shape matches, and the shape of lower lattice chamber formpiston 2 and the shape of the lower lattice chamber of support to be prepared match.
2nd, prepared by prepreg
Carbon fiber/epoxy resin sweat connecting material is prepared, the quality index of sweat connecting material is prepreg thickness 0.125- 0.20mm, resin quality degree 30%-38%, volatile content≤1%, fiber areal densities 130-220g/m2
3rd, prepreg blanking
According to stent size to be prepared, cutting blanking is carried out to prepreg using automatic blanking machine.
4th, formpiston laying
It is illustrated in figure 4 composite material bracket laying schematic diagram of the present invention;The upper surface of lattice chamber point valve formpiston 1 on n Respectively laying prepreg and under turn to and be laid on its side surface, laid in the upper surface of lower lattice chamber formpiston 2 prepreg and under turn to It is laid on its side surface.I.e. laying when formed under the prepreg of web and turn to listrium, it is ensured that web prepreg and listrium prepreg Fiber is continuous.As shown in figure 4, including upper lattice chamber formpiston laying 20, lower formpiston laying 21, listrium laying 22, web sandwich material paving Layer 23, gusset sandwich material laying 24.
Often the laying of laying 0.5-1mm thickness is once vacuumized compacting, the laying degree of packing is improved, to unnecessary after compacting Material side be removed.
It is illustrated in figure 5 rack forming mould assembling schematic diagram of the present invention;Prepreg overlay and 1 lower lattice chamber prepreg are spread When layer is assembled, n upper lattice chamber prepregs of built-in n soft mode 3 are placed side by side on the lower lattice of built-in lower lattice chamber formpiston 2 successively Chamber prepreg overlay top, and upper surface and the upper surface of lower lattice chamber prepreg overlay of the individual upper lattice chamber prepreg overlays of n And compress, the web 10 of support to be prepared is formed, the outer surface of 2 upper lattice chamber prepreg overlays at two ends is presoaked with lower lattice chamber The outer surface of material laying aligns respectively, is formed between the listrium 11 of support to be prepared, adjacent 2 upper lattice chamber prepreg overlays Side surface laying forms the gusset 12 of support to be prepared.As shown in Figure 5.
If the thickness of the web 10 of support to be prepared is H1, the thickness of listrium 11 is H2, the thickness of gusset 12 is H3, then in advance The overlay thickness of leaching material is H1, H2, H3The half of middle minimum value, i.e. overlay thickness are 1/2MIN { H1, H2, H3}。
If web thickness H1, listrium thickness H2, gusset thickness H3Midfield plate thickness H1For maximum, that is, meet H1≥MAX {H2, H3, then increase laying web sandwich material 13 is needed, is laid before assembly;If web thickness H1, listrium thickness H2、 Gusset thickness H3Midfield plate thickness H1For minimum value, that is, meet H1≤MIN{H2, H3, then increase laying gusset sandwich material 14 is needed, Laid before assembly.
During composite material bracket laying, according to web, listrium, gusset thickness feature, as far as possible ensure fiber continuity and Symmetry is laid, and improves product bearing capacity, as shown in Figure 4.If composite material bracket web thickness H1(4mm≤H1≤ 20mm), Listrium thickness H2, gusset thickness H3, by web and gusset thickness difference Δ H1Individually it is coated with into sandwich material, 1/2MIN { H1, H2, H3Abdomen Prepreg is carried out above plate with supramarginal plate and gusset continuously to lay, 1/2MIN { H1, H2, H3Carry out with inframarginal below web it is pre- Leaching material is continuous to be laid.If H1≥MAX{H2, H3, then sandwich material is web sandwich material, and gusset can be achieved and connects with web fiber 100% It is continuous, web and listrium fiber H2/H1* 100% is continuous;If H1For minimum thickness, H1≤MIN{H2, H3, then sandwich material presss from both sides for gusset Core material, can be achieved gusset and web fiber H1/H3* 100% is continuous, web and listrium fiber 100% are continuous.
5th, middle temperature pre-compacted
The big thickness of product is coated with that to easily cause prepreg compaction not enough, product type face is poor before solidification, decrement compared with Greatly (15-25%), solidification when many clouts extrusion produce built on stilts etc., pressure uniformly can not be transmitted effectively when causing solidification, cause production There is large area defect (percentage of defects is more than 3.5%), thickness deviation and are more than 10% in product, it is impossible to which meeting designing technique index will Ask.In addition, being related to the assembling of lattice chamber formpiston and the replacement qualifying chamber of silicon rubber soft mode in forming process, due to laying material pre-polymerization journey Degree is low, expects partially soft, the demoulding is difficult, and material compaction is poor, easily causes the problems such as assembling position deviation, assembling quality are poor, seriously Influence the Forming Quality of product.Therefore pre-compacted must be carried out to product in forming process.
After product is wrapped up using isolated material, suction glue material, vacuum bag, enter in baking oven, heating platform or autoclave Row pre-compacted, 70-90 DEG C of holding temperature, soaking time 30min-120min.
6th, core rod substitutes
Pre-compacted after cooling, removes n upper lattice chamber point valve formpistons 1, forms lattice on n prepreg after pre-compacted cooling Chamber, n silicon rubber mantle 3 is respectively put on n prepreg in lattice chamber, shape between lattice chamber on silicon rubber soft mode 3 and prepreg Into gap 3-3, as shown in Figure 5.If necessary, first upper lattice chamber laying point valve formpiston laying material product can be freezed after 1-2h, will be upper Lattice chamber point valve formpiston 1 is deviate from.Silicon rubber soft mode 3 (metal core) is put into lattice chamber.
7th, cavity is assembled
Upper lattice chamber laying material is assembled with lower lattice chamber laying material according to drawing, side is alignd, compressed.Specific assembling ginseng Step 4 is seen, if H1、H2、H3It is not completely equivalent, then is specifically described according in step 4, web sandwich material or gusset sandwich material are entered After row is laid, then assembled.
8th, listrium remaining material laying
After assembling, if the outermost surfaces of 2 of two ends upper lattice chamber prepreg overlays and lower lattice chamber prepreg overlay is outer Side surface align respectively after overlay thickness, less than the thickness of the listrium 11 of support to be prepared, then increase the preimpregnation of outer surface Laying is expected, with the thickness requirement for the listrium 11 for meeting support to be prepared.
9th, mould is assembled
Two pieces of side shields 4, upper cover plate 5 are connected with lower shoe 6 using screw, i.e., entered lower shoe 6 with lower lattice chamber formpiston 2 Row is fixedly connected, and lower shoe 6 is fixedly connected with n mantle 3, and side shield 4 is fixedly connected with upper cover plate 5, lower shoe 6 respectively;By It is larger in product decrement before solidification, 2-4 group is carried out using the external former of cramp frame ((upper cover plate, lower shoe, side shield)) Compacting is filled, unnecessary material side is removed, outer former (upper cover plate, lower shoe, side shield) before solidification is fully compressed, is assembled in place, Form closed cavity 18.
10th, heating or heat-pressure curing
Send into baking oven or autoclave and solidify after assembling.Curing process is 10~40 DEG C/h of heating rate in the present embodiment, 150 DEG C~185 DEG C of solidification temperature, hardening time 3h~8h.
11st, it is stripped
Two pieces of side shields 4, upper cover plate 5, silicon rubber soft modes 3 are removed successively, product is deviate from from lower shoe 6, and cleaning is dry The flash of net surrounding, obtains composite material bracket.
The composite material bracket that the present invention is prepared loss of weight about 30%-50% compared with conventional metal member, meets boat Its model lighting requirement.
Embodiment 1
Name of product:Four cell method orchid reinforced composite material support
Product size:Arc length 1000mm, web thickness H1For 10mm, gusset thickness H3For 8mm, listrium thickness H2For 8mm. Lay up design is that gusset is continuous with web fiber 100%, and web and listrium fiber 80% are continuous.The thickness of laying prepreg is 1/ 2MIN{H1, H2, H3, i.e., overlay thickness is 4mm.And meet H1≥MAX{H2, H3, it is necessary to increase laying web sandwich material, in group Laid before dress.
Implementation steps are as follows:
Mold design is closed metal-rubber composition mould, and upper lattice chamber formpiston is divided into 3 according to gusset mid-depth line Valve, as shown in Figure 2.Product lattice cavity volume V to be formed1With silicon rubber (metal core) volume V2Difference Δ V=7%V1
From prepreg thickness 0.15mm, resin content 35 ± 3%, volatile content≤1%, fiber areal densities 165 ± 5g/m2
According to product size, cutting blanking is carried out to prepreg using automatic blanking machine.
Prepreg 4mm layings are carried out on upper lattice chamber laying point valve formpiston and lower lattice chamber formpiston, web is formed during laying Listrium is turned under prepreg, it is ensured that web prepreg and listrium prepreg fiber are continuous.2mm web sandwich material are spread simultaneously.Often 0.6mm layings are once vacuumized compacting, and unnecessary material side is removed after compacting.
After product is wrapped up using isolated material, suction glue material, vacuum bag, pre-compacted, holding temperature are carried out in an oven 80-85 DEG C, soaking time 45min.
After pre-compacted, upper lattice chamber laying point valve formpiston laying material is cooled down into 1h in icebox, upper lattice chamber formpiston block is deviate from. Silicon rubber soft mode (metal core) is put into lattice chamber.
Web sandwich material is laid on lower lattice chamber laying material, then upper lattice chamber laying material and lower lattice chamber is spread according to drawing Layered material is assembled, and side is alignd, and is compressed.
Complete listrium residue 4mm material layings.
Two pieces of side shields, upper cover plate and lower shoe laying mould are connected using screw.2 are carried out using the external former of cramp frame Secondary assembling compacting, removes unnecessary material side, outer former before solidification is fully compressed, and assembling in place, forms closed cavity.
Send into baking oven or autoclave and solidify after assembling.Curing process is 20~30 DEG C/h of heating rate, solidification temperature 165 DEG C~175 DEG C, hardening time 6h.
After solidification, two pieces of side shields, upper cover plate, silicon rubber soft modes are removed successively, product is deviate from from lower shoe, clear up The flash of clean surrounding, obtains product.
Embodiment 2
Name of product:Six cell method orchid reinforced composite material support
Product size:Arc length 1500mm, web thickness H1For 12mm, gusset thickness H3For 14mm, listrium thickness H2For 12mm.Lay up design is that gusset is continuous with web fiber 85.7%, and web and listrium fiber 100% are continuous.Laying prepreg Thickness is 1/2MIN { H1, H2, H3, i.e., overlay thickness is 6mm.Meet H1≤MIN{H2, H3, then need increase laying gusset folder Core material, is laid before assembly.
Implementation steps are as follows:
Mold design is closed metal-rubber composition mould, and upper lattice chamber formpiston is divided into 5 valves according to gusset center line. Shaped article lattice cavity volume V1With silicon rubber (metal core) volume V2Difference Δ V=6%V1
From prepreg thickness 0.15mm, resin content 35 ± 3%, volatile content≤1%, fiber areal densities 165 ± 5g/m2
According to product size, cutting blanking is carried out to prepreg using automatic blanking machine.
Prepreg 6mm layings are carried out on upper lattice chamber laying point valve formpiston and lower lattice chamber formpiston, web is formed during laying Listrium is turned under prepreg, it is ensured that web prepreg and listrium prepreg fiber are continuous.2mm gusset sandwich material are spread simultaneously.Per 1mm Laying is once vacuumized compacting, and unnecessary material side is removed after compacting.
After product is wrapped up using isolated material, suction glue material, vacuum bag, pre-compacted, holding temperature are carried out in an oven 85-90 DEG C, soaking time 30min.
After pre-compacted, upper lattice chamber laying point valve formpiston laying material is cooled down into 2h in icebox, upper lattice chamber formpiston block is deviate from. Silicon rubber soft mode (metal core) is put into lattice chamber.
Upper lattice chamber laying material is assembled with lower lattice chamber laying material according to drawing, 2mm gusset sandwich material are sandwiched between gusset, Side is alignd, and is compressed.
Complete listrium residue 6mm material layings.
Two pieces of side shields, upper cover plate and lower shoe laying mould are connected using screw.4 are carried out using the external former of cramp frame Secondary assembling compacting, removes unnecessary material side, outer former before solidification is fully compressed, and assembling in place, forms closed cavity.
Send into baking oven or autoclave and solidify after assembling.Curing process is 10~15 DEG C/h of heating rate, solidification temperature 170 DEG C~180 DEG C, hardening time 6h.
After solidification, two pieces of side shields, upper cover plate, silicon rubber soft modes are removed successively, product is deviate from from lower shoe, clear up The flash of clean surrounding, obtains product.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto, Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, It should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.

Claims (13)

1. a kind of high-quality forming method of composite material bracket, it is characterised in that:The mould of use includes n upper lattice chamber sun The lower lattice chamber formpiston (2) of mould (1), m, n soft mode (3), side shield (4), upper cover plate (5) and lower shoe (6), the n is individual to go up lattice Chamber formpiston (1), the shape and the shape of n upper lattice chambers of support to be prepared of n soft mode (3) match, the m lower lattice chamber sun The shape of mould (2) and the shape of the m of support to be prepared lower lattice chambers match, and specific forming method comprises the following steps:
The surfaces of step (1), the surface that prepreg is laid on to n upper lattice chamber formpistons (1) respectively and m lower lattice chamber formpistons (2);
Step (2), the prepreg progress heating pre-compacted that laying will be completed;
N upper lattice chamber formpistons (1) are removed after step (3), pre-compacted cooling, n upper lattice chamber prepreg overlays are formed, it is soft by n Mould (3) is respectively put into the n upper lattice chamber prepreg overlays;
Step (4), the upper lattice chamber prepreg overlays of n and the m lower lattice chamber formpiston (2) for laying prepreg assembled so that Upper lattice chamber prepreg overlay is contacted and compressed with lower lattice chamber prepreg overlay;
Step (5), lower shoe (6) is fixedly connected with the lower lattice chamber formpistons (2) of m and n soft mode respectively, side shield (4) It is fixedly connected respectively with upper cover plate (5), lower shoe (6), forms closed cavity;
Step (6), it is heating and curing, side shield (4), upper cover plate (5), soft mode (3) and lower shoe is removed after the completion of solidification (6) composite material bracket, is obtained;
Described n, m are positive integer, and n >=2, m >=1.
2. forming method according to claim 1, it is characterised in that:In the step (1) on n lattice chamber formpiston (1) Upper surface lay respectively prepreg and under turn to its side surface, lower lattice chamber formpiston (2) is 1, in the upper of lower lattice chamber formpiston (2) Surface lay prepreg and under turn to its side surface.
3. forming method according to claim 1, it is characterised in that:In step (1) process of deployment, 0.5- is often laid The laying of 1mm thickness is once vacuumized compacting, improves the laying degree of packing, unnecessary material side is removed after compacting.
4. forming method according to claim 1, it is characterised in that:The specific method of pre-compacted is in the step (2): After the prepreg for completing laying is wrapped up successively using isolated material, suction glue material and vacuum bag, in baking oven, heating platform or heat Pre-compacted is carried out in pressure tank, holding temperature is 70-90 DEG C, and soaking time is 30min-120min.
5. forming method according to claim 1, it is characterised in that:The prepreg is that carbon fiber epoxy hot melt is pre- Leaching material, prepreg thickness be 0.125-0.20mm, resin quality degree be 30%-38%, volatile content≤1%, Fiber areal densities are 130-220g/m2
6. forming method according to claim 1, it is characterised in that:The soft mode (3) is silicon rubber soft mode, and silicon rubber is soft Metal core in mould, it is metal-cored to be connected with lower shoe (6).
7. forming method according to claim 6, it is characterised in that:The upper lattice cavity volume V of the support to be prepared1With The volume V of silicon rubber soft mode2Difference Δ V meet:5% < Δs V/V1< 12%.
8. forming method according to claim 2, it is characterised in that:N upper lattice chamber prepreg overlays in the step (4) When being assembled with 1 lower lattice chamber prepreg overlay, n upper lattice chamber prepreg overlays of built-in n soft mode (3) are placed sequentially in The lower lattice chamber prepreg overlay top of built-in lower lattice chamber formpiston (2), and upper surface and the lower lattice chamber of the individual upper lattice chamber prepreg overlays of n The upper surface and compression of prepreg overlay, form the web (10) of support to be prepared, 2 upper lattice chamber prepreg pavings at two ends The outer surface of layer aligns respectively with the outer surface of lower lattice chamber prepreg overlay, forms the listrium (11) of support to be prepared, phase Side surface laying between adjacent 2 upper lattice chamber prepreg overlays forms the gusset (12) of support to be prepared;The built-in n soft mode (3) n upper lattice chamber prepreg overlays are placed side by side on the lower lattice chamber prepreg overlay top of built-in lower lattice chamber formpiston (2).
9. forming method according to claim 8, it is characterised in that:If web (10) thickness of support to be prepared is H1, edge Plate (11) thickness is H2, gusset (12) thickness is H3, then the overlay thickness of prepreg is H1, H2, H3The half of middle minimum value, that is, spread Thickness degree is 1/2MIN { H1, H2, H3}。
10. forming method according to claim 8 or claim 9, it is characterised in that:If web thickness H1, listrium thickness H2, gusset Thickness H3Midfield plate thickness H1For maximum, that is, meet H1≥MAX{H2, H3, then increase laying web sandwich material (13) is needed, Laid before assembling;If web thickness H1, listrium thickness H2, gusset thickness H3Midfield plate thickness H1For minimum value, that is, meet H1≤MIN{H2, H3, then increase laying gusset sandwich material (14) is needed, is laid before assembly.
11. forming method according to claim 8 or claim 9, it is characterised in that:The step (4) goes up lattice chamber prepregs by n After laying is assembled with 1 lower lattice chamber prepreg overlay, if the outer surface of the upper lattice chamber prepreg overlay of 2 of two ends is with The outer surface of lattice chamber prepreg overlay align respectively after overlay thickness, less than listrium (11) thickness of support to be prepared, then Increase the prepreg overlay of outer surface, with the thickness requirement for the listrium (11) for meeting support to be prepared.
12. the forming method according to one of claim 1-7, it is characterised in that:The side shield (4) is two, is U Type structure, annular housing is formed after the end face alignment of U-shape structure.
13. the forming method according to one of claim 1-7, it is characterised in that:Be solidificated in the step (6) baking oven or In autoclave carry out, solidification heating rate be 10~40 DEG C/h, solidification temperature be 150 DEG C~185 DEG C, hardening time for 3h~ 8h。
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN112092410A (en) * 2020-07-31 2020-12-18 北京卫星制造厂有限公司 Co-curing molding method for high-stability integrated support bearing high-precision camera
CN112123811A (en) * 2020-07-24 2020-12-25 北京卫星制造厂有限公司 Forming method of split tooling composite material bracket

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Publication number Priority date Publication date Assignee Title
CN103407019A (en) * 2013-07-18 2013-11-27 航天材料及工艺研究所 Combined die and its application in molding composite material structure member
CN105034403A (en) * 2015-06-25 2015-11-11 北京卫星制造厂 Method for manufacturing composite shell
CN106113522A (en) * 2016-06-29 2016-11-16 航天材料及工艺研究所 A kind of variable cross-section I-shaped beam mantle assistant formation method containing corrugated listrium

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103407019A (en) * 2013-07-18 2013-11-27 航天材料及工艺研究所 Combined die and its application in molding composite material structure member
CN105034403A (en) * 2015-06-25 2015-11-11 北京卫星制造厂 Method for manufacturing composite shell
CN106113522A (en) * 2016-06-29 2016-11-16 航天材料及工艺研究所 A kind of variable cross-section I-shaped beam mantle assistant formation method containing corrugated listrium

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN108943769B (en) * 2018-06-21 2020-05-12 西安爱生技术集团公司 Manufacturing method of non-equal-diameter closed square tubular carbon fiber beam structural part of unmanned aerial vehicle
CN112123811A (en) * 2020-07-24 2020-12-25 北京卫星制造厂有限公司 Forming method of split tooling composite material bracket
CN112092410A (en) * 2020-07-31 2020-12-18 北京卫星制造厂有限公司 Co-curing molding method for high-stability integrated support bearing high-precision camera

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