CN105437566A - Manufacturing method of composite material supporting part for satellite radiation refrigerator - Google Patents
Manufacturing method of composite material supporting part for satellite radiation refrigerator Download PDFInfo
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- CN105437566A CN105437566A CN201511024241.0A CN201511024241A CN105437566A CN 105437566 A CN105437566 A CN 105437566A CN 201511024241 A CN201511024241 A CN 201511024241A CN 105437566 A CN105437566 A CN 105437566A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping 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
- B29C70/34—Shaping 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping 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
- B29C70/32—Shaping 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 on a rotating mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08G—MACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
- C08G59/00—Polycondensates containing more than one epoxy group per molecule; Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
- C08G59/18—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing
- C08G59/40—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing characterised by the curing agents used
- C08G59/50—Amines
- C08G59/5006—Amines aliphatic
- C08G59/502—Polyalkylene polyamines
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- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a manufacturing method of a composite material supporting part for a satellite radiation refrigerator. The manufacturing method comprises the following steps: (1) designing and manufacturing a winding mold according to shape requirements and dimensional requirements of the to-be-prepared composite material supporting part for the satellite radiation refrigerator, and performing surface treatment on the manufactured winding mold; (2) preparing resin glue liquid by adopting epoxy resin or cyanate ester resin as a raw material; (3) performing wind-molding to obtain a winded part; (4) curing and subsequently performing accurate grinding on the surface to obtain the composite material supporting part for the satellite radiation refrigerator. According to the manufacturing method disclosed by the invention, the winding mold is designed and manufactured according to the shape requirements and dimensional requirements of the product, high-performance organic fibers are taken as a reinforcing body, and a winding machine is used for manufacturing the supporting part, so the performance stability repeatability and the dimensional accuracy of the product can be guaranteed.
Description
Technical field
The invention belongs to technical field of composite preparation, be specifically related to a kind of preparation method of satellite radiation refrigerator composite material support.
Background technology
In early stage, satellite radiation refrigerator support member adopts manual Wrapping formed glass fiber compound material, along with the development of the high performance of spaceborne precision instrument, there is problems such as being wound around by hand, product mechanical property is low, performance inconsistency is large, dimensional accuracy is low and reliability is low owing to adopting glass fiber compound material support member, cannot meet Satellite Product growth requirement of new generation.
In addition, because support member is as mechanics load-carrying construction in precision instrument, need that there is electrical insulating property simultaneously, be therefore not suitable for adopting carbon fibre composite.
Summary of the invention
Technical problem to be solved by this invention is for above-mentioned the deficiencies in the prior art, provides a kind of preparation method of satellite radiation refrigerator composite material support.The present invention designs according to shape of product and dimensional requirement and makes Wound Dies, chooses high-performance organic fibre as reinforcement, adopts wrapping machine to carry out the preparation of support member, can ensure the dimensional accuracy of stable performance repeatability and product.
For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of preparation method of satellite radiation refrigerator composite material support, and it is characterized in that, the method comprises the following steps:
Step one, require design and make Wound Dies according to the shape and size of satellite radiation refrigerator composite material support to be prepared, then surface treatment is carried out to made Wound Dies;
Step 2, by epoxy resin and amine curing agent in mass ratio 1: (0.03 ~ 0.09) mixes, and obtains resin adhesive liquid A; Or, by epoxy resin, amine curing agent and acetone in mass ratio 1: (0.03 ~ 0.09): (1 ~ 3) mixes, and obtains resin adhesive liquid B; Or, by cyanate ester resin and acetone in mass ratio 1: (1 ~ 3) mixes, and obtains resin adhesive liquid C;
Step 3, resin adhesive liquid A described in step 2 is added in glue groove, Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, process a locating slot for positioning fiber, then utilize wrapping machine to carry out Wet Winding Process to fiber, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of fiber to be 30N ~ 80N in described Wet Winding Process process; Described fiber is APMOC fiber, aramid III fiber, pbo fiber or UHMWPE fiber;
Or, resin adhesive liquid B described in step 2 or resin adhesive liquid C is added in glue groove, fiber is immersed in resin adhesive liquid B or resin adhesive liquid C and carry out dipping process, obtain prepegged strands, then the Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, process a locating slot for positioning prepegged strands, utilize wrapping machine to carry out dry method winding to prepegged strands afterwards, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of prepegged strands to be 30N ~ 80N in described dry method winding process; Described fiber is APMOC fiber, aramid III fiber, pbo fiber or UHMWPE fiber;
Step 4, wrap described in step 3 is placed in heating furnace together with Wound Dies, be solidify 2h ~ 6h under the condition of 150 DEG C ~ 200 DEG C in temperature, Wound Dies is removed with after stove cooling, adopt sand paper to carry out surface fine grinding to the wrap after solidification, obtain satellite radiation refrigerator composite material support.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, it is characterized in that, amine curing agent described in step 2 is triethylene tetramine, and described organic solvent is acetone.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, it is characterized in that, in prepegged strands described in step 3, the mass percentage of fiber is 50% ~ 80%.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, is characterized in that, the degree of depth of locating slot described in step 3 is 2mm ~ 5mm.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, is characterized in that, the order number of sand paper described in step 4 is 200 order ~ 800 orders.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, is characterized in that, the shape of the radiation refrigerator of satellite described in step 4 composite material support is annular or ellipse annular.
The preparation method of above-mentioned a kind of satellite radiation refrigerator composite material support, it is characterized in that, resin adhesive liquid before curing, is evenly coated in wrap surface by wrap in advance described in step 4, and coated resin adhesive liquid is resin adhesive liquid A or acrylic resin.
The present invention compared with prior art has the following advantages:
1, first the present invention designs according to shape of product and dimensional requirement and makes Wound Dies, then chooses high-performance organic fibre as reinforcement, adopts wrapping machine to carry out the preparation of support member, can ensure the dimensional accuracy of stable performance repeatability and product.
2, the present invention adopts wrapping machine can prepare miniature composite product, adopt wet method/dry method winding technology and Design of Dies to ensure the dimensional accuracy of stable performance repeatability and product, the dimensional accuracy that glue processing method and surperficial fine grinding technology can ensure product is covered on top layer.
3, the present invention effectively can ensure the preparation of high-quality composite material support, the product developed has that production efficiency is high, product mechanical stability, dimensional accuracy are high and the advantage such as apparent flat smooth, can meet satellite precise instrument of new generation completely to the growth requirement of composite product.
Below in conjunction with embodiment, the present invention is described in further detail.
Detailed description of the invention
Embodiment 1
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 75mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support comprises the following steps:
Step one, require design and make Wound Dies according to the shape and size of satellite radiation refrigerator composite material support to be prepared, then surface treatment is carried out to made Wound Dies;
Wound Dies made by the present embodiment comprises tabular core, is arranged on the side plate of the core left and right sides, and the cover plate be arranged on above core, described core, form airtight chamber between side plate and cover plate, the shape and size of described airtight chamber require all to require to match with the shape and size of satellite radiation refrigerator composite material support to be prepared;
Step 2, epoxy resin and amine curing agent to be mixed in mass ratio at 1: 0.06, obtain resin adhesive liquid A; Described amine curing agent is preferably triethylene tetramine;
Step 3, resin adhesive liquid A described in step 2 is added in glue groove, Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, processing degree of depth being 2mm ~ 5mm and locating slot for positioning fiber, then utilize wrapping machine to carry out Wet Winding Process to fiber, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of fiber to be 50N in described Wet Winding Process process; Described fiber is APMOC fiber;
When implementing to be wound around, first core and side plate are assembled complete, be then arranged on wrapping machine and carry out fiber Wet Winding Process, after Filament-wound Machine thickness is concordant with side plate top, stops being wound around, then fit on cover plate, the shape and size of wrap are required accurately controlled;
Step 4, wrap described in step 3 is placed in heating furnace together with Wound Dies, be be incubated 4h under the condition of 180 DEG C to be cured process in temperature, Wound Dies is removed with after stove cooling, adopt order number to be that 500 object sand paper carry out surface fine grinding to the wrap after solidification, obtain satellite radiation refrigerator composite material support.
In the present embodiment, before described wrap is cured process, in advance resin adhesive liquid is evenly coated in wrap surface, coated resin adhesive liquid is resin adhesive liquid A or acrylic resin, in order to improve the flat smooth degree of product external surfaces.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 2
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 60mm, and the wall thickness of described satellite radiation refrigerator composite material support is 1.5mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 1 are only: the mass ratio of epoxy resin described in step 2 and amine curing agent is 1: 0.09; Fiber described in step 3 is aramid III fiber, and the tension force of described fiber is 20N; The temperature of solidifying described in step 4 is 200 DEG C, and the time of described solidification is 2h, and the order number of described sand paper is 200 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 3
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 70mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 1 are only: the mass ratio of epoxy resin described in step 2 and amine curing agent is 1: 0.03; Fiber described in step 3 is pbo fiber, and the tension force of described fiber is 80N; The temperature of solidifying described in step 4 is 150 DEG C, and the time of described solidification is 6h, and the order number of described sand paper is 800 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 4
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 50mm, and the wall thickness of described satellite radiation refrigerator composite material support is 1mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 1 are only: the mass ratio of epoxy resin described in step 2 and amine curing agent is 1: 0.06; Fiber described in step 3 is UHMWPE fiber, and the tension force of described fiber is 60N; The temperature of solidifying described in step 4 is 160 DEG C, and the time of described solidification is 5h, and the order number of described sand paper is 400 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 5
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 100mm, and the wall thickness of described satellite radiation refrigerator composite material support is 3mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support comprises the following steps:
Step one, require design and make Wound Dies according to the shape and size of satellite radiation refrigerator composite material support to be prepared, then surface treatment is carried out to made Wound Dies;
Wound Dies made by the present embodiment comprises tabular core, is arranged on the side plate of the core left and right sides, and the cover plate be arranged on above core, described core, form airtight chamber between side plate and cover plate, the shape and size of described airtight chamber require all to require to match with the shape and size of satellite radiation refrigerator composite material support to be prepared;
Step 2, epoxy resin, amine curing agent and acetone to be mixed in mass ratio at 1: 0.05: 2, obtain resin adhesive liquid B; Described amine curing agent is triethylene tetramine;
Step 3, add in glue groove by resin adhesive liquid B described in step 2, immersed by fiber in resin adhesive liquid B and carry out dipping process, obtain prepegged strands, in described prepegged strands, the mass percentage of resin adhesive liquid B is 40%.Then the Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, processing degree of depth being 2mm ~ 5mm and locating slot for positioning prepegged strands, utilize wrapping machine to carry out dry method winding to prepegged strands afterwards, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of prepegged strands to be 50N in described dry method winding process; Described fiber is APMOC fiber;
When implementing to be wound around, first core and side plate are assembled complete, be then arranged on wrapping machine and carry out the winding of prepegged strands dry method, after prepegged strands winding thickness is concordant with side plate top, stop being wound around, then fit on cover plate, the shape and size of wrap are required accurately controlled;
Step 4, wrap described in step 3 is placed in heating furnace together with Wound Dies, be be incubated 5h under the condition of 180 DEG C to be cured process in temperature, Wound Dies is removed with after stove cooling, adopt order number to be that 500 object sand paper carry out surface fine grinding to the wrap after solidification, obtain satellite radiation refrigerator composite material support.
In the present embodiment, before described wrap is cured process, in advance resin adhesive liquid is evenly coated in wrap surface, coated resin adhesive liquid is resin adhesive liquid A or acrylic resin, in order to improve the flat smooth degree of product external surfaces.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 6
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 70mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 5 are only: the mass ratio of epoxy resin described in step 2, amine curing agent and acetone is 1: 0.09: 3; Fiber described in step 3 is aramid III fiber, and the tension force of described fiber is 20N; The temperature of solidifying described in step 4 is 200 DEG C, and the time of described solidification is 2h, and the order number of described sand paper is 200 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 7
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 68mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 5 are only: the mass ratio of epoxy resin described in step 2, amine curing agent and acetone is 1: 0.03: 1; Fiber described in step 3 is pbo fiber, and the tension force of described fiber is 80N, and in described prepegged strands, the mass percentage of resin adhesive liquid B is 30%, and the mass percentage of fiber is 70%; The temperature of solidifying described in step 4 is 150 DEG C, and the time of described solidification is 6h, and the order number of described sand paper is 800 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 8
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 50mm, and the wall thickness of described satellite radiation refrigerator composite material support is 1mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support is only with the difference of embodiment 5: the mass ratio of epoxy resin described in step 2, amine curing agent and acetone is to mix at 1: 0.03: 3; Fiber described in step 3 is UHMWPE fiber, and the tension force of described fiber is 60N, and in described prepegged strands, the mass percentage of resin adhesive liquid B is 50%, and the mass percentage of fiber is 50%; The temperature of solidifying described in step 4 is 160 DEG C, and the time of described solidification is 5h, and the order number of described sand paper is 400 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 9
The shape of the present embodiment satellite to be prepared radiation refrigerator composite material support is ellipse annular, distance between the left part of described satellite radiation refrigerator composite material support and right part is 90mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2.5mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support is only with the difference of embodiment 5: the mass ratio of epoxy resin described in step 2, amine curing agent and acetone is to mix at 1: 0.09: 1; Fiber described in step 3 is pbo fiber, and the tension force of described fiber is 50N; The temperature of solidifying described in step 4 is 150 DEG C, and the time of described solidification is 4h, and the order number of described sand paper is 200 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 10
The shape of the present embodiment satellite radiation refrigerator to be prepared composite material support is annular, and the external diameter of described satellite radiation refrigerator composite material support is 80mm, and the wall thickness of described satellite radiation refrigerator composite material support is 3mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support comprises the following steps:
Step one, require design and make Wound Dies according to the shape and size of satellite radiation refrigerator composite material support to be prepared, then surface treatment is carried out to made Wound Dies;
Wound Dies made by the present embodiment comprises cylindrical core mold, is set in the tubular side plate of the core left and right sides, and the tubular cover plate be set in outside core, described core, form airtight chamber between side plate and cover plate, the shape and size of described airtight chamber require all to require to match with the shape and size of satellite radiation refrigerator composite material support to be prepared;
Step 2, cyanate ester resin and acetone to be mixed in mass ratio at 1: 2, obtain resin adhesive liquid C;
Step 3, resin adhesive liquid C described in step one is added in glue groove, fiber is immersed in resin adhesive liquid C and carry out dipping process, obtain prepegged strands, in described prepegged strands, the mass percentage of resin adhesive liquid C is 30%, then the Wound Dies after surface treatment in step 2 is arranged on wrapping machine, and on the silk mouth of wrapping machine, processing degree of depth being 2mm ~ 5mm and locating slot for positioning prepegged strands, utilize wrapping machine to carry out dry method winding to prepegged strands afterwards, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of prepegged strands to be 50N in described dry method winding process; Described fiber is APMOC fiber;
When implementing to be wound around, first core and side plate are assembled complete, be then arranged on wrapping machine and carry out the winding of prepegged strands dry method, after prepegged strands winding thickness is concordant with side plate top, stop being wound around, then fit on cover plate, the shape and size of wrap are required accurately controlled;
Step 4, wrap described in step 3 is placed in heating furnace together with Wound Dies, be be incubated 4h under the condition of 180 DEG C to be cured process in temperature, Wound Dies is removed with after stove cooling, adopt order number to be that 500 object sand paper carry out surface fine grinding to the wrap after solidification, obtain satellite radiation refrigerator composite material support.
In the present embodiment, before described wrap is cured process, in advance resin adhesive liquid is evenly coated in wrap surface, coated resin adhesive liquid is resin adhesive liquid A or acrylic resin, in order to improve the flat smooth degree of product external surfaces.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 11
The shape of the present embodiment satellite radiation refrigerator to be prepared composite material support is annular, and the external diameter of described satellite radiation refrigerator composite material support is 70mm, and the wall thickness of described satellite radiation refrigerator composite material support is 2mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 10 are only: the mass ratio of cyanate ester resin described in step 2 and acetone is 1: 3; Fiber described in step 3 is aramid III fiber, and the tension force of described fiber is 20N, and in described prepegged strands, the mass percentage of resin adhesive liquid C is 30%, and the mass percentage of fiber is 70%; The temperature of solidifying described in step 4 is 200 DEG C, and the time of described solidification is 2h, and the order number of described sand paper is 200 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 12
The shape of the present embodiment satellite radiation refrigerator to be prepared composite material support is annular, and the external diameter of described satellite radiation refrigerator composite material support is 100mm, and the wall thickness of described satellite radiation refrigerator composite material support is 3mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 10 are only: the mass ratio of cyanate ester resin described in step 2 and acetone is 1: 1; Fiber described in step 3 is pbo fiber, and the tension force of described fiber is 80N, and in described prepegged strands, the mass percentage of resin adhesive liquid C is 50%, and the mass percentage of fiber is 50%; The temperature of solidifying described in step 4 is 150 DEG C, and the time of described solidification is 6h, and the order number of described sand paper is 800 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 13
The shape of the present embodiment satellite radiation refrigerator to be prepared composite material support is annular, and the external diameter of described satellite radiation refrigerator composite material support is 60mm, and the wall thickness of described satellite radiation refrigerator composite material support is 3mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 10 are only: the mass ratio of cyanate ester resin described in step 2 and acetone is 1: 1.5; Fiber described in step 3 is UHMWPE fiber, and the tension force of described fiber is 60N, and in described prepegged strands, the mass percentage of resin adhesive liquid C is 40%, and the mass percentage of fiber is 60%; The temperature of solidifying described in step 4 is 160 DEG C, and the time of described solidification is 5h, and the order number of described sand paper is 400 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
Embodiment 14
The shape of the present embodiment satellite radiation refrigerator to be prepared composite material support is annular, and the external diameter of described satellite radiation refrigerator composite material support is 60mm, and the wall thickness of described satellite radiation refrigerator composite material support is 1.5mm.The preparation method of the present embodiment satellite radiation refrigerator composite material support and the difference of embodiment 10 are only: the mass ratio of cyanate ester resin described in step 2 and acetone is 1: 2; Fiber described in step 3 is pbo fiber, and the tension force of described fiber is 50N; The temperature of solidifying described in step 4 is 150 DEG C, and the time of described solidification is 4h, and the order number of described sand paper is 200 orders.
First the present embodiment designs according to shape of product and dimensional requirement and makes Wound Dies, then high-performance organic fibre is chosen as reinforcement according to resin, adopt wrapping machine to carry out the preparation of support member, the dimensional accuracy of stable performance repeatability and product can be ensured.The present embodiment has the advantages such as production efficiency is high, product mechanical stability, dimensional accuracy are high, apparent flat smooth, meets satellite precise instrument of new generation completely to the growth requirement of composite product.
The above is only preferred embodiment of the present invention, not imposes any restrictions the present invention.Every above embodiment is done according to invention technical spirit any simple modification, change and equivalence change, all still belong in the protection domain of technical solution of the present invention.
Claims (7)
1. a preparation method for satellite radiation refrigerator composite material support, is characterized in that, the method comprises the following steps:
Step one, require design and make Wound Dies according to the shape and size of satellite radiation refrigerator composite material support to be prepared, then surface treatment is carried out to made Wound Dies;
Step 2, by epoxy resin and amine curing agent in mass ratio 1: (0.03 ~ 0.09) mixes, and obtains resin adhesive liquid A; Or, by epoxy resin, amine curing agent and acetone in mass ratio 1: (0.03 ~ 0.09): (1 ~ 3) mixes, and obtains resin adhesive liquid B; Or, by cyanate ester resin and acetone in mass ratio 1: (1 ~ 3) mixes, and obtains resin adhesive liquid C;
Step 3, resin adhesive liquid A described in step 2 is added in glue groove, Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, process a locating slot for positioning fiber, then utilize wrapping machine to carry out Wet Winding Process to fiber, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of fiber to be 30N ~ 80N in described Wet Winding Process process; Described fiber is APMOC fiber, aramid III fiber, pbo fiber or UHMWPE fiber;
Or, resin adhesive liquid B described in step 2 or resin adhesive liquid C is added in glue groove, fiber is immersed in resin adhesive liquid B or resin adhesive liquid C and carry out dipping process, obtain prepegged strands, then the Wound Dies after surface treatment in step one is arranged on wrapping machine, and on the silk mouth of wrapping machine, process a locating slot for positioning prepegged strands, utilize wrapping machine to carry out dry method winding to prepegged strands afterwards, Wound Dies obtains wrap; Tension controller is adopted to regulate the tension force of prepegged strands to be 30N ~ 80N in described dry method winding process; Described fiber is APMOC fiber, aramid III fiber, pbo fiber or UHMWPE fiber;
Step 4, wrap described in step 3 is placed in heating furnace together with Wound Dies, be solidify 2h ~ 6h under the condition of 150 DEG C ~ 200 DEG C in temperature, Wound Dies is removed with after stove cooling, adopt sand paper to carry out surface fine grinding to the wrap after solidification, obtain satellite radiation refrigerator composite material support.
2. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, it is characterized in that, amine curing agent described in step 2 is triethylene tetramine, and described organic solvent is acetone.
3. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, it is characterized in that, in prepegged strands described in step 3, the mass percentage of fiber is 50% ~ 80%.
4. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, is characterized in that, the degree of depth of locating slot described in step 3 is 2mm ~ 5mm.
5. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, is characterized in that, the order number of sand paper described in step 4 is 200 order ~ 800 orders.
6. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, is characterized in that, the shape of the radiation refrigerator of satellite described in step 4 composite material support is annular or ellipse annular.
7. the preparation method of a kind of satellite radiation refrigerator composite material support according to claim 1, it is characterized in that, wrap described in step 4 before curing, in advance resin adhesive liquid is evenly coated in wrap surface, coated resin adhesive liquid is resin adhesive liquid A or acrylic resin.
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| US4244765A (en) * | 1978-06-27 | 1981-01-13 | Tomotoshi Tokuno | Method for manufacturing a resin-reinforced carbon fiber product |
| CN101012024A (en) * | 2007-02-14 | 2007-08-08 | 西安航天复合材料研究所 | Flame-proof ball convenient for fast transferring and manufacturing method for composite material casing thereof |
| CN101214729A (en) * | 2007-12-26 | 2008-07-09 | 东华大学 | Method for preparing composite material tube with bamboo joint structure |
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Application publication date: 20160330 |