CN219392428U - High-performance large-size carbon fiber light shield and preparation mold thereof - Google Patents
High-performance large-size carbon fiber light shield and preparation mold thereof Download PDFInfo
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- CN219392428U CN219392428U CN202223043894.1U CN202223043894U CN219392428U CN 219392428 U CN219392428 U CN 219392428U CN 202223043894 U CN202223043894 U CN 202223043894U CN 219392428 U CN219392428 U CN 219392428U
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Abstract
The utility model provides a high-performance large-size carbon fiber light shield and a preparation mold thereof, and belongs to the technical field of composite materials. Solves the problem that the high-performance large-size carbon fiber light shield and the corresponding preparation mold are not available in the market. The light shield is designed into a die structure which is easy to assemble and form, and the high-performance space camera composite material light shield structure is designed by adopting the die structure. The composite material light shield is formed by adding grid ribs into the skin, the stability of the whole light shield system is guaranteed by the structure of the added grid ribs, the quality of the whole light shield is reduced, the forming process can be realized in a short period, and preparation can be made for mass production. The light shield has large size and simple forming process, and is suitable for protecting optical systems of cameras, telescopes and the like of the spacecraft so as to prevent the cameras, telescopes and the like of the spacecraft from being damaged by solar radiation in a space environment.
Description
Technical Field
The utility model belongs to the technical field of composite materials, and particularly relates to a high-performance large-size carbon fiber light shield and a preparation mold thereof.
Background
Solar radiation is widely present in space environments, including sunlight and moon reflected light. Solar radiation is one of the main reasons for causing aerospace faults, and has serious influence on optical systems such as cameras, telescopes and the like, and damage to materials or structures of the spacecraft can be caused. In order to solve the problem that a spacecraft is subjected to solar radiation in a space environment, a most effective method is to install a light shield mechanism on the spacecraft. The shading area and the structural rigidity are important indexes for evaluating the shading mechanism, and the shading mechanism is also developed towards light weight and intelligent performance.
The high-performance carbon fiber composite material is widely applied to the light shield at present, and has the advantages of light weight, high rigidity, high specific strength and specific modulus, fatigue resistance, strong designability and the like compared with the traditional metal material. The demanding environment places increasing demands on the light shield, not only that it has sufficient strength and rigidity, but also that it must be very reliable. High reliability will, from a certain point of view, lead to an increase in the mass of the outer shield, which is in contradiction with low carrying and transmitting costs. Therefore, reducing the mass of the mask while satisfying both strength and rigidity is a primary concern of the present utility model.
Disclosure of Invention
In view of the above, the present utility model aims to provide a high-performance large-size carbon fiber light shield, a preparation method and a preparation mold thereof, so as to solve the problem that there is no high-performance large-size carbon fiber light shield and a corresponding preparation mold on the market.
In order to achieve the above purpose, the present utility model adopts the following technical scheme:
the light shield prepared by the preparation method of the high-performance large-size carbon fiber light shield comprises grid ribs and a skin, wherein the skin is wrapped outside the grid ribs, the grid ribs are of a T-shaped beam structure, and the grid ribs and the skin are integrally formed by prepreg.
Further, the height of the light shield is 2 meters.
Furthermore, the grid rib is composed of a plurality of hollow T-shaped beam structures, and the hollow T-shaped beam structures are formed by combining inverted 7-shaped structures and 7-shaped structures.
Further, the thickness of each side of the hollow T-shaped beam structure is 1-2mm.
The preparation mould that preparation method of high performance jumbo size carbon fiber lens hood utilized, including outer pressurization frame, inner core mould, a plurality of split mould, surround pressurization board and bottom plate mould, a plurality of split moulds are located inside the combined material lens hood, combined material lens hood periphery is provided with around pressurization board, it is provided with outer pressurization frame to surround pressurization board periphery, and a plurality of split moulds are fixed on the inner core mould, then the inner core mould is fixed on the bottom plate mould.
Still further, the surrounding pressurization plate comprises a left pressurization plate, a rear pressurization plate, a front pressurization plate and a right pressurization plate, and the left pressurization plate, the rear pressurization plate, the front pressurization plate and the right pressurization plate are arranged in a surrounding mode.
Further, the plurality of split molds are fixed to the inner core mold by bolts, and then the inner core mold is fixed to the base plate mold by bolts.
Furthermore, the external pressing frame, the inner core die, the split dies, the surrounding pressing plate and the bottom plate die are all made of metal materials.
Compared with the prior art, the high-performance large-size carbon fiber light shield, the preparation method and the preparation mold thereof have the beneficial effects that:
(1) The utility model designs a die structure which is easy to assemble and easy to form, and a high-performance space camera composite material light shield structure is designed by adopting the die structure. The composite material light shield is formed by adding grid ribs into the skin, the stability of the whole light shield system is guaranteed by the structure of the added grid ribs, the quality of the whole light shield is reduced, the forming process can be realized in a short period, and preparation can be made for mass production.
(2) According to the utility model, a metal die matching process and a prepreg laying process are adopted, the whole structure of the carbon fiber reinforced composite material light shield is integrally formed, the inner grid of the composite material light shield is reinforced, the large-size outer skin and the inner grid are jointly solidified and integrally formed, and the continuity of fibers is ensured. The process is reliable, the die can be conveniently disassembled and assembled during product molding and demolding, and meanwhile, the positioning standard is provided, so that the overall dimensional tolerance of the die after assembly can be ensured.
(3) According to the structural characteristics of the composite material light shield, the forming process adopts a hot-melting prepreg laying technology, and a metal mold is pressed on a die and is heated, solidified and formed. The prepreg laying process can well ensure the laying angle of each layer, can ensure the continuity of the reinforcing ribs and the skin fibers to the greatest extent, and enables the performance of the product to be matched with the actual calculation result. The metal die-casting pressurizing process can well ensure the size of the product for complex structural members, and can well control the wall thickness of the product in the die-casting process.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model. In the drawings:
FIG. 1 is a front three-axis view of a carbon fiber mask according to the present utility model;
FIG. 2 is a left side view of a carbon fiber mask according to the present utility model;
FIG. 3 is a front view of a carbon fiber mask according to the present utility model;
FIG. 4 is a top view of a carbon fiber mask according to the present utility model;
FIG. 5 is an exploded view of a mask mold according to the present utility model;
in the figure: 1-grid ribs; 2-covering; 3-externally pressing the frame; 4-inner core die, 5-split die; 6-left pressurizing plate; 7-a rear pressing plate; 8-a composite material light shield; 9-a front pressurizing plate; 10-right pressurizing plate; 11-floor mold.
Detailed Description
The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. It should be noted that, in the case of no conflict, embodiments of the present utility model and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present utility model, not all embodiments.
1. Referring to fig. 1-5, a high-performance large-size carbon fiber light shield comprises a grid rib 1 and a skin 2, wherein the skin 2 is wrapped outside the grid rib 1, the grid rib is of a T-shaped beam structure, and the grid rib and the skin 2 are integrally formed by prepreg.
The height of the light shield is 2 meters.
The composite material carbon fiber light shield is formed by adopting the high-performance carbon fiber epoxy resin prepreg, the size of the light shield is large, the height of the light shield is about 2 meters, the skin 2 and the reinforcing grid ribs 1 are integrally formed, and the forming mode can ensure the continuity of the composite material carbon fiber prepreg to the greatest extent, and ensure the performance stability and the size reliability of the composite material carbon fiber light shield. However, the requirement of the large-size continuous skin 2 on the die is high, the size of the die of the light shield structure is large, the required split is large, and the shape surfaces of all split dies are anastomotic, if the anastomosis is not good, the performance and the structure size of the product are directly affected.
Compared with the traditional light shield made of metal materials, the high-performance large-size carbon fiber light shield has the advantages of light weight, low material density, high structural strength and the like, and the carbon fiber composite material support frame can highly realize light weight while supporting the normal operation of a space remote sensing camera.
The high-performance large-size carbon fiber light shield structure is a T-shaped beam grid rib structure and a skin structure with large size and thin thickness, and is manufactured by integrally forming the grid rib 1 and the skin 2 with equal thickness. The skin contains the annular longitudinal stiffening rib of integrated into one piece, and this annular longitudinal stiffening rib can be regarded as a T word roof beam structure, and this lens hood design is not as thick flange turn-ups of 1mm, and follow-up lens hood whole butt joint of being convenient for improves the whole torsional rigidity of structure and has reduced the quality of whole product.
Compared with the prior carbon fiber composite material light shield, the carbon fiber composite material light shield structure comprises a more stable T-shaped beam structure with an inner hollow structure, the T-shaped beam structure with the inner hollow structure is formed by combining a 7-shaped structure and a 7-shaped structure, the 7-shaped structure and the 7-shaped structure are combined together through a metal die to form a T shape, and the T-shaped structure reduces the quality of the whole remote sensing camera system while ensuring large bearing, and ensures the high stability and high dimensional accuracy of the whole remote sensing camera system. And each T-shaped beam structure and the skin 2 are integrally formed, so that the integral rigidity is improved, and an interface is provided for subsequent assembly.
Compared with a metal material, the composite material has the advantages of smaller density, high specific strength, high specific modulus and the like, so that the composite material and the metal material have smaller mass under the condition of the same bearing, and the composite material can obviously reduce the mass of the whole space system and has important effects of reducing the satellite emission cost and improving the stability of the whole remote sensing camera system when being used as a supporting structure of the remote sensing camera in the aerospace field. And the designability of the composite material is strong, so that the dimensional accuracy of the remote sensing camera can be improved by optimizing the forming mode of the carbon fiber prepreg while the design requirement is met.
The thickness of each side of the T-shaped beam of the grid rib 1 can be controlled between 1mm and 2mm. The structure of the utility model is formed by high-performance composite material carbon fiber prepreg, the composite material carbon fiber prepreg has strong designability, the thickness of the T-shaped beam structure can be flexibly controlled according to the load size, for example, the bearing is small, and the thickness of each side of the T-shaped beam rib 1 can be controlled to be about 1 mm; if the bearing is large, the thickness of each side of the T-shaped beam rib 1 can be controlled to be about 2mm. The skin structure formed integrally with the skin structure needs to be formed in positive correlation according to the thickness of the T-shaped beam structure so as to meet the design requirement, and the size of the skin 2 can be designed according to the requirement.
The preparation mould that the preparation method of high performance jumbo size carbon fiber lens hood utilized, including outer pressurization frame 3, inner core mould 4, a plurality of split mould 5, surround pressurization board and bottom plate mould 11, inner core mould 4 is used for fixed split mould 5, a plurality of split mould 5 are located the combined material lens hood inside, combined material lens hood 8 periphery is provided with surrounds the pressurization board, it is provided with outer pressurization frame 3 to surround pressurization board periphery, a plurality of split mould 5 are fixed on inner core mould 4, then inner core mould 4 is fixed on bottom plate mould 11.
The surrounding pressurization plates comprise a left pressurization plate 6, a rear pressurization plate 7, a front pressurization plate 9 and a right pressurization plate 10, and the left pressurization plate 6, the rear pressurization plate 7, the front pressurization plate 9 and the right pressurization plate 10 are arranged in a surrounding manner.
The plurality of split molds 5 are fixed to the core mold 4 by bolts, and then the core mold 4 is fixed to the base mold 11.
The application method of the preparation die of the high-performance large-size carbon fiber light shield comprises the following steps:
(1) After the laying of all split molds 5 is completed, fixing the split molds 5 on an inner core mold 4 by bolts, finishing the fixing of the split molds 5, enabling the thickness of all grid rib prepregs to reach a design value, then laying a large skin 2, circularly performing the laying angle according to 0/90/45/-45, and after the laying of the large skin 2 is completed, closing the mold, wherein the closing order is that (1) a pressurizing plate 9 is lifted to a design position by a crane before the lifting is performed, and fixing the pressurizing plate on a bottom plate mold 11 by bolts; (2) hoisting the rear pressurizing plate 7 to a designed position by using a crane, and fixing the pressurizing plate on the bottom plate mold 11 by using bolts; (3) hoisting the left pressurizing plate 6 to a designed position by using a crane, and fixing the left pressurizing plate on the bottom plate die 11 by using bolts; (4) the right pressurizing plate 10 is hoisted to a designed position by a crane and is fixed on the bottom plate die 11 by bolts; (5) the inner core mould 4, the split mould 5, the left pressing plate 6, the rear pressing plate 7, the composite material light shield 8, the front pressing plate 9 and the right pressing plate 10 are covered by the external pressing frame 3, all bolts are screwed to the design position, and finally the curing is carried out.
(2) And after the curing is finished, carrying out demoulding operation, wherein the demoulding sequence is opposite to the mould closing sequence, and sequentially removing the outer pressurizing frame 3, the right pressurizing plate 10, the left pressurizing plate 6, the rear pressurizing plate 7, the front pressurizing plate 9, the inner core mould 4, the split mould 5 and the like.
The utility model adopts a metal die-matching process, and the process die consists of each split die 5, the split forming dies are independently manufactured, and the base plate die 11 is assembled with a Cheng Nawang grid rib die structure so as to prepare the grid rib 1. Each split mold 5 ensures that the shape and the size precision of the light shield meet the design requirements, and the bottom plate mold 11 and the inner core mold 4 ensure that each split mold 5 can be fixed.
The preparation method of the high-performance large-size carbon fiber light shield specifically comprises the following steps:
A. and (3) forming the grid rib 1:
a1, preparing composite material carbon fiber prepreg, a metal split die, a metal flat die, an airfelt, a sealing adhesive tape and vacuumizing equipment;
a2, paving a composite material carbon fiber prepreg on the metal split die 5 according to the designed paving layer;
a3, adhering a sealing adhesive tape on the metal flat plate, and adhering a vacuum bag on the sealing adhesive tape;
a4, wrapping the metal split die 5 paved with the prepreg by using a separation film and an airfelt;
a5, vacuumizing the metal split mold 5 paved with the prepreg through a vacuumizing device, and when the pressure in the vacuum bag reaches-95 KPa, maintaining for 60-100min after reaching-95 KPa;
a6, opening a vacuum bag, and sequentially taking down the airfelt and the isolating film on the metal split mold 5 paved with the prepreg;
after all metal split sections A6 are prepared according to A1-A5, fixing the metal split sections on an inner core die 4 by bolts to assemble an inner grid rib structure for covering and pasting in the next step;
B. and (3) integrally forming the skin 2:
after all the inner grid rib structures are fixed on the metal inner core die 4, paving fiber integrated skins according to the designed paving layers, wherein carbon fiber prepreg fibers of each layer of skin composite material are continuous;
C. curing and demolding:
and (3) assembling the metal mold of the composite material carbon fiber light shield, which is paved with all the designed prepreg, by using a metal outer mold, putting the metal mold into a curing furnace, raising the temperature in the curing furnace from room temperature to the designed curing temperature, completing the curing at 150 ℃ and the pressure of minus 90KPa to minus 80KPa for 5 hours, and naturally cooling the temperature in the curing furnace to room temperature and then demoulding.
The grid reinforcing rib and the skin 2 are integrally formed, and although the process has higher requirement on the die, for the product, the connecting flanging is reserved for independent forming, and meanwhile, the bonding and the screw connection can increase a certain weight, so that the weight can be greatly saved by integrally forming the integral skin reinforcing rib, and meanwhile, the integral process of the product can be used for adding the bonding finite element calculation.
(1) The grid rib 1 is prepared and molded by adopting a split die molding process and a prepreg laying molding process
(2) Assembling split dies after spreading all the prepregs, and integrally forming the skin 2 by adopting the prepregs;
(3) And machining and assembling the machined light shield, so as to ensure the structural strength in the working state.
The prepreg is composed of high modulus carbon fiber and high performance epoxy resin. Epoxy value of epoxy resin in the prepreg is more than or equal to 0.85, volatile content is less than or equal to 2%, gel time (105 ℃) is (40+/-5) min, and tensile modulus is more than or equal to 330GPa.
Preparation of the prepreg:
1. preparing raw material high modulus carbon fiber, high performance resin and a hot melt prepreg machine;
2. preparing a high-performance resin system;
3. and (3) impregnating the high-modulus fibers at a proper temperature by adopting a hot-melt prepreg machine, and rolling the impregnated prepreg by using a polyethylene plastic film and a release paper for laying in the next step.
The preparation of the prepreg generally uses a hot melting method, a reinforcing material subjected to heat treatment or chemical treatment is impregnated with resin glue solution through a glue dipping tank, the resin content of the prepreg is controlled through a glue scraping device and a traction device, and the prepreg is prepared through baking for a certain time at a certain temperature.
The prepreg is prepared by a hot melting method, the thickness of a single layer is 0.15mm, the volume content of carbon fiber is (58+/-2)%, and the mass per unit area is (300+/-5) g/m 2 。
A die molding process and a prepreg laying molding process:
the metal die matching process is a process of firstly paving prepreg on a metal female die or a metal male die according to requirements, then closing the metal male die or the metal female die after paving, and completing solidification at a certain temperature and a certain pressure for a period of time. The utility model specifically completes the curing after 5 hours at 150 ℃ and the pressure of minus 90KPa to minus 80 KPa.
The prepreg laying process is a composite material forming process in which prepregs composed of fibers and resin with certain thickness are laid according to a certain laying mode and a certain laying angle and are laid sequentially, and the process can exert the advantage of strong designability of the composite material and meet the requirements of forming of large-size and special-shaped structures. The utility model adopts the prepreg with the thickness of 0.15mm to design the product, and adopts the mode of circularly laying at the laying angles of 0 DEG, 90 DEG, 45 DEG or-45 DEG and the like.
The embodiments of the utility model disclosed above are intended only to help illustrate the utility model. The examples are not intended to be exhaustive or to limit the utility model to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the utility model and the practical application, to thereby enable others skilled in the art to best understand and utilize the utility model.
Claims (8)
1. The utility model provides a high performance jumbo size carbon fiber lens hood which characterized in that: the novel composite material comprises grid ribs (1) and a skin (2), wherein the skin (2) is wrapped outside the grid ribs (1), the grid ribs are of a T-shaped beam structure, and the grid ribs and the skin (2) are integrally formed by prepreg.
2. The high performance large size carbon fiber shade of claim 1, wherein: the height of the light shield is 2 meters.
3. The high performance large size carbon fiber shade of claim 1, wherein: the grid rib (1) is composed of a plurality of hollow T-shaped beam structures, and each hollow T-shaped beam structure is composed of an inverse 7-shaped structure and a 7-shaped structure.
4. A high performance large size carbon fiber shade as defined in claim 3 wherein: the thickness of each side of the hollow T-shaped beam structure is 1-2mm.
5. A production die used in the production method of a high-performance large-size carbon fiber shade according to claim 1, characterized in that: including outer pressurization frame (3), inner core mould (4), a plurality of split mould (5), surround pressurization board and bottom plate mould (11), a plurality of split mould (5) are located inside the combined material lens hood, combined material lens hood (8) periphery is provided with around the pressurization board, it is provided with outer pressurization frame (3) to surround the pressurization board periphery, and a plurality of split moulds (5) are fixed on inner core mould (4), then inner core mould (4) are fixed on bottom plate mould (11).
6. The preparation mold used in the preparation method of the high-performance large-size carbon fiber shade according to claim 5, which is characterized in that: the surrounding pressurizing plate comprises a left pressurizing plate (6), a rear pressurizing plate (7), a front pressurizing plate (9) and a right pressurizing plate (10), and the left pressurizing plate (6), the rear pressurizing plate (7), the front pressurizing plate (9) and the right pressurizing plate (10) are arranged in a surrounding mode.
7. The preparation mold used in the preparation method of the high-performance large-size carbon fiber shade according to claim 5, which is characterized in that: the split dies (5) are fixed on the inner core die (4) through bolts, and then the inner core die (4) is fixed on the bottom plate die (11) through bolts.
8. The preparation mold used in the preparation method of the high-performance large-size carbon fiber shade according to claim 5, which is characterized in that: the external pressing frame (3), the inner core die (4), the split dies (5), the surrounding pressing plate and the bottom plate die (11) are all made of metal materials.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202223043894.1U CN219392428U (en) | 2022-11-16 | 2022-11-16 | High-performance large-size carbon fiber light shield and preparation mold thereof |
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| CN202223043894.1U CN219392428U (en) | 2022-11-16 | 2022-11-16 | High-performance large-size carbon fiber light shield and preparation mold thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117681465A (en) * | 2024-02-02 | 2024-03-12 | 哈尔滨远驰航空装备有限公司 | Aviation reinforced stringer and integral forming method thereof |
| CN117698169A (en) * | 2024-02-02 | 2024-03-15 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
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2022
- 2022-11-16 CN CN202223043894.1U patent/CN219392428U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117681465A (en) * | 2024-02-02 | 2024-03-12 | 哈尔滨远驰航空装备有限公司 | Aviation reinforced stringer and integral forming method thereof |
| CN117698169A (en) * | 2024-02-02 | 2024-03-15 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
| CN117698169B (en) * | 2024-02-02 | 2024-04-30 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
| CN117681465B (en) * | 2024-02-02 | 2024-04-30 | 哈尔滨远驰航空装备有限公司 | Aviation reinforced stringer and integral forming method thereof |
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