Composite material secondary mirror support bracket for space camera and integrated molding method thereof

Abstract

The present invention relates to the technical field of composite material preparation, specifically providing a composite material secondary mirror support bracket for a space camera and an integrated molding method thereof, wherein the secondary mirror support bracket comprises a bracket body, a wing plate, a light shielding tube, a light shielding plate, and embedded metal parts; the molding method comprises the following steps: S1: preparing a metal core mold, a water-soluble mold, and a press molding mold; S2: surface treating the water-soluble mold, the metal core mold, and the embedded metal parts; S3: laying prepreg on the metal core mold, pre-pressing the combined components, and laying a skin; S4: laying the water-soluble mold and the embedded metal parts, and placing the water-soluble mold and the embedded metal parts on the metal core mold; S5: compacting the layers and curing them in an oven; S6: demolding after curing, and assembling and finishing to obtain an integrated structure of the secondary mirror support bracket for a space camera. The present invention can realize the integrated molding of a secondary mirror bracket with a variable wall thickness structure, improve the structural specific stiffness and stability, and achieve product lightweighting.

Description

Technical Field

[0001] The present invention relates to the technical field of composite material preparation, and in particular to a composite material secondary mirror support bracket for a space camera and an integrated molding method thereof. Background Art

[0002] As an important device in aerospace remote sensing systems, space cameras have many advantages, such as borderless observation of the sky and the earth, and comprehensive and accurate information collection. They play a huge role in defense monitoring, target change detection, precise mapping, resource surveys, environmental monitoring, atmospheric and ocean observations, earth radiation measurement, and target guidance, involving many fields such as astronomy, earth science, military applications, and civilian production. They have become one of the key research directions in the field of space science in various countries.

[0003] The composite secondary mirror support structure is the core optical support component of space remote sensing cameras. Its primary function is to secure the secondary mirror and maintain its spatial position, ensuring its positional accuracy and reducing environmental impacts on its stability. Prior art patents include the following:

[0004] 1. The patent number is "202110057977.7", and the patent name is "A lightweight integrated multifunctional secondary mirror support structure suitable for space cameras". It includes a bracket ring, a bracket arm, a thin-walled tube, a front frame ring, a rear frame ring and a light barrier assembly. The invention adopts a plane assembly form, the assembly process is simple and reduces the assembly difficulty. At the same time, it adopts metal titanium alloy material for integral casting, which has the advantages of high specific stiffness and high stability.

[0005] 2. The patent number is "201910963545.5", and the patent description is "A back cover device and overall molding method suitable for a satellite-borne all-composite camera". It discloses a molding method for composite components in a space camera, specifically including a structural molding step, a laying step, a connection step, a pressurization step and an overall mold closing step; the molding method in this invention can effectively ensure molding pressurization, reduce the overall weight of the camera back cover, reduce the overall thermal expansion deformation, improve the overall thermal expansion reliability, reduce the stress concentration at the junction of the prefabricated block and the carbon cloth, and improve the overall reliability and stability of the all-composite camera back cover.

[0006] However, the above-mentioned comparative documents still have the following shortcomings:

[0007] 1. Currently, the secondary mirror support structure of small space cameras is mainly a thin-walled tubular structure and a combined structure of a connecting tube and a support member. The secondary mirror support structure in Comparative Document 1 is mainly a thin-walled tubular structure, which has disadvantages such as large size, heavy weight, low specific stiffness, large assembly workload, and repeated shading functions. This is not conducive to ensuring the position accuracy of the secondary mirror, achieving lightweight structure, and improving the environmental applicability of the secondary mirror.

[0008] 2. The composite material molding method in Comparative Document 2 is mainly processed through metal molds, which makes it difficult to ensure the stability of the integrated molding of various components and the continuity of the composite material fibers.

[0009] In summary, how to design a composite material support bracket and molding method for a space camera to ensure the optical performance of the space camera in the microgravity and thermal environment of space, improve the strength, stiffness and thermal stability of the secondary support structure in the space camera, and make the space camera and its secondary support structure applicable to various complex space environments is an urgent problem that needs to be solved. Summary of the Invention

[0010] In order to solve the above problems, the present invention provides a composite material secondary mirror support bracket for a space camera and an integrated molding method thereof. The secondary mirror is made into a bracket and integrated molding is performed by combining a water-soluble mold with a metal core mold, which can improve the mechanical properties of the product, increase the structural specific stiffness and installation stability, and achieve lightweight structure.

[0011] To achieve the above-mentioned object, the present invention proposes the following technical solution: a method for integrally forming a composite material secondary mirror support bracket for a space camera, comprising the following steps:

[0012] S1: Preparation of a metal core mold, a water-soluble mold, and a press molding mold for the integrated molding of the secondary mirror support bracket;

[0013] The water-soluble mold is used to form the bracket body closed cavity structure of the secondary mirror support bracket;

[0014] The metal core mold is used to form the light shielding tube and light shielding plate thin-wall structure of the secondary mirror support bracket;

[0015] The pressurizing mold is used to pressurize the molded bracket body, light shielding tube, light shielding plate and embedded metal parts in the secondary mirror support bracket;

[0016] S2: Surface treatment of the water-soluble mold, metal core mold and embedded metal parts of the secondary mirror support bracket;

[0017] S3: Laying prepreg on the metal core mold and pre-pressing the combination, and then laying the skin on the pre-pressed metal core mold;

[0018] S4: Laying out the water-soluble mold and embedded metal parts, and placing the laid-out water-soluble mold and embedded metal parts on the metal core mold;

[0019] S5: compact the ply and put it into the furnace for curing;

[0020] S6: After curing, demoulding is performed and assembly finishing is performed to obtain a space camera secondary mirror support bracket structure that integrates a thin-wall structure and a grid rib frame structure.

[0021] Preferably, the water-soluble mold in step S1 includes a plurality of water-soluble mold blocks matched with the bracket body of the secondary mirror support bracket, and the metal core mold includes a plurality of metal core modules matched with the shading tube, shading plate and embedded metal parts of the secondary mirror support bracket.

[0022] Preferably, the laying process of the prepreg in step S3 is as follows:

[0023] S31: Laying out metal core modules and assembling multiple metal core modules into a metal core mold; the metal core modules include a cavity forming area for forming a cavity; when the metal core modules are assembled, a forming boss with a polygonal structure is provided extending outwardly in a circumferential direction of the cavity forming area;

[0024] S32: Lay the skin on the metal core mold and reserve the skin flanging layer on the forming boss.

[0025] Preferably, the skin flanging layer is L-shaped; laying the skin in step S4 is specifically as follows:

[0026] S41: placing the water-soluble mold block and the embedded metal part on the forming boss and on the skin flanging layer; the inner sides of the water-soluble mold block and the embedded metal part abut against the vertical surface of the L-shaped skin flanging layer, and the horizontal surface of the skin flanging layer extends to the outer side of the bottom end surface of the water-soluble mold block and the embedded metal part;

[0027] S42: After the water-soluble mold blocks and embedded metal parts are laid out, the L-shaped skin flanging layer is folded and then pre-pressed.

[0028] Preferably, in step S42, the skin flanging layer is folded, and the horizontal surface of the skin flanging layer extending to the outer side of the bottom end surface of the water-soluble mold block and the embedded metal part, and the vertical surface of the skin flanging layer are folded to wrap the water-soluble mold.

[0029] Preferably, when laying the skin in step S3, the laying angle of the skin layer is [-45|+45|90|0]6; while laying the skin, the wing plate thickening area of ​​the secondary mirror support bracket is laid, and the laying angle of the wing plate thickening area is [0|90|+45|-45]4;

[0030] The laying angle of the water-soluble mold and the metal core mold in step S4 is [0|90|+45|-45];

[0031] In step S5, a stepwise curing method is used for curing, the curing temperature is 120-160° C., the curing time is 6-8 hours, and the heating rate during curing is 2-4° C. / min.

[0032] Preferably, the prepreg laid on the metal core mold in step S3 is M40JB / cyanate ester or T700HB / cyanate ester, and the laying thickness is 0.3-1 mm;

[0033] The compaction layer in step S5 is a secondary pre-pressing molding after the water-soluble mold and embedded metal parts are laid out; the mold gap during room temperature pre-pressing is 0.3-0.5mm, and when the mold is heated for hot closing, the mold gap is 0-0.3mm.

[0034] Preferably, the water-soluble mold in step S1 is made by mixing quartz sand, water and a water-soluble adhesive in a certain proportion and processing; the metal core mold is made by processing aluminum alloy; and the pressurized forming mold is made by processing steel;

[0035] In step S2, the surface of the water-soluble mold is treated with waterproof glue and release cloth; the metal core mold is treated with sandpaper and cleaning agent; the surface of the embedded metal parts is treated by sandblasting, and a high-temperature adhesive film is pasted on the contact surface between the embedded metal parts and the secondary mirror support bracket.

[0036] Preferably, the dimensional design tolerance of the water-soluble mold is -0.4 to -0.2, the surface treatment thickness of the water-soluble mold is 0.2 to 0.3 mm, and the mixing ratio of quartz sand, water-soluble adhesive and water in the water-soluble mold is: 1.25:0.15:0.3;

[0037] When treating the surface of the water-soluble mold, the water-soluble mold is first dried for 3-4 hours, and then the dried water-soluble mold is covered with 1-4 layers of release cloth; the thickness of the release cloth and waterproof glue is 0.2-0.3 mm.

[0038] A composite secondary mirror support bracket for a space camera is prepared using the above-mentioned integrated molding method, comprising a bracket main body with a regular polygonal ring structure, the bracket main body being in the shape of a closed cavity grid rib; a plurality of wing panels are evenly distributed in the closed cavity of the bracket main body, the wing panels are provided with light shielding plates, and the plurality of light shielding plates are connected to a light shielding tube located in the middle of the bracket main body; embedded metal parts are also provided in the cavity of the bracket main body.

[0039] The beneficial effects of the present invention are as follows: the closed cavity frame, support wings and thin-walled structure of the shading tube and shading plate of the secondary mirror support bracket main body can be integrated into one by combining a water-soluble mold and a metal core mold; prepreg is laid during the molding process, and the laying sequence, number of layers and laying angle of the prepreg are controlled, which can improve the continuity of the composite material fibers of each part of the secondary mirror support bracket, ensure the molding quality, and realize the integrated performance of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 2 is a schematic structural diagram of a secondary mirror support bracket provided according to embodiment 1 of the present invention.

[0041] Figure 2 Schematic diagram of the structure of the metal core mold and the water-soluble mold provided according to the first embodiment of the present invention.

[0042] Figure 3 This is a table of physical and chemical properties analysis of the integrated secondary mirror support structure prepared by the molding method provided in Example 1 and Example 2 of the present invention.

[0043] Figure numerals: 1. bracket body; 2. wing plate; 3. sunshade; 4. sunshade tube; 5. embedded metal parts; 6. cavity; 7. water-soluble mold block; 8. metal core module; 9. embedded metal parts buckle plate; 10. forming boss; 11. cavity forming area. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of the present invention more clear, the following Figure 1-3 It should be understood that the specific embodiments described herein are only used to illustrate the present invention and do not constitute a limitation of the present invention.

[0045] Example 1

[0046] A composite material secondary mirror support bracket for a space camera, such as Figure 1 As shown, the bracket body 1 includes a regular polygonal ring structure, the bracket body 1 is a closed cavity grid rib shape, the bracket body 1 in this embodiment is a regular octagonal structure, and the inner cavity 6 of the bracket body 1 is an annular closed cavity shape; a plurality of wing plates 2 are evenly distributed in the cavity 6 of the bracket body 1, and a shading plate 3 is provided on the wing plate 2, and a shading tube 4 located in the middle of the bracket body 1 is connected to the plurality of shading plates 3; in this embodiment, there are four wing plates 2 and shading plates 3, and the shading plates 3 and the shading tube 4 are thin-walled structures; an embedded metal part 5 is also provided in the cavity 6 of the bracket body 1.

[0047] The bracket body 1, wing plate 2, sunshade tube 4 and sunshade plate 3 are all formed by multi-layer laying and molding of fiber and resin composite materials. In the fiber and resin composite materials, the volume fraction of the fiber is 57% to 63%, and the embedded metal parts are made of titanium alloy; the fiber is preferably glass fiber, quartz fiber or high silica fiber, and the resin is cyanate ester, epoxy resin or aminophenol resin; the embedded metal parts are preferably titanium alloy.

[0048] A method for integrally forming a composite material secondary mirror support bracket for a space camera comprises the following steps:

[0049] S1: Preparation of a metal core mold, a water-soluble mold, and a press molding mold for the integrated molding of the secondary mirror support bracket;

[0050] The water-soluble mold is made by mixing quartz sand, water, and water-soluble adhesive in a certain proportion. The mixing ratio of quartz sand, water-soluble adhesive, and water in the water-soluble mold is 1.25:0.15:0.3. The dimensional design tolerance of the water-soluble mold is -0.4 to -0.2. The water-soluble mold is used to form the closed cavity structure of the bracket body 1 of the secondary mirror support bracket. Figure 2 As shown, the water-soluble mold includes eight water-soluble mold blocks 7 matched with the bracket body 1 of the secondary mirror support bracket. The water-soluble mold blocks 7 are in the shape of closed cavity grid ribs; the water-soluble mold blocks 7 are matched with the embedded metal parts 5 and are provided with embedded metal parts gussets 9;

[0051] The metal core mold is made of aluminum alloy, and the thermal expansion coefficient of aluminum alloy is 2.36×10 -5 / K, the thermal expansion coefficient of the composite material is about 1.5×10 -6 / K, due to the large thermal expansion coefficient of aluminum alloy, it is more conducive to compacting composite material products under high temperature curing conditions, and it is also easier to demould the metal core mold, which can significantly improve the processability; the metal core mold is used to form the thin-walled structure of the light shielding tube 4 and the light shielding plate 3 of the secondary mirror support bracket; Figure 2 As shown, the metal core mold includes four metal core modules 8 that are matched with the light shielding tube 4, the light shielding plate 3 and the embedded metal parts 5 of the secondary mirror support bracket;

[0052] The press forming mold is made of steel; the press forming mold is used to pressurize the formed bracket body 1, the light shielding tube 4, the light shielding plate 3 and the embedded metal parts 5 in the secondary mirror support bracket.

[0053] S2: Surface treatment is performed on the water-soluble mold, the metal core mold, and the embedded metal parts 5 of the secondary mirror support bracket;

[0054] The surface of the water-soluble mold is treated with waterproof glue and release cloth. When treating the surface of the water-soluble mold, the water-soluble mold is first dried at a drying temperature of 110° C. for 3-4 hours, and then the dried water-soluble mold is covered with 1-4 layers of release cloth, preferably 2 layers of release cloth. The thickness of the release cloth and waterproof glue is 0.2-0.3 mm. The surface treatment thickness of the water-soluble mold is 0.2-0.3 mm.

[0055] The metal core mold is treated with sandpaper and cleaning agent; specifically, 600-grit sandpaper is used to polish it and then cleaned with acetone solvent;

[0056] The surface of the embedded metal part 5 is processed by sandblasting, and a high-temperature adhesive film is pasted on the contact surface between the embedded metal part 5 and the secondary mirror support bracket. The high-temperature adhesive film is WF-2A type adhesive film + SJ-2C type adhesive.

[0057] S3: Lay prepreg on the metal core mold and pre-press the combination, and then lay the skin on the pre-pressed metal core mold; the prepreg laid on the metal core mold is M40JB / cyanate ester, with a laying thickness of 0.3-1mm, and the thickness of a single prepreg layer is 1mm. Preferably, 4 layers of prepreg are laid; the laying angle of the water-soluble mold and the metal core mold is [0|90|+45|-45];

[0058] The prepreg placement process is as follows:

[0059] S31: Laying out metal core modules 8 and assembling multiple metal core modules 8 into a metal core mold; the metal core modules 8 include a cavity forming area 11 for forming a cavity. When the metal core modules 8 are assembled, a forming boss 10 with a polygonal structure is provided extending outwardly from the circumference of the cavity forming area 11;

[0060] S32: Laying a skin on the metal core mold and reserving a skin flanging layer on the forming boss 10; the skin flanging layer is L-shaped, including a vertical surface and a horizontal surface.

[0061] When laying the skin, the laying angle of the skin layer is [-45|+45|90|0]6; while laying the skin, the wing plate thickening area of ​​the secondary mirror support bracket is laid at the same time. The wing plate thickening area is the branch part at the shading tube 4, which supports the shading tube 4 and the shading plate 3. The laying angle of the wing plate thickening area is [0|90|+45|-45]4; to ensure the maximum continuity of the fibers between the wing plate 2 and the skin.

[0062] S4: Laying out the water-soluble mold and the embedded metal parts 5, and placing the laid-out water-soluble mold and the embedded metal parts 5 on the metal core mold;

[0063] The step S4 of laying out the skin is as follows:

[0064] S41: Lay the water-soluble mold block 7 and the embedded metal part 5 on the forming boss 10 and on the skin flanging layer; the inner sides of the water-soluble mold block 7 and the embedded metal part 5 abut against the vertical surface of the L-shaped skin flanging layer, and the horizontal surface of the skin flanging layer extends to the outer side of the bottom end surface of the water-soluble mold block 7 and the embedded metal part 5;

[0065] S42: After the water-soluble mold block 7 and the embedded metal part 5 are laid out, the L-shaped skin flanging layer is folded over and then pre-pressed. Specifically, the horizontal surface of the skin flanging layer extending to the outer side of the bottom end surface of the water-soluble mold block 7 and the embedded metal part 5 and the vertical surface of the skin flanging layer are folded over and the water-soluble mold is wrapped, and then pre-pressed.

[0066] S5: Compacting the layer is a secondary pre-pressing operation after laying the skin. During pre-pressing at room temperature, the mold gap is 0.3-0.5mm. When the mold is heated and hot-closed, the mold gap is 0-0.3mm. The mold temperature is raised to 75℃.

[0067] Enter the furnace for curing and use a step-by-step curing method:

[0068] When the mold temperature is 70℃, close the mold and the mold gap is less than 0.2mm;

[0069] The curing temperature is 120-160°C, the curing time is 6-8h, and the heating rate during curing is 3-4°C / min.

[0070] S6: After curing, demoulding is performed, process holes are opened to remove the water-soluble mold, and assembly finishing is performed. After demoulding, a drilling jig is used to ensure the accuracy of the assembly holes; thus, a space camera secondary mirror support bracket structure integrating a thin-wall structure and a grid rib frame structure is obtained.

[0071] Example 2

[0072] The difference between this embodiment and the first embodiment is that the prepreg material laid by the metal core mold is T700HB / cyanate ester.

[0073] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art may make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

[0074] The above specific embodiments of the present invention do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made based on the technical concept of the present invention should be included in the scope of protection of the claims of the present invention.

Claims

1. An integrated molding method for a composite material secondary mirror support bracket for a space camera, characterized in that: The composite secondary mirror support bracket for a space camera comprises a bracket body (1) of a regular polygonal ring structure, wherein the bracket body (1) is in the shape of a closed cavity grid rib; a plurality of wing plates (2) are uniformly distributed in the closed cavity of the bracket body (1), and a light shielding plate (3) is provided on the wing plates (2); a plurality of light shielding plates (3) are connected to a light shielding tube (4) located in the middle of the bracket body (1); an embedded metal part (5) is further provided in the cavity (6) of the bracket body (1), and the method comprises the following steps: S1: Preparation of a metal core mold, a water-soluble mold, and a press molding mold for the integrated molding of the secondary mirror support bracket; The water-soluble mold is used to form a closed cavity structure of a support body (1) of a secondary mirror support support; The metal core mold is used to form a light shielding tube (4) and a light shielding plate (3) of a thin-walled structure in the secondary mirror support bracket; The pressurized molding die is used to perform a pressurizing operation on the molded bracket body (1), the light shielding tube (4), the light shielding plate (3), and the embedded metal parts (5) in the secondary mirror support bracket; S2: Surface treatment of the water-soluble mold, the metal core mold and the embedded metal parts (5) of the secondary mirror support bracket; S3: laying prepreg on the metal core mold and pre-pressing the combination, then laying the skin on the pre-pressed metal core mold, and laying the wing plate thickening area of ​​the secondary mirror support bracket at the same time as the skin is laid, the wing plate thickening area is the branch part of the light shielding tube (4); S4: Laying out the water-soluble mold and the embedded metal parts (5), and placing the laid-out water-soluble mold and the embedded metal parts (5) on the metal core mold; S5: compact the ply and put it into the furnace for curing; S6: After curing, demoulding is performed and assembly finishing is performed to obtain a space camera secondary mirror support bracket structure that integrates a thin-wall structure and a grid rib frame structure.

2. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 1, characterized in that: The water-soluble mold described in step S1 includes a plurality of water-soluble mold blocks (7) matched with the support body (1) of the secondary mirror support bracket, and the metal core mold includes a plurality of metal core modules (8) matched with the light shielding tube (4), the light shielding plate (3) and the embedded metal parts (5) of the secondary mirror support bracket.

3. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 2, characterized in that: The process of laying the prepreg in step S3 is as follows: S31: laying out a metal core module (8) and assembling a plurality of metal core modules (8) into a metal core mold; the metal core module (8) includes a cavity forming area (11) for forming a cavity; after the metal core module (8) is assembled, a forming boss (10) with a polygonal structure is provided extending outwardly in the circumferential direction of the cavity forming area (11); S32: Lay the skin on the metal core mold and reserve the skin flanging layer on the forming boss (10).

4. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 3, characterized in that: The skin flanging layer is L-shaped; the skin laying in step S4 is specifically as follows: S41: Laying the water-soluble mold block (7) and the embedded metal part (5) on the forming boss (10) and positioned on the skin flanging layer; the inner sides of the water-soluble mold block (7) and the embedded metal part (5) abut against the vertical surface of the L-shaped skin flanging layer, and the horizontal surface of the skin flanging layer extends to the outer side of the bottom end surface of the water-soluble mold block (7) and the embedded metal part (5); S42: After the water-soluble mold block (7) and the embedded metal part (5) are laid, the L-shaped skin flanging layer is folded and then pre-pressed.

5. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 4, characterized in that: In step S42, the skin flanging layer is folded, and the horizontal surface of the skin flanging layer extending to the outer side of the bottom end surface of the water-soluble mold block (7) and the embedded metal part (5) and the vertical surface of the skin flanging layer are folded to wrap the water-soluble mold.

6. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 1, characterized in that: When laying the skin in step S3, the laying angle of the skin layer is [-45|+45|90|0]6; the laying angle of the wing panel thickening area is [0|90|+45|-45]4; The laying angle of the water-soluble mold and the metal core mold described in step S4 is [0|90|+45|-45]; In step S5, a stepwise curing method is used for curing, the curing temperature is 120-160° C., the curing time is 6-8 hours, and the heating rate during curing is 2-4° C. / min.

7. The method for integrally forming a composite material secondary mirror support bracket for a space camera according to any one of claims 1 to 6, characterized in that: In step S3, the prepreg laid on the metal core mold is M40JB / cyanate ester or T700HB / cyanate ester, and the laying thickness is 0.3-1 mm; The compacted layer in step S5 is a secondary pre-pressing process after the water-soluble mold and the embedded metal parts (5) are laid out. The mold gap during pre-pressing at room temperature is 0.3-0.5 mm, and when the mold is heated for hot closing, the mold gap is 0-0.3 mm.

8. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 7, characterized in that: The water-soluble mold in step S1 is made by mixing quartz sand, water and water-soluble adhesive in proportion and processing; the metal core mold is made by processing aluminum alloy; and the pressurized forming mold is made by processing steel; In step S2, the surface of the water-soluble mold is treated with waterproof glue and demoulding cloth; the metal core mold is treated with sandpaper and a cleaning agent; the surface of the embedded metal part (5) is treated by sandblasting, and a high-temperature adhesive film is pasted on the contact surface between the embedded metal part (5) and the secondary mirror support bracket.

9. The integrated molding method of composite material secondary mirror support bracket for space camera according to claim 8, characterized in that: The dimensional design tolerance of the water-soluble mold is -0.4~-0.2, the surface treatment thickness of the water-soluble mold is 0.2~0.3mm, and the mixing ratio of quartz sand, water-soluble adhesive and water in the water-soluble mold is: 1.25:0.15:0.3; When treating the surface of the water-soluble mold, the water-soluble mold is first dried for 3-4 hours, and then the dried water-soluble mold is covered with 1-4 layers of release cloth; the thickness of the release cloth and waterproof glue is 0.2~0.3mm.

10. A composite material secondary mirror support bracket for a space camera, characterized in that: The invention is prepared by the integrated molding method described in any one of claims 1 to 9, comprising a bracket body (1) of a regular polygonal ring structure, wherein the bracket body (1) is in the shape of a closed cavity grid rib; a plurality of wing plates (2) are evenly distributed in the closed cavity of the bracket body (1), and a light shielding plate (3) is provided on the wing plates (2), and a light shielding tube (4) located in the middle of the bracket body (1) is connected to the plurality of light shielding plates (3); and a pre-embedded metal part (5) is also provided in the cavity (6) of the bracket body (1).

Images