Ceramic matrix composite satellite mirror barrel and method of assembling the same

Abstract

The application relates to a satellite mirror barrel, in particular to a ceramic matrix composite satellite mirror barrel and an assembling method thereof. The technical problem that the flatness and parallelism of the existing ceramic matrix composite satellite optical machine mirror barrel are difficult to meet the precision requirement is solved. The mirror barrel comprises a barrel body, a three-pole support assembly, a plurality of metal patches and three metal blocks, the barrel body and the three-pole support assembly are prepared from ceramic matrix composite materials. The plurality of metal patches are evenly attached to the bottom surface of the lower end flange of the barrel body, and the bottom surfaces of the plurality of metal patches are flush, which are used for guaranteeing the flatness requirement of the bottom surface of the satellite mirror barrel; three triangular cavities are arranged on the upper end surface of the triangular hollow frame; the three metal blocks are respectively arranged in the three triangular cavities, the upper end surfaces of the three metal blocks are flush with the upper end surface of the triangular hollow frame, the bottom surface of the processed mirror barrel is taken as a reference surface, the upper end surface of the triangular hollow frame and the upper end surfaces of the three metal blocks are uniformly processed, and the parallelism requirement of the whole upper and lower end surfaces of the satellite mirror barrel is guaranteed.

Description

Technical Field

[0001] This invention relates to a satellite telescope tube, specifically to a ceramic matrix composite satellite telescope tube and its assembly method. Background Technology

[0002] With advancements in materials innovation, manufacturing technology, and market demand, the development of satellite optical and mechanical lens barrel components is accelerating. Lightweighting, which effectively reduces the overall weight of the satellite and lowers launch costs, has always been a key objective in satellite component manufacturing. Therefore, component manufacturing increasingly favors high-strength, lightweight materials, such as carbon fiber composites. The manufacturing of satellite optical and mechanical lens barrel components requires extremely high precision to ensure the performance of the optical system. Modern precision manufacturing technologies, such as CNC machine tools and 3D printing, offer greater flexibility and accuracy in component manufacturing. However, the extreme temperature variations faced by satellites in space place even higher demands on the thermal stability of components. Therefore, the selection and design of materials are crucial, requiring not only applicability to a wider temperature range but also the ability to maintain stability across this broad temperature spectrum.

[0003] Ceramic matrix composites (CMCs) possess numerous performance advantages, making them highly favored in satellite optomechanical lens components. For example, compared to metals, CMCs offer the advantage of lightweight construction, which helps reduce satellite load and improve launch efficiency. Simultaneously, CMCs provide sufficient strength and stiffness. In space, satellites typically face extreme temperature variations; CMCs exhibit excellent high-temperature stability, ensuring stable operation of optical systems under diverse environments. CMCs possess superior optical properties, enabling the manufacture of high-precision optical components such as reflectors and lenses, ensuring the proper functioning of signal transmission, data acquisition, and remote sensing missions. CMCs also exhibit excellent corrosion resistance and radiation resistance, guaranteeing stable satellite operation in high-radiation environments. The application of CMCs in satellite optomechanical lens components is expected to continue to increase to meet the evolving demands of satellite technology, while the advantages of CMCs will provide crucial support for the success and reliability of satellite missions.

[0004] However, there are still some drawbacks to using ceramic matrix composites to prepare satellite optical and mechanical lens tube components. After machining, the ceramic matrix composite components usually need to undergo silicon carbide matrix deposition to ensure that there are no exposed carbon fibers on the surface of the ceramic matrix components. During the deposition process, some silicon carbide deposits will be generated on the surface of the components, making it difficult to ensure the high precision requirements of the flatness and parallelism of the satellite lens tube. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problem that silicon carbide deposits will form on the surface of existing ceramic matrix composite satellite optical and mechanical lens barrel components, making it difficult to achieve the high-precision dimensional requirements of satellite optical and mechanical lens barrels in terms of flatness and parallelism. The invention provides a ceramic matrix composite satellite lens barrel and its assembly method.

[0006] The technical solution of this invention is:

[0007] This invention discloses a ceramic matrix composite satellite telescope tube, comprising a tube body and a three-bar support assembly disposed on the upper end face of the tube body; the three-bar support assembly includes a triangular hollow frame and three connecting beams; the triangular hollow frame is located on one side of the upper end of the tube body and is coaxially arranged with the tube body, and the three corners of the triangular hollow frame are respectively fixed to the upper end face of the tube body through the three connecting beams; a flange structure is provided on the lower end face of the tube body;

[0008] Its special feature is:

[0009] The cylindrical body, triangular hollow frame and three connecting beams are all made of ceramic matrix composite material;

[0010] It also includes multiple metal patches and three metal blocks;

[0011] The multiple metal patches are evenly attached to the bottom surface of the flange at the lower end of the cylinder along the circumferential direction, and the bottom surfaces of the multiple metal patches are flush.

[0012] The triangular hollow frame includes three blocks set at three interior corners. The two sides of the blocks are fixed to the two sides of the corresponding interior corners, and the two end faces of the blocks are flush with the two end faces of the triangular hollow frame. The blocks and the two sides of the corresponding interior corners together form a triangular cavity.

[0013] The three metal blocks are fixed in the three triangular cavities respectively, and the upper surface of the three metal blocks is flush with the upper surface of the triangular hollow frame.

[0014] Furthermore, the upper end face of the metal patch is provided with a circular boss; the bottom surface of the lower flange of the cylinder is provided with a plurality of limiting holes adapted to the circular boss; the number of limiting holes is the same as the number of metal patches, and the circular bosses of the plurality of metal patches are respectively inserted into the plurality of limiting holes.

[0015] Furthermore, three limiting protrusions extending outward are evenly arranged along the circumferential direction on the side wall of the upper end of the metal block, and the upper surface of the three limiting protrusions is flush with the upper end face of the metal block; the upper end face of the triangular cavity is provided with three limiting grooves that are adapted to the three limiting protrusions, and the three limiting protrusions of each metal block are respectively placed in the three limiting grooves of the corresponding triangular cavity.

[0016] Furthermore, the metal block has a hollow structure.

[0017] Furthermore, the metal block is a triangular block, and its external dimensions are adapted to the inner surface of the triangular cavity; the metal patch is square in shape.

[0018] Furthermore, both the metal patch and the metal block are made of titanium alloy.

[0019] Meanwhile, the present invention also provides an assembly method for the above-mentioned ceramic matrix composite satellite lens barrel, which is characterized by including the following steps:

[0020] 1) The cylindrical body and the three-bar support assembly were prepared using ceramic matrix composite materials, and then the cylindrical body and the three-bar support assembly were assembled.

[0021] 2) Clean the residual material inside the cylinder and the triangular cavity, and grind the easily detachable areas on the surface of the cylinder and the three-bar support assembly to remove surface attachments;

[0022] 3) Install multiple metal patches on the bottom surface of the flange at the lower end of the cylinder, so that the multiple metal patches are evenly distributed along the circumference;

[0023] 4) Process the bottom surfaces of multiple metal patches according to the flatness requirements of the bottom surface;

[0024] 5) Install the metal block so that the metal block and the upper surface of the triangular hollow frame are flush. According to the flatness requirements of the upper surface and the parallelism requirements of the bottom surface of the cylinder and the upper surface of the triangular hollow frame, take the bottom surface of the processed multiple metal patches as the reference surface, process the upper surface of the metal block and the triangular hollow frame as a whole, and complete the assembly of the ceramic matrix composite satellite tube.

[0025] Furthermore, in step 3), multiple metal patches are installed on the bottom surface of the flange at the lower end of the cylinder using high-temperature adhesive, requiring the surface to be flat and free of adhesive residue or high spots.

[0026] Further, step 5) specifically involves: installing the metal block so that the metal block and the upper surface of the triangular hollow frame are flush. Based on the flatness requirements of the upper surface and the parallelism requirements of the bottom surface of the cylinder and the upper surface of the triangular hollow frame, the bottom surface of the processed multiple metal patches is used as the reference surface. The upper surface of the metal block and the triangular hollow frame are processed as a whole. High-temperature adhesive is applied to the fiber-exposed area of ​​the upper surface of the triangular hollow frame to ensure that no fibers are exposed, thus completing the assembly of the ceramic matrix composite satellite tube.

[0027] The beneficial effects of this invention are:

[0028] 1. This invention relates to a ceramic matrix composite satellite telescope tube. A metal patch is installed on the bottom surface of the lower flange of the ceramic matrix composite satellite telescope tube. The flatness of the bottom surface of the lower flange is adjusted by the metal patch, solving the problem of performance degradation caused by exposed fibers in the ceramic matrix composite components and ensuring the high precision requirements of the lower end face of the satellite telescope tube. A metal block is installed inside the upper triangular hollow frame, with the upper end face of the metal block flush with the upper end face of the satellite telescope tube. The metal block and the upper end face of the triangular hollow frame are then uniformly machined in the later stages to ensure the flatness of the upper end face of the satellite telescope tube, as well as the parallelism accuracy requirements between the upper end face and the bottom surface of the upper end face of the satellite telescope tube.

[0029] 2. This invention discloses an assembly method for a ceramic matrix composite satellite telescope tube. After the ceramic matrix composite satellite telescope tube is assembled, a metal patch is designed at the bottom of the tube to adjust the flatness and parallelism of the overall components. After the metal patch is installed and fixed, it is machined to ensure the flatness requirement of the bottom surface of the satellite telescope tube. Using the machined bottom surface of the tube as a reference surface, the upper end area of ​​the triangular hollow frame of the satellite telescope tube and the upper end surfaces of the three metal blocks are machined to ensure the overall parallelism requirement of the upper and lower end surfaces of the satellite telescope tube. Attached Figure Description

[0030] Figure 1 This is an isometric side view of an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0031] Figure 2 This is a front view of an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0032] Figure 3 This is a bottom view of an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0033] Figure 4 This is a top view of an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0034] Figure 5 This is a schematic diagram of the structure of the metal patch in an embodiment of a ceramic matrix composite satellite lens barrel according to the present invention;

[0035] Figure 6 This is a side view of a metal patch in an embodiment of a ceramic matrix composite satellite lens barrel according to the present invention;

[0036] Figure 7 This is a schematic diagram of the structure of the metal block in an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0037] Figure 8 This is a front view of the metal block in an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0038] Figure 9 This is a top view of the metal block in an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0039] Figure 10 This is a bottom view of the metal block in an embodiment of a ceramic matrix composite satellite mirror tube according to the present invention;

[0040] Figure 11 This is an enlarged view of the assembly of the metal block and the three-bar support assembly in an embodiment of a ceramic matrix composite satellite lens barrel according to the present invention.

[0041] Marking description: 1-Cylinder, 2-Three-bar support assembly, 3-Metal patch, 4-Metal block, 5-Triangular hollow frame, 6-Connecting beam, 31-Circular boss, 41-Limiting boss. Detailed Implementation

[0042] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0043] This invention provides a ceramic matrix composite satellite telescope tube, such as... Figure 1 and Figure 2 As shown, the system includes a cylindrical body 1 and a three-bar support assembly 2 fixedly mounted on the upper surface of the cylindrical body 1. The three-bar support assembly 2 includes a triangular hollow frame 5 and three connecting beams 6. The triangular hollow frame 5 is located on one side of the upper end of the cylindrical body 1 and is coaxially arranged with the cylindrical body 1. The three corners of the triangular hollow frame 5 are respectively fixed to the upper surface of the cylindrical body 1 through the three connecting beams 6. A flange structure is provided on the lower surface of the cylindrical body 1. The cylindrical body 1, the triangular hollow frame 5, and the three connecting beams 6 are all made of ceramic matrix composite material.

[0044] After machining, ceramic matrix composite components typically require silicon carbide matrix deposition to ensure no exposed carbon fibers on the surface. During deposition, some silicon carbide deposits form on the component surface, making it difficult to guarantee the high precision requirements for the flatness and parallelism of the satellite mirror tube. To improve the flatness and parallelism accuracy of the satellite mirror tube fabricated from ceramic matrix composites and ensure its operation is unaffected, this invention designs 18 metal patches 3 on the bottom surface of the tube 1 and three metal blocks 4 at the upper end of the overall structure. Both the metal patches 3 and the metal blocks 4 are made of titanium alloy.

[0045] See Figure 3 Eighteen metal patches 3 are evenly attached to the bottom surface of the flange at the lower end of the cylinder 1 along the circumferential direction. The bottom surfaces of the 18 metal patches 3 are machined as a whole to ensure a flush surface, thereby guaranteeing the high precision requirements for the flatness and parallelism of the bottom of the satellite tube. For convenient and quick installation, the metal patches 3 are square in shape, and each metal patch 3 has a circular boss 31 on its upper surface. (See [reference]). Figure 5 and Figure 6The bottom surface of the flange at the lower end of the cylinder 1 is provided with 18 limiting holes that are adapted to the circular bosses 31; the number of limiting holes is the same as the number of metal patches 3. During installation, the circular bosses 31 of the 18 metal patches 3 are inserted into the 18 limiting holes respectively.

[0046] A stop block is installed at each of the three interior corners of the triangular hollow frame 5. The two sides of each stop block are fixed to the two sides of the corresponding interior corner, and the two end faces of each stop block are flush with the two end faces of the triangular hollow frame. The stop blocks and the two sides of the corresponding interior corners together form a triangular cavity. Three metal blocks 4 are fixed inside the three triangular cavities, and the upper end faces of all three metal blocks 4 are flush with the upper end face of the triangular hollow frame 5. (See [reference]). Figure 4 After assembly, subsequent standardized processing ensures that the flatness and parallelism of the upper surface of the satellite telescope tube meet the required precision. (See also...) Figures 7-10 To facilitate installation, three outwardly extending limiting protrusions 41 are evenly provided circumferentially on the side wall of the upper end of the metal block 4. The upper surfaces of the three limiting protrusions 41 are flush with the upper end face of the metal block 4. The upper end face of the triangular cavity is provided with three limiting grooves that fit the three limiting protrusions 41. During installation, the three limiting protrusions of each metal block 4 are placed into the three limiting grooves of the corresponding triangular cavity to ensure proper installation. To reduce the overall weight, the metal block 4 is designed as a hollow structure. In this embodiment, the metal block 4 is designed as a triangular block, so that its outer dimensions fit the inner surface of the triangular cavity. The three limiting protrusions 41 are respectively designed on each side. Through structural design, it can be directly inserted into the triangular cavity along the surface during installation, making installation convenient, quick, and precise. See [link to documentation]. Figure 11 The bottom of metal block 4 is provided with stepped holes for assembly and connection with other parts.

[0047] Meanwhile, the present invention also provides an assembly method for a ceramic matrix composite satellite lens barrel, comprising the following steps:

[0048] 1) Cylinder 1 and three-bar support assembly 2 were prepared by ceramic matrix composite material and then assembled.

[0049] 2) Clean the residual material inside the cylinder 1 and the triangular cavity, and grind the easily detachable areas on the surface of the cylinder 1 and the three-bar support assembly 2 to remove surface attachments.

[0050] 3) Use high-temperature adhesive to install 18 metal patches 3 on the bottom surface of the flange at the lower end of the cylinder 1, so that the 18 metal patches 3 are evenly distributed along the circumference. It is required that there are no large pieces of adhesive residue between the metal patches 3 and the surface of the composite material. Remove the adhesive residue from the surface of the metal patches 3, and the surface should be flat and free of adhesive residue high points.

[0051] 4) Based on the flatness requirements of the bottom surface, the bottom surfaces of 18 metal patches 3 are uniformly processed by mechanical processing to ensure the flatness requirements of the bottom surface of the satellite tube.

[0052] 5) Install the metal block 4 so that the upper surface of the metal block 4 and the upper surface of the triangular hollow frame 5 are flush. According to the flatness requirements of the upper surface and the parallelism requirements of the bottom surface of the cylinder 1 and the upper surface of the triangular hollow frame 5, the bottom surface of the processed multiple metal patches 3 is used as the reference surface. The upper surface of the metal block 4 and the upper surface of the triangular hollow frame 5 are processed as a whole. High temperature adhesive is applied to the fiber exposed area of ​​the upper surface of the triangular hollow frame 5 to ensure that no fibers are exposed, and the assembly of the ceramic matrix composite satellite tube is completed.

Claims

1. A ceramic matrix composite satellite telescope tube, comprising a tube body (1) and a three-bar support assembly (2) disposed on the upper end face of the tube body (1); the three-bar support assembly (2) comprises a triangular hollow frame (5) and three connecting beams (6); the triangular hollow frame (5) is located on one side of the upper end of the tube body (1) and is coaxially disposed with the tube body (1), and the three corners of the triangular hollow frame (5) are respectively fixedly connected to the upper end face of the tube body (1) through the three connecting beams (6); a flange structure is provided on the lower end face of the tube body (1); Its features are: The cylindrical body (1), the triangular hollow frame (5), and the three connecting beams (6) are all made of ceramic matrix composite material; It also includes multiple metal patches (3) and three metal blocks (4); The plurality of metal patches (3) are evenly attached to the bottom surface of the flange at the lower end of the cylinder (1) along the circumferential direction, and the bottom surfaces of the plurality of metal patches (3) are flush. The triangular hollow frame (5) includes three blocks set at three interior corners. The two sides of the blocks are fixed to the two sides of the corresponding interior corners, and the two end faces of the blocks are flush with the two end faces of the triangular hollow frame. The blocks and the two sides of the corresponding interior corners enclose a triangular cavity. The three metal blocks (4) are fixed in the three triangular cavities respectively, and the upper surface of the three metal blocks (4) is flush with the upper surface of the triangular hollow frame (5). The upper surface of the metal patch (3) is provided with a circular boss (31). The bottom surface of the flange at the lower end of the cylinder (1) is provided with multiple limiting holes that are adapted to the circular boss (31); the number of limiting holes is the same as the number of metal patches (3), and the circular bosses (31) of the multiple metal patches (3) are respectively inserted into the multiple limiting holes. Three limiting protrusions (41) extending outward are evenly arranged along the circumferential direction on the side wall of the upper end of the metal block (4), and the upper surface of the three limiting protrusions (41) is flush with the upper end surface of the metal block (4). The upper end face of the triangular cavity is provided with three limiting grooves that are adapted to the three limiting bosses (41). The three limiting bosses of each metal block (4) are respectively placed in the three limiting grooves of the corresponding triangular cavity.

2. The ceramic matrix composite satellite telescope tube according to claim 1, characterized in that: The metal block (4) has a hollow structure.

3. The ceramic matrix composite satellite telescope tube according to claim 2, characterized in that: The metal block (4) is a triangular block, and its outer dimensions are adapted to the inner surface of the triangular cavity; The metal patch (3) is square in shape.

4. A ceramic matrix composite satellite telescope tube according to claim 3, characterized in that: Both the metal patch (3) and the metal block (4) are made of titanium alloy.

5. A method for assembling a ceramic matrix composite satellite lens barrel according to any one of claims 1-4, characterized in that, Includes the following steps: 1) A cylindrical body (1) and a three-bar support assembly (2) were prepared using ceramic matrix composite materials, and the cylindrical body (1) and the three-bar support assembly (2) were assembled. 2) Clean the residual material inside the cylinder (1) and the triangular cavity, and grind the easily detachable areas on the surface of the cylinder (1) and the three-bar support assembly (2) to remove surface attachments; 3) Install multiple metal patches (3) on the bottom surface of the flange at the lower end of the cylinder (1) so that the multiple metal patches (3) are evenly distributed along the circumference; 4) Process the bottom surfaces of multiple metal patches (3) according to the flatness requirements of the bottom surface; 5) Install the metal block (4) so ​​that the upper surface of the metal block (4) and the triangular hollow frame (5) are flush. According to the flatness requirements of the upper surface and the parallelism requirements of the bottom surface of the cylinder (1) and the upper surface of the triangular hollow frame (5), the bottom surface of the processed multiple metal patches (3) is used as the reference surface. The upper surface of the metal block (4) and the triangular hollow frame (5) are processed as a whole to complete the assembly of the ceramic matrix composite satellite tube.

6. The assembly method of a ceramic matrix composite satellite telescope tube according to claim 5, characterized in that: In step 3), multiple metal patches (3) are installed on the bottom surface of the flange at the lower end of the cylinder (1) using high-temperature adhesive. The surface should be flat and free of adhesive residue.

7. The assembly method of a ceramic matrix composite satellite telescope tube according to claim 6, characterized in that: Step 5) Specifically, install the metal block (4) so ​​that the upper surface of the metal block (4) and the triangular hollow frame (5) are flush. According to the flatness requirements of the upper surface and the parallelism requirements of the bottom surface of the cylinder (1) and the upper surface of the triangular hollow frame (5), take the bottom surface of the processed multiple metal patches (3) as the reference surface, process the upper surface of the metal block (4) and the triangular hollow frame (5) as a whole, and apply high temperature glue to the fiber exposed area of ​​the upper surface of the triangular hollow frame (5) to ensure that there is no fiber exposed, and complete the assembly of the ceramic matrix composite satellite tube.

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