Primary and secondary mirror support structure for high resolution coaxial space camera

Abstract

The application discloses a high-resolution coaxial space camera primary and secondary mirror supporting structure, relates to the technical field of space remote sensing, and comprises a primary mirror back plate which is integrally manufactured by adopting a carbon fiber composite material, simplifies assembly and debugging process, shortens installation time, improves development efficiency, guarantees position precision between the primary and secondary mirrors, improves stability of the supporting structure, generates heat energy when starting to work, absorbs the heat energy by means of a set of heat dissipation plates, and connected antimony blocks are shrunk due to the heat energy and are expanded due to too low temperature in space, at this time, the heat dissipation stabilizing mechanism and the bending mechanism are hinged, the connected rising plate can reciprocate, the fixed plate connected therewith can stabilize the variable cross-section supporting inclined frame in the process, and therefore, the stability of the space camera primary and secondary mirror supporting structure is enhanced, the service life is improved, and parts are not damaged due to overheating.

Description

Technical Field

[0001] This invention relates to the field of space remote sensing technology, and more specifically to a support structure for the primary and secondary mirrors of a high-resolution coaxial space camera. Background Technology

[0002] Coaxial space cameras are small and lightweight, and are often used in optoelectronic payloads of micro and nano satellites. However, due to size and weight limitations, their spatial resolution is generally above the meter level. To improve the ground pixel resolution of micro and nano satellite remote sensing cameras and achieve sub-meter level imaging, long focal length and large aperture coaxial three-mirror optical systems are typically used. This results in a relatively long distance between the primary and secondary mirrors, making it difficult to guarantee positional accuracy, leading to lower resonant frequencies, poor stability, and high obstruction ratios. The support structure between the primary and secondary mirrors, as the main support structure of the space camera, provides the interface for the installation and positioning of each mirror assembly. It needs to ensure that the relative positional accuracy and surface accuracy of the optical elements remain unchanged under the harsh mechanical environment of temperature changes, launch, and on-orbit operation. Compared to the optical elements, the primary and secondary mirror support structure accounts for a large proportion of the total weight of the camera. Therefore, under the premise of ensuring high rigidity and high stability, ultra-lightweight optimization design is one of the key technologies in the development of space cameras.

[0003] The main support forms for primary and secondary mirrors in coaxial space cameras include strut type, thin-walled load-bearing cylinder type, and truss type. Stirrup type has advantages such as simplicity, ease of assembly and adjustment, and light weight, and is widely used in space cameras requiring high lightweight designs. However, its stability is relatively poor, and it is more commonly used in space cameras with small apertures and small distances between primary and secondary mirrors. Thin-walled cylinder structure has high rigidity, high stability, and ease of processing and inspection, but it is relatively heavy. Truss structure is widely used in space cameras, offering advantages such as high rigidity, flexible assembly, light weight, and strong design flexibility, which can reduce manufacturing difficulty. Currently, it often adopts a modular structure, requiring multiple parts to be assembled individually, which can easily introduce assembly stress, and the disassembly and assembly process is relatively complex.

[0004] To address the technical challenges posed by the large distance between primary and secondary mirrors in existing primary and secondary mirror support structures, such as poor stability, low fundamental frequency, large mass, and complex manufacturing and assembly processes, a high-resolution coaxial space camera primary and secondary mirror support structure is proposed. This device balances high rigidity, high stability, and ultra-lightweight requirements, employing a long-distance carbon fiber composite variable cross-section hollow cross-shaped primary and secondary mirror support structure. The integrated and optimized design of the primary and secondary mirror support structure simplifies the assembly and adjustment process, ensuring positional accuracy and surface shape accuracy between the primary and secondary mirrors, thus meeting the high rigidity, high stability, low obstruction, and ultra-lightweight requirements of high-resolution space cameras for their primary and secondary mirror support structures. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a high-resolution coaxial space camera primary and secondary mirror support structure, including a primary mirror backplate. A primary reflecting mirror mount is movably connected to the top central axis of the primary mirror backplate. A heat sink is fixedly connected to the bottom of the primary mirror backplate. The heat sink is irregularly curved. The structure also includes a thin-walled cylindrical mechanism. The thin-walled cylindrical mechanism includes a stabilizing base mechanism fixedly connected to the top of the primary mirror backplate. A stabilizing primary reflecting mirror mechanism is fixedly connected to the central axis of the middle of the stabilizing base mechanism. A stabilizing secondary mirror mechanism is fixedly connected to the top inner wall of the stabilizing base mechanism. An exoskeleton stabilizing mechanism is also included. The exoskeleton stabilizing mechanism includes three heat dissipation mechanisms fixedly connected to the top inner wall of the heat sink. Three heat dissipation stabilizing mechanisms are fixedly connected to the top central axis of the heat sink. A bending mechanism is fixedly connected to the central axis of the right wall inside the bottom of each heat dissipation mechanism. A supporting stabilizing mechanism is fixedly connected to the right end of the bottom of each heat dissipation mechanism.

[0006] Furthermore, the stabilizing base mechanism includes three embedded parts 1 that are fixedly connected to the inner walls of the top four sides of the primary mirror back plate. A back plate connecting ring is fixedly connected to the top four sides of the primary mirror back plate. Three embedded parts 2 are fixedly connected to the inner walls of the outer walls of the back plate connecting ring. A variable cross-section support bracket is fixedly connected to the top of the back plate connecting ring. A secondary mirror support connecting ring is fixedly connected to the top of the variable cross-section support bracket. Three embedded parts 3 are fixedly connected to the inner walls of the top of the secondary mirror support connecting ring.

[0007] Furthermore, the stabilizing primary reflector mechanism includes three flexible hinges that are respectively fixedly connected to the inner wall of the top central axis of the primary reflector back plate. The outer wall of the top end of the flexible hinge is rotatably connected to the inner wall of the bottom central axis of the primary reflector mount. The primary reflector is fixedly connected to the top of the primary reflector mount.

[0008] Furthermore, the stabilizing secondary mirror mechanism includes three secondary mirror supports that are fixedly connected to the inner wall of the secondary mirror support connecting ring. The inner walls of the three secondary mirror supports are fixedly connected to secondary mirror bases. Three pre-embedded parts are fixedly connected to the inner walls of the top of the secondary mirror bases. A secondary mirror flexible support is fixedly connected to the bottom of the secondary mirror base. A secondary mirror is fixedly connected to the top central axis of the secondary mirror flexible support.

[0009] Furthermore, the heat dissipation mechanism includes a limiting shell fixedly connected to the inner wall of the top of the heat dissipation plate, an antimony block fixedly connected to the left end of the top of the inner wall of the limiting shell, the left wall of the antimony block fixedly connected to the inner wall of the top of the heat dissipation plate, and a connecting plate fixedly connected to the central axis at the bottom of the right wall of the antimony block.

[0010] Furthermore, the bending mechanism includes a fixed rod fixedly connected to the central axis of the inner wall of the connecting plate, a rotating plate rotatably connected to the central axis of the outer wall of the fixed rod, and a connecting rod rotatably connected to the inner wall of the bottom end of the rotating plate.

[0011] Furthermore, the supporting and stabilizing mechanism includes rising plates rotatably connected to the outer walls of the front and rear ends of the connecting rod, a limiting rod rotatably connected to the inner wall of the middle end of the rising plate, a fixing plate fixedly connected to the central axis of the bottom right end of the limiting shell, the central axis of the bottom inner wall of the fixing plate fixedly connected to the front and rear ends of the limiting rod, and a stabilizing plate fixedly connected to the left wall of the rising plate.

[0012] Furthermore, the heat dissipation stabilization mechanism includes an antimony plate fixedly connected to the central axis at the top of the heat dissipation plate, a sponge block fixedly connected to the left wall of the antimony plate, and the left wall of the sponge block movably connected to the outer wall of the secondary mirror flexible support.

[0013] Compared with the prior art, the beneficial effects of the present invention are:

[0014] (1) The high-resolution coaxial space camera primary and secondary mirror support structure adopts a variable cross-section hollow structure. The carbon fiber material is optimized according to the stress to achieve the requirements of ultra-lightweight and high rigidity of the space remote sensing camera. The primary and secondary mirror support truss adopts a concentric circle structure with the primary mirror, so that the imaging light reaching the primary mirror is not blocked by the support structure between the primary and secondary mirrors. The structure is compact and the outer envelope size is small. The secondary mirror support rod has a thin wall, which minimizes the obstruction of incident light and meets the requirements of high stability and low obstruction of the main support structure of the high-resolution space camera.

[0015] (2) The high-resolution coaxial space camera primary and secondary mirror support structure is manufactured in one piece using carbon fiber composite material, which simplifies the assembly and debugging process, shortens the installation time, improves the development efficiency, ensures the positional accuracy between the primary and secondary mirrors, and improves the stability of the support structure. The tilt angle difference between the primary and secondary mirrors is less than 5 seconds, and the change in the distance between the primary and secondary mirrors is better than 1μm under the temperature fluctuation condition of 20±4℃. The first-order frequency of the overall structure is better than 90Hz, which is higher than the target requirement of 80Hz.

[0016] (3) When the high-resolution coaxial space camera primary and secondary mirror support structure starts working, it generates heat energy. The heat dissipation plate absorbs the heat energy, and the antimony block connected to it will contract due to the heat energy and expand due to the low temperature in space. At this time, the heat dissipation stabilization mechanism and the bending mechanism are hinged, so that the connected rising plate can reciprocate. The fixed plate connected to it can stabilize the variable cross section support bracket in this process, thereby enhancing the stability of the space camera primary and secondary mirror support structure and improving its service life. It will not cause damage to parts due to overheating.

[0017] (4) When the high-resolution coaxial space camera primary and secondary mirror support structure starts working, the heat generated causes the antimony plate located on the top of the heat sink to contract, and the sponge connected to it can also expand outward, freeing the fixation of the secondary mirror flexible support so that it will not hinder the operation of the space camera. When the operation stops, the antimony plate expands due to the low temperature in space, and the sponge is squeezed inward. In this process, the stability effect of the secondary mirror flexible support is enhanced, and the secondary mirror flexible support is cleaned. Attached Figure Description

[0018] Figure 1 This is a front view of the overall structure of the present invention;

[0019] Figure 2 This is a top view of the overall structure of the present invention;

[0020] Figure 3 This is a front sectional view of the overall structure of the present invention;

[0021] Figure 4 This is a front cross-sectional view of the thin-walled cylindrical mechanism of the present invention;

[0022] Figure 5 This is a front view of the thin-walled cylindrical mechanism of the present invention;

[0023] Figure 6 This is a front view of the exoskeleton stabilization mechanism of the present invention;

[0024] Figure 7 This is a frontal cross-sectional view of the exoskeleton stabilization mechanism of the present invention.

[0025] In the diagram: 1. Primary mirror backplate; 2. Heat sink; 3. Primary mirror mount; 4. Backplate connecting ring; 5. Variable cross-section support bracket; 6. Secondary mirror bracket connecting ring; 7. Embedded part three; 8. Antimony plate; 9. Limiting shell; 201. Thin-walled cylindrical mechanism; 401. Stabilizing base mechanism; 402. Stabilizing primary mirror mechanism; 403. Stabilizing secondary mirror mechanism; 202. Exoskeleton stabilizing mechanism; 205. Heat dissipation mechanism; 206. Heat dissipation stabilizing mechanism; 204. Bending Mechanism; 203, Support and stabilization mechanism; 19, Embedded part one; 23, Embedded part two; 31, Flexible hinge; 22, Primary reflector; 14, Secondary mirror bracket; 11, Secondary mirror base; 12, Embedded part four; 21, Secondary mirror flexible support; 13, Secondary mirror; 51, Antimony block; 49, Connecting plate; 48, Fixing rod; 47, Rotating plate; 46, Connecting rod; 44, Rising plate; 45, Limiting rod; 42, Fixing plate; 15, Stabilizing plate; 41, Sponge block. Detailed Implementation

[0026] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. The embodiments of the present invention are given for illustrative and descriptive purposes only, and are not intended to be exhaustive or to limit the invention to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art. The embodiments were chosen and described to better illustrate the principles and practical application of the invention, and to enable those skilled in the art to understand the invention and design various embodiments with various modifications suitable for a particular purpose.

[0027] Example 1,

[0028] Please see Figures 1-4 As shown, it includes a primary mirror back plate 1, a primary mirror mount 3 is movably connected to the top central axis of the primary mirror back plate 1, the purpose of which is to support the primary mirror 22, a heat sink 2 is fixedly connected to the bottom of the primary mirror back plate 1, the purpose of which is to absorb the dissipated heat, the heat sink 2 is in the shape of an irregularly curved plate, and also includes;

[0029] Thin-walled cylindrical mechanism 201; The thin-walled cylindrical mechanism 201 includes a stabilizing base mechanism 401 fixedly connected to the top of the primary mirror back plate 1, a stabilizing primary mirror mechanism 402 fixedly connected to the central axis at the middle end of the stabilizing base mechanism 401, and a stabilizing secondary mirror mechanism 403 fixedly connected to the top inner wall of the stabilizing base mechanism 401.

[0030] Exoskeleton stabilization mechanism 202; Exoskeleton stabilization mechanism 202 includes three heat dissipation mechanisms 205 fixedly connected to the inner wall of the top of heat dissipation plate 2, three heat dissipation stabilization mechanisms 206 fixedly connected to the central axis of the top of heat dissipation plate 2, a bending mechanism 204 fixedly connected to the central axis of the right wall inside the bottom of heat dissipation mechanism 205, and a support stabilization mechanism 203 fixedly connected to the right end of the bottom of heat dissipation mechanism 205.

[0031] Example 2,

[0032] The distinguishing features from Example 1 are

[0033] like Figures 1-7 As shown,

[0034] The stabilizing base mechanism 401 includes three embedded parts 19 fixedly connected to the inner walls of the top four sides of the primary mirror back plate 1. This arrangement facilitates precise connection. A back plate connecting ring 4 is fixedly connected to the top four sides of the primary mirror back plate 1. This arrangement improves the stability of the device. Three embedded parts 23 are fixedly connected to the inner walls of the outer walls of the back plate connecting ring 4. This arrangement shortens the installation time. A variable cross-section support bracket 5 is fixedly connected to the top of the back plate connecting ring 4. This arrangement enhances the stability of the device. A secondary mirror support bracket connecting ring 6 is fixedly connected to the top of the variable cross-section support bracket 5. This arrangement reduces the obstruction of incident light. Three embedded parts 37 are fixedly connected to the inner walls of the top of the secondary mirror support bracket connecting ring 6.

[0035] The stabilizing primary reflector mechanism 402 includes three flexible hinges 31 that are fixedly connected to the inner wall of the top central axis of the primary reflector back plate 1. This arrangement aims to improve the stability of the support structure. The top outer wall of the flexible hinge 31 is rotatably connected to the inner wall of the bottom central axis of the primary reflector base 3. The primary reflector 22 is fixedly connected to the top of the primary reflector base 3.

[0036] The stabilizing secondary mirror mechanism 403 includes three secondary mirror supports 14 that are fixedly connected to the inner wall of the secondary mirror support connecting ring 6. The purpose of this arrangement is to strengthen and fix the secondary mirror base 11. The secondary mirror base 11 is fixedly connected to the inner wall of the three secondary mirror supports 14. Three pre-embedded parts 12 are fixedly connected to the inner walls of the top of the secondary mirror base 11. The purpose of this arrangement is to improve the efficiency of the development. The secondary mirror flexible support 21 is fixedly connected to the bottom of the secondary mirror base 11. The secondary mirror 13 is fixedly connected to the top central axis of the secondary mirror flexible support 21.

[0037] The heat dissipation mechanism 205 includes a limiting shell 9 fixedly connected to the inner wall of the top of the heat dissipation plate 2. The purpose of this arrangement is to install the antimony block 51. The antimony block 51 is fixedly connected to the left end of the top of the inner wall of the limiting shell 9. The purpose of this arrangement is to allow it to contract when heated. The left wall of the antimony block 51 is fixedly connected to the inner wall of the top of the heat dissipation plate 2. A connecting plate 49 is fixedly connected to the central axis at the bottom of the right wall of the antimony block 51. The purpose of this arrangement is to fix the bending mechanism 204.

[0038] The bending mechanism 204 includes a fixed rod 48 fixedly connected to the central axis of the inner wall of the connecting plate 49. The purpose of this arrangement is to connect the rotating plate 47. The rotating plate 47 is rotatably connected to the central axis of the outer wall of the fixed rod 48. The inner wall of the bottom end of the rotating plate 47 is rotatably connected to the connecting rod 46. The purpose of this arrangement is to enable left and right rotation.

[0039] The support and stabilization mechanism 203 includes a rising plate 44 rotatably connected to the outer walls of the front and rear ends of the connecting rod 46, which is designed to allow for reciprocating up and down movement. A limiting rod 45 is rotatably connected to the inner wall of the middle end of the rising plate 44, which limits the rising plate 44. A fixing plate 42 is fixedly connected to the central axis of the bottom right end of the limiting shell 9. The central axis of the bottom inner wall of the fixing plate 42 is fixedly connected to the front and rear ends of the limiting rod 45. A stabilizing plate 15 is fixedly connected to the left wall of the rising plate 44, which is designed to fix the variable cross-section support inclined frame 5.

[0040] The heat dissipation stabilization mechanism 206 includes an antimony plate 8 fixedly connected to the central axis at the top of the heat dissipation plate 2. The purpose of this arrangement is to shrink the antimony plate 8. A sponge block 41 is fixedly connected to the left wall of the antimony plate 8. The purpose of this arrangement is to fix and clean the secondary mirror flexible support 21. The left wall of the sponge block 41 is movably connected to the outer wall of the secondary mirror flexible support 21.

[0041] One specific application of this embodiment is:

[0042] The support structure for the primary and secondary mirrors 13 adopts a variable cross-section hollow structure. The carbon fiber material is optimized according to the stress to achieve the requirements of ultra-lightweight and high rigidity for the space remote sensing camera. The support truss of the primary and secondary mirrors 13 adopts a concentric circle structure with the primary mirror, so the imaging light reaching the primary reflector 22 is not obstructed by the support structure between the primary and secondary mirrors 13. The structure is compact with a small outer envelope size. The walls of the secondary mirror 13 support rods are thin, minimizing the obstruction of incident light and meeting the requirements of high-resolution space cameras for high stability and low obstruction of the main support structure.

[0043] The integrated manufacturing process using carbon fiber composite materials simplifies assembly and debugging, shortens installation time, improves development efficiency, ensures the positional accuracy between the primary and secondary mirrors 13, and enhances the stability of the support structure. The tilt angle difference between the primary and secondary mirrors 13 is less than 5 seconds, and the spacing between the primary and secondary mirrors 13 changes better than 1 μm under temperature fluctuation conditions of 20±4℃. The first-order frequency of the overall structure is better than 90Hz, which is higher than the required 80Hz.

[0044] When the machine starts working, it generates heat. The heat sink 2 absorbs the heat, and the antimony block 51 connected to it contracts due to the heat and expands due to the low temperature in space. At this time, the heat dissipation stabilization mechanism 206 and the bending mechanism 204 are hinged, so that the connected rising plate 44 can reciprocate. The fixed plate 42 connected to it can stabilize the variable cross-section support frame 5 during this process, thereby enhancing the stability of the support structure of the space camera primary and secondary mirrors 13, and also improving the service life, preventing parts from being damaged due to overheating.

[0045] When the camera starts working, the heat generated causes the antimony plate 8 on top of the heat sink 2 to contract, and the sponge 41 connected to it can also expand outward, freeing the flexible support 21 of the secondary mirror 13 from being fixed and preventing it from hindering the operation of the space camera. When the camera stops working, the low temperature in space causes the antimony plate 8 to expand, and the sponge 41 to be squeezed inward. In this process, the stability of the flexible support of the secondary mirror 13 is enhanced, and the flexible support 21 of the secondary mirror 13 is cleaned.

[0046] Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art and related fields based on the embodiments of the present invention without inventive effort should fall within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described and explained in the present invention, unless otherwise specified or limited, shall be implemented according to conventional means in the art.

Claims

1. A primary and secondary mirror support structure for a high-resolution coaxial space camera, comprising a primary mirror back plate (1), wherein a primary reflecting mirror mount (3) is movably connected to the top central axis of the primary mirror back plate (1), and a heat sink (2) is fixedly connected to the bottom of the primary mirror back plate (1), wherein the heat sink (2) is in the shape of an irregularly curved plate, characterized in that: Also includes; Thin-walled cylindrical mechanism (201); the thin-walled cylindrical mechanism (201) includes a stabilizing base mechanism (401) fixedly connected to the top of the primary mirror back plate (1), a stabilizing primary mirror mechanism (402) fixedly connected to the central axis at the middle end of the stabilizing base mechanism (401), and a stabilizing secondary mirror mechanism (403) fixedly connected to the inner top wall of the stabilizing base mechanism (401). Exoskeleton stabilization mechanism (202); The exoskeleton stabilization mechanism (202) includes three heat dissipation mechanisms (205) fixedly connected to the inner wall of the top of the heat dissipation plate (2), three heat dissipation stabilization mechanisms (206) are fixedly connected to the central axis of the top of the heat dissipation plate (2), a bending mechanism (204) is fixedly connected to the central axis of the right wall inside the bottom of the heat dissipation mechanism (205), and a support stabilization mechanism (203) is fixedly connected to the right end of the bottom of the heat dissipation mechanism (205). The heat dissipation mechanism (205) includes a limiting shell (9) fixedly connected to the inner wall of the top of the heat dissipation plate (2). An antimony block (51) is fixedly connected to the left end of the top of the inner wall of the limiting shell (9). The left wall of the antimony block (51) is fixedly connected to the inner wall of the top of the heat dissipation plate (2). A connecting plate (49) is fixedly connected to the central axis at the bottom of the right wall of the antimony block (51). The bending mechanism (204) includes a fixed rod (48) fixedly connected to the central axis of the inner wall of the connecting plate (49), a rotating plate (47) rotatably connected to the central axis of the outer wall of the fixed rod (48), and a connecting rod (46) rotatably connected to the inner wall of the bottom end of the rotating plate (47). The supporting and stabilizing mechanism (203) includes a rising plate (44) rotatably connected to the outer walls of the front and rear ends of the connecting rod (46), a limiting rod (45) rotatably connected to the inner wall of the middle end of the rising plate (44), a fixing plate (42) fixedly connected to the central axis of the bottom right end of the limiting shell (9), the central axis of the bottom inner wall of the fixing plate (42) fixedly connected to the front and rear ends of the limiting rod (45), and a stabilizing plate (15) fixedly connected to the left wall of the rising plate (44). The heat dissipation stabilization mechanism (206) includes an antimony plate (8) fixedly connected to the central axis of the top of the heat dissipation plate (2). A sponge block (41) is fixedly connected to the left wall of the antimony plate (8). The left wall of the sponge block (41) is movably connected to the outer wall of the secondary mirror flexible support (21).

2. The high-resolution coaxial space camera primary and secondary mirror support structure according to claim 1, characterized in that: The stabilizing base mechanism (401) includes three embedded parts (19) fixedly connected to the inner walls of the top four sides of the main mirror back plate (1). A back plate connecting ring (4) is fixedly connected to the top four sides of the main mirror back plate (1). Three embedded parts (23) are fixedly connected to the inner walls of the outer walls of the back plate connecting ring (4). A variable cross-section support bracket (5) is fixedly connected to the top of the back plate connecting ring (4). A secondary mirror support bracket connecting ring (6) is fixedly connected to the top of the variable cross-section support bracket (5). Three embedded parts (7) are fixedly connected to the inner walls of the top of the secondary mirror support bracket connecting ring (6).

3. The high-resolution coaxial space camera primary and secondary mirror support structure according to claim 2, characterized in that: The stabilizing main mirror mechanism (402) includes three flexible hinges (31) that are fixedly connected to the inner wall of the top central axis of the main mirror back plate (1). The outer wall of the top of the flexible hinge (31) is rotatably connected to the inner wall of the bottom central axis of the main mirror mount (3). The top of the main mirror mount (3) is fixedly connected to the main mirror (22).

4. The high-resolution coaxial space camera primary and secondary mirror support structure according to claim 3, characterized in that: The stabilizing secondary mirror mechanism (403) includes three secondary mirror supports (14) that are fixedly connected to the inner wall of the secondary mirror support connecting ring (6). The inner walls of the three secondary mirror supports (14) are fixedly connected to a secondary mirror base (11). The inner walls of the top of the secondary mirror base (11) are fixedly connected to three pre-embedded parts (12). The bottom of the secondary mirror base (11) is fixedly connected to a secondary mirror flexible support (21). The secondary mirror (13) is fixedly connected to the top central axis of the secondary mirror flexible support (21).

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