Extrasolar planet imaging coronagraph structure with detection function

Abstract

The invention discloses an extrasolar planetary imaging coronagraph structure with a detection function, the extrasolar planetary imaging coronagraph structure comprises a main frame, and an optical assembly, a visible light imaging camera, a high-order wave aberration correction box, a wavefront detection camera, a scientific data processing electric box and a tilt correction box which are mounted in a sealed cavity in the main frame, and the optical assembly is provided with a light inlet hole. According to the invention, the main frame is made of a high-strength carbon fiber composite material, and through optimized mechanical architecture design and material combination, the structural strength is obviously improved on the basis of light weight, larger load and a harsh working environment can be borne, rigid body displacement or deformation of an internal optical instrument is prevented, and the service life is prolonged; meanwhile, innovative materials and structural design of the pre-embedded aluminum bee layer are adopted, the overall weight is greatly reduced on the premise that the functional integrity is guaranteed, material consumption is effectively reduced, and the installation efficiency of the product is improved; it is guaranteed that the coronagraph structure and internal components can bear the dynamic environment when a rocket is launched.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of coronagraph, in particular to a structure of an exoplanet imaging coronagraph with a detection function. BACKGROUND

[0002] The exoplanet imaging coronagraph (CPI-C) module is a fine scientific observation load of the all-sky space telescope (CSST) all-sky optical facility of the Chinese space station project major project, and the target is to perform high-contrast direct imaging observation on exoplanets, break through the limitation of ground observation equipment in imaging contrast detection capability, and realize imaging detection and scientific research of exoplanets for the first time, thereby laying an important foundation for human search for extraterrestrial life. The severe and complex dynamic launch environment is an important process that each precise astronomical optical load must experience, which mainly occurs in the rocket flight stage.

[0003] Due to the extremely high imaging contrast of the CPI-C, the complex environment during the rocket flight process has a more obvious influence on the CPI-C, which is easy to cause rigid displacement or deformation of the internal optical instrument, affect the imaging contrast, and even cause the failure of the entire module performance and the failure of the task. It is necessary to ensure that the coronagraph structure and internal components can withstand the dynamic environment during the rocket launch.

[0004] Therefore, it is necessary to develop an exoplanet imaging coronagraph structure with a detection function to solve the above problems. SUMMARY

[0005] The technical problem to be solved by the present application is to solve the above problems, and to provide an exoplanet imaging coronagraph structure with a detection function, so as to ensure that the coronagraph structure and internal components can withstand the dynamic environment during the rocket launch. At the same time, the risks existing in the process of assembling the electronic components of the coronagraph are solved, and the reliability of the coronagraph structure is improved.

[0006] To solve the above technical problems, the technical scheme adopted by the present application is: An exoplanet imaging coronagraph structure with a detection function, comprising a main frame, an optical assembly, a visible light imaging camera, a high-order wave aberration correction box, a wavefront detection camera, a scientific data processing electric box and an inclination correction box installed in a sealed cavity inside the main frame, wherein the optical assembly is provided with a light inlet hole. The main frame includes a frame body, with an upper cover plate and a lower cover plate fastened to the top and bottom of the frame body, respectively. Positioning posts are fixedly connected to the four corners of the upper cover plate and the lower cover plate. Multiple positioning sleeves corresponding to the positioning posts are fixedly arranged inside the frame body, and the positioning posts and positioning sleeves are slidably engaged. A collar is fixedly connected to both the upper cover plate and the lower cover plate. A traction mechanism is installed inside the main frame. The output end of the traction mechanism is synchronously connected to two tension springs, and the two tension springs are detachably installed and removed from the two collars by means of hooks. The frame body includes a support frame composed of carbon fiber rods and joints. The gap in the middle of the outer wall of the support frame is filled with aluminum honeycomb layer components, and the inner and outer sides of the interlocking structure of the support frame and the aluminum honeycomb layer components are glued together.

[0007] Preferably, both the upper cover plate and the lower cover plate include a support platform. The top of the support platform of the upper cover plate is covered with component piece one, component piece three, component piece four and component piece five in sequence, and a through hole matching the outer diameter of the optical component is reserved. Component piece two is installed on the support platform of the lower cover plate.

[0008] Preferably, a plurality of titanium alloy embedded parts are embedded in the inner wall of the frame body, and the titanium alloy embedded parts are located inside the main frame and protrude from the skin. The positioning sleeve and the traction mechanism are both installed on the corresponding titanium alloy embedded parts, and the positioning column and the collar are both fixedly connected to the support platform.

[0009] Preferably, component piece one, component piece two, component piece three, component piece four and component piece five are all detachably installed to the support platform via screws.

[0010] Preferably, the traction mechanism includes a drive motor, the output end of which is connected to a gear. Two titanium alloy embedded parts inside the frame body are each equipped with a slide rail, and a vertical cantilever rod is slidably connected to the inner side of each slide rail. The tension spring is connected to one end of the vertical cantilever rod via a ball joint, and a rack is connected to the end of the vertical cantilever rod away from the tension spring. Two racks are centrally symmetrically distributed on both sides of the gear and mesh with the gear for transmission.

[0011] Preferably, the aluminum honeycomb layer component is configured as a hexagonal aluminum honeycomb layer, and the skin is made of CCM40J-phenol91 carbon fiber composite material.

[0012] Preferably, there is a height difference of length L between the positioning sleeve and the outer edge of the frame body, the thickness of the upper cover plate and the lower cover plate is set to m, and L > m, and sealing packing is provided between the upper cover plate, the lower cover plate and the frame body.

[0013] Preferably, the back of the optical assembly is provided with a visible light filter wheel, a laser, a deformable mirror and a laser controller, wherein the laser is arranged in the internal optical path of the optical assembly for internal optical path calibration, the laser is electrically connected with the laser controller, the high-order wave aberration correction box and the tilt correction box are sequentially arranged on the internal optical path output line, the tilt correction box is used for controlling the fast steering mirror, the high-order wave aberration correction box is used for controlling the deformable mirror to correct the optical path, the output end of the deformable mirror is provided with a beam splitter for splitting the optical path into a wavefront optical path and a visible light optical path, wherein the wavefront optical path is incident to a wavefront detection camera, the visible light optical path is incident to a visible light imaging camera after being filtered by the visible light filter wheel, and the wavefront detection camera and the visible light imaging camera are electrically connected with the input end of a scientific data processing electric box.

[0014] Preferably, a visible light refrigeration machine assembly is further installed inside the main frame to provide a refrigeration environment inside the main frame, so that the imaging working environment of the visible light imaging camera is maintained at -100℃ to -80℃.

[0015] Preferably, the front of the optical assembly is embedded in a through hole, and a sealing packing is arranged between the optical assembly and the upper cover plate, the optical assembly is made of SiCp / Al-HT8 type aluminum-based silicon carbide material, and a plurality of lightening holes are arranged on the back of the optical assembly, and the cross-sectional shape of the lightening hole is triangular.

[0016] The present application has the following advantages: By selecting high-strength carbon fiber composite material to manufacture the main frame, and by optimizing the mechanical architecture design and material combination, the structural strength is significantly improved on the basis of lightening, which can withstand greater load and more severe working environment, prevent rigid body displacement or deformation of internal optical instruments, and prolong the service life; at the same time, the innovative material and structure design of pre-embedded aluminum honeycomb can greatly reduce the overall weight on the premise of ensuring the integrity of the function, effectively reduce material consumption, and improve the installation efficiency of the product; it is beneficial to ensure that the star coronagraph structure and internal components can withstand the dynamic environment during rocket launch.

[0017] By optimizing the installation mode of the internal optical instruments of the star coronagraph structure, the local component pieces can be individually disassembled for inspection, or the whole can be disassembled, the whole operation process is convenient and fast, and the traction mechanism is applied, which can simultaneously pull and press the upper cover plate and the lower cover plate to close them, or simultaneously open them, greatly improving the construction efficiency; under the driving of the driving motor, the upper cover plate and the lower cover plate are pulled tightly and buckled on the frame body, and then they are reinforced by using bolt connection and other methods, so that the structure is more stable and can be sealed under the action of pre-tightening force; the risk existing in the process of integrating and assembling various electronic components of the star coronagraph is solved, and the reliability of the star coronagraph structure is improved. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 This is a schematic diagram of the internal structure of the main frame of the star coronagraph structure provided by the present invention.

[0019] Figure 2 This is a schematic diagram of the distribution structure of the frame body and the titanium alloy embedded parts in this invention.

[0020] Figure 3 This is a schematic diagram of the supporting frame in this invention.

[0021] Figure 4 This is a schematic diagram of the aluminum honeycomb layer component in this invention.

[0022] Figure 5 This is a schematic diagram of the upper cover plate and the lower cover plate in this invention.

[0023] Figure 6 This is a schematic diagram of the distribution structure of the visible light filter wheel, laser, deformable mirror and laser controller in this invention.

[0024] Figure 7 This is a schematic diagram of the cooperation structure between the upper cover plate and the lower cover plate and the traction mechanism in this invention.

[0025] In the picture: Main frame - 1; Optical components - 2; Visible light imaging camera - 3; Higher-order wavefront aberration correction box - 4; Wavefront detection camera - 5; Visible light cooling unit assembly - 6; Scientific data processing box - 7; Tilt correction box - 8; Entrance aperture - 9; Visible light filter wheel - 10; Laser - 11; Deformable mirror - 12; Laser controller - 13; Positioning post - 14; Positioning sleeve - 15; Skin - 16; Collar - 17; Traction mechanism - 18; Tension spring - 19; Support platform - 100; Frame body - 101; Component piece 1 - 102; Component piece 3 - 104; Component piece 4 - 105; Component piece 5 - 106; Through hole - 107; Drive motor - 181; Gear - 182; Slide rail - 183; Vertical cantilever - 184; Rack - 185; Carbon fiber rods - 1011; joints - 1012; aluminum honeycomb structure components - 1013; titanium alloy embedded parts - 1014. Detailed Implementation

[0026] The present invention will now be described in further detail with reference to the accompanying drawings and specific preferred embodiments.

[0027] In the description of the present application, it should be understood that the terms "left side", "right side", "upper part", "lower part" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and "first", "second" and the like do not represent the importance of the parts, and therefore cannot be understood as a limitation on the present application. The specific dimensions used in the embodiments are only for the purpose of illustrating the technical solutions and do not limit the protection scope of the present application.

[0028] As shown in Figures 1-7 A structure of an exoplanet imaging coronagraph with detection function, comprising a main frame 1 and an optical assembly 2, a visible light imaging camera 3, a high-order wave aberration correction box 4, a wavefront detection camera 5, a scientific data processing electric box 7 and a tilt correction box 8 installed in the sealed cavity inside the main frame 1, wherein the optical assembly 2 is provided with a light inlet hole 9; the exoplanet light enters the body of the coronagraph structure from the light inlet hole 9.

[0029] The main frame 1 is a force bearing structure of the visible light imaging coronagraph, the main frame 1 comprises a frame body 101, the top and bottom of the frame body 101 are respectively clamped with an upper cover plate and a lower cover plate, the upper cover plate and the lower cover plate are fixedly connected with positioning columns 14 at four corners, a plurality of positioning sleeves 15 corresponding to the positioning columns 14 are fixedly arranged in the inside of the frame body 101, and the positioning columns 14 and the positioning sleeves 15 are in sliding fit, the upper cover plate and the lower cover plate are fixedly connected with sleeve rings 17, a traction mechanism 18 is installed inside the main frame 1, the output end of the traction mechanism 18 is synchronously connected with two tension spring members 19, and the two tension spring members 19 are detachably installed with the two sleeve rings 17 through hooks; the installation is convenient and fast, and this mode can reduce the loss between structures and improve the service life and safety of the device.

[0030] The frame body 101 comprises a support frame composed of carbon fiber rod members 1011 and joints 1012, the middle gap of the outer wall of the support frame is filled with aluminum honeycomb members 1013, and the embedded structure of the support frame and the aluminum honeycomb members 1013 is glued with a skin 16 on the inside and outside. After the frame body 101 is processed, it forms an integrated glue joint forming closed structure, and a closed cavity is formed in its inside, which can effectively inhibit the generation of excess materials. If there are small glue particles, aluminum chips and other excess materials inside, they cannot be transmitted to the outside optical assembly through the closed cavity, thereby avoiding pollution of the optical mirror surface and the camera light window.

[0031] Further, in the above technical solution, the upper cover plate and the lower cover plate each comprise a support platform 100, the support platform 100 of the upper cover plate has the assembly sheet one 102, the assembly sheet three 104, the assembly sheet four 105 and the assembly sheet five 106 sequentially laid and buckled on the top, and a through hole 107 matched with the outer diameter of the optical assembly 2 is reserved; the support platform 100 of the lower cover plate is provided with the assembly sheet two 103. The assembly sheet one 102, the assembly sheet two 103, the assembly sheet three 104, the assembly sheet four 105 and the assembly sheet five 106 are first installed on the corresponding support platform 100, and the structure still maintains the structure that can be individually detached to realize individual inspection, the upper cover plate and the lower cover plate can be integrally installed and detached during installation, and safety traction and elastic buffering are provided, so that the sealing cavity of the main frame 1 is sealed, and the installation efficiency and the anti-deformation capability of the device are further improved. In the embodiment given in the application, the high-order wave aberration correction box 4 is installed on the assembly sheet one 102; the wavefront detection camera 5 is installed on the assembly sheet two 103; the visible light imaging camera 3 and the scientific data processing electric box 7 are installed on the assembly sheet four 105; and the tilt correction box 8 is installed on the assembly sheet three 104.

[0032] Further, in the above technical solution, since the carbon fiber cannot be used as a mechanical interface, a titanium alloy embedded part 1014 needs to be pre-embedded in the carbon fiber structure, and a mechanical interface is processed on the embedded part. A plurality of titanium alloy embedded parts 1014 are embedded on the inner wall of the frame body 101, and the titanium alloy embedded parts 1014 are located on the inner side of the main frame 1 and protrude from the skin 16, the positioning sleeve 15 and the traction mechanism 18 are installed on the corresponding titanium alloy embedded parts 1014, and the positioning column 14 and the sleeve ring 17 are fixedly connected to the support platform 100.

[0033] Further, in the above technical solution, the assembly sheet one 102, the assembly sheet two 103, the assembly sheet three 104, the assembly sheet four 105 and the assembly sheet five 106 are detachably installed with the support platform 100 through screws. Each component can be individually detached for inspection and maintenance, and the precision requirement is met.

[0034] As a preferred embodiment of the traction mechanism 18 disclosed in this application, the traction mechanism 18 includes a drive motor 181, the output end of which is connected to a gear 182. Two titanium alloy embedded parts 1014 on the inner side of the frame body 101 are each equipped with a slide rail 183. A vertical cantilever rod 184 is slidably connected to the inner side of each slide rail 183. A tension spring 19 is connected to one end of the vertical cantilever rod 184 via a ball joint, and a rack 185 is connected to the end of the vertical cantilever rod 184 away from the tension spring 19. Two racks 185 are centrally symmetrically distributed on both sides of the gear 182 and mesh with the gear 182 for transmission. Of course, other embodiments that can achieve similar effects can also be used. In this embodiment, when the upper and lower cover plates with the installed electrical components are assembled onto the frame body 101, the two sets of vertical cantilever rods 184 are connected to the collars 17 of the upper and lower cover plates respectively using tension springs 19. Then, the output shaft of the drive motor 181 is controlled to rotate, causing the racks 185 on both sides of the gear 182 to move relative to each other. At this time, it is only necessary to insert and assemble the positioning pins 14 and positioning sleeves 15 one by one. Under the drive of the drive motor 181, the final position is... The upper and lower cover plates are fastened to the frame body 101 and then reinforced using bolts or other methods. The pre-tension makes the structure more stable and provides a seal. For maintenance, individual component pieces can be disassembled for inspection, or the entire assembly can be disassembled, making the operation convenient and quick.

[0035] Furthermore, in the above technical solution, the aluminum honeycomb layer component 1013 is set as a hexagonal aluminum honeycomb layer, and the skin 16 is made of CCM40J-phenol 91 carbon fiber composite material. The hexagonal aluminum honeycomb layer has an extremely thin wall thickness, providing sufficient support. This significantly reduces the overall weight while ensuring functional integrity, effectively reducing material consumption. Each electrical module is installed in the sealed cavity of the main frame 1. The skin 16 is thermosetting after adhesive bonding, exhibiting good temperature resistance; temperature boundaries will not cause delamination or detachment.

[0036] Furthermore, in the above technical solution, there is a height difference of length L between the positioning sleeve 15 and the outer edge of the frame body 101, the thickness of the upper cover plate and the lower cover plate is set to m, and L>m, and sealing packing is provided between the upper cover plate, the lower cover plate and the frame body 101.

[0037] Further, in the above technical solution, the back of the optical assembly 2 is provided with a visible light filter wheel 10, a laser 11, a deformable mirror 12 and a laser controller 13, wherein the laser 11 is arranged in the inner light path of the optical assembly 2 and is used for inner light path calibration, and after calibration is completed, planetary light observation is performed. The laser 11 is electrically connected with the laser controller 13, the high-order wave aberration correction box 4 and the tilt correction box 8 are sequentially arranged on the inner light path output line, the tilt correction box 8 is used for controlling the fast steering mirror, and the high-order wave aberration correction box 4 is used for controlling the deformable mirror 12 to correct the light path. The output end of the deformable mirror 12 is provided with a beam splitter, which is used to divide the light path into a wavefront light path and a visible light path. The wavefront light path is incident into the wavefront detection camera 5, and the visible light path is incident into the visible light imaging camera 3 after being filtered by the visible light filter wheel 10. The wavefront detection camera 5 and the visible light imaging camera 3 are electrically connected with the input end of the scientific data processing electric box 7. When the exoplanet light is incident into the coronagraph structure body from the light inlet hole 9 on the upper surface of the optical assembly 2, after being processed by the inner light path in the optical assembly 2 and the high-order wave aberration correction box 4 and the tilt correction box 8, and after being filtered by the visible light filter wheel 10 and calibrated by the laser 11, the light is incident into the visible light imaging camera 3 and the wavefront detection camera 5 for high-contrast imaging, and finally is processed by the scientific data processing electric box 7.

[0038] The circuit and the control involved in the present application are prior art, and will not be described in detail here.

[0039] Further, in the above technical solution, the visible light refrigeration machine assembly 6 is further installed in the main frame 1, which is used to provide a refrigeration environment in the main frame 1, so that the imaging working environment of the visible light imaging camera 3 is maintained at -100℃ to -80℃. In the embodiment given in the present application, the visible light refrigeration machine assembly 6 is installed on the assembly sheet four 105.

[0040] Further, in the above technical solution, the front of the optical assembly 2 is embedded in the through hole 107, and a sealing packing is arranged between the optical assembly 2 and the upper cover plate. The optical assembly 2 adopts SiCp / Al-HT8 type aluminum-based silicon carbide material, which has the characteristics of high thermal conductivity and low thermal expansion coefficient. The optical assembly 2 adopts a semi-closed lightweight form, and a plurality of lightweight holes are formed on the back of the optical assembly 2, and the cross-sectional shape of the lightweight hole is triangular.

[0041] When the structure of the exoplanet imaging coronagraph with a detection function is working, the exoplanet light enters the optical assembly 2 from the light inlet hole 9 on the top, enters the inner light path, and then is corrected by the fast mirror controlled by the tilt correction box 8 and the deformable mirror 12 controlled by the high-order wavefront aberration correction box 4, and then is filtered by the visible light filter wheel 10 and calibrated by the laser 11, and then is observed, specifically, the target object is divided into a wavefront light path and a visible light path by a beam splitter, the wavefront light path is incident to a wavefront detection camera 5, the visible light path is filtered by the visible light filter wheel 10 and then is incident to a visible light imaging camera 3, high-contrast imaging is performed by the visible light imaging camera 3 and the wavefront detection camera 5, and finally processing is performed by a scientific data processing electric box 7. Each component is arranged in a main frame mainly composed of high-strength carbon fiber composite material, and through optimized mechanical architecture design and material combination, the structure strength is significantly improved on the basis of light weight, can bear greater load and more severe working environment, prevents rigid body displacement or deformation of internal optical instruments, and prolongs the service life.

[0042] The embodiments of the present application are described in detail above with reference to the drawings, but the present application is not limited to the described embodiments. For those skilled in the art, various changes, modifications, replacements and variations of the embodiments can be made without departing from the principles and spirits of the present application, and still fall within the protection scope of the present application.

Claims

1. An exoplanet imaging coronagraphic structure with a probing function, characterized in that: It comprises a main frame (1), an optical assembly (2), a visible light imaging camera (3), a high-order wave aberration correction box (4), a wavefront detection camera (5), a scientific data processing electric box (7) and a tilt correction box (8) which are installed in the sealed cavity inside the main frame (1), wherein the optical assembly (2) is provided with an entrance hole (9); The main frame (1) comprises a frame body (101), the top and bottom of the frame body (101) are respectively buckled with an upper cover plate and a lower cover plate, the upper cover plate and the lower cover plate are fixedly connected with positioning columns (14) at four corners, a plurality of positioning sleeves (15) corresponding to the positioning columns (14) are fixedly arranged on the inner side of the frame body (101), the positioning columns (14) and the positioning sleeves (15) are in sliding fit, the upper cover plate and the lower cover plate are fixedly connected with sleeve rings (17), a traction mechanism (18) is installed in the main frame (1), the output end of the traction mechanism (18) is synchronously connected with two tension spring members (19), and the two tension spring members (19) are detachably installed with the two sleeve rings (17) through hooks. The frame body (101) comprises a support frame which is composed of carbon fiber rod members (1011) and joints (1012), the middle gap of the outer wall of the support frame is filled with aluminum honeycomb members (1013), and the embedded structure of the support frame and the aluminum honeycomb members (1013) is glued with a skin (16) on the inner and outer sides.

2. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The upper cover plate and the lower cover plate both comprise a support platform (100), the support platform (100) of the upper cover plate is sequentially and flatly buckled with an assembly piece one (102), an assembly piece three (104), an assembly piece four (105) and an assembly piece five (106) on the top, and a through hole (107) matched with the outer diameter of the optical assembly (2) is reserved; the support platform (100) of the lower cover plate is installed with an assembly piece two (103).

3. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 2, characterized in that: A plurality of titanium alloy embedded members (1014) are embedded on the inner wall of the frame body (101), and the titanium alloy embedded members (1014) are protruded from the skin (16) on the inner side of the main frame (1), the positioning sleeves (15) and the traction mechanism (18) are both installed on the corresponding titanium alloy embedded members (1014), and the positioning columns (14) and the sleeve rings (17) are both fixedly connected on the support platform (100).

4. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 2, characterized in that: The assembly piece one (102), the assembly piece two (103), the assembly piece three (104), the assembly piece four (105) and the assembly piece five (106) are detachably installed with the support platform (100) through screws.

5. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 3, characterized in that: The traction mechanism (18) comprises a driving motor (181), the output end of the driving motor (181) is transmissionally connected with a gear (182), two titanium alloy embedded parts (1014) on the inner side of the frame body (101) are both provided with a sliding rail (183), the inner side of the two sliding rails (183) are both slidingly connected with a vertical lifting lever (184), the pulling spring part (19) is connected with the gear (182) through a ball hinge at one end of the vertical lifting lever (184), and a rack (185) is connected to the other end of the vertical lifting lever (184) away from the pulling spring part (19), the two racks (185) are centrally symmetrically distributed on the two sides of the gear (182) and are in mesh transmission with the gear (182).

6. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The aluminum honeycomb layer component (1013) is set as a hexagonal aluminum honeycomb layer, and the skin (16) is made of CCM40J-phenol 91 carbon fiber composite material.

7. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The positioning sleeve (15) and the outer side edge of the frame body (101) have a height difference with a length of L, the thickness of the upper cover plate and the lower cover plate is set as m, and L>m, and sealing packing is arranged between the upper cover plate, the lower cover plate and the frame body (101).

8. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The back of the optical assembly (2) is provided with a visible light filter wheel (10), a laser (11), a deformable mirror (12) and a laser controller (13), wherein the laser (11) is arranged in the inner light path of the optical assembly (2) and is used for inner light path calibration, the laser (11) is electrically connected with the laser controller (13), a high-order wave aberration correction box (4) and a tilt correction box (8) are sequentially arranged on the inner light path output line, the tilt correction box (8) is used for controlling a fast swing mirror, the high-order wave aberration correction box (4) is used for controlling the deformable mirror (12) to correct the light path, the output end of the deformable mirror (12) is provided with a beam splitter, which is used for splitting the light path into a wavefront light path and a visible light path, wherein the wavefront light path is incident to a wavefront detection camera (5), the visible light path is incident to a visible light imaging camera (3) after being filtered by the visible light filter wheel (10), and the wavefront detection camera (5) and the visible light imaging camera (3) are electrically connected with the input end of a scientific data processing electric box (7).

9. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The main frame (1) is further provided with a visible light refrigeration machine assembly (6) inside, which is used for providing a refrigeration environment inside the main frame (1) to maintain the imaging working environment of the visible light imaging camera (3) at-100℃ to-80℃.

10. The exoplanet imaging coronagraphic instrument structure with a probing function according to claim 1, characterized in that: The front of the optical assembly (2) is embedded in the through hole (107), and sealing packing is arranged between the optical assembly (2) and the upper cover plate, the optical assembly (2) is made of SiCp / Al-HT8 type aluminum-based silicon carbide material, and a plurality of light weight holes are formed in the back of the optical assembly (2), and the cross section shape of the light weight hole is set as a triangle.

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