Truss structure for large-size space cameras

Abstract

This invention relates to the field of space optical remote sensing technology, and more particularly to a truss structure for a large-size space camera, comprising: a top-level support frame, a bottom-level support frame, a truss system, and an external interface connection assembly; the top-level support frame and the bottom-level support frame are parallel and coaxially arranged; the truss system includes a first truss group, a second truss group, a third truss group, and a fourth truss group; the first truss group is connected between the top-level support frame and the bottom-level support frame; the external interface connection assembly is located between the top-level support frame and the bottom-level support frame; the top-level support frame includes a secondary mirror support ring and a primary mirror support frame, the secondary mirror support ring and the primary mirror support frame being connected by the second truss group; the third truss group is disposed inside the primary mirror support frame; and the fourth truss group is disposed inside the bottom-level support frame. The advantage of this invention is that, through the coordinated design of the top-level support frame, the bottom-level support frame, the truss system, and the external interface connection assembly, an ultra-large-size truss structure is achieved.

Description

Technical Field

[0001] This invention relates to the field of space optical remote sensing technology, and more particularly to a truss structure for large-size space cameras. Background Technology

[0002] Long-focal-length coaxial space cameras are core equipment for deep space exploration and high-resolution Earth observation. Their optical systems typically consist of a primary mirror, secondary mirrors, third mirrors, and detectors. The secondary mirror is indirectly mounted to the main support frame via a connecting component. The main support frame also has installation relationships with other mirrors, components, and satellite platforms. Therefore, it is one of the key structures for ensuring the stability of optical elements and withstanding the impact and vibration during launch. As the size of the primary mirror increases and the requirements for camera weight control become more stringent, the weight ratio of the main support frame needs to be continuously reduced (typically, the truss structure is required to account for 30% to 40% of the total camera weight), placing higher demands on its lightweight design.

[0003] Currently, the commonly used materials for space camera support frames are cast titanium alloys and carbon fiber composites, both of which have been applied in numerous space missions. Carbon fiber has the advantages of low density and high elastic modulus, but its molding process is complex; titanium alloys, on the other hand, possess high specific stiffness and good processing stability, making them suitable for complex structural molding. Space camera main support frames using either cast titanium alloys or carbon fiber composites suffer from the following problems:

[0004] (1) Size limitation: Due to the limitations of domestic casting technology, it is difficult to achieve one-time casting of large-size, complex closed structures;

[0005] (2) Weight limitation: In order to control casting defects, the wall thickness usually needs to be greater than 5mm, which makes it difficult to further reduce the weight of the frame;

[0006] (3) Insufficient stiffness: Large-size cast beams often adopt "L" or "I" shaped open sections, which have low stiffness and require the addition of auxiliary beams for reinforcement, further increasing the structural weight. Summary of the Invention

[0007] Based on this, the present invention proposes a truss structure for large-size space cameras. The ultra-large-size truss structure is achieved through a top-level support frame, a bottom-level support frame, a truss strut system, and external interface connection components.

[0008] To achieve the above objectives, the technical solution of this invention is implemented as follows: A truss structure for a large-size space camera includes: a top-level support frame, a bottom-level support frame, a truss system, and an external interface connection assembly; the top-level support frame and the bottom-level support frame are parallel and coaxially arranged; the truss system includes a first truss group, a second truss group, a third truss group, and a fourth truss group; wherein, the first truss group is connected between the bottom of the top-level support frame and the top of the bottom-level support frame; the external interface connection assembly is located between the top-level support frame and the bottom-level support frame and is connected to the first truss group, for connecting the space camera... The primary mirror of the camera has optical elements and a focal plane assembly on its back. The top support frame includes a secondary mirror support ring and a primary mirror support frame located inside the secondary mirror support ring. The secondary mirror support ring and the primary mirror support frame are connected by a second truss assembly. The secondary mirror support ring is used to connect to the secondary mirror support cylinder of the space camera. The primary mirror support frame is used to connect to the primary mirror assembly of the space camera. The third truss assembly is located inside the primary mirror support frame and connected to it. The fourth truss assembly is located inside the bottom support frame and connected to it. The bottom support frame is a polygonal frame structure used to connect to the satellite where the space camera is located.

[0009] Furthermore, the secondary mirror support ring includes an inner ring arm, an outer ring arm, and an intermediate crossbeam located between the inner and outer ring arms; the cross-section of the secondary mirror support ring is H-shaped, and the opening of the H-shape faces the axial direction of the secondary mirror support ring; the secondary mirror support ring has an equal number of first connection points and second connection points evenly distributed on it, the first connection points are located on the side of the inner ring arm facing the primary mirror support frame; the second connection points are located on the lower surface of the intermediate crossbeam; each first connection point and its corresponding second connection point are located in the same circumferential position of the secondary mirror support ring.

[0010] Furthermore, the primary mirror support frame includes a first connector and a support beam for forming a polygonal frame structure, and the three vertices of the polygonal frame structure, which are evenly distributed along the circumference, are all connected to the secondary mirror load-bearing ring.

[0011] Furthermore, the support beam includes an upper support arm, a lower support arm, and a connecting beam, with the connecting beam positioned between the upper and lower support arms; the cross-section of the support beam is H-shaped, and the opening of the H-shape faces the radial direction of the secondary mirror bearing ring.

[0012] Furthermore, the first connector includes at least three first connecting joints in different directions, and a first connecting interface for connecting with the secondary mirror support tube of the space camera; the third truss rod group is connected to the inside of the primary mirror support frame through the first connecting joints.

[0013] Furthermore, one end of each second truss member in the second truss member group is connected to the corresponding first connecting joint, and the other end of each second truss member is connected to the corresponding first connecting point.

[0014] Furthermore, the third truss rod group includes a third truss rod and a second connector for forming a triangular grid structure; the second connector is provided with at least six second connection joints in different directions for connecting the third truss rods; any two adjacent second connectors are connected by the third truss rods, and every three third truss rods are connected to form a triangular structure.

[0015] Furthermore, the fourth truss assembly includes a fourth truss member for forming a triangular grid structure and a third connector; the third connector is provided with at least six third connecting joints and second connecting interfaces in different directions, the third connecting joints are used to connect the fourth truss member, and the second connecting interfaces are used to connect with the accessories of the space camera; any two adjacent third connectors are connected by the fourth truss member, and every three fourth truss members are connected to form a triangular structure.

[0016] Furthermore, the bottom support frame includes a fifth truss rod and a fourth connector for forming a polygonal frame, with any two adjacent fifth truss rods connected by the fourth connector; the fourth connector includes at least five fourth connection joints and a third connection interface; the third connection interface is used to connect to the satellite where the space camera is located; the fourth truss rod group is connected to the inside of the bottom support frame through the fourth connection joints.

[0017] Furthermore, the truss members in the first, second, third, and fourth truss member groups are all hollow, thin-walled titanium alloy round tubes, with an outer diameter to length ratio not exceeding 1:20.

[0018] Furthermore, the external interface connection assembly includes at least one first interface connector and at least two second interface connectors; each first interface connector is provided with a fifth connection joint for connecting to a corresponding truss rod, and a fourth connection interface for connecting to a space camera accessory; both ends of each second interface connector are respectively connected to a corresponding truss rod; each second interface connector is provided with a fifth connection interface for connecting to a space camera accessory.

[0019] The present invention can achieve the following beneficial effects:

[0020] 1) Through the coordinated design of the top-level support frame, bottom-level support frame, truss strut system, and external interface connection components, an ultra-large truss structure was achieved. The truss struts are reliably connected to the top-level support frame, bottom-level support frame, and external interface connection components via connecting joints, thereby ensuring the strength of the entire truss structure.

[0021] 2) By selecting thin-walled titanium alloy round tubes as the truss rod material, the overall mass of the truss structure is significantly reduced while its overall stiffness is effectively improved. This allows the weight of the truss structure to be controlled within 20% of the total camera weight, making it lighter than a carbon fiber truss structure of the same size. Furthermore, the V-shaped arrangement of adjacent truss rods in the truss system primarily utilizes the stability principle of triangles to ensure the stability of the truss structure.

[0022] 3) Finite element simulation analysis results show that the first-order fundamental frequency of the truss structure in the X, Y and Z directions of the space camera coordinate system is greater than 40Hz, and the dynamic performance is excellent. When a 10g overload is applied in the X, Y and Z directions respectively for strength analysis, the structural safety margin is greater than 4.2, which shows that it has extremely high load-bearing capacity and reliability. Attached Figure Description

[0023] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0024] Figure 1 This is a first-view structural schematic diagram of a truss structure for a large-size space camera provided according to an embodiment of the present invention;

[0025] Figure 2 This is a structural schematic diagram of a truss structure for a large-size space camera from a second perspective, provided according to an embodiment of the present invention.

[0026] Figure 3 This is a structural schematic diagram of a truss structure for a large-size space camera from a third-view perspective, provided according to an embodiment of the present invention.

[0027] Figure 4 This is a schematic diagram of the main mirror support frame provided according to an embodiment of the present invention;

[0028] Figure 5 This is a structural schematic diagram of the third connector provided according to an embodiment of the present invention;

[0029] Figure 6 This is a schematic diagram of the structure of the first interface connector provided according to an embodiment of the present invention;

[0030] Figure 7 This is a schematic diagram of the structure of the second interface connector provided according to an embodiment of the present invention.

[0031] The reference numerals in the attached drawings include: 1. Top-level support frame; 11. Secondary mirror bearing ring; 12. Primary mirror support frame; 121. First connector; 122. Support beam; 123. First connecting joint; 124. First connecting interface; 2. Bottom-level support frame; 21. Fifth truss member; 22. Fourth connector; 221. Fourth connecting joint; 222. Third connecting interface; 3. Truss member system; 31. First truss member group; 32. Second truss member group; 33. Third truss member group; 331. Second connector; 332. Second connecting joint; 34. Fourth truss member group; 341. Third connector; 342. Third connecting joint; 343. Second connecting interface; 4. External interface connection assembly; 41. First interface connector; 411. Fifth connecting joint; 412. Fourth connecting interface; 42. Second interface connector; 421. Fifth connecting interface. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0033] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0034] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0035] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0036] The invention will now be described in detail with reference to specific embodiments.

[0037] like Figures 1 to 7 As shown in the figure, an embodiment of the present invention provides a truss structure for a large-size space camera, including: a top support frame 1, a bottom support frame 2, a truss system 3, and an external interface connection assembly 4. The top support frame 1 and the bottom support frame 2 are parallel and coaxially arranged. The top support frame 1 is used to connect to the primary mirror assembly and secondary mirror support cylinder of the space camera, and the bottom support frame 2 is used to connect to the satellite where the space camera is located. The external interface connection assembly 4 is connected between the top support frame 1 and the bottom support frame 2, and is used to connect the optical elements and focal plane assembly on the back of the primary mirror of the space camera.

[0038] In this embodiment, the primary mirror assembly includes a primary mirror and a support member connected to the primary mirror. The optical elements on the back side of the primary mirror include three mirrors and a folding mirror.

[0039] The top support frame 1 includes a secondary mirror support ring 11 and a primary mirror support frame 12 disposed inside the secondary mirror support ring 11. The secondary mirror support ring 11 is used to connect the secondary mirror support cylinder. The cross-section of the secondary mirror support ring 11 is H-shaped, and the opening of the H-shape faces the axial direction of the secondary mirror support ring 11. The secondary mirror support ring 11 includes an inner ring arm, an outer ring arm, and an intermediate crossbeam located between the inner ring arm and the outer ring arm.

[0040] The secondary mirror support ring 11 has an equal number of first and second connection points evenly distributed. The first connection points are located on the inner ring arm facing the primary mirror support frame 12. The second connection points are located on the lower surface of the intermediate crossbeam. Each first connection point and its corresponding second connection point are located in the same circumferential position on the secondary mirror support ring 11. This arrangement ensures that the truss structure is subjected to uniform stress, thereby improving its overall stability.

[0041] The primary mirror support frame 12 is used to connect the primary mirror assembly. The primary mirror support frame 12 includes multiple first connectors 121 and multiple support beams 122. The multiple support beams 122 form a polygonal frame structure. The three vertices of the polygonal frame structure, which are evenly distributed along the circumference, are all connected to the secondary mirror support ring 11. The cross-section of the support beam 122 is H-shaped, and the opening of the H-shape faces the radial direction of the secondary mirror support ring 11. The support beam 122 includes an upper support arm, a lower support arm, and a connecting beam, which is disposed between the upper support arm and the lower support arm.

[0042] Each first connector 121 is disposed between two support beams 122. The first connector 121 includes at least three first connector joints 123 in different directions, and a first connector interface 124 for connection with the primary lens assembly.

[0043] In this embodiment, the main mirror support frame 12 is an equilateral triangle-like structure. The total number of first connectors 121 is 9.

[0044] It should be noted that not all first connectors 121 are provided with first connection interfaces 124; only the first connectors 121 connected to the main mirror assembly are provided with first connection interfaces 124. The number and extension direction of the first connection joints 123 on each first connector 121 may be the same or different, depending on the number and extension direction of the trusses in the truss system 3 to be connected.

[0045] The bottom support frame 2 is a polygonal frame structure. In this embodiment, the bottom support frame 2 is a hexagonal frame structure, including six fifth truss rods 21 and six fourth connectors 22. Any two adjacent fifth truss rods 21 are connected by the fourth connectors 22.

[0046] Each fourth connector 22 is provided with at least five fourth connector joints 221 and one third connector interface 222. Two of the fourth connector joints 221 are used to connect two adjacent hexagonal fifth truss rods 21, and the remaining fourth connector joints 221 are connected to the first truss rod and the fourth truss rod, respectively. The third connector interfaces 222 are all used to secure satellites carrying space cameras.

[0047] In some embodiments, the number of fifth truss members 21 and fourth connectors 22 is six or more. Accordingly, the bottom support frame 2 is constructed as a polygon, such as an octagon, with the number of sides matching the aforementioned number.

[0048] The truss system 3 includes a first truss group 31, a second truss group 32, a third truss group 33, and a fourth truss group 34.

[0049] The secondary mirror support ring 11 is connected to the primary mirror support frame 12 via a second truss rod group 32. The primary mirror support frame 12 is internally connected to a third truss rod group 33.

[0050] The first truss rod group 31 is composed of multiple first truss rods. The first truss rods are respectively connected between the secondary mirror bearing ring 11 and the bottom support frame 2, the third truss rod group 33 and the fourth truss rod group 34. The external interface connection component 4 is connected between the third truss rod group 33 and the fourth truss rod group 34 through the first truss rods, and two adjacent first truss rods are arranged in a V-shape to ensure the overall rigidity of the truss structure.

[0051] In this invention, all truss rods connected between the bottom of the top support frame 1 and the top of the bottom support frame 2 are defined as the first truss rods.

[0052] The second truss rod group 32 is composed of multiple second truss rods. One end of each second truss rod is connected to the corresponding first connecting joint 123, and the other end of each second truss rod is welded to the corresponding first connecting point. Adjacent two second truss rods are arranged in a V-shape, so that the main mirror support frame 12 is stably connected to the secondary mirror bearing ring 11.

[0053] The third truss assembly 33 is connected to the interior of the main mirror support frame 12 via the first connecting joint 123. The third truss assembly 33 includes multiple third truss members and multiple second connectors 331. Each second connector has at least six second connecting joints in different directions. Any two adjacent second connectors 331 are connected by third truss members, and every three third truss members form a triangular structure.

[0054] Specifically, with each second connector 331 as the center point, the third truss rods are radially connected to the adjacent second connectors 331, thereby forming a triangular grid structure in the third truss rod group 33, thus ensuring the rigidity and geometric stability of the top support frame 1.

[0055] The fourth truss assembly 34 includes multiple fourth truss members and multiple third connectors 341. Each third connector 341 includes at least six third connecting joints 342 in different directions and a second connecting interface 343. The second connecting interface 343 is used for connecting to an accessory of a space camera. Any two adjacent third connectors 341 are connected by fourth truss members, and every three fourth truss members connected together form a triangular structure.

[0056] Specifically, with the third connector 341 as the center point, the fourth truss rod is radially connected to the adjacent third connector 341, thereby forming a triangular grid structure, which in turn ensures the rigidity and geometric stability of the bottom support frame 2.

[0057] In this embodiment, all connecting joints are thin-walled titanium alloy round tubes.

[0058] In this embodiment, the first, second, third, fourth, and fifth truss members 21 are all hollow, thin-walled titanium alloy tubes with an outer diameter to length ratio not exceeding 1:20. The wall thickness of the thin-walled titanium alloy tubes is 2.5 mm. Cross-shaped reinforcing ribs are provided inside the first, second, third, fourth, and fifth truss members 21.

[0059] The external interface connection assembly 4 includes at least one first interface connector 41 and at least two second interface connectors 42. Each first interface connector 41 is provided with a fifth connecting joint 411 and a fourth connecting interface 412. The fifth connecting joint 411 is used to connect to a corresponding first truss rod, and the fourth connecting interface 412 is used to connect to a space camera accessory. The first interface connector 41 is connected between the top support frame 1 and the bottom support frame 2 through the fifth connecting joint 411 and the first truss rod.

[0060] Each second interface connector 42 is connected to its corresponding truss rod at both ends. Each second interface connector 42 is provided with a fifth connection interface 421 for connecting to a space camera accessory.

[0061] In this embodiment, the first connecting joint 123, the second connecting joint 332, the third connecting joint 342, the fourth connecting joint 221, and the fifth connecting joint 411 are all hollow thin-walled titanium alloy round tubes with a wall thickness of 2.5 mm. If the joint length is large, a cross-shaped reinforcing rib is provided inside.

[0062] It should be noted that the present invention does not limit the structure of the first interface connector 41 and the second interface connector 42, and designs them into different structural forms according to the installation requirements of the space camera in order to adapt to the limited installation space.

[0063] The truss structure for a large-size space camera of the present invention has a diameter of not less than 3.6 meters and a height of not more than 1.5 meters. To ensure structural rigidity, the length of each truss member in the truss system 3 does not exceed 1.5 meters, and they are interconnected by connectors, thereby ensuring overall rigidity.

[0064] This invention achieves an ultra-large truss structure through the synergistic effect of the top-level support frame 1, the bottom-level support frame 2, the truss strut system 3, and the external interface connection assembly 4. The truss struts are reliably connected to the top-level support frame 1, the bottom-level support frame 2, and the external interface connection assembly 4 through connecting joints, thereby ensuring the strength of the entire truss structure.

[0065] The triangular mesh structure of the third truss group 33 and the fourth truss group 34 ensures the rigidity and geometric stability of the top support frame 1 and the bottom support frame 2.

[0066] By selecting thin-walled titanium alloy round tubes as the truss rod material, the overall mass of the truss structure is significantly reduced while its overall stiffness is effectively improved. This allows the weight of the truss structure to be kept within 20% of the total camera weight, making it lighter than a carbon fiber truss structure of the same size. Furthermore, the V-shaped arrangement of adjacent truss rods in truss rod system 3 primarily utilizes the stability principle of triangles to ensure the stability of the truss structure.

[0067] The truss structure of the present invention was analyzed using finite element analysis software. The results show that under full load conditions, the first-order fundamental frequency of the truss structure in the X, Y, and Z directions of the space camera coordinate system is greater than 40Hz. When a 10g overload is applied to each of the X, Y, and Z directions for strength analysis, the structural safety margin is greater than 4.2, indicating that it has extremely high load-bearing capacity and reliability.

[0068] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A truss structure for a large-format space camera, characterized by, The application relates to a support frame for a space camera, which comprises a top support frame, a bottom support frame, a truss rod system and an external interface connecting assembly; the top support frame and the bottom support frame are arranged in parallel and coaxially; the truss rod system comprises a first truss rod group, a second truss rod group, a third truss rod group and a fourth truss rod group; wherein the first truss rod group is connected between the bottom of the top support frame and the top of the bottom support frame; the external interface connecting assembly is located between the top support frame and the bottom support frame and is connected with the first truss rod group, and is used for connecting optical elements and focal plane assemblies at the back of a main mirror of the space camera; the top support frame comprises a secondary mirror force bearing ring and a main mirror support frame arranged in the secondary mirror force bearing ring, and the secondary mirror force bearing ring and the main mirror support frame are connected through the second truss rod group; the secondary mirror force bearing ring is used for being connected with a secondary mirror force bearing cylinder of the space camera; the main mirror support frame is used for being connected with a main mirror assembly of the space camera; the third truss rod group is arranged in the interior of the main mirror support frame and is connected with the main mirror support frame; the fourth truss rod group is arranged in the interior of the bottom support frame and is connected with the bottom support frame; the bottom support frame is a polygonal frame structure and is used for being connected with a satellite where the space camera is located; the secondary mirror force bearing ring comprises inner ring arms, outer ring arms and an intermediate cross beam between the inner ring arms and the outer ring arms; the cross section of the secondary mirror force bearing ring is in the shape of H, and the opening of the H shape is directed to the axial direction of the secondary mirror force bearing ring; the same number of first connecting points and second connecting points are uniformly distributed on the secondary mirror force bearing ring; the first connecting points are arranged on one side of the inner ring arms which is directed to the main mirror support frame; the second connecting points are arranged on the lower surface of the intermediate cross beam; each first connecting point and the corresponding second connecting point are located at the same circumferential position of the secondary mirror force bearing ring; the main mirror support frame comprises first connecting pieces and support beams which are used for forming a polygonal frame structure; three vertices of the polygonal frame structure which are uniformly distributed in the circumferential direction are all connected with the secondary mirror force bearing ring; the support beam comprises upper support arms, lower support arms and connecting beams which are arranged between the upper support arms and the lower support arms; the cross section of the support beam is in the shape of H, and the opening of the H shape is directed to the radial direction of the secondary mirror force bearing ring; the first connecting piece comprises at least three first connecting joints in different directions and a first connecting interface which is used for being connected with the secondary mirror force bearing cylinder of the space camera; the third truss rod group is connected in the interior of the main mirror support frame through the first connecting joints; one end of each second truss rod in the second truss rod group is connected with the corresponding first connecting joint, and the other end of each second truss rod is connected with the corresponding first connecting point; the third truss rod group comprises third truss rods and second connecting pieces which are used for forming a triangular grid structure; at least six second connecting joints in different directions for connecting the third truss rods are arranged on the second connecting pieces; any two adjacent second connecting pieces are connected through third truss rods, and every three third truss rods form a triangular structure. ​ ​ ​ ​ ​ ​ 2. The truss structure for a large-format space camera according to claim 1, characterized by, ​ ​ 3. The truss structure for a large-format space camera according to claim 2, characterized by, ​ 4. The truss structure for a large-format space camera according to claim 3, characterized by, ​ 5. The truss structure for a large-format space camera of claim 3, wherein, ​ 6. The truss structure for a large-format space camera according to claim 5, characterized by, ​ 7. The truss structure for a large-format space camera of claim 1, wherein, ​ 8. The truss structure for a large-format space camera of claim 1, wherein, The fourth truss rod set comprises fourth truss rods and third connecting members for forming a triangular grid structure; the third connecting members are provided with at least six third connecting joints in different directions for connecting the fourth truss rods and second connecting interfaces for connecting accessories of the space camera; Any two adjacent third connecting members are connected by fourth truss rods, and every three fourth truss rods form a triangular structure.

9. The truss structure for a large-format space camera of claim 1, wherein, The bottom support frame comprises fifth truss rods and fourth connecting members for forming a polygonal frame; any two adjacent fifth truss rods are connected by fourth connecting members; The fourth connecting members comprise at least five fourth connecting joints and a third connecting interface; the third connecting interface is used for connecting the satellite on which the space camera is located; and the fourth truss rod set is connected to the inside of the bottom support frame through the fourth connecting joints.

10. The truss structure for a large-format space camera of claim 1, wherein, The truss rods in the first truss rod set, the second truss rod set, the third truss rod set and the fourth truss rod set are all hollow thin-walled titanium alloy circular tubes, and the ratio of the outer diameter to the length is not greater than 1:

20.

11. The truss structure for a large-format space camera of claim 1, wherein, The external interface connecting assembly comprises at least one first interface connecting member and at least two second interface connecting members; each first interface connecting member is provided with a fifth connecting joint for connecting a corresponding truss rod and a fourth connecting interface for connecting accessories of the space camera; each second interface connecting member is connected to a corresponding truss rod at both ends; and each second interface connecting member is provided with a fifth connecting interface for connecting accessories of the space camera.

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