Truss structure for large-size space camera

Abstract

The invention relates to the technical field of space optical remote sensing, in particular to a truss structure for a large-size space camera, which comprises a top-layer support frame, a bottom-layer support frame, a truss rod system and an external interface connecting assembly, the top-layer supporting frame and the bottom-layer supporting frame are parallel and are coaxially arranged; 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; the first truss rod group is connected between the top-layer supporting frame and the bottom-layer supporting frame; the external interface connecting assembly is located between the top layer supporting frame and the bottom layer supporting frame. The top layer supporting frame comprises a secondary mirror bearing ring and a primary mirror supporting frame, and the secondary mirror bearing ring is connected with the primary mirror supporting frame through a second truss rod group; the third truss rod group is arranged in the primary mirror supporting frame; the fourth truss rod set is arranged in the bottom layer supporting frame. The oversized truss structure has the advantages that through collaborative design of the top-layer supporting frame, the bottom-layer supporting frame, the truss rod system and the external interface connecting assembly, the oversized 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: (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; (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; (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

[0004] 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.

[0005] To achieve the above object, the technical scheme of the present application is implemented as follows: a truss structure for a large-size space camera, comprising: a top layer support frame, a bottom layer support frame, a truss rod system and an external interface connection assembly; the top layer support frame and the bottom layer 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 layer support frame and the top of the bottom layer support frame; the external interface connection assembly is located between the top layer support frame and the bottom layer support frame and 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 layer support frame comprises a secondary mirror force bearing ring and a main mirror support frame arranged inside 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 inside the main mirror support frame and connected with the main mirror support frame; the fourth truss rod group is arranged inside the bottom layer support frame and connected with the bottom layer support frame; the bottom layer support frame is a polygonal frame structure and is used for being connected with a satellite on which the space camera is located.

[0006] Further, the secondary mirror force bearing ring comprises an inner ring arm, an outer ring arm and an intermediate cross beam between the inner ring arm and the outer ring arm; the cross section of the secondary mirror force bearing ring is in the shape of H, and the opening of the H shape faces the axial direction of the secondary mirror force bearing ring; the same number of first connection points and second connection points are uniformly distributed on the secondary mirror force bearing ring, the first connection points are arranged on one side of the inner ring arm facing the main mirror support frame; the second connection points are arranged on the lower surface of the intermediate cross beam; each first connection point and its corresponding second connection point are located at the same circumferential position of the secondary mirror force bearing ring.

[0007] Further, the main mirror support frame comprises first connecting pieces and support beams for constituting a polygonal frame structure, and 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.

[0008] Further, the support beam comprises an upper support arm, a lower support arm and a connecting beam arranged between the upper support arm and the lower support arm; the cross section of the support beam is in the shape of H, and the opening of the H shape faces the radial direction of the secondary mirror force bearing ring.

[0009] Further, the first connecting piece comprises at least three first connecting joints in different directions, and a first connecting interface for being connected with the secondary mirror force bearing cylinder of the space camera; the third truss rod group is connected inside the main mirror support frame through the first connecting joints.

[0010] Further, one end of each second truss rod in the second truss rod group is connected with a corresponding first connecting joint, and the other end of each second truss rod is connected with a corresponding first connection point.

[0011] Further, the third truss rod group comprises third truss rods and second connecting members for forming a triangular grid structure; the second connecting members are provided with at least six second connecting joints in different directions for connecting the third truss rods; any two adjacent second connecting members are connected by the third truss rods, and every three third truss rods form a triangular structure.

[0012] Further, the fourth truss rod group 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 the fourth truss rods, and every three fourth truss rods form a triangular structure.

[0013] Further, 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 the fourth connecting members; the fourth connecting members comprise at least five fourth connecting joints and one third connecting interface; the third connecting interface is used for connecting the satellite on which the space camera is located; the fourth truss rod group is connected to the inside of the bottom support frame through the fourth connecting joints.

[0014] Further, the truss rods in the first truss rod group, the second truss rod group, the third truss rod group and the fourth truss rod group are hollow thin-walled titanium alloy pipes, and the ratio of the outer diameter to the length is not greater than 1:20.

[0015] Further, 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 the corresponding truss rod and a fourth connecting interface for connecting the accessories of the space camera; each second interface connecting member is connected to the corresponding truss rod at both ends; and each second interface connecting member is provided with a fifth connecting interface for connecting the accessories of the space camera.

[0016] The application can achieve the following beneficial effects: 1) Through the collaborative design of the top support frame, the bottom support frame, the truss rod system and the external interface connecting assembly, a super-large-size truss structure is realized; the truss rods are reliably connected to the top support frame, the bottom support frame and the external interface connecting assembly through the connecting joints, thereby ensuring the strength of the entire truss structure.

[0017] 2) By selecting thin-walled titanium alloy round tube as the truss rod material, the overall truss structure stiffness is effectively improved while the overall truss structure mass is significantly reduced. The weight of the truss structure is controlled within 20% of the total weight of the camera, and the truss structure is lighter than the carbon fiber truss structure of the same size. Meanwhile, two adjacent truss rods in the truss rod system are arranged in a V shape, mainly using the stability principle of a triangle to ensure the stability of the truss structure.

[0018] 3) The finite element simulation analysis results show that the first-order fundamental frequency of the truss structure of the application in the X, Y and Z directions of the space camera coordinate system is greater than 40Hz, and the dynamic performance is excellent; the structural safety margin is greater than 4.2 when 10g overload is applied in the X, Y and Z directions respectively, and the truss structure has extremely high carrying capacity and reliability. BRIEF DESCRIPTION OF DRAWINGS

[0019] The drawings constituting a part of the present application provide a further understanding of the present application, and the illustrative embodiments of the present application and their descriptions serve to explain the present application, and do not constitute an improper limitation of the present application. In the drawings: Figure 1 is a structural schematic diagram of a first view of a truss structure for a large-size space camera according to an embodiment of the present application; Figure 2 is a structural schematic diagram of a second view of a truss structure for a large-size space camera according to an embodiment of the present application; Figure 3 is a structural schematic diagram of a third view of a truss structure for a large-size space camera according to an embodiment of the present application; Figure 4 is a structural schematic diagram of a primary mirror support frame according to an embodiment of the present application; Figure 5 is a structural schematic diagram of a third connecting piece according to an embodiment of the present application; Figure 6 is a structural schematic diagram of a first interface connecting piece according to an embodiment of the present application; Figure 7 is a structural schematic diagram of a second interface connecting piece according to an embodiment of the present application.

[0020] The reference signs include: 1, top layer support frame; 11, secondary mirror force bearing ring; 12, primary mirror support frame; 121, first connecting piece; 122, support beam; 123, first connecting joint; 124, first connecting interface; 2, bottom layer support frame; 21, fifth truss rod; 22, fourth connecting piece; 221, fourth connecting joint; 222, third connecting interface; 3, truss rod system; 31, first truss rod group; 32, second truss rod group; 33, third truss rod group; 331, second connecting piece; 332, second connecting joint; 34, fourth truss rod group; 341, third connecting piece; 342, third connecting joint; 343, second connecting interface; 4, external interface connecting assembly; 41, first interface connecting piece; 411, fifth connecting joint; 412, fourth connecting interface; 42, second interface connecting piece; 421, fifth connecting interface. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme and advantages of the present application clearer, the present application will be further described in detail below with reference to the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application, and do not constitute a limitation on the present application.

[0022] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0023] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" 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 therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second" and the like are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" and the like can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0024] 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.

[0025] The invention will now be described in detail with reference to specific embodiments.

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] The primary mirror support frame 12 is used to connect the primary mirror assembly, and the primary mirror support frame 12 comprises a plurality of first connecting pieces 121 and a plurality of support beams 122. The plurality of support beams 122 and the plurality of support beams 122 constitute a polygonal frame structure, and three vertices of the polygonal frame structure uniformly distributed in the circumferential direction are connected with the secondary mirror force bearing ring 11. The cross section of the support beam 122 is H-shaped, and the opening of the H-shaped is directed to the radial direction of the secondary mirror force bearing ring 11; the support beam 122 comprises an upper support arm, a lower support arm and a connecting beam, and the connecting beam is arranged between the upper support arm and the lower support arm.

[0031] Each first connecting piece 121 is arranged between two support beams 122. The first connecting piece 121 comprises at least three first connecting joints 123 in different directions, and a first connecting interface 124 for connecting with the primary mirror assembly.

[0032] In the embodiment, the primary mirror support frame 12 is an isosceles triangle structure. The total number of the first connecting pieces 121 is nine.

[0033] It should be noted that not all first connecting pieces 121 are provided with first connecting interfaces 124, only the first connecting pieces 121 connected with the primary mirror assembly are provided with first connecting interfaces 124. The number and extension direction of the first connecting joints 123 on each first connecting piece 121 can be the same or different, which is determined by the number and extension direction of the trusses in the truss bar system 3 to be connected.

[0034] The bottom support frame 2 is a polygonal frame structure. In the embodiment, the bottom support frame 2 is a hexagonal frame structure, comprising six fifth truss bars 21 and six fourth connecting pieces 22, and any two adjacent fifth truss bars 21 are connected by the fourth connecting piece 22.

[0035] Each fourth connecting piece 22 is provided with at least five fourth connecting joints 221 and a third connecting interface 222. Among them, two fourth connecting joints 221 are used to connect two fifth truss bars 21 adjacent to the hexagon, and the remaining fourth connecting joints 221 are connected with the first truss bar and the fourth truss bar respectively. The third connecting interface 222 is used to fix the satellite carrying the space camera.

[0036] In some embodiments, the number of fifth truss bars 21 and fourth connecting pieces 22 is more than six. Correspondingly, the bottom support frame 2 is constructed into a polygon with a number of sides adapted to the above number, for example, an octagon.

[0037] The truss bar system 3 comprises a first truss bar group 31, a second truss bar group 32, a third truss bar group 33 and a fourth truss bar group 34.

[0038] The second truss rod set 32 connects the secondary mirror force ring 11 and the primary mirror support frame 12.

[0039] The first truss rod set 31 is composed of a plurality of first truss rods. The first truss rods are respectively connected between the secondary mirror force ring 11 and the bottom layer support frame 2, the third truss rod set 33 and the fourth truss rod set 34. The external interface connection assembly 4 is connected between the third truss rod set 33 and the fourth truss rod set 34 through the first truss rods. Adjacent two first truss rods are arranged in a V shape to ensure the overall rigidity of the truss structure.

[0040] In the present application, all truss rods connected between the bottom of the top layer support frame 1 and the top of the bottom layer support frame 2 are defined as first truss rods.

[0041] The second truss rod set 32 is composed of a plurality of second truss rods. One end of each second truss rod is connected with a corresponding first connecting joint 123. The other end of each second truss rod is welded with a corresponding first connecting point. Adjacent two second truss rods are arranged in a V shape to stably connect the primary mirror support frame 12 in the secondary mirror force ring 11.

[0042] The third truss rod set 33 is connected to the inside of the primary mirror support frame 12 through the first connecting joint 123. The third truss rod set 33 includes a plurality of third truss rods and a plurality of second connecting pieces 331. The second connecting piece is provided with at least six second connecting joints in different directions. Any adjacent two second connecting pieces 331 are connected through third truss rods. Every three third truss rods are connected to form a triangular structure.

[0043] Specifically, taking each second connecting piece 331 as a center point, the third truss rods are connected to adjacent second connecting pieces 331 in a radial manner, so that the third truss rod set 33 forms a triangular grid structure, thereby ensuring the rigidity and geometric stability of the top layer support frame 1.

[0044] The fourth truss rod set 34 includes a plurality of fourth truss rods and a plurality of third connecting pieces 341. The third connecting piece 341 includes at least six third connecting joints 342 in different directions and a second connecting interface 343, and the second connecting interface 343 is used to connect with accessories of the space camera. Any adjacent two third connecting pieces 341 are connected through fourth truss rods. Every three fourth truss rods are connected to form a triangular structure.

[0045] Specifically, taking the third connecting piece 341 as a center point, the fourth truss rods are connected to adjacent third connecting pieces 341 in a radial manner, so as to form a triangular grid structure, thereby ensuring the rigidity and geometric stability of the bottom layer support frame 2.

[0046] In the present embodiment, all connecting joints are thin-walled titanium alloy pipes.

[0047] In the embodiment, the first truss rod, the second truss rod, the third truss rod, the fourth truss rod and the fifth truss rod 21 are all hollow thin-walled titanium alloy round pipes, and the ratio of the outer diameter to the length is not greater than 1:20. The wall thickness of the thin-walled titanium alloy round pipe is 2.5 mm. A cross-shaped reinforcing rib is arranged in the interior of the first truss rod, the second truss rod, the third truss rod, the fourth truss rod and the fifth truss rod 21.

[0048] The external interface connecting assembly 4 comprises at least one first interface connecting piece 41 and at least two second interface connecting pieces 42. The fifth connecting joint 411 for connecting the corresponding first truss rod and the fourth connecting interface 412 for connecting the space camera accessory are arranged on each first interface connecting piece 41. The first interface connecting piece 41 is connected between the top layer support frame 1 and the bottom layer support frame 2 through the fifth connecting joint 411, the first truss rod.

[0049] The two ends of each second interface connecting piece 42 are connected with the corresponding truss rod respectively. The fifth connecting interface 421 for connecting the space camera accessory is arranged on each second interface connecting piece 42.

[0050] In the 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 pipes, and the wall thickness of the thin-walled titanium alloy round pipe is 2.5 mm. If the length of the joint is large, a cross-shaped reinforcing rib is arranged in the interior.

[0051] It should be noted that the structure of the first interface connecting piece 41 and the second interface connecting piece 42 is not limited in the application, and different structure forms are designed according to the installation requirements of the space camera to adapt to the limited installation space.

[0052] The truss structure for large-size space cameras of the application has a diameter of not less than 3.6 meters and a height of not more than 1.5 meters. In order to ensure the structural rigidity, the length of each truss rod in the truss rod system 3 is not more than 1.5 meters, and the truss rods are connected with each other through the connecting pieces, so as to ensure the overall rigidity.

[0053] The truss structure for large-size space cameras of the application has a diameter of not less than 3.6 meters and a height of not more than 1.5 meters. In order to ensure the structural rigidity, the length of each truss rod in the truss rod system 3 is not more than 1.5 meters, and the truss rods are connected with each other through the connecting pieces, so as to ensure the overall rigidity.

[0054] The triangular grid structure of the third truss rod set 33 and the fourth truss rod set 34 ensures the rigidity and geometric stability of the top support frame 1 and the bottom support frame 2.

[0055] By selecting a thin-walled titanium alloy circular tube as the truss rod material, the overall truss structure mass is significantly reduced while the overall rigidity is effectively improved. The weight of the truss structure is controlled within 20% of the total weight of the camera, and the mass is lighter than that of a carbon fiber truss structure of the same size. At the same time, the two adjacent truss rods in the truss rod system 3 are arranged in a V shape, mainly using the stability principle of a triangle to ensure the stability of the truss structure.

[0056] Through finite element analysis software analysis of the truss structure of the present application, the results show that: under full load working condition, the first order fundamental frequency of the truss structure in X, Y, Z three directions of the space camera coordinate system are all greater than 40Hz; in X, Y, Z three directions respectively exert 10g overload to carry out strength analysis, the structure safety margin is all greater than 4.2, has extremely high carrying capacity and reliability.

[0057] The above specific embodiments do not constitute a limitation on the protection scope of the present application. 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 the present application shall be included in the protection scope of the present application.

Claims

1. A truss structure for a large-size space camera, characterized in that, include: The top-level support frame, the bottom-level support frame, the truss system, and the external interface connection components; 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 rod group is connected between the bottom of the top support frame and the top of the bottom support frame; the external interface connection assembly is located between the top support frame and the bottom support frame and is connected to the first truss rod group, and is used to connect the optical elements and focal plane assembly on the back of the main mirror of the space camera; The top-level support frame includes a secondary mirror support ring and a primary mirror support frame disposed inside the secondary mirror support ring. The secondary mirror support ring and the primary mirror support frame are connected by a second truss rod group. The secondary mirror support ring is used to connect with the secondary mirror support cylinder of the space camera. The primary mirror support frame is used to connect with the primary mirror assembly of the space camera. The third truss rod group is disposed inside the main mirror support frame and connected to the main mirror support frame; The fourth truss rod group is located inside the bottom support frame and connected to the bottom support frame; the bottom support frame is a polygonal frame structure used to connect to the satellite where the space camera is located.

2. The truss structure for a large-size space camera according to claim 1, characterized in that, The secondary mirror support ring includes an inner ring arm, an outer ring arm, and an intermediate crossbeam located between the inner ring arm and the outer ring arm; 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.

3. The truss structure for a large-size space camera according to claim 2, characterized in that, The primary mirror support frame includes a first connector and a support beam for forming 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 load-bearing ring.

4. The truss structure for a large-size space camera according to claim 3, characterized in that, The support beam includes an upper support arm, a lower support arm, and a connecting beam, with the connecting beam disposed between the upper support arm and the lower support arm; 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.

5. The truss structure for a large-size space camera according to claim 3, characterized in that, 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 cylinder 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.

6. The truss structure for a large-size space camera according to claim 5, characterized in that, In the second truss rod group, one end of each second truss rod is connected to the corresponding first connecting joint, and the other end of each second truss rod is connected to the corresponding first connecting point.

7. The truss structure for a large-size space camera according to claim 1, characterized in that, 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 connecting joints in different directions for connecting the third truss rod; any two adjacent second connectors are connected by the third truss rod, and every three third truss rods are connected to form a triangular structure.

8. The truss structure for a large-size space camera according to claim 1, characterized in that, 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 a fourth truss rod, and every three of the fourth truss rods form a triangular structure.

9. The truss structure for a large-size space camera according to claim 1, characterized in that, The bottom support frame includes a fifth truss rod and a fourth connector for forming a polygonal frame, and any two adjacent fifth truss rods are connected by the fourth connector; The fourth connector includes at least five fourth connectors and one third connector; the third connector is used to connect to the satellite where the space camera is located; the fourth truss assembly is connected to the interior of the bottom support frame through the fourth connectors.

10. The truss structure for a large-size space camera according to claim 1, characterized in that, 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.

11. The truss structure for a large-size space camera according to claim 1, characterized in that, 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 the corresponding truss rod; each second interface connector is provided with a fifth connection interface for connecting to a space camera accessory.

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