A plate and truss combined force transmission remote sensing satellite configuration

Abstract

The present application relates to commercial remote sensing satellite technical field, especially a kind of plate and truss combined force transmission remote sensing satellite configuration.It includes satellite structure, solar cell array structure, satellite structure includes docking ring, bottom plate, side plate, partition, three layers of plate, truss support bar system, CMG support bar system, support ring, three layers of plate includes CMG plate, camera mounting plate, top plate, bottom plate is connected in docking ring, support ring is installed in bottom plate, CMG support bar system is connected support ring and CMG plate respectively, truss support bar system is installed in CMG plate, truss support bar system is connected camera mounting plate and CMG plate respectively, three partitions are connected with bottom plate, support ring, truss support bar system, camera mounting plate respectively, six side plates are located in six faces around six prism, top plate is connected with the upper edge of six side plates, and solar cell array structure is installed on the outside of side plate connected with partition.This structure has small weight ratio, good openness, short production time, and can conveniently load and platform parallel combination installation.

Description

Technical Field

[0001] This invention relates to the field of commercial remote sensing satellite technology, and in particular to a remote sensing satellite configuration that combines plate and truss for force transmission. Background Technology

[0002] A satellite can be broadly divided into two parts: the payload and the satellite platform. Satellite configuration design generally includes either a separate payload-platform design (i.e., a payload bay and a platform bay) or an integrated payload-platform design. Each has its advantages and disadvantages. Separate designs are suitable for large satellites, allowing for parallel assembly and testing of the payload and platform bays, shortening the development cycle. For microsatellites, considering space requirements and control capabilities, an integrated design is often used. Regardless of the configuration approach, satellite structures are generally pure plate-type, plate-type with a load-bearing cylinder, or plate-type with a frame. For commercial satellites, if a load-bearing cylinder is used, the development cycle is limited, and under the constraints of the launch envelope, installing the CMG (Control Moment Gyroscope) inside the load-bearing cylinder presents challenges such as difficulty in heat pipe installation and CMG disassembly / reassembly. If a pure plate-type structure is used, due to the specific installation angle and quantity requirements of the CMG, the plate structure may have enclosed cavities, making disassembly and assembly inconvenient, and the force transmission path may be discontinuous, or there may be a mismatch between the CMG and the star sensor, or the number of sides in the overall configuration cross-section. Summary of the Invention

[0003] This invention provides a remote sensing satellite configuration that combines plate and truss structures for force transmission. It aims to provide a separate medium-to-large commercial remote sensing satellite configuration while ensuring low cost and short development cycle. The configuration combines plate and truss structures, which has good openness and low rotational inertia.

[0004] This invention provides a remote sensing satellite configuration combining plate and truss force transmission, including a hexahedral satellite structure and an unfolded solar array structure. The satellite structure includes a docking ring, a base plate, six side plates, three partitions, three layer plates, a truss support system, a CMG support system, and a support ring. The three layer plates, from bottom to top, are a CMG plate, a camera mounting plate, and a top plate. The base plate is connected to the upper surface of the docking ring, the support ring is mounted on the upper surface of the base plate, the CMG plate is located on the upper surface of the support ring, the CMG support system connects the support ring and the CMG plate, the truss support system is mounted on the CMG plate, and the upper and lower surfaces of the truss support system are connected to the camera mounting plate and the CMG plate, respectively. The three partitions are connected to the sides of the base plate, the support ring, the truss support system, and the camera mounting plate, respectively. The six side plates are located on the six faces around the hexagonal prism. The top plate is connected to the upper edge of the six side plates. The solar array structure is installed on the outer side of the side plates connected to the partitions.

[0005] As a further improvement of the present invention, the solar cell array structure includes a solar cell array substrate, an unfolding hinge, and a pressing device. The solar cell array substrate is connected to a base plate via the unfolding hinge. The pressing device includes a side plate pressing device and a substrate pressing device. The side plate pressing device is fixed on a side plate, and the substrate pressing device is fixed on the solar cell array substrate. When the solar cell array substrate is folded, the side plate pressing device and the substrate pressing device are docked and fixed.

[0006] As a further improvement of the present invention, the solar cell array structure includes a substrate support rod, the two ends of which are respectively connected to the back side and the side plate of the solar cell array substrate.

[0007] As a further improvement of the present invention, the remote sensing satellite configuration of the combined plate and truss force transmission also includes an on-board payload camera. The on-board payload camera is connected to a camera mounting plate. The on-board payload camera has three star sensors and one camera heat dissipation surface. The star sensors face the outside of the side plate that is not connected to the partition. The camera heat dissipation surface extends from between two of the star sensors and points to the outside of one of the side plates on which the partition is mounted.

[0008] As a further improvement of the present invention, the on-board payload camera also includes a star-sensor heat pipe and a star-sensor heat dissipation surface. The star-sensor heat dissipation surface is installed on the side plate and the top plate, and the star-sensor is connected to the star-sensor heat dissipation surface through the star-sensor heat pipe.

[0009] As a further improvement of the present invention, the remote sensing satellite configuration of the combined plate and truss force transmission also includes a CMG device and a CMG heat pipe. The CMG device is installed inside the truss support system and connected to the CMG plate. One end of the CMG heat pipe is connected to the CMG device, and the other end is connected to the partition or side plate.

[0010] As a further improvement of the present invention, the remote sensing satellite configuration of the combined plate and truss force transmission also includes a propulsion system. The propulsion system includes a tank and nozzles. The tank is installed inside the support ring and connected to the base plate. The tank includes multiple nozzles, which are respectively disposed on the base plate and the side plate. The pipeline between the tank and the nozzles is arranged along the base plate and the side plate.

[0011] As a further improvement of the present invention, the truss support system includes multiple longitudinal bars, multiple lower transverse bars, multiple upper transverse bars, and multiple joints. The multiple upper transverse bars are connected to each other through joints, and the multiple lower transverse bars are connected to each other through joints. The two ends of the longitudinal bars are respectively connected to the upper transverse bars and the lower transverse bars through joints, and the partition is connected to the longitudinal bars.

[0012] As a further improvement of the present invention, the CMG support rod system includes multiple rods and multiple joints. The multiple rods are evenly distributed along the Z-axis. The upper end of the rod is connected to the CMG mounting foot of the CMG plate through the joint, and the lower end of the rod is connected to a position near the bottom of the support ring through the joint.

[0013] As a further improvement of the present invention, the partition is connected to the support ring and the truss support rod system respectively by corner strips, and the multiple side plates are connected to each other by corner strips. The side plates not connected to the partition are detachably connected to the side plates connected to the partition.

[0014] The beneficial effects of this invention are:

[0015] (1) Under the combined influence of CMG installation requirements, star sensor installation orientation and solar cell array distribution, the present invention adopts a commonly used regular hexagonal columnar structure for the satellite shape, and integrates plate, truss and ring structure internally to form a satellite configuration with good openness. All mounting plates connected to the partition are not removed during the final assembly stage, and all equipment has the conditions to be disassembled and assembled at any time without damaging the structural accuracy.

[0016] (2) The truss support rod system used in this invention has a reserved CMG disassembly window, which eliminates the problem of strength reduction caused by opening the side of the load-bearing tube; the upper surface of the truss support rod system is in the same position as the camera mounting foot, and the CMG rod system is in the same position as the CMG mounting foot, which can ensure continuous and direct force transmission.

[0017] (3) Compared with the traditional configuration, the satellite structure of the present invention has a shorter production cycle, better satellite openness, and can support complex thermal control and heat dissipation designs, such as heat pipes and heat dissipation surfaces. At the same time, the coupling between the satellite structure and the camera is relatively low, allowing for parallel research and development. In addition, at the equipment layout level, heavier equipment is arranged around the center of mass to ensure a smaller moment of inertia.

[0018] (4) The plate and truss combined satellite configuration provided in this invention is installed from bottom to top and from inside to outside during the initial installation. The propulsion system and the structure are installed simultaneously. After installation, the side plates and top plate that are not connected to the bulkhead can be removed, while other plates do not need to be disassembled. When installing the camera, the top plate is removed first. After the camera is installed, the top plate does not need to be disassembled again. After the equipment is installed, the heat pipe, multilayer, heating element and other thermal control subsystem equipment are installed. Finally, the external equipment and solar cell array are installed. Attached Figure Description

[0019] Figure 1 This is a first structural schematic diagram of the satellite's on-orbit configuration in this invention;

[0020] Figure 2 This is a second structural schematic diagram of the satellite's on-orbit configuration in this invention;

[0021] Figure 3 This is a diagram illustrating the composition of the satellite structure in this invention;

[0022] Figure 4 This is a structural diagram of the truss support system and the CMG support system in this invention;

[0023] Figure 5 This is a schematic diagram of the heat pipe installation after the CMG equipment is installed in this invention. Detailed Implementation

[0024] 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 embodiments.

[0025] This invention proposes a configuration for a medium-to-large commercial remote sensing satellite platform. Considering the installation requirements of 5 CMGs, camera and star sensor installation requirements, and overall satellite heat conduction design, the traditional composite material load-bearing tube force transmission form is no longer applicable. Therefore, a main load-bearing structure combining plate and truss is proposed.

[0026] like Figures 1 to 3 As shown, a remote sensing satellite configuration combining plate and truss for force transmission includes a hexahedral satellite structure 1 and an unfolded solar array structure 2. The satellite structure 1 includes a docking ring 101, a base plate 102, six side plates 106-111, three partition plates 112-114, three layer plates, a truss support system 120, a CMG support system 150, and a support ring 115. The three layer plates, from bottom to top, are a CMG plate 103, a camera mounting plate 104, and a top plate 105. The docking ring 101 is located at the bottom of the satellite structure 1 and serves as the reference for the overall satellite installation and assembly. The base plate 102 is connected to the upper surface of the docking ring 101. The support ring 115 is installed on the upper surface of the base plate 102. The CMG plate 103 is located on the upper surface of the support ring 115. The CMG support system... 150 connects the support ring 115 to the CMG plate 103 respectively. The truss support rod system 120 is installed on the CMG plate 103. The upper and lower surfaces of the truss support rod system 120 are connected to the camera mounting plate 104 and the CMG plate 103 respectively. The three partitions 112~114 are distributed at 120°. The three partitions 112~114 are connected to the sides of the bottom plate 102, the support ring 115, the truss support rod system 120, and the camera mounting plate 104 respectively. The six side plates 106~111 are installed around the satellite structure 1. The six side plates 106~111 are located on the six faces around the hexagonal prism. The top plate 105 is connected to the upper edge of the six side plates 106~111. The solar cell array structure 2 is installed on the outer side of the side plates 107 / 109 / 111 connected to the partitions 112~114.

[0027] The solar array structure 2 includes solar array substrates 21-23, a unfolding hinge 24, and a clamping device. The solar array substrates 21-23 are hinged to the satellite structure 1 via the unfolding hinge 24. Specifically, the solar array substrates 21-23 are connected to the base plate 102 via the unfolding hinge 24. The clamping device includes a side plate clamping device 26 and a substrate clamping device 25. The side plate clamping device 26 is fixed to the side plates 107 / 109 / 111, and the substrate clamping device 25 is fixed to the solar array substrates 21-23. When the solar array substrates 21-23 are folded, the side plate clamping device 26 and the substrate clamping device 25 are mated and fixed. The solar array structure 2 includes three solar array substrates 21-23. The solar array substrates 21-23 are mounted on the base plate 102 by hinges. With the cooperation of the side plate clamping device 26 and the substrate clamping device 25, the solar array substrates 21-23 can be clamped in a single or double fold according to the area of ​​the array. After the satellite is successfully launched, the clamping device is unlocked and the solar array substrates 21-23 are unfolded into place.

[0028] The solar array structure 2 includes a substrate support rod 27, with its two ends connected to the back side of the solar array substrates 21-23 and the side plates 107 / 109 / 111, respectively. To ensure the overall rigidity after deployment, the solar array structure 2 has a substrate support rod 27 on the back side of the solar array substrates 21-23.

[0029] The remote sensing satellite configuration, which combines plate and truss structures for force transmission, also includes a thermal control assembly 3, onboard payloads and platform equipment 4, and piping and accessories 5. The satellite structure 1 houses all onboard equipment, including the propulsion system and piping, camera payload, platform equipment, and thermal control assembly 3. The onboard payloads and platform equipment 4 includes the onboard camera 41 and CMG equipment 43; the thermal control assembly 3 includes star-sensor heat pipes, star-sensor heat dissipation surfaces, and CMG heat pipes 44. The propulsion system includes a propellant tank 61 and corresponding piping.

[0030] like Figure 1 and Figure 2As shown, the on-board payload and platform equipment 4 includes an on-board payload camera 41, which is connected to a camera mounting plate 104. The on-board payload camera 41 has three star sensors 34 and one camera heat dissipation surface 42. The star sensors 34 face outwards from the side plates 106 / 108 / 110 that are not connected to the partitions 112-114. The camera heat dissipation surface 42 extends between two star sensors 34 and points outwards from the side plate 107 / 109 / 111 that mounts partitions 112-114. The on-board payload camera 41 is mounted on the camera mounting plate 104. During installation, the top plate 105 is removed first; after the on-board payload camera 41 is installed, the top plate 105 is not removed again. The onboard camera 41 is decoupled from the satellite structure 1. The onboard camera 41 carries three star sensors 34 distributed at 120° and a camera heat dissipation surface 42. The camera heat dissipation surface 42 is parallel to the side plate 111, and the side plate 111 has an opening at the position corresponding to the camera heat dissipation surface 42. The three star sensors 34 are located on the side of the side plates 106 / 108 / 110 respectively. To ensure the field of view of the star sensors 34, the side plates 106 / 108 / 110 are provided with openings at the corresponding positions. The star sensors 34 face the outside of the side plates 106 / 108 / 110, which are at a 60° angle to the partition plates 112~114.

[0031] The onboard camera 41 also includes a star-sensor heat pipe and star-sensor heat dissipation surfaces 31-33. Star-sensor heat dissipation surfaces 31-33 are mounted on the side plates 107 / 109 / 111 and the top plate 105. The star sensor is connected to the star-sensor heat dissipation surfaces 31-33 via the star-sensor heat pipe. After the star sensor 34 is installed, to meet temperature requirements, the star sensor bracket is connected to one end of the star-sensor heat pipe's connection hole, and the other end of the star-sensor heat pipe's connection hole is located on the heat dissipation plate mounted on the side plates 107 / 109 / 111 or the top plate 105.

[0032] Each of the three star sensors 34 has a star sensor heat pipe. The bracket of each star sensor 34 is equipped with a connection point for one end of the heat pipe. The other end of two of the star sensor heat pipes is connected to the star sensor heat dissipation surfaces 31 and 32 located on the side plate 111, and the other end of the third star sensor heat pipe is connected to the star sensor heat dissipation surface 33 located on the top plate 105. Since the star sensors 34 point outward, the corresponding star sensor heat pipes are connected outside the cabin. The bending of the star sensor heat pipes is determined according to the actual connection position and the space outside the cabin.

[0033] like Figure 5As shown, the onboard payload and platform equipment 4 also includes a CMG device 43 and a CMG heat pipe 44. The CMG device 43 is installed inside the truss support system 120 and connected to the CMG plate 103. One end of the CMG heat pipe 44 is connected to the CMG device 43, and the other end is connected to the partition plate 112~114 or the side plate 107 / 109 / 111. After the CMG device 43 is installed, in order to meet the temperature requirements, the CMG device 43 is connected to the side of the CMG heat pipe 44, and the other end of the CMG heat pipe 44 is fixed to the partition plate 112~114 or the side plate 107 / 109 / 111.

[0034] The upper and lower support points of the truss support system 120 are located at the flange of the support ring 115 and the camera mounting point, respectively. Considering the satellite's zero-momentum control requirements in orbit and minimizing rotational inertia, the five CMG devices 43 are installed inside the truss support system 120 and connected to the CMG plate 103. The CMG devices 43 are evenly distributed along the satellite's Z-axis, and the five CMG low-speed axes form the same angle with the XOY plane. The angle between the CMG low-speed axes and the satellite's ground is 55°, and the projection of one of them on the XOY plane passes through the satellite's X-axis. The CMG devices 43 are installed in the space structure enclosed by the truss support system 120, with the mounting points located on the CMG plate 103. To ensure that the CMG devices 43 can be easily removed after installation, two transverse bars of the truss support system 120 are detachable, while the other bars are glued together as a whole structure during the manufacturing stage. Five CMG devices 43 have pre-drilled connection holes for CMG heat pipes 44 on their sides. One end of the CMG heat pipe 44 is connected to the CMG device 43 through the hole on the side of the CMG device 43, and the other end of the CMG heat pipe 44 is connected to the corresponding partition 112~114 or side plate 107 / 109 / 111. The corresponding CMG heat pipe is three-dimensionally bent according to the internal space of the satellite and the location of the connection point. The CMG heat pipe 44 can be disassembled at any time during the final assembly process.

[0035] The remote sensing satellite configuration that combines plate and truss for force transmission also includes a propulsion system. The propulsion system includes a tank 61 and a nozzle 62. The tank 61 is installed inside the support ring 115 and connected to the base plate 102. The nozzles 62 are respectively set on the base plate 102 and the side plates 107 / 109 / 111. The pipeline between the tank 61 and the nozzle 62 is set along the base plate 102 and the side plates 107 / 109 / 111.

[0036] The propulsion system tank 61 is installed inside the support ring 115 and connected to the base plate 102. To minimize the impact of fuel consumption on the satellite's lateral center of mass, the tank 61 is installed as symmetrically as possible. The propulsion system includes eight nozzles 62. Six of them are located on the outer surface of the base plate 102 at different angles, and the other two nozzles 62 are located at the height of the Z-axis center of mass and are installed on the side plates 107 / 111. The pipeline between the tank 61 and the nozzles 62 is set along the base plate 102 and the side plates 107 / 111. The side plates 107 / 111 in the direction corresponding to the nozzles 62 have reserved opening positions for the nozzles 62.

[0037] The support ring 115 adopts a cylindrical support ring 115 structure. The support ring 115 uses metal material with optimized design. In order to meet the longitudinal stiffness, reinforcing ribs can be added around the support ring 115. The propulsion system tank 61 is installed inside the cylindrical support ring 115.

[0038] like Figure 4 As shown, the truss support system 120 includes multiple longitudinal members 121-130, multiple lower transverse members 131-139, multiple upper transverse members 140-145, and multiple joints. The multiple upper transverse members 140-145 are connected to each other through joints, and the multiple lower transverse members 131-139 are connected to each other through joints. The two ends of the longitudinal members 121-130 are respectively connected to the upper transverse members 140-145 and the lower transverse members 131-139 through joints. The partition plates 112-114 are connected to the longitudinal members 121-130.

[0039] Specifically, the truss support system 120 includes longitudinal members 121-130, lower transverse members 131-139, upper transverse members 140-145, and several joints. Among them, joints 146-148 are located at the same position as the camera mounting feet. Special embedded parts are set for the camera mounting plate 104 at this location. This connection method transmits force more directly and effectively. Specifically, the lower transverse members 131 / 135 can be removed to facilitate the disassembly of the CMG equipment 43 from the space enclosed by the truss support system 120 during the final assembly process. Other members and joints are bonded with structural adhesive. The longitudinal members 123 / 126 / 129 are connected to the partitions 112-114.

[0040] The CMG support rod system 150 includes multiple rods 151-155 and multiple connectors. The rods 151-155 are evenly distributed along the Z-axis. The upper ends of the rods 151-155 are connected to the CMG mounting feet of the CMG plate 103 via connectors, and the lower ends of the rods 151-155 are connected to a position near the bottom of the support ring 115 via connectors. Specifically, the CMG support rod system 150, comprising five rods 151-155 and ten connectors, is installed between the CMG plate 103 and the support ring 115. Five connectors connecting to the CMG plate 103 are located at the CMG mounting feet, with the rods 151-155 evenly distributed along the Z-axis. The other five connectors are connected to the side wall of the support ring 115, with the lower connector as close as possible to the bottom of the cylindrical support ring 115. The specific inclination angle must fully consider the volume and position of the storage tank 61 inside the cylindrical support ring 115.

[0041] The truss support rod system 120 and CMG support rod system 150 rods and joints can be formed by metal materials or carbon fiber composite material lay-up. The entire star's structural plates, namely the bottom plate 102, partitions 112~114, side plates 106~111, top plate 105, CMG plate 103, and camera mounting plate 104, are aluminum skin honeycomb panels.

[0042] Partitions 112-114 are connected to the side of support ring 115 and truss support rod system 120 via corner strips. Multiple side plates 106-111 are connected to each other via corner strips. Side plates 106 / 108 / 110 not connected to partitions 112-114 are detachably connected to side plates 107 / 109 / 111 connected to partitions 112-114. Support ring 115 is machined from metal ring material. To ensure local strength and longitudinal stiffness, reinforcing strips are evenly distributed on the side wall of metal support ring 115. At the same time, special reinforcement designs are made at three locations: support ring 115, partitions 112-114, and the connection with bottom plate 102. Specifically, special embedded parts are designed in the connection area between bottom plate 102 and partitions 112-114. In particular, the cylindrical support ring 115 is connected to partitions 112-114 via corner strips.

[0043] During final assembly, side panels 106 / 108 / 110 are detachable, while the other three side panels 107 / 109 / 111 are not. During satellite configuration development, because the satellite payload camera is decoupled from the satellite platform, it can be developed in parallel. After the satellite payload camera is delivered and installed, the top panel 105 will not be removed, and ultimately only the side panels 106 / 108 / 110 will be openable.

[0044] The platform equipment of the entire satellite includes various subsystem equipment. The equipment is mainly installed inside the cabin and distributed on the base plate 102 and the side plates 107 / 109 / 111 with better heat dissipation. Since the side plates 106 / 108 / 110 are open and close plates during the final assembly and are in a disassembly state, no equipment is installed on the side plates 106 / 108 / 110, which ensures that the satellite equipment has good openness and operability. Antenna equipment is installed on the outside of the base plate 102 facing the sky or the top plate 105 facing the ground. The nozzle 62 of the propulsion system tank 61 in the pipeline and accessories 5 is installed on the base plate 102 or the side plates 107 / 109 / 111, and the nozzle 62 is connected to the tank 61 by the pipeline set along the base plate 102 and the side plates 107 / 109 / 111.

[0045] The remote sensing satellite structure of this invention has a small weight ratio, good openness, short production time, and can facilitate the parallel development of the payload and platform, which can then be assembled and installed.

[0046] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

Claims

1. A remote sensing satellite configuration combining plate and truss for force transmission, characterized in that, The satellite structure includes a hexahedral satellite structure and a deployable solar array structure. The satellite structure includes a docking ring, a base plate, six side plates, three partitions, three layer plates, a truss support system, a CMG support system, and a support ring. The three layer plates, from bottom to top, are a CMG plate, a camera mounting plate, and a top plate. The base plate is connected to the upper surface of the docking ring, the support ring is mounted on the upper surface of the base plate, the CMG plate is located on the upper surface of the support ring, the CMG support system connects the support ring and the CMG plate, the truss support system is mounted on the CMG plate, and the upper and lower surfaces of the truss support system are connected to the camera mounting plate and the CMG plate, respectively. The three partitions are connected to the sides of the base plate, the support ring, the truss support system, and the camera mounting plate, respectively. The six side plates are located on the six faces around the hexagonal prism. The top plate is connected to the upper edge of the six side plates. The solar array structure is installed on the outer side of the side plates connected to the partitions. It also includes CMG equipment and CMG heat pipes. The CMG equipment is installed inside the truss support system and connected to the CMG plate. One end of the CMG heat pipe is connected to the CMG equipment, and the other end is connected to the partition or side plate. The truss support system has two detachable transverse bars, and the other bars are glued together as a whole structure during the manufacturing stage.

2. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, The solar array structure includes a solar array substrate, an unfolding hinge, and a clamping device. The solar array substrate is connected to a base plate via the unfolding hinge. The clamping device includes a side plate clamping device and a substrate clamping device. The side plate clamping device is fixed to a side plate, and the substrate clamping device is fixed to the solar array substrate. When the solar array substrate is folded, the side plate clamping device and the substrate clamping device are docked and fixed.

3. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 2, characterized in that, The solar cell array structure includes a substrate support rod, with its two ends connected to the back and side plates of the solar cell array substrate, respectively.

4. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, It also includes an on-board payload camera, which is connected to a camera mounting plate. The on-board payload camera has three star sensors and one camera heat dissipation surface. The star sensors face the outside of a side plate that is not connected to a partition. The camera heat dissipation surface extends from between two of the star sensors and points to the outside of one of the side plates on which the partition is mounted.

5. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 4, characterized in that, The on-board camera also includes a star-sensor heat pipe and a star-sensor heat dissipation surface. The star-sensor heat dissipation surface is installed on the side plate and the top plate, and the star-sensor is connected to the star-sensor heat dissipation surface through the star-sensor heat pipe.

6. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, It also includes a propulsion system, which includes a tank and nozzles. The tank is installed inside the support ring and connected to the base plate. The tank includes multiple nozzles, which are respectively disposed on the base plate and the side plate. The pipeline between the tank and the nozzles is arranged along the base plate and the side plate.

7. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, The truss support system includes multiple longitudinal members, multiple lower transverse members, multiple upper transverse members, and multiple joints. The multiple upper transverse members are connected to each other through joints, and the multiple lower transverse members are connected to each other through joints. The two ends of the longitudinal members are respectively connected to the upper transverse members and the lower transverse members through joints. The partition is connected to the longitudinal members.

8. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, The CMG support rod system includes multiple rods and multiple connectors. The multiple rods are evenly distributed along the Z-axis. The upper end of each rod is connected to the CMG mounting foot of the CMG plate through a connector, and the lower end of each rod is connected to a position near the bottom of the support ring through a connector.

9. The remote sensing satellite configuration for combined plate and truss force transmission according to claim 1, characterized in that, The partition is connected to the support ring and the truss support rod system respectively by corner strips. The multiple side plates are connected to each other by corner strips. The side plates not connected to the partition are detachably connected to the side plates connected to the partition.

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