A remote sensing satellite configuration for in-motion imaging

Abstract

The application relates to a remote sensing satellite configuration for in-flight imaging, and belongs to the technical field of spacecraft design. The application comprises a propulsion cabin, an equipment cabin and an antenna solar wing integrated support structure, which are sequentially connected from bottom to top. The application is composed of a high-load light-weight propulsion cabin, a variable cross-section machine-heat integrated plate type equipment cabin, an expandable fixed solar cell array and a multi-stage collaborative control product layout, so that the collaborative design of high rigidity, force, heat, stability and precision of the high-resolution attitude agile remote sensing satellite is realized.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft design technology and relates to a remote sensing satellite configuration for in-motion imaging. Background Technology

[0002] With the development of optical remote sensing technology, payload resolution, size, and weight are increasing daily, and the operating mode is shifting from traditional fixed-point static imaging to dynamic, high-resolution imaging. This has significantly increased the demands on satellite platforms in terms of agility, energy carrying capacity, and stiffness. Furthermore, to achieve rapid attitude response and high-precision steady-state imaging, control products such as high-torque CMG (Control Moment Gyroscope) clusters and high-load-bearing ultra-precise, ultra-stable, and ultra-agile platforms (referred to as "three-super" platforms) are beginning to be applied to remote sensing satellites. The substantial improvement in satellite performance and the introduction of new products have placed higher demands on the mechanical, thermal, and stability performance of satellite platforms.

[0003] Traditional satellite configurations include China's Resource series satellite platforms and the US Loral's LS satellite platform. The 1300 satellite platform and others often employ a slender central load-bearing cylinder + plate structure + rotating solar array configuration. Due to limitations in overall satellite and solar array stiffness, as well as satellite control modes, high-resolution satellites suffer from low overall stiffness due to high payload altitude and large solar array size, making it impossible to meet the requirements of attitude response and in-motion high-resolution imaging modes. Even with large-scale fixed solar arrays, there are still issues with solar elevation angle compensation and support structure design. Furthermore, with the increasing power consumption of satellite payloads and the higher requirements for platform thermal stability, the traditional design relying on the outer assembly plate for heat dissipation results in a large number of devices being installed on the outer plate, which brings difficulties to assembly operations and tooling design, and urgently requires a configuration design with an expandable heat dissipation surface.

[0004] A prior art search revealed that the invention patent number CN 201910750005.9, entitled "Agile Satellite Configuration," utilizes an external support cylinder, an eight-link pointing mechanism, and a body-mounted solar array to form a satellite configuration capable of orbital maneuvers and payload pointing maneuvers with a large overall fuel load. While the external support cylinder increases propellant carrying capacity, its complex tank support structure and underutilized space above the tank, coupled with the limited space on the surface of the service module for mounting solar panels, restrict overall satellite energy carrying capacity, platform thermal stability, and surface layout space, ultimately failing to meet the attitude response and stable imaging design requirements of high-resolution remote sensing satellites. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a remote sensing satellite configuration for in-motion imaging. Through a high-rigidity, high-stability, and high-precision satellite configuration consisting of a high-load-bearing lightweight propulsion cabin, a variable cross-section integrated mechanical and thermal plate equipment cabin, a deployable fixed solar cell array, and a multi-level collaborative control product layout, a collaborative design of high rigidity, force, heat, stability, and precision for high-resolution attitude-agile remote sensing satellites is achieved.

[0006] The solution of the present invention is: a remote sensing satellite configuration for in-motion imaging, comprising: a propulsion module, an equipment module, and an integrated support structure for the antenna solar array, which are connected sequentially from bottom to top; The propulsion module includes a load-bearing cylinder and a tank support structure; the outer wall of the load-bearing cylinder is provided with a solar panel mounting interface; the tank support structure is fixed to the lower flange inside the load-bearing cylinder to support the configured tank; the portions of the upper and lower surfaces of the tank that protrude from the propulsion module are respectively sunk into the upper equipment compartment and the lower space shared by the spacecraft and rocket. The equipment compartment is a variable cross-section box structure, with the top cross-section being larger than the bottom cross-section. The bottom is connected to the top of the load-bearing cylinder and also bears the high-torque CMG group for attitude maneuvering. The top carries the "three-super" platform for vibration isolation and load steady-state imaging during satellite attitude maneuvering. An integrated support structure for the antenna solar array is used to support the solar array and the data transmission antenna.

[0007] Furthermore, the tank support structure includes: a fan-shaped tank bracket, a support partition, and two small crescent-shaped base plates; The fan-shaped tank support, together with two small crescent-shaped base plates, forms a circular structure that matches the inner diameter of the load-bearing cylinder, used for tank support and installation of thermal control components; the circular structure is installed on the lower flange inside the load-bearing cylinder. Supporting partitions are fixed to the sector-shaped storage tank bracket, dividing the sector-shaped storage tank bracket into several areas, each area allowing a storage tank to pass through and be fixed.

[0008] Furthermore, the aforementioned fan-shaped storage tank support has an elongated oval structure, and its outer contour includes: two parallel straight sides and symmetrical arc-shaped sides; The outer contour of the crescent-shaped base plate includes: an arc segment and a straight line segment; The arc-shaped edge of the fan-shaped storage tank support matches and connects with the inner wall of the load-bearing cylinder; the two straight edges match and connect with the straight segments of the two small crescent-shaped base plates respectively. The crescent-shaped bottom plate arc segment matches and connects with the inner wall of the load-bearing cylinder.

[0009] Furthermore, the supporting partition has an I-shaped structure, including two flanges and a web connecting the two flanges. The bottom ends of the two flange plates correspond one-to-one with the two straight edges of the fan-shaped storage tank support and are vertically connected; the two side wall ends of each flange plate are connected to the inner wall of the load-bearing cylinder; the bottom end of the web plate is vertically connected to the fan-shaped storage tank support.

[0010] Furthermore, the equipment compartment includes: a top plate, a bottom plate, and several outer plates; The top and bottom slabs are installed in parallel. The top of each outer panel is connected to the lower surface of the top panel, and the bottom is connected to the bottom panel; the side ends of several outer panels are connected one after another along the circumference to form a closed box structure side wall.

[0011] Furthermore, the box structure has an internal support plate; the bottom end of the support plate is connected to the bottom plate, and the top end is connected to the top plate. The support plate includes several long partitions and several short partitions; the long partitions are arranged in parallel at intervals, and the short partitions are arranged in parallel at intervals. Each long partition runs through all the short partitions along its own length and is perpendicularly connected at the intersection. All the long partitions and short partitions intersect to form a matrix grid structure, which supports the top plate to achieve multi-point support for the load and the integrated layout of electronic equipment.

[0012] Furthermore, both the long and short partitions extend from the inside to the outside along the radial direction of the box structure, with the top of the extended portion connected to the lower surface of the top plate to support the top plate.

[0013] Furthermore, the protruding portion is surface-mounted with an optical solar reflector (OSR) and has embedded heat pipes to provide additional heat dissipation surface for the electronic equipment inside the cabin.

[0014] Furthermore, the bottom plate has through holes at positions corresponding to the protruding propulsion compartment portion on the upper surface of the tank, for use in the assembly and operation of equipment inside the compartment and to avoid the protruding portion on the upper surface of the tank.

[0015] Furthermore, the integrated support structure for the antenna solar array includes: two symmetrically arranged side compartments and two parallel and spaced connecting outer plates; the four components together form a closed support structure.

[0016] Furthermore, a data transmission antenna is installed on the top surface of the side cabin, and the outer wall provides a clamping seat for the solar array, which is used to clamp and fix it to the end of the support rod of the solar array.

[0017] The advantages of this invention compared to the prior art are: (1) The propulsion module of this invention, through the dual-tank configuration and the method of sinking its protruding part into the space of the adjacent module, reduces the height of the load-bearing cylinder based on the external load-bearing cylinder design, thereby effectively reducing the overall center of mass height of the satellite while ensuring an increase in propellant loading. Compared with the traditional slender load-bearing cylinder satellite platform, this configuration significantly improves the overall rigidity of the satellite and the load installation conditions, and can better meet the load-bearing requirements of medium-sized optical, SAR and other payloads; (2) The present invention achieves the transition of the propulsion compartment cross section from round to square and from small to large size by using the variable cross section support plate structure layout of the equipment compartment to improve space utilization. The exposed size of the main support bulkhead of the lower compartment serves as the heat dissipation surface of the bulkhead equipment, realizing the integrated mechanical and thermal steady-state design. (3) The present invention supports flexible adaptation and structural reuse. The satellite equipment cabin adopts a variable cross-section box structure design. The cross-sectional size and height can be flexibly adjusted according to the load-bearing requirements of medium-sized remote sensing satellite payloads. The load-bearing capacity of the propulsion cabin and the connection method between the cabin plates remain unchanged, which facilitates satellite technical status control and mass production. (4) The present invention installs the antenna on the upper part of the solar wing support structure and is not limited by the size of the solar wing, making full use of the available space inside the fairing and maximizing the space utilization rate; (5) This invention breaks through the contradiction between "high rigidity" and "high energy" and "high agility" and "high stability" in traditional satellites by using a collaborative layout design of deployable fixed solar array + high rigidity integrated platform structure + high agility CMG group + high stability "three super" platform. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of a satellite launch configuration provided in an embodiment of the present invention; Figure 2 This is an exploded view of the satellite launch configuration provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of satellite flight provided for an embodiment of the present invention; Figure 4 This is an exploded view of the equipment compartment structure provided in an embodiment of the present invention; Figure 5 This is an exploded view of the propulsion module structure provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of an integrated support structure for the antenna solar array provided in an embodiment of the present invention. Detailed Implementation

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Taking a hyperspectral remote sensing satellite configuration with active backscan capability as an example, such as Figure 1 and Figure 2As shown, the satellite configuration includes: a propulsion module 1, an equipment module 2, and an integrated antenna solar array support structure 3; the integrated antenna solar array support structure 3 and a payload 4 are mounted on the upper part of the equipment module 2, and high-rigidity solar arrays 5 are installed on the left and right sides of the propulsion module 1, equipment module 2, and integrated antenna solar array support structure 3. The payload 4 is an optical payload weighing approximately 1.5 tons.

[0021] The high-rigidity propulsion module 1, located at the bottom of the satellite, provides stable support for the satellite platform and a high-rigidity satellite-rocket interface; the first-order fundamental frequency of the entire satellite is ≥10Hz.

[0022] The variable cross-section, integrated mechanical and thermal plate-type equipment compartment 2 is used to achieve high integration of platform equipment and coordinated mechanical and thermal stability design. The integrated support structure 3 for the antenna solar array is used to support the high-rigidity large solar cell array, which improves the rigidity of the solar array, antenna transmission and on-orbit section while ensuring power supply.

[0023] This multi-level collaborative control product consists of a high-torque CMG group 201 and a high-load-bearing "three-super" platform 6. The high-torque CMG group 201 is used to achieve large-angle, high-acceleration attitude maneuvers, while the "three-super" platform 6 is used to achieve vibration isolation and payload steady-state imaging during satellite attitude maneuvers. The attitude stability is better than 1x10. -4 .

[0024] The bottom plate 2-2 and top plate 2-1 of Equipment Module 2 are respectively equipped with a multi-level collaborative control product consisting of a high-torque CMG group 201 and a "three-super" platform 6. Among them, the high-torque CMG group 201 is installed on the bottom plate 2-2 of Equipment Module 2, which is located on the large-section, high-rigidity propulsion module. In addition to being used for active back-scan imaging and other modes, it can also adjust the solar angle of the satellite body to ensure that the fixed, high-rigidity solar array 5 is always at the optimal illumination angle. The "three-super" platform 6 is installed between the variable cross-section, multi-point supported top plate 2-1 of Equipment Module 2 and the payload 4 to meet the on-orbit steady-state imaging requirements of the payload 4.

[0025] The propulsion compartment 1 includes a large-diameter (≥2m) load-bearing cylinder 1-1 and a tank support structure 1-2. A flange is installed at the bottom of the large-diameter load-bearing cylinder 1-1, through which the tank support structure 1-2 is supported and fixed inside the load-bearing cylinder 1-1. The load-bearing cylinder 1-1 adopts an outer load-bearing cylinder with a small length-to-diameter ratio ≤ 0.5; the outer surface of the load-bearing cylinder 1-1 is provided with a first mounting interface 106 and a second mounting interface 107 for the solar array 5 and the antenna. The load-bearing cylinder 1-1 is the transport docking surface, and its upper end is connected to the bottom plate 2-5 of the equipment compartment 2.

[0026] like Figure 4 As shown, the tank support structure 1-2 includes a fan-shaped tank bracket 101, a support partition 102, and two small crescent-shaped bottom plates 105; Two small crescent-shaped base plates 105 are symmetrically arranged on both sides of the sector-shaped storage tank support 101. The arc section of the small crescent-shaped base plate 105 matches and connects with the lower surface of the flange on the inner wall of the support cylinder 1-1, and the straight section matches and connects with the sector-shaped storage tank support 101. The sector-shaped storage tank support 101 and the two small crescent-shaped base plates 105 together form a circular structure that matches the inner diameter of the support cylinder 1-1, enclosing the interior of the support cylinder 1-1 for the support of the storage tank 103 and the installation of the thermal control components.

[0027] The support partition 102 is fixed on the sector-shaped storage tank bracket 101, dividing the sector-shaped storage tank bracket 101 into two areas, each of which is used for a storage tank 103 to pass through and be fixed.

[0028] The supporting partition 102 has an I-shaped structure, including two flanges and a web connecting the two flanges; the fan-shaped storage tank support 101 has an elongated oval structure, and the structural outline includes two parallel straight sides and symmetrical arc-shaped sides, with the two ends of the straight sides smoothly connected to the arc-shaped sides to form a closed outline. The bottom ends of the two flange plates correspond to and are perpendicularly connected to the two straight edges of the fan-shaped storage tank support 101; the two side wall ends of each flange plate are connected to the inner wall of the load-bearing cylinder 1-1; the bottom end of the web plate is perpendicularly connected to the fan-shaped storage tank support 101.

[0029] The arc-shaped edge of the fan-shaped storage tank bracket 101 is installed on the inner surface of the lower flange of the load-bearing cylinder 1-1, and its two straight edges are connected to the outer surface of the lower flange of the load-bearing cylinder 1-1 through two small crescent-shaped base plates 105.

[0030] The protruding parts on the upper and lower surfaces of the storage tank 103 correspond to the upper equipment compartment 2 and the lower space shared by the satellite and rocket, respectively. Special thermal control measures are adopted in orbit to ensure that sufficient installation space is provided for the storage tank 103. The storage tank 103 is installed on the storage tank bracket 101, and the storage tank thermal control cover 104 is installed on the exposed part of the storage tank 103 on the back of the storage tank bracket 101.

[0031] Equipment compartment 2 is a partially protruding variable cross-section box structure. The box structure includes: top plate 2-1, bottom plate 2-2, long partition 2-3, short partition 2-4, and outer plate 2-5. The length of the long partition 2-3 is greater than the length of the short partition 2-4; The top plate 2-1 mounts the satellite payload 4 and the "three-super" platform 6. The bottom plate 2-2 connects to the propulsion module 1. The cross-section of the bottom plate 2-2 is smaller than that of the top plate 2-1, achieving a "square-to-round" transition with the propulsion module's load-bearing cylinder 1-1. These components respectively match the installation space of the upper surface and top of the propulsion module 1 for the "three-super" platform 6 and payload 4. like Figure 5As shown, the base plate 2-2 has a rectangular-like structure. The overall shape of the rectangular-like structure is rectangular, with two parallel straight sides and two symmetrically arranged wide sides. Each wide side has a protruding section at the center, matching the flange on the load-bearing cylinder 1-1. The two ends of the protruding sections smoothly connect to the two long sides. The eight outer plates 2-5 are connected end-to-end along the circumference of the base plate 2-2, forming a closed cavity structure. The top of the cavity structure connects to the lower surface of the top plate 2-1, and the bottom connects to the edge contour of the outer plates 2-5, providing high-precision and stable installation support for the load 4.

[0032] Five bulkheads and eight outer plates 2-5 provide mounting surfaces for electronic units with heat dissipation requirements for the entire satellite. The ends of the five bulkheads extend radially from the inside to the outside of the outer plates 2-5. The top of the extended portion is used to support the top plate 2-1. At the same time, the extended portion is surface-mounted with OSR and embedded with heat pipes, providing additional heat dissipation surfaces for electronic equipment inside the cabin. Together with the outer plates 2-5, they provide heat dissipation surfaces for the entire satellite's equipment. The size of the extended area is determined according to the heat dissipation requirements of the installed equipment.

[0033] The internal five partitions are arranged in a "2 horizontal, 3 vertical" configuration to achieve multi-point support for payload 4 and integrated layout of electronic equipment. Two long partitions 2-3 are arranged parallel with intervals, and three short partitions 2-4 are arranged parallel with intervals. Each long partition 2-3 runs through the three short partitions 2-4 along its own length, and each long partition 2-3 is perpendicularly connected to the three short partitions 2-4 at the intersection. All the long partitions 2-3 and short partitions 2-4 form a matrix grid structure, providing high-rigidity support for the top plate 2-1 and the satellite payload 4 and the "triple super" platform 6 on it within the cabin. Payload 4 and the "triple super" platform 6 are installed on the top plate 2-1 as an integrated assembly and adjustment unit. At the same time, OSR is applied to the structural plates around the pre-embedded heat pipes in the plate to ensure the accuracy and stability of the installation structure.

[0034] The bottom plate 2-2 has six high-torque CMG groups 201 distributed in a forward and backward manner. A square through hole 202 is opened between the two long bulkheads 2-3 for the assembly operation of the equipment inside the cabin and for the upper protrusion of the storage tank 103 to avoid obstruction.

[0035] like Figure 6 As shown, the integrated support structure 3 for the antenna solar array includes: two symmetrically arranged side cabins 3-1 and two parallel spaced connecting outer plates 3-2; the four together form a closed support structure; the side cabins 3-1 are narrow support cabins with trapezoidal cross-sections, with the data transmission antenna 301 installed on the upper part and the solar array 5 provided with a clamping seat on the side.

[0036] To accommodate the large-scale solar array 5 and the requirements for remote sensing data transmission, integrated antenna solar array support structures 3 are installed on both sides above the equipment compartment 2 to support the large solar array 5 and the data transmission antenna 301. The two side support compartments 3-1 and the outer plate 3-2 are connected as a single unit. The solar array 5 is supported by a fixed solar array 5 with support rods, significantly improving the rigidity of the solar array 5 and antenna during transmission and on-orbit phases. Figure 3 As shown.

[0037] The multi-level collaborative control product consists of the high-torque CMG group 201 and the "three-super" platform 6.

[0038] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A remote sensing satellite configuration for on-the-moment imaging, characterized in that, include: The propulsion compartment (1), equipment compartment (2), and integrated support structure for antenna solar array (3) are connected sequentially from bottom to top. The propulsion compartment (1) includes a load-bearing cylinder (1-1) and a tank support structure (1-2); the outer wall of the load-bearing cylinder (1-1) is provided with an installation interface for the solar panel (5); the tank support structure (1-2) is fixed on the inner wall of the load-bearing cylinder (1-1) and its lower flange inside, for supporting the configured tank (103); the upper and lower surfaces of the tank (103) protruding from the propulsion compartment (1) are respectively sunk into the upper equipment compartment (2) and the lower space shared by the spacecraft and rocket; The equipment compartment (2) is a variable cross-section box structure with a top cross-section larger than the bottom cross-section. The bottom is connected to the top of the load-bearing cylinder (1-1), and the bottom bears the large torque CMG group (201) for attitude maneuvering. The top bears the "three super" platform (6) for vibration isolation and steady-state imaging of the load (4) during satellite attitude maneuvering. An integrated support structure (3) for the antenna solar array is used to support the solar array (5) and the data transmission antenna (301).

2. The remote sensing satellite configuration for on-the-moment imaging according to claim 1, characterized in that, The tank support structure (1-2) includes: a fan-shaped tank bracket (101), a support partition (102), and two small crescent-shaped base plates (105). The fan-shaped tank support (101), together with two small crescent-shaped base plates (105), forms a circular structure that matches the inner diameter of the load-bearing cylinder (1-1) and is used for supporting the tank (103) and installing the thermal control components; the circular structure is installed on the lower flange inside the load-bearing cylinder (1-1); A support partition (102) is fixed on a sector-shaped storage tank bracket (101) to divide the sector-shaped storage tank bracket (101) into several areas, each of which is used for a storage tank (103) to pass through and be fixed.

3. A remote sensing satellite configuration for on-the-moment imaging according to claim 2, characterized in that, The fan-shaped storage tank support (101) has an elongated oval structure, and its outer contour includes two parallel straight sides and symmetrical arc-shaped sides. The outer contour of the crescent-shaped base plate (105) includes: an arc segment and a straight line segment; The arc-shaped edge of the fan-shaped storage tank support (101) matches and connects with the inner wall of the load-bearing cylinder (1-1); the two straight edges match and connect with the straight segments of the two small crescent-shaped base plates (105) respectively. The small crescent-shaped base plate (105) arc segment matches and connects with the inner wall of the load-bearing cylinder (1-1).

4. A remote sensing satellite configuration for on-the-moment imaging according to claim 3, characterized in that, The supporting partition (102) has an I-shaped structure and includes two flanges and a web connecting the two flanges; The bottom ends of the two flanges correspond one-to-one with the two straight edges of the fan-shaped storage tank support (101) and are vertically connected; the two side wall ends of each flange are connected to the inner wall of the load-bearing cylinder (1-1); the bottom end of the web is vertically connected to the fan-shaped storage tank support (101).

5. A remote sensing satellite configuration for on-the-moment imaging according to claim 1, characterized in that, The equipment compartment (2) includes: a top plate (2-1), a bottom plate (2-2), and several outer plates (2-5); The top plate (2-1) and the bottom plate (2-2) are set in parallel; The top of each outer panel (2-5) is connected to the lower surface of the top panel (2-1), and the bottom is connected to the bottom panel (2-2); the side ends of several outer panels (2-5) are connected in sequence along the circumferential direction to form a closed box structure side wall.

6. A remote sensing satellite configuration for on-the-moment imaging according to claim 5, characterized in that, The box structure described herein has an internal support plate; the bottom end of the support plate is connected to the bottom plate (2-2), and the top end is connected to the top plate (2-1); The support plate includes several long partitions (2-3) and several short partitions (2-4); the long partitions (2-3) are arranged in parallel at intervals, and the short partitions (2-4) are arranged in parallel at intervals. Each long partition (2-3) runs through all the short partitions (2-4) along its own length direction and is perpendicularly connected at the intersection. All the long partitions (2-3) and short partitions (2-4) intersect to form a matrix grid structure, supporting the top plate (2-1) to achieve multi-point support for the load (4) and integrated layout of electronic equipment.

7. A remote sensing satellite configuration for on-the-moment imaging according to claim 6, characterized in that, The long partition (2-3) and the short partition (2-4) both extend from the inside to the outside along the radial direction of the box structure (2-5), and the top of the extended part is connected to the lower surface of the top plate (2-1) to support the top plate (2-1).

8. A remote sensing satellite configuration for on-the-moment imaging according to claim 7, characterized in that, The protruding portion is covered with an optical solar reflector and has an embedded heat pipe, providing additional heat dissipation surface for the electronic equipment inside the cabin.

9. A remote sensing satellite configuration for on-the-moment imaging according to claim 5, characterized in that, The bottom plate (2-2) is provided with a through hole (202) at a position corresponding to the part of the upper surface of the tank (103) that protrudes from the propulsion compartment (1), for the assembly operation of the equipment inside the compartment and to avoid the protruding part of the upper surface of the tank (103).

10. A remote sensing satellite configuration for on-the-moment imaging according to claim 1, characterized in that, The integrated support structure (3) for the antenna solar array includes: two symmetrically arranged side cabins (3-1) and two parallel spaced connecting outer plates (3-2); the four together form a closed support structure.

11. A remote sensing satellite configuration for on-the-moment imaging according to claim 10, characterized in that, The top surface of the side cabin (3-1) is equipped with a data transmission antenna (301), and the outer wall provides a clamping seat for the solar wing (5) to clamp and fix it to the end of the support rod of the solar wing (5).

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