Spatial situation awareness strong light cursor calibration satellite

Abstract

The invention relates to the technical field of satellites, and discloses a space situation awareness strong cursor calibration satellite. The satellite comprises a calibration satellite body, and a power supply subsystem, a calibration light source subsystem, a GNSS navigation system, an energy storage system, a telemetering and remote control subsystem, a monocular / multi-view space optical camera system and the like which are integrated on the calibration satellite body. Through a multi-stage linkage mechanism, multi-directional adjustment of a camera system can be realized, images of other satellites or fragments can be accurately captured, target errors are updated by combining image processing, star map matching and GNSS orbit data, and high-precision space situation awareness is realized. The satellites can work independently or a plurality of satellites are distributed on different orbits to form constellations for cooperative work; the calibration light source provides standardized strong light, ensures accurate coverage of an imaging view field, and improves the calibration reliability. The structural design gives consideration to the on-orbit stability and the assembly and maintenance convenience, and the adaptability and practicability are outstanding.

Description

Technical Field

[0001] This invention belongs to the field of satellite technology, and more specifically, relates to a space situational awareness strong calibration satellite. Background Technology

[0002] With the rapid deployment of global satellite internet constellations and the continued advancement of space exploration activities by various countries, the number of space targets (including various spacecraft, space debris, rocket debris, etc.) is growing exponentially, significantly increasing the risk of space collisions and placing higher demands on the accuracy of space situational awareness. As core equipment for space asset security protection, space environment maintenance, space traffic management, and spacecraft lifespan management, the calibration accuracy of low-Earth orbit situational awareness satellites directly determines the reliability of situational awareness data. Therefore, efficient and accurate on-orbit calibration technology has become a key area that the industry urgently needs to overcome.

[0003] However, there are still many problems to be solved in the imaging calibration technology and related satellite design of existing space situational awareness satellites: Existing calibration methods mostly use ground-based targets or passive on-orbit targets. Ground-based targets are greatly affected by atmospheric transmission and weather conditions, limiting calibration accuracy. Passive on-orbit targets suffer from uncontrollable brightness and a single spectrum, failing to meet the calibration requirements of imaging payloads in different bands. At the same time, traditional target satellites lack high-precision orbital broadcasting capabilities, making it difficult to provide accurate spatial position references, further reducing the reliability of image processing accuracy calibration. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the basic concept of the technical solution adopted by the present invention is as follows: A space situational awareness strong calibration satellite includes a calibration satellite body, and a power supply subsystem, a calibration light source subsystem, and a space situational imaging system integrated on the calibration satellite body; The power subsystem includes flexible solar panels and energy storage components symmetrically arranged on both sides of the calibration satellite body. The flexible solar panels are equipped with a solar orientation adaptation mechanism for adjusting the position of the flexible solar panels. The calibration light source subsystem is installed at the bottom of the calibration satellite body and is used to provide a standardized high-intensity light source for imaging accuracy calibration of the low-orbit situational awareness satellite imaging payload; The space situational awareness imaging system includes a space camera. The calibration satellite is rotatably mounted with a gimbal, and a jib arm is rotatably mounted on the gimbal. The space camera is mounted at the end of the jib arm. The mounting position is adjusted by swinging the jib arm and the gimbal to accurately detect the relative positional relationship between the calibration satellite and the low-orbit situational awareness satellite. This ensures that the beam of the calibration light source subsystem accurately covers the target satellite's imaging field of view, ensuring the reliability of the imaging accuracy calibration. The calibration satellite is also equipped with a navigation and orbital broadcasting subsystem. This system includes a four-system GNSS receiver integrating GPS, BeiDou, GLONASS, and Galileo, a multi-frequency multi-mode antenna, and a spaceborne atomic clock GNSS antenna module. This module is used to transmit the orbital position of the calibration satellite to the Earth-based satellite remote control device.

[0005] In a preferred embodiment of the present invention, a commutator motor is installed on the calibration satellite body, and a synchronous shaft is installed at the output end of the commutator motor. The end of the synchronous shaft is connected to the rotation center of the gimbal. The commutator motor is used to adjust the direction of the gimbal, thereby driving the space camera to deflect.

[0006] In a preferred embodiment of the present invention, a plurality of positioning seats are mounted on the gimbal, and a positioning shaft is rotatably mounted inside the positioning seat. One end of the positioning shaft is connected to the rotation center of the rocker arm. A flip motor is also mounted on the gimbal, and the output end of the flip motor is connected to the positioning shaft. The flip motor is used to drive the rocker arm calibration, thereby driving the space camera to deflect.

[0007] In a preferred embodiment of the present invention, the calibration satellite body has a storage compartment inside, a tray is slidably installed inside the storage compartment, energy storage components are stacked on the tray, a back plate is installed at one end of the tray, and a cover plate is installed at the other end of the tray. The cover plate is used to cover the outer wall of the storage compartment for sealing the storage compartment.

[0008] In a preferred embodiment of the present invention, a guide rod is installed on the cover plate, and a plurality of guide holes are provided on the calibration satellite body. The guide rod is movably inserted into the guide holes. An observation window is installed on the cover plate, and a handle is also installed on the cover plate. The surface of the handle is provided with anti-slip grooves.

[0009] In a preferred embodiment of the present invention, a connecting frame is installed between the cover plate and the back plate, and a top rod is inserted into the connecting frame. A clamping plate is installed at one end of the top rod, and the clamping plate is located on the outer side wall of the energy storage component. The other end of the top rod corresponds to a slide rail opened on the inner side wall of the storage compartment, and the initial end of the slide rail is provided with a ramp. When the top rod slides along the ramp to the slide rail, the top rod drives the clamping plate to clamp the energy storage component.

[0010] In a preferred embodiment of the present invention, a pressure plate and a limiting plate are respectively installed on the surface of the top rod. The pressure plate and the limiting plate are located on both sides of the connecting frame, and the limiting plate is closer to the clamping plate. A compression spring is sleeved on the outer wall of the top rod. One end of the compression spring is clamped to the side wall of the connecting frame, and the other end of the compression spring is clamped to the pressure plate. A ball is installed at the end of the top rod, and the ball corresponds to the slide rail.

[0011] Compared with the prior art, the present invention has the following advantages: This invention utilizes a multi-level linkage structure achieved through various means such as gimbals, rocker arms, and sliding rails. It enables flexible adjustment of the horizontal and pitch directions of monocular / multi-view space optical camera systems, accurately capturing image information from other space situational awareness calibration satellites or other space satellites and debris. Through image processing technology, star map matching technology, calibration satellite GNSS orbit data, and image processing errors, it updates the errors of all captured space targets, ultimately achieving high-precision space target situational awareness. The space situational awareness calibration satellite can operate independently or in multiple configurations distributed across low, medium, and high orbits, forming a constellation. The satellite's calibration light source subsystem provides a standardized high-intensity light source, ensuring precise beam coverage of the imaging field of view of other space situational awareness calibration satellites, significantly improving the reliability and accuracy of imaging precision calibration. Simultaneously, the storage compartment's guiding and positioning structure, along with the clamping mechanism composed of a top rod and compression spring, balances the stability requirements of satellite operation in orbit with the convenience of ground assembly and on-orbit maintenance, resulting in a highly adaptable and practical overall structure.

[0012] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings. Attached Figure Description

[0013] In the attached diagram: Figure 1 A three-dimensional image of a space situational awareness-enhanced calibration satellite; Figure 2 For a local area of ​​a space situational awareness strong calibration satellite Figure 1 ; Figure 3 For a type of space situational awareness strong calibration satellite Figure 2 Bottom view; Figure 4 A diagram showing the open structure of a cover plate for a high-precision calibration satellite for space situational awareness. Figure 5 For a local area of ​​a space situational awareness strong calibration satellite Figure 2 ; Figure 6 For a type of space situational awareness strong calibration satellite Figure 5Enlarged view of point A in the middle; Figure 7 For a local area of ​​a space situational awareness strong calibration satellite Figure 3 .

[0014] In the diagram: 1. Calibration satellite body; 2. Flexible solar panel; 3. Calibration light source subsystem; 4. Gimbal; 5. Rocker arm; 6. Space camera; 7. Positioning base; 8. Positioning axis; 9. Tilting motor; 10. Reversing motor; 11. Synchronous shaft; 12. Cover plate; 13. Handle; 14. Observation window; 15. Guide rod; 16. Storage compartment; 17. Support plate; 18. Back plate; 19. Connecting frame; 20. Clamping plate; 21. Top rod; 22. Ball bearing; 23. Limiting plate; 24. Pressure plate; 25. Compression spring; 26. Guide hole; 27. Slide rail; 28. Ramp. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate the present invention.

[0016] Example 1:

[0017] like Figures 1 to 7 As shown, a space situational awareness strong calibration satellite includes a calibration satellite body 1, and a power supply subsystem, a calibration light source subsystem 3, and a space situational imaging system integrated on the calibration satellite body 1; The power subsystem includes flexible solar panels 2 and energy storage components symmetrically arranged on both sides of the calibration satellite body 1. The flexible solar panels 2 are equipped with a solar orientation adaptation mechanism for adjusting the position of the flexible solar panels 2. The calibration light source subsystem 3 is installed at the bottom of the calibration satellite body 1 and is used to provide a standardized high-intensity light source for the imaging payload of the low-orbit situational awareness satellite to calibrate imaging accuracy. The space situational awareness imaging system includes a space camera 6, a gimbal 4 rotatably mounted on the calibration satellite body 1, a rocker arm 5 rotatably mounted on the gimbal 4, and a space camera 6 mounted at the end of the rocker arm 5. The installation position is adjusted by swinging the rocker arm 5 and the gimbal 4 to accurately detect the relative positional relationship between the calibration satellite and the low-orbit situational awareness satellite, ensuring that the beam of the calibration light source subsystem 3 accurately covers the target satellite's imaging field of view and ensuring the reliability of the imaging accuracy calibration.

[0018] like Figures 1 to 7As shown, in a specific embodiment, a commutator motor 10 is installed on the calibration satellite body 1, and a synchronous shaft 11 is installed at the output end of the commutator motor 10. The end of the synchronous shaft 11 is connected to the rotation center of the gimbal 4. The commutator motor 10 is used to adjust the direction of the gimbal 4, thereby driving the space camera 6 to deflect. Through the rigid connection between the commutator motor 10 and the synchronous shaft 11, precise stepless speed regulation of the gimbal 4 can be achieved, improving the control accuracy of the horizontal deflection of the space camera 6, ensuring the accuracy of relative position detection, and providing reliable data support for the beam direction adjustment of the calibration light source subsystem 3. The calibration satellite body 1 is also equipped with a navigation and orbit broadcasting subsystem: the system includes a four-system GNSS receiver integrating GPS, Beidou, GLONASS, and Galileo, a multi-frequency multi-mode antenna, and a spaceborne atomic clock GNSS antenna module, which is used to transmit the orbital position of the calibration satellite to the Earth satellite remote control device.

[0019] like Figures 1 to 7 As shown, furthermore, the gimbal 4 is equipped with several pairs of positioning seats 7, and a positioning shaft 8 is rotatably mounted inside the positioning seat 7. One end of the positioning shaft 8 is connected to the rotation center of the rocker arm 5. The gimbal 4 is also equipped with a tilting motor 9, the output end of which is connected to the positioning shaft 8. The tilting motor 9 is used to drive the rocker arm 5 for calibration, thereby driving the space camera 6 to deflect. The cooperation between the positioning seats 7 and the positioning shaft 8 can improve the stability of the rocker arm 5's rotation. The tilting motor 9 driving the positioning shaft 8 to rotate can realize the precise pitch adjustment of the rocker arm 5, which complements the horizontal adjustment of the gimbal 4, enabling the space camera 6 to capture position information in multiple dimensions and further ensuring the accuracy of the beam coverage of the calibration light source subsystem 3.

[0020] Example 2:

[0021] The difference between the above embodiments and this embodiment is that: Figures 1 to 7 As shown, the calibration satellite body 1 has a storage compartment 16 inside. A tray 17 is slidably installed inside the storage compartment 16, and energy storage components are stacked on the tray 17. A back plate 18 is installed at one end of the tray 17, and a cover plate 12 is installed at the other end. The cover plate 12 covers the outer wall of the storage compartment 16 to seal it. The storage compartment 16 provides an independent protective space for the energy storage components. The sliding tray 17 facilitates the placement and maintenance of the energy storage components. The sealing design of the cover plate 12 isolates the energy storage components from dust, radiation, and other interference from the space environment, protecting the stable performance of the energy storage components and extending the service life of the power subsystem.

[0022] like Figures 1 to 7As shown in the specific embodiment, a guide rod 15 is installed on the cover plate 12, and several pairs of guide holes 26 are opened on the calibration satellite body 1. The guide rod 15 moves through the guide holes 26. An observation window 14 is installed on the cover plate 12, and a handle 13 is also installed on the cover plate 12. The surface of the handle 13 is provided with anti-slip grooves. The cooperation between the guide rod 15 and the guide holes 26 can ensure the coaxiality of the cover plate 12 when it is opened and closed, and avoid misalignment of the seal. The observation window 14 can monitor the status of the energy storage components in real time, and troubleshooting can be carried out without opening the cover plate 12. The anti-slip groove design of the handle 13 improves the ease of operation and facilitates on-orbit or ground maintenance operations.

[0023] like Figures 1 to 7 As shown, a connecting frame 19 is further installed between the cover plate 12 and the back plate 18. A top rod 21 is inserted into the connecting frame 19. A clamping plate 20 is installed at one end of the top rod 21, and the clamping plate 20 is located on the outer wall of the energy storage component. The other end of the top rod 21 corresponds to a slide rail 27 opened on the inner wall of the storage compartment 16. The initial end of the slide rail 27 is provided with a ramp 28. When the top rod 21 slides along the ramp 28 to the slide rail 27, the top rod 21 drives the clamping plate 20 to clamp the energy storage component. The connecting frame 19 provides a stable installation base for the top rod 21. The design of the ramp 28 realizes the automatic clamping of the clamping plate 20 without the need for an additional drive structure, saving space and energy consumption. The clamping plate 20 can firmly fix the energy storage component, avoiding displacement of the energy storage component due to vibration during satellite operation in orbit, and ensuring power supply stability.

[0024] like Figures 1 to 7 As shown, furthermore, a pressure plate 24 and a limiting plate 23 are respectively installed on the surface of the push rod 21. The pressure plate 24 and the limiting plate 23 are located on both sides of the connecting frame 19, with the limiting plate 23 closer to the clamping plate 20. A compression spring 25 is sleeved on the outer wall of the push rod 21. One end of the compression spring 25 is engaged with the side wall of the connecting frame 19, and the other end is engaged with the pressure plate 24. A ball bearing 22 is installed at the end of the push rod 21, and the ball bearing 22 corresponds to the slide rail 27. The pressure plate 24 and the limiting plate 23 can limit the movement stroke of the push rod 21 to avoid excessive extension and contraction damaging the structure. The compression spring 25 can provide continuous clamping force to adapt to energy storage components of different sizes. The ball bearing 22 can reduce the friction between the push rod 21 and the slide rail 27, improve the smoothness of sliding, and extend the service life of the clamping mechanism.

[0025] The implementation principle of a space situational awareness strong calibration satellite of the present invention is as follows: 1. Orbital Deployment: After the satellite enters orbit, it completes the deployment of solar panels, attitude initialization, GNSS receiver calibration, and enters the predetermined working orbit; 2. Command Reception: Receive calibration mission commands sent by the ground station and determine the orbital rendezvous time, illumination mode, and working duration with the low-Earth orbit situational awareness satellite; 3. Calibration Execution: The attitude control subsystem adjusts the satellite's attitude so that the bottom light source is precisely pointed at the target satellite's imaging field of view. The two sets of space cameras 6 take turns photographing the target satellite. The space cameras 6 achieve precise detection of their relative positions through the linkage adjustment of the gimbal 4 and the rocker arm 5. Specifically, the reversing motor 10 drives the synchronous shaft 11 to rotate, which in turn drives the gimbal 4 to adjust its direction around the rotation center, thereby achieving the horizontal deflection of the space camera 6. At the same time, the flip motor 9 on the gimbal 4 is activated, driving the positioning shaft 8 to rotate. The positioning shaft 8 is connected to the rotation center of the rocker arm 5, which drives the rocker arm 5 to flip and swing around the positioning seat 7, further adjusting the pitch angle of the space camera 6. Through the coordinated control of the commutation motor 10 and the flipping motor 9, combined with the multi-stage swing adjustment of the gimbal 4 and the rocker arm 5, the space camera 6 can accurately capture the relative positional relationship between the calibration satellite and the target satellite, and feed the positional information back to the control system. The control system fine-tunes the attitude of the calibration satellite body 1 and the beam direction of the calibration light source subsystem 3 according to the feedback data, ensuring that the strong light source accurately covers the imaging field of view of the target satellite. The two sets of space cameras 6 can start the designated light emission mode, while the navigation and orbit broadcasting subsystem continuously broadcasts high-precision orbital information for the target satellite to carry out image processing accuracy calibration. 4. Mission complete: After completing the calibration mission, the satellite switches to low-power mode and awaits the next mission command.

[0026] In this invention, the calibration satellite body 1 is used as the core carrier, and the various subsystems work together to achieve precise calibration of the imaging payload of the low-orbit situational awareness satellite. The whole follows the closed-loop operation logic of "stable power supply - precise positioning - light source coverage - structural protection".

[0027] In the initial stage of operation, the power supply subsystem starts working first. The flexible solar panels 2, symmetrically arranged on both sides of the calibration satellite body 1, adjust their positions through the solar orientation adaptation mechanism to capture solar energy to the maximum extent and convert it into electrical energy. Part of the electrical energy is directly supplied to each power consumption subsystem, and the other part is stored in the energy storage component for backup, providing continuous and stable energy support for the entire calibration process. The energy storage components are stacked on a tray 17 inside the storage compartment 16 of the calibration satellite body 1. The tray 17 slides smoothly through a guide rod 15 and a guide hole 26 on the calibration satellite body 1, facilitating the placement and maintenance of the energy storage components. A cover plate 12 covers the outer wall of the storage compartment 16 for sealing and protection, and can be easily opened and closed through a handle 13. An observation window 14 can monitor the status of the energy storage components in real time. When the tray 17 is pushed into the storage compartment 16, the ball bearing 22 at the end of the push rod 21 slides along the ramp 28 at the initial end of the slide rail 27 into the slide rail 27. Under the elastic force of the compression spring 25, the push rod 21 drives the clamping plate 20 to tightly clamp the energy storage components. The pressure plate 24 and the limiting plate 23 cooperate to limit the movement range of the push rod 21, ensuring that the energy storage components remain stable during satellite operation and avoiding the impact of vibration on power supply reliability.

[0028] After the energy supply stabilizes, the calibration system enters the positioning and light source projection phase. The calibration light source subsystem 3, installed at the bottom of the calibration satellite body 1, is activated, emitting a standardized high-intensity light source to provide a calibration benchmark for the imaging payload of the low-orbit situational awareness satellite. To ensure accurate coverage of the target satellite's imaging field of view by the light source, a calibration light source subsystem 3 is installed at the bottom of the satellite platform. This subsystem provides a standardized, high-intensity light source for calibrating the image processing accuracy of the low-Earth orbit situational awareness satellite imaging payload. It includes a xenon flash array, a high-brightness LED supplementary lighting module, an optical collimation system, and a liquid-cooled heat dissipation circuit. The calibration light source subsystem supports three programmable switching modes: high-speed strobe, breathing light, and continuous high-intensity light. In high-speed strobe mode, the frequency is adjustable from 1Hz to 100Hz, with a single flash power ≥500W and a pulse width adjustable from 1ms to 10ms, used to calibrate the dynamic response characteristics of the imaging payload. In breathing light mode, the brightness changes periodically from 10% to 100%, with a period adjustable from 5s to 60s, used to calibrate the grayscale response linearity of the imaging payload. In continuous high-intensity light mode, the stable output power is ≥200W, with a continuous working time ≥2 hours, used to calibrate the geometric distortion and pixel uniformity of the imaging payload. The optical collimation system ensures that the beam divergence angle is ≤0.5°, guaranteeing the uniformity of illumination on the target within the low-Earth orbit imaging payload's field of view.

[0029] The space camera 6 achieves precise detection of its relative position through the coordinated adjustment of the gimbal 4 and the jib arm 5. Specifically, the reversing motor 10 drives the synchronous shaft 11 to rotate, causing the gimbal 4 to adjust its direction around the rotation center, thereby achieving the horizontal deflection of the space camera 6. Simultaneously, the flip motor 9 on the gimbal 4 is activated, driving the positioning shaft 8 to rotate. The positioning shaft 8 is connected to the rotation center of the jib arm 5, causing the jib arm 5 to flip and swing around the positioning seat 7, further adjusting the pitch angle of the space camera 6. Through the coordinated control of the reversing motor 10 and the flip motor 9, combined with the multi-stage swing adjustment of the gimbal 4 and the jib arm 5, the space camera 6 can accurately capture the relative positional relationship between the calibration satellite and the target satellite, and feed the position information back to the control system. The control system fine-tunes the attitude of the calibration satellite body 1 and the beam direction of the calibration light source subsystem 3 based on the feedback data, ensuring that the strong light source accurately covers the imaging field of view of the target satellite.

[0030] Throughout the process, the flexible solar panels 2 and energy storage components of the power subsystem ensure a continuous energy supply. The adjustment mechanism consisting of the gimbal 4, rocker arm 5, commutator motor 10, and flip motor 9 enables the precise positioning of the space camera 6. The calibration light source subsystem 3 provides a standardized calibration light source. The storage compartment 16 and its internal clamping structure ensure the stable installation and convenient maintenance of the energy storage components. Finally, through the coordinated operation of each subsystem, reliable calibration of the imaging accuracy of the low-Earth orbit situational awareness satellite imaging payload is achieved, ensuring the detection accuracy of the low-Earth orbit situational awareness satellite.

[0031] Finally, it should be noted that the above descriptions are merely preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A space situational awareness strong calibration satellite, characterized in that: It includes the calibration satellite body (1), as well as the power supply subsystem, calibration light source subsystem (3) and space potential imaging system integrated on the calibration satellite body (1); The power subsystem includes flexible solar panels (2) symmetrically arranged on both sides of the calibration satellite body (1) and energy storage components. The flexible solar panels (2) are equipped with a solar orientation adaptation mechanism for adjusting the position of the flexible solar panels (2). The calibration light source subsystem (3) is installed at the bottom of the calibration satellite body (1) and is used to provide a standardized strong light source for imaging accuracy calibration of the low-orbit situational awareness satellite imaging payload; The space situational awareness imaging system includes a space camera (6), a gimbal (4) is rotatably mounted on the calibration satellite body (1), and a rocker arm (5) is rotatably mounted on the gimbal (4), and a space camera (6) is mounted at the end of the rocker arm (5). The installation position is adjusted by swinging the rocker arm (5) and the gimbal (4) to accurately detect the relative positional relationship between the calibration satellite and the low-orbit situational awareness satellite, ensuring that the beam of the calibration light source subsystem (3) accurately covers the target satellite's imaging field of view, and ensuring the reliability of the imaging accuracy calibration. The calibration satellite body (1) is also equipped with a navigation and orbit broadcasting subsystem: the system includes a four-system GNSS receiver integrating GPS, Beidou, GLONASS and Galileo, a multi-frequency multi-mode antenna and a spaceborne atomic clock GNSS antenna module, which is used to transmit the orbital position of the calibration satellite to the ground satellite remote control device.

2. The space situational awareness strong calibration satellite according to claim 1, characterized in that, The calibration satellite body (1) is equipped with a commutator motor (10), and a synchronous shaft (11) is installed at the output end of the commutator motor (10). The end of the synchronous shaft (11) is connected to the rotation center of the gimbal (4). The commutator motor (10) is used to adjust the direction of the gimbal (4), thereby driving the space camera (6) to deflect.

3. A space situational awareness strong calibration satellite according to claim 1, characterized in that, The gimbal (4) is equipped with several pairs of positioning seats (7). A positioning shaft (8) is rotatably installed inside the positioning seat (7). One end of the positioning shaft (8) is connected to the rotation center of the rocker arm (5). The gimbal (4) is also equipped with a flip motor (9). The output end of the flip motor (9) is connected to the positioning shaft (8). The flip motor (9) is used to drive the rocker arm (5) for calibration, thereby driving the space camera (6) to deflect.

4. A space situational awareness strong calibration satellite according to claim 1, characterized in that, The calibration satellite body (1) has a storage compartment (16) inside. A tray (17) is slidably installed inside the storage compartment (16). Energy storage components are stacked on the tray (17). A back plate (18) is installed at one end of the tray (17), and a cover plate (12) is installed at the other end of the tray (17). The cover plate (12) is used to cover the outer wall of the storage compartment (16) and to seal the storage compartment (16).

5. A space situational awareness strong calibration satellite according to claim 4, characterized in that, A guide rod (15) is installed on the cover plate (12), and several pairs of guide holes (26) are opened on the calibration satellite body (1). The guide rod (15) is movably inserted into the guide hole (26). An observation window (14) is installed on the cover plate (12), and a handle (13) is also installed on the cover plate (12). Anti-slip grooves are opened on the surface of the handle (13).

6. A space situational awareness strong calibration satellite according to claim 4, characterized in that, A connecting frame (19) is installed between the cover plate (12) and the back plate (18). A top rod (21) is inserted inside the connecting frame (19). A clamping plate (20) is installed at one end of the top rod (21), and the clamping plate (20) is located on the outer wall of the energy storage component. The other end of the top rod (21) corresponds to the slide rail (27) opened on the inner wall of the storage compartment (16). The slide rail (27) has a ramp (28) at its initial end. When the top rod (21) slides along the ramp (28) to the slide rail (27), the top rod (21) drives the clamping plate (20) to clamp the energy storage component.

7. A space situational awareness strong calibration satellite according to claim 6, characterized in that, The top rod (21) is respectively equipped with a pressure plate (24) and a limiting plate (23). The pressure plate (24) and the limiting plate (23) are located on both sides of the connecting frame (19), and the limiting plate (23) is closer to the clamping plate (20). A compression spring (25) is sleeved on the outer wall of the top rod (21). One end of the compression spring (25) is clamped to the side wall of the connecting frame (19), and the other end of the compression spring (25) is clamped to the pressure plate (24). A ball bearing (22) is installed at the end of the top rod (21), and the ball bearing (22) corresponds to the slide rail (27).

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