A satellite on-orbit observation imaging simulation device

Abstract

The present invention discloses a satellite on-orbit observation imaging simulation device, belonging to the technical field of space earth observation. The present invention includes an astronomical dome fixed on the ground and internally lined with black light-absorbing and sound-absorbing materials; the interior of the astronomical dome includes a payload motion simulation system fixed on the ground; a sand table placed in the center of the ground for simulating a complex ground environment; a constant temperature system placed inside the astronomical dome. The payload motion simulation system can simulate different solar illumination angles and illumination intensities by controlling the pitch, azimuth, and current magnitude of the solar simulator in a room without external interference and with a constant environment. Similarly, based on the same control principle, the payload can perform simulated on-orbit imaging of various real targets such as vegetation, soil, water bodies, and minerals, enabling targeted, traceable, and precise quantitative verification, evaluating the rationality of payload indicators and the performance of processing and inversion algorithms. The on-orbit simulation test can improve the development efficiency of the payload and the realization of the expected effect.

Description

Technical Field

[0001] The present invention relates to the technical field of space earth observation, and particularly to a satellite on-orbit observation imaging simulation device. Background Art

[0002] Due to the characteristics of high cost and non-maintainability of spaceborne remote sensing instruments, they usually need to be analyzed and demonstrated first during design, and then field tests, aerial calibration flights, or even launch test satellites for verification. Among them, the field aerial calibration flight test is an essential verification process, which is time-consuming and costly.

[0003] The design verification of common ground remote sensing instruments is to verify the correctness of the design through field tests. However, during field tests, it is also limited by weather conditions, because environmental parameters such as outdoor air conditions, air pressure, temperature, and humidity are difficult to accurately normalize, which greatly reduces the verification effect. Summary of the Invention

[0004] The present invention provides a satellite on-orbit observation imaging simulation device to ensure that the experimental results are not affected by the environment and make the verification results more accurate. The content of the present invention is as follows:

[0005] The purpose of the present invention is to provide a satellite on-orbit observation imaging simulation device, and its technical points are as follows: including an astronomical dome fixed on the ground and internally lined with black light-absorbing and sound-absorbing materials; the inside of the astronomical dome includes:

[0006] - A payload motion simulation system fixed on the ground;

[0007] - A sand table placed in the center of the ground for simulating a complex ground environment;

[0008] - A constant temperature system for ensuring a constant temperature inside the astronomical dome;

[0009] The outside of the astronomical dome includes a master control machine fixed on the ground for acquiring data information of the payload motion simulation system;

[0010] The payload motion simulation system includes:

[0011] - An outer layer solar simulation light source circular orbit and an inner layer satellite circular orbit coaxially installed on the ground with the astronomical dome;

[0012] - A first semi-circular orbit vertically fixed on the outer layer solar simulation light source circular orbit through a first horizontal movement module, the first semi-circular orbit can rotate horizontally and its center is offset from the center of the astronomical dome;

[0013] - A second semi-circular orbit vertically fixed on the inner layer satellite circular orbit through a second horizontal movement module, the second semi-circular orbit can rotate horizontally and coincides with the center of the astronomical dome;

[0014] - A simulated solar light source module fixed on the first semi-circular track by a first load moving module. The simulated solar light source module can slide along the first semi-circular track. The outer-layer circular track of the solar simulation light source cooperates with the first horizontal moving module to control the azimuth angle of the simulated solar light source module. The first semi-circular track cooperates with the first load moving module to control the pitch angle of the simulated solar light source module relative to the center of the astronomical dome, thereby simulating the movement trajectory of the sun.

[0015] - A satellite remote sensing camera module fixed on the second semi-circular track by a second load moving module. The satellite remote sensing camera module can slide along the second semi-circular track. The inner-layer circular track of the satellite cooperates with the second horizontal moving module to control the azimuth angle of the satellite remote sensing camera module. The second semi-circular track cooperates with the second load moving module to control the pitch angle of the satellite remote sensing camera module relative to the center of the astronomical dome, so that the satellite remote sensing camera module always performs simulated on-orbit imaging on the sand table.

[0016] Further, the master control machine in the satellite on-orbit observation imaging simulation device of the present invention includes a control instruction transmitting module and a signal receiving module, which are used to control and obtain the position of the moving module.

[0017] Further, the horizontal moving module in the satellite on-orbit observation imaging simulation device of the present invention includes:

[0018] - A horizontal moving frame;

[0019] - A first control circuit box fixed above the horizontal moving frame. The first control circuit box sends signals to the master control machine and receives control instructions in real time through a wireless transmission method;

[0020] - Two single-wheel support limit wheels fixed below the horizontal moving frame and moving on the circular track;

[0021] - Several auxiliary gears located below the horizontal moving frame and outside the circular track;

[0022] - Several side limit wheels located inside the semi-circular track and cooperating with the auxiliary gears;

[0023] - A first rotating gear control system located between the two single-wheel support limit wheels and outside the circular track. The first rotating gear control system is electrically connected to the first control circuit box, and the first rotating gear control system drives the horizontal moving module to rotate horizontally on the circular track.

[0024] Further, the load moving module in the satellite on-orbit observation imaging simulation device of the present invention includes:

[0025] - A load moving frame, with the semi-circular track running through the middle of the load moving module;

[0026] - A second control circuit box fixed to one side of the load moving frame, which sends signals to the master control machine in real time via wireless transmission and receives control instructions;

[0027] - Four I-shaped support limit wheels fixed inside the load moving frame and symmetrically clamped on the four edges of the semi-circular track;

[0028] - A second rotating gear control system fixed to the other side of the load moving frame, which is electrically connected to the second control circuit box, and the second rotating gear control system drives the load moving module to slide on the semi-circular track.

[0029] Further, the rotating gear control system in the satellite on-orbit observation imaging simulation device of the present invention includes a gear, a support frame, a reducer, and a servo motor. The gear meshes with the track, the control circuit box controls the operation of the servo motor, and the servo motor drives the gear to move on the track through the reducer.

[0030] Further, the moving module in the satellite on-orbit observation imaging simulation device of the present invention is powered by a sliding contact wire, and the moving module is provided with a contact wheel in contact with the sliding contact wire for power supply.

[0031] Further, the working band of the simulated solar light source module in the satellite on-orbit observation imaging simulation device of the present invention is 400 - 2500nm, the irradiation distance is 6 - 10m, and the spot area is 2000 * 2000mm.

[0032] Further, the simulated solar light source module in the satellite on-orbit observation imaging simulation device of the present invention is composed of several light sources arranged in a matrix mode, and each light source includes a light source housing, a halogen lamp module and a xenon lamp module placed inside the light source housing.

[0033] Further, the halogen lamp module in the satellite on-orbit observation imaging simulation device of the present invention includes a lamp cover, a halogen lamp placed inside the lamp cover, an air-cooling system, a reflector, a ventilation port, and a fly-eye lens.

[0034] Further, the xenon lamp module in the satellite on-orbit observation imaging simulation device of the present invention includes a lamp cover, a xenon lamp placed inside the lamp cover, an air-cooling system, a reflector, a ventilation port, a fly-eye lens, and a filter, and the bandwidth of the filter is 400 - 900nm.

[0035] The above at least one technical solution adopted in the embodiments of the present invention can achieve the following beneficial effects:

[0036] The satellite on-orbit observation imaging simulation device of the present invention includes an astronomical dome fixed on the ground and internally lined with black light-absorbing and sound-absorbing materials; the interior of the astronomical dome includes a payload motion simulation system fixed on the ground; a sand table placed in the center of the ground for simulating a complex ground environment; a constant temperature system placed inside the astronomical dome. The payload motion simulation system can simulate different solar illumination angles and intensities by controlling the pitch, azimuth, and current magnitude of the solar simulator indoors without external interference and in a constant environment. Similarly, the payload can simulate on-orbit imaging of various real targets such as vegetation, soil, water bodies, and minerals, and obtain the bidirectional reflectance distribution function BRDF (Bidirectional Reflectance Distribution Function) for describing the inherent properties of the reflection mode of the target through an on-board camera. It can also carry an airborne and ground object camera to perform multi-angle measurement or three-dimensional imaging of the target, evaluate the rationality of the payload index and the performance of the processing inversion algorithm. The on-orbit simulation test can improve the development efficiency of the payload and the realization of the expected effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The drawings described herein are used to provide a further understanding of the present invention and form a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0038] Figure 1 is a schematic structural diagram of the satellite on-orbit observation imaging simulation device of the present invention;

[0039] Figure 2 is an external view of the astronomical dome of the satellite on-orbit observation imaging simulation device of the present invention;

[0040] Figure 3 is a movement schematic diagram of the horizontal movement module and the payload movement module of the satellite on-orbit observation imaging simulation device of the present invention;

[0041] Figure 4 is a schematic diagram of the payload movement module of the satellite on-orbit observation imaging simulation device of the present invention for controlling the payload pitch angle;

[0042] Figure 5 is a left view of the horizontal movement module of the satellite on-orbit observation imaging simulation device of the present invention;

[0043] Figure 6 is a right view of the horizontal movement module of the satellite on-orbit observation imaging simulation device of the present invention;

[0044] Figure 7 is a front view of the horizontal movement module of the satellite on-orbit observation imaging simulation device of the present invention;

[0045] Figure 8 Schematic diagram of the rotation gear control system of the satellite on-orbit observation imaging simulation device of the present invention;

[0046] Figure 9 Schematic diagram of the load moving module of the satellite on-orbit observation imaging simulation device of the present invention;

[0047] Figure 10 Left view of the load moving module of the satellite on-orbit observation imaging simulation device of the present invention;

[0048] Figure 11 Front view of the load moving module of the satellite on-orbit observation imaging simulation device of the present invention;

[0049] Figure 12 Schematic diagram of the structure of the simulated solar light source module of the satellite on-orbit observation imaging simulation device of the present invention;

[0050] Figure 13 Schematic diagram of the light source structure of the simulated solar light source module of the present invention;

[0051] Figure 14 Schematic diagram of the structures of the halogen lamp module and the xenon lamp module of the present invention;

[0052] Figure 15 Schematic diagram of the compound eye lens of the present invention.

[0053] Accompanying drawings

[0054] 1 - Ground; 2 - Astronomical dome; 3 - Outer layer circular orbit of the solar simulation light source; 4 - Slide wire; 5 - Second horizontal moving module; 6 - Second semi-circular orbit; 7 - First load moving module; 8 - Simulated solar light source module; 9 - Satellite remote sensing camera module; 10 - Sand table; 11 - Master control machine; 12 - Single-wheel support limiting wheel; 13 - Allen screw; 14 - Pillow block bearing; 15 - Heavy load spring; 16 - First control circuit box; 17 - Auxiliary gear; 18 - First rotation gear control system; 19 - Side limiting wheel; 20 - Slide wire contact wheel; 21 - Horizontal moving frame; 22 - Gear; 23 - Support frame; 24 - Reducer; 25 - Servo motor; 26 - I-shaped support limiting wheel; 27 - Load moving frame; 28 - Light source; 29 - Light source housing; 30 - Halogen lamp module; 31 - Xenon lamp module; 32 - Halogen lamp; 33 - Xenon lamp; 34 - Compound eye lens; 34 - Inner layer circular orbit of the satellite; 35 - First horizontal moving module; 36 - First semi-circular orbit; 37 - Second load moving module; 38 - Second control circuit box; 39 - Second rotation gear control system; 40 - Lamp shade; 41 - Filter; 42 - Air cooling system; 43 - Reflector; 44 - Ventilation opening. Detailed implementation mode

[0055] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with specific embodiments of the present invention and the corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the scope of protection of the present invention.

[0056] In the drawings, components with the same structure are denoted by the same numerical labels, and components with similar structures or functions everywhere are denoted by similar numerical labels. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. To make the illustration clearer, the thickness of some components in the drawings is appropriately exaggerated. For the convenience of description, the "upper", "lower", "left", "right", "front", "rear", "inside", and "outside" mentioned hereinafter are consistent with the upper, lower, left, right, front, rear, inside, and outside directions of the drawings themselves, but do not limit the structure of the present invention.

[0057] The following will detail the technical solutions provided by each embodiment of the present invention in conjunction with the drawings.

[0058] As Figure 1 shown, a satellite on-orbit observation imaging simulation device includes an astronomical dome 2 fixed on the ground 1 and internally lined with black light-absorbing and sound-absorbing materials as Figure 2 shown. The astronomical dome 2 made of this material provides a quiet and dark environment for the load movement simulation system mentioned later, preventing the influence of other sounds and stray light on the internal test environment. Specifically, the black light-absorbing and sound-absorbing material of the present invention is a black aluminum honeycomb board material as Figure 2 shown; the interior of the astronomical dome 2 includes:[[]]

[0059] - A load movement simulation system fixed on the ground 1, which can simulate the movement trajectories of the sun and the satellite;

[0060] - A sand table 10 placed in the center of the ground 1 for simulating a complex ground environment;

[0061] - A constant temperature system (not shown in the figure) for ensuring a constant temperature inside the astronomical dome 2. This constant temperature system can make the astronomical dome 2 have a constant temperature environment, prevent the influence of temperature changes on the test structure, exclude external factors, and increase the accuracy of the test;

[0062] The exterior of the astronomical dome 2 includes a master control machine 11 fixed to the ground 1 for obtaining data information of the load movement simulation system as Figure 1 shown in 2;

[0063] The described load motion simulation system includes:

[0064] - As Figure 3 shown, an outer - layer solar simulation light source circular orbit 3 and an inner - layer satellite circular orbit 34 installed on the ground 1 and coaxial with the astronomical dome 2;

[0065] - As Figure 3 shown, a first semi - circular orbit 36 vertically fixed on the outer - layer solar simulation light source circular orbit 3 through a first horizontal moving module 35. The first semi - circular orbit 36 can rotate horizontally back and forth, and its center is offset from the center of the astronomical dome 2 to avoid light interference with the remote - sensing camera;

[0066] - As Figure 3 shown, a second semi - circular orbit 6 vertically fixed on the inner - layer satellite circular orbit 34 through a second horizontal moving module 5. The second semi - circular orbit 6 can rotate horizontally back and forth and coincides with the center of the astronomical dome 2;

[0067] - A simulated solar light source module 8 fixed on the first semi - circular orbit 36 through a first load moving module 7. The simulated solar light source module 8 can slide back and forth along the first semi - circular orbit 36. The outer - layer solar simulation light source circular orbit 3 and the first horizontal moving module 35 cooperate to control the azimuth angle of the simulated solar light source module 8, and the first semi - circular orbit 36 and the first load moving module 7 cooperate to control the pitch angle of the simulated solar light source module 8 relative to the center of the astronomical dome 2, thereby simulating the movement trajectory of the sun;

[0068] - A satellite remote - sensing camera module 9 fixed on the second semi - circular orbit 6 through a second load moving module 37. The satellite remote - sensing camera module 9 can slide back and forth along the second semi - circular orbit 6. The inner - layer satellite circular orbit 34 and the second horizontal moving module 5 cooperate to control the azimuth angle of the satellite remote - sensing camera module 9. As Figure 4 shown, the second semi - circular orbit 6 and the second load moving module 37 cooperate to control the pitch angle of the satellite remote - sensing camera module 9 relative to the center of the astronomical dome 2, so that the satellite remote - sensing camera module 9 always performs simulated on - orbit imaging on the sand table 10.

[0069] Preferably, the master control machine 11 in the satellite on - orbit observation imaging simulation device of the present invention includes a control instruction transmitting module and a signal receiving module, which are used to control and obtain the positions of the moving modules 5, 35, 7, 37. Furthermore, the operator can use the master control machine to control and obtain the positions of the solar simulator and the satellite remote - sensing camera in real - time.

[0070] Preferably, as Figures 5 - 7 shown, the horizontal moving modules 5, 35 in the satellite on - orbit observation imaging simulation device of the present invention include:

[0071] - The horizontal movement frame 21;

[0072] - The first control circuit box 16 fixed above the horizontal movement frame 21, and the first control circuit box 16 sends signals to the master control machine 11 in real time through wireless transmission and receives control instructions. By using this method for signal connection, the cable structure is simple, and the accuracy and flexibility are good;

[0073] - Two single-wheel support and limit wheels 12 fixed below the horizontal movement frame 21 and moving on the circular tracks 3 and 34. As a preference, as Figure 6 、 7 shown, the single-wheel support and limit wheels 12 of the present invention are fixed on the horizontal movement frame 21 through a screw structure to further improve the stability of the horizontal movement modules 5 and 35. The screw structure includes an internal hexagon screw 13, a pillow block bearing 14, and a heavy-duty spring 15. The pillow block bearing 14 and the heavy-duty spring 15 are sleeved on the internal hexagon screw 13 in sequence, and the internal hexagon screw 13 is fixed to the horizontal movement frame 21. In addition, other fixing methods well-known to those skilled in the art can also be selected.

[0074] - Several auxiliary gears 17 located below the horizontal movement frame 21 and outside the circular tracks 3 and 34;

[0075] - Several side limit wheels 19 located inside the semi-circular tracks 6 and 36 and cooperating with the auxiliary gears 17. The combined use of the single-wheel support and limit wheels 12, the auxiliary gears 17, and the side limit wheels 19 of the present invention ensures the stability of the horizontal movement modules 5 and 35 during the movement.

[0076] - The first rotating gear control system 18 located between the two single-wheel support and limit wheels 12 and outside the circular tracks 3 and 34. The first rotating gear control system 18 is electrically connected to the first control circuit box 16, and the first rotating gear control system 18 drives the horizontal movement modules 5 and 35 to rotate horizontally on the circular tracks 3 and 34.

[0077] As a preference, as Figures 9 - 11 shown, the payload movement modules 7 and 37 in the satellite on-orbit observation imaging simulation device of the present invention include:

[0078] - The payload movement frame 27, and the semi-circular tracks 6 and 36 cross through the middle of the payload movement modules 7 and 37;

[0079] - A second control circuit box 38 fixed to one side of the load moving frame 27, which sends signals to the master controller 11 in real time via wireless transmission and receives control instructions. By using this method for signal connection, the cable structure is simple, and the accuracy and flexibility are good.

[0080] - Four I-shaped support limit wheels 26 fixed inside the load moving frame 27 and symmetrically clamped on the four edges of the semi-circular tracks 6 and 36. The I-shaped support limit wheels 26 of the present invention ensure the stability of the load moving modules 7 and 37 during sliding. Preferably, as Figure 6 、 7 shown, the I-shaped support limit wheels 26 of the present invention are fixed to the load moving frame 27 by a screw structure to further improve the stability of the load moving modules 7 and 37. The screw structure includes an internal hexagonal screw 13, a pillow block bearing 14, and a heavy load spring 15. The pillow block bearing 14 and the heavy load spring 15 are sequentially sleeved on the internal hexagonal screw 13, and the internal hexagonal screw 13 is fixed to the load moving frame 27. In addition, other fixing methods well-known to those skilled in the art can also be selected.

[0081] - A second rotating gear control system 39 fixed to the other side of the load moving frame 27. The second rotating gear control system 39 is electrically connected to the second control circuit box 38, and the second rotating gear control system 39 drives the load moving modules 7 and 37 to slide on the semi-circular tracks 6 and 36.

[0082] Preferably, as Figure 8 shown, the rotating gear control systems 18 and 39 in the satellite on-orbit observation imaging simulation device of the present invention include a gear 22, a support frame 23, a reducer 24, and a servo motor 25. The gear 22 meshes with the tracks 3, 34, 6, and 36. The control circuit boxes 16 and 38 control the operation of the servo motor 25. The servo motor 25 drives the gear 22 to move on the tracks 3, 34, 6, and 36 through the reducer 24. Compared with the traditional slide rail system, the gear method can accurately adjust and fix the azimuth and pitch of the load, improving the accuracy of the simulation test results.

[0083] Preferably, as Figure 1 、 6 shown, the moving modules 5, 35, 7, and 37 in the satellite on-orbit observation imaging simulation device of the present invention are powered by a sliding contact wire 4. The moving modules 5, 35, 7, and 37 are provided with a contact wheel 20 in contact with the sliding contact wire 4 for power supply, avoiding the influence and limitation of the power cable on the movement of the load.

[0084] Preferably, the working band of the simulated solar light source module 8 in the satellite on-orbit observation imaging simulation device of the present invention is 400 - 2500 nm, the irradiation distance is 6 - 10 m, and the spot area is 2000 * 2000 mm, enabling simulated imaging of visible and short-wave satellite remote sensing cameras. More preferably, the irradiation distance of the simulated solar light source module 8 of the present invention is 8 m, so that the uniformity of the simulated solar light source module 8 reaches 80% ± 5%, and the time instability reaches ± 1%, meeting the requirements of simulated sunlight.

[0085] Preferably, as Figure 12 shown, the simulated solar light source module 8 in the satellite on-orbit observation imaging simulation device of the present invention is composed of several light sources 28 arranged in a matrix pattern. As Figure 13 shown, each light source 28 of the present invention includes a light source housing 29, a halogen lamp module 30 and a xenon lamp module 31 placed inside the light source housing 29, emitting light similar to the solar spectrum, and adjusting the current magnitude of each module to achieve the adjustment of the light intensity, thereby simulating the position of the sun at different times and different lighting conditions, such as performing hyperspectral imaging of satellite-borne wide spectral bands, low-light imaging under low illumination conditions, panchromatic imaging for monitoring target details, or active laser radar imaging under full black conditions to obtain the BRDF information of the target. It can also perform multi-angle measurement and three-dimensional imaging by carrying an airborne camera or a ground object camera.

[0086] Preferably, as Figure 14 shown, the halogen lamp module 31 in the satellite on-orbit observation imaging simulation device of the present invention includes a lamp cover 40, a halogen lamp 32 placed inside the lamp cover, an air-cooling system 42, a reflector 43, a ventilation port 44 and a fly-eye lens 45, realizing similarity to the solar spectrum in the 900 - 2500 nm band.

[0087] Preferably, as Figure 14 shown, the xenon lamp module 31 in the satellite on-orbit observation imaging simulation device of the present invention includes a lamp cover 40, a xenon lamp 33 placed inside the lamp cover, an air-cooling system 42, a reflector 43, a ventilation port 44, a fly-eye lens 45 and a filter 41. The bandwidth of the filter 41 is 400 - 900 nm, realizing similarity to the solar spectrum in the 400 - 900 nm band. The fly-eye lens 45 of the present invention is Figure 15 shown as a honeycomb structure.

[0088] The above are only embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the scope of the claims of the present invention.

Claims

1. A satellite on-orbit observation imaging simulation device, characterized in that, It includes an astronomical dome (2) fixed on the ground (1) with black matte sound-absorbing material laid inside; the inside of the astronomical dome (2) includes: - A payload motion simulation system fixed on the ground (1); - A sand table (10) placed in the center of the ground (1) for simulating a complex ground environment; - A constant temperature system for ensuring a constant temperature inside the astronomical dome (2); Outside the astronomical dome (2), it includes a master control machine (11) fixed on the ground (1) for acquiring data information of the payload motion simulation system; The payload motion simulation system includes: - An outer layer solar simulation light source circular orbit (3) and an inner layer satellite circular orbit (34) installed on the ground (1) and coaxial with the astronomical dome (2); - A first semi-circular orbit (36) vertically fixed on the outer layer solar simulation light source circular orbit (3) through a first horizontal movement module (35), the first semi-circular orbit (36) can rotate horizontally and its center deviates from the center of the astronomical dome (2); - A second semi-circular orbit (6) vertically fixed on the inner layer satellite circular orbit (34) through a second horizontal movement module (5), the second semi-circular orbit (6) can rotate horizontally and coincides with the center of the astronomical dome (2); - A simulated solar light source module (8) fixed on the first semi-circular orbit (36) through a first payload movement module (7), the simulated solar light source module (8) can slide along the first semi-circular orbit (36), the outer layer solar simulation light source circular orbit (3) and the first horizontal movement module (35) cooperate to control the azimuth angle of the simulated solar light source module (8), and the first semi-circular orbit (36) and the first payload movement module (7) cooperate to control the pitch angle of the simulated solar light source module (8) relative to the center of the astronomical dome (2) so as to simulate the movement trajectory of the sun; - A satellite remote sensing camera module (9) fixed on the second semi-circular orbit (6) through a second payload movement module (37), the satellite remote sensing camera module (9) can slide along the second semi-circular orbit (6), the inner layer satellite circular orbit (34) and the second horizontal movement module (5) cooperate to control the azimuth angle of the satellite remote sensing camera module (9), and the second semi-circular orbit (6) and the second payload movement module (37) cooperate to control the pitch angle of the satellite remote sensing camera module (9) relative to the center of the astronomical dome (2) so that the satellite remote sensing camera module (9) always performs simulated on-orbit imaging on the sand table (10); the master control machine (11) includes a control instruction transmission module and a signal reception module for controlling and acquiring the positions of the movement modules (5, 35, 7, 37); the working wavelength band of the simulated solar light source module (8) is 400 - 2500 nm, the irradiation distance is 6 - 10 m, and the spot area is 2000 * 2000 mm.

2. The satellite on-orbit observation imaging simulation device according to claim 1, wherein The horizontal movement modules (5, 35) include: - A horizontal movement frame (21); - A first control circuit box (16) fixed above the horizontal moving frame (21), which sends signals to the master control machine (11) in real time through wireless transmission and receives control instructions; - Two single-wheel support limit wheels (12) fixed below the horizontal moving frame (21) and moving on the circular tracks (3, 34); - Several auxiliary gears (17) located below the horizontal moving frame (21) and outside the circular tracks (3, 34); - Several side limit wheels (19) located inside the semi-circular tracks (6, 36) and cooperating with the auxiliary gears (17); - A first rotating gear control system (18) located between the two single-wheel support limit wheels (12) and outside the circular tracks (3, 34), the first rotating gear control system (18) is electrically connected to the first control circuit box (16), and the first rotating gear control system (18) drives the horizontal moving module (5, 35) to rotate horizontally on the circular tracks (3, 34).

3. The satellite on-orbit observation imaging simulation device according to claim 1, characterized in that, The load moving module (7, 37) includes: - A load moving frame (27), and the semi-circular tracks (6, 36) pass through the middle of the load moving module (7, 37); - A second control circuit box (38) fixed on one side of the load moving frame (27), which sends signals to the master control machine (11) in real time through wireless transmission and receives control instructions; - Four I-shaped support limit wheels (26) fixed inside the load moving frame (27) and symmetrically clamped on the four edges of the semi-circular tracks (6, 36); - A second rotating gear control system (39) fixed on the other side of the load moving frame (27), the second rotating gear control system (39) is electrically connected to the second control circuit box (38), and the second rotating gear control system (39) drives the load moving module (7, 37) to slide on the semi-circular tracks (6, 36).

4. A satellite on-orbit observation imaging simulation device according to any one of claims 2 or 3, characterized in that, The rotating gear control systems (18, 39) include gears (22), support frames (23), reducers (24) and servo motors (25), the gears (22) are engaged with the tracks (3, 34, 6, 36), the control circuit boxes (16, 38) control the operation of the servo motors (25), and the servo motors (25) drive the gears (22) to move on the tracks (3, 34, 6, 36) through the reducers (24).

5. A satellite on-orbit observation imaging simulation device according to any one of claims 3 or 4, characterized in that, The moving modules (5, 35, 7, 37) are powered by a sliding contact wire (4), and the moving modules (5, 35, 7, 37) are provided with a contact wheel (20) in contact with the sliding contact wire (4) for power supply.

6. The satellite on-orbit observation imaging simulation device according to claim 1, characterized in that The simulated solar light source module (8) is composed of several light sources (28) arranged in a matrix mode, and each light source (28) includes a light source housing (29), a halogen lamp module (30) and a xenon lamp module (31) placed inside the light source housing (29).

7. The satellite on-orbit observation imaging simulation device according to claim 6, wherein, The halogen lamp module (30) includes a lamp cover (40), a halogen lamp (32) placed inside the lamp cover, an air-cooling system (42), a reflector (43), a vent (44), and a fly-eye lens (45).

8. A satellite on-orbit observation imaging simulation device according to claim 7, characterized in that, The xenon lamp module (31) includes a lamp cover (40), a xenon lamp (33) placed inside the lamp cover, an air-cooling system (42), a reflector (43), a vent (44), a fly-eye lens (45), and a filter (41), and the bandwidth of the filter (41) is 400 - 900 nm.

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