Physical simulation demonstration device for satellite simulation

Abstract

The invention provides a physical simulation demonstration device for satellite simulation, and relates to the technical field of satellite simulation demonstration devices.The physical simulation demonstration device comprises a demonstration device base, a rotating platform is rotationally installed on the demonstration device base, and the two sides of the rotating platform are each provided with a supporting rod mechanism used for supporting a sensor; the protection plate comprises a rotating platform, the rotating platform is provided with two sets of supporting rod mechanisms, the rotating platform is provided with an ejector rod connected with the two sets of supporting rod mechanisms, the two sides of the ejector rod are each provided with a protection mechanism, and the two sides of the ejector rod are each provided with a lifting mechanism. The protection plate is prevented from shaking due to vibration or external force, it is ensured that the reflecting layer continuously and accurately simulates target characteristics, when the protection plate is stored in a vertical state, sensors such as a microwave radiometer and other precision equipment on the supporting rod mechanism can be covered and protected, damage of external dust and collision to the equipment is reduced, and the service life of the device is prolonged.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite simulation demonstration devices, and more specifically, particularly relates to a demonstration device for physical simulation in satellite simulation. Background Art

[0002] Satellite measurement and control is an important link in space engineering. A satellite measurement and control station is the basis for realizing the control of an on-orbit flying satellite, ground communication, data transmission, status monitoring, emergency repair, etc. However, the construction of a satellite measurement and control station is expensive and the conditions are complex. It can only be used for engineering applications, and it cannot be accessed by the public, let alone meet the needs of science teaching for teenagers.

[0003] Currently, for satellite simulation demonstration devices, it is found that there are at least the following technical problems: 1. In existing devices, the sensor protection and signal simulation functions are usually separated. The protection structure (such as a fixed housing) can only provide physical protection and cannot actively participate in the simulation of the reflection and scattering characteristics of satellite communication signals. The reflection components used to simulate the electromagnetic environment are mostly independent components, which need to be installed additionally and are inconvenient to adjust, and it is difficult to be linked with the protection mechanism. In addition, the operation of traditional latches and lifting mechanisms is cumbersome. Manually unfolding and storing the protection components easily leads to insufficient structural stability or equipment damage, and cannot meet the requirements of efficient, safe, and accurate scene switching in satellite simulation demonstrations.

[0004] 2. Currently, when a physical simulation demonstration device for satellite simulation is equipped with sensors (such as optical cameras, microwave radiometers, etc.) to simulate signal transmission and reception, the position adjustment mechanism of the sensors is mostly manual or a simple mechanical structure, with low adjustment accuracy and insufficient flexibility. For example, the traditional strut mechanism is difficult to achieve dynamic and accurate positioning of the sensor in the horizontal or multi-angle directions, resulting in the inability to simulate the signal transmission scenarios of the satellite in different orbits or attitudes, and restricting the simulation ability of complex space environments. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention provides a demonstration device for physical simulation in satellite simulation to solve the above problems.

[0006] The present invention provides a demonstration device for physical simulation in satellite simulation, including a demonstration device base. A rotating platform is rotatably installed on the demonstration device base. Support rod mechanisms for supporting sensors are provided on both sides of the rotating platform. A top rod connected to the two support rod mechanisms is provided on the rotating platform. Protection mechanisms are provided on both sides of the top rod. Lifting mechanisms are provided on both sides of the top rod. Locking mechanisms are provided on both sides of the top rod. The protection mechanism includes two protection plates. Both protection plates are hingedly installed on the top rod. Reflective layers are provided below the two protection plates. Triangular locking pins are fixedly installed at the separated ends of the two protection plates. A small motor is fixedly installed in the top rod. An adjustment screw rod is fixedly installed on the small motor through an output shaft. A lifting rod is installed through the adjustment screw rod in a threaded manner. The two side ends of the lifting rod are respectively connected to the two lifting mechanisms, so as to control the rising and falling of the two lifting mechanisms.

[0007] Preferably, the support rod mechanism includes a triangular support rod. A servo motor and a transverse screw rod are provided at the lower end of the triangular support rod. The servo motor is fixedly installed on the triangular support rod through a connecting plate. The servo motor is fixedly connected to the transverse screw rod through an output shaft. A movable plate is slidably sleeved on the triangular support rod. The transverse screw rod is installed through the movable plate in a threaded manner.

[0008] Preferably, a transverse adjustment plate is provided at the lower end of the movable plate. A hanger is provided at the lower end of the triangular support rod. The transverse adjustment plate is slidably installed through the hanger. The locking mechanism includes two lock block bodies. L-shaped lock holes are formed in both lock block bodies. The triangular locking pin is clamped in the L-shaped lock hole formed in the lock block body. The lifting mechanism includes two connecting rods.

[0009] Preferably, the lifting rod is fixedly installed between the two connecting rods. Connecting blocks are fixedly installed at the lower ends of the two connecting rods. T-shaped sliding grooves are formed in the side ends of the two connecting blocks. T-shaped sliding blocks are slidably installed in the T-shaped sliding grooves formed in the two connecting blocks. Extrusion support plates are fixedly installed at the side ends of the two T-shaped sliding blocks. A U-shaped unlocking block is fixedly installed between the two connecting rods.

[0010] Compared with the prior art, the present invention has the following beneficial effects: In the present invention, through the inverted hook type clamping connection between the L-shaped lock hole of the lock block body and the triangular locking pin, stable mechanical locking can be provided when the protection plate is unfolded, avoiding the shaking of the protection plate caused by vibration or external force, ensuring that the reflective layer continuously and accurately simulates the target characteristics. When the protection plate is retracted to the vertical state, it can cover and protect sensors such as microwave radiometers and other precision equipment on the support rod mechanism, reducing the damage of external dust and collision to the equipment and extending the service life of the device.

[0011] In the present invention, a reflective layer is provided below the protective plate of the protection mechanism. When unfolded, the special surface formed by the electroplating process can simulate different reflectivities and scattering rates, constructing a real scenario of signal reflection and scattering in satellite communication, such as the signal transmission between a ground base station and a satellite. Cooperating with the engagement of the triangular locking pin of the locking mechanism with the L-shaped locking hole, it ensures that the protective plate is stably in a parallel state, providing a reliable physical simulation environment for the optimization and testing of the satellite communication system.

[0012] Through the cooperation of the servo motor and the transverse screw in the support rod mechanism, the movable plate is driven to slide along the triangular support rod, thereby driving the sensors on the transverse adjustment plate, such as optical cameras, microwave radiometers, etc., to adjust their transverse positions. This structure can achieve high-precision dynamic adjustment of the sensor positions, meet the test requirements of different signal transmission and reception angles in satellite simulation, and improve the scene adaptability of the demonstration device.

[0013] In the present invention, a small motor in the ejector rod drives the adjustment screw to rotate, driving the lifting rod to link the connecting rod and the extrusion support plate, realizing the automatic unfolding and storage of the protective plate. When unfolded, the trapezoidal extrusion support plate pushes the protective plate to flip through the inclined surface; when storing, the U-shaped unlocking block presses down to unlock the triangular locking pin, eliminating the need for manual operation, reducing the risk of human intervention, and improving the convenience and safety of using the device.

[0014] In the present invention, the ejector rod connects the support rod mechanism, the protection mechanism, the lifting mechanism and the locking mechanism. Each module has a clear division of labor and is interconnected: the support rod mechanism supports and adjusts the sensors, the protection mechanism simulates the electromagnetic environment, the lifting and locking mechanisms control the protection state. At the same time, precision devices such as signal generators and data collectors integrated at the upper end of the rotating platform (the signal generators, controllers, etc. mentioned in the document) can interact with external systems through communication modules, facilitating the subsequent expansion of functional modules for satellite simulation, such as adding new sensor types or signal processing algorithms, to meet diverse scientific research and teaching needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is the overall structural schematic diagram of the present invention; Figure 2 is the structural schematic diagram of the protective plate of the present invention; Figure 3 is the structural schematic diagram of the base of the demonstration device of the present invention; Figure 4 is the structural schematic diagram of the triangular support rod of the present invention; Figure 5 is the structural schematic diagram of the ejector rod of the present invention; Figure 6 is the structural schematic diagram of the lifting rod of the present invention; Figure 7 is the structural schematic diagram of the connecting rod of the present invention; Figure 8 is the enlarged schematic view of the structure at position A of the present invention Figure 5 ; Figure 9 is the enlarged schematic view of the structure at position B of the present invention Figure 1 ; Figure 10 is the schematic view of the extrusion support plate structure of the present invention

[0016] In the figure, the corresponding relationship between the component names and the drawing reference numbers is as follows: 11, extrusion support plate; 12, connecting block; 13, connecting rod; 14, U-shaped unlocking block; 15, T-shaped slider; 16, T-shaped chute; 21, ejector rod; 22, lock block body; 23, L-shaped lock hole; 24, placement groove; 25, small motor; 26, adjusting screw; 27, lifting rod; 28, reflective layer; 29, protective plate; 31, triangular support rod; 32, transverse screw; 33, servo motor; 34, transverse adjustment plate; 36, hanger; 37, movable plate; 38, demonstration device base; 39, rotating platform; 41, triangular locking pin Specific embodiments

[0017] The following further describes the embodiments of the present invention in detail with reference to the drawings and embodiments. The following embodiments are used to illustrate the present invention, but cannot be used to limit the scope of the present invention

[0018] Please refer to Figure 1 - Figure 10 , the present invention provides a demonstration device for physical simulation in satellite simulation, including a demonstration device base 38, a rotating platform 39 is rotatably installed on the demonstration device base 38, support rod mechanisms for supporting sensors are provided on both sides of the rotating platform 39, the support rod mechanisms are used to support the sensors for simulating the operation of the satellite, and a structure for adjusting the sensors is further provided in the two support rod mechanisms. An ejector rod 21 connected to the two support rod mechanisms is provided on the rotating platform 39. Protective mechanisms are provided on both sides of the ejector rod 21. Lifting mechanisms are provided on both sides of the ejector rod 21. The lifting mechanisms are used for opening and closing the protective mechanisms. Locking mechanisms are provided on both sides of the ejector rod 21 The protection mechanism includes two protection plates 29, both of the two protection plates 29 are hingedly installed on the ejector rod 21, a reflection layer 28 is provided below each of the two protection plates 29, and triangular locking pins 41 are fixedly installed at the separated ends of the two protection plates 29. Among them, the number of protection plates 29 in the two groups of protection mechanisms is four, which are respectively located on the front and back sides of both ends of the ejector rod 21. The reflection layer 28 is arranged below the protection plate 29 through electroplating technology. The protection mechanism can be contracted and expanded. When contracted, it can protect the two groups of support rod mechanisms and the sensors inside them. When expanded, due to the special materials or surface treatments used in the protection mechanism, it can simulate targets with different reflectivities and scattering rates, and is used for the research on the reflection and scattering characteristics of satellite communication signals, assisting in the optimization and testing of satellite communication systems. For example, it can simulate the signal transmission between a ground communication base station and a satellite under different scenarios; A small motor 25 is fixedly installed inside the ejector rod 21. An adjusting screw rod 26 is fixedly installed on the small motor 25 through an output shaft. A lifting rod 27 is installed through the adjusting screw rod 26 in a threaded manner. Both side ends of the lifting rod 27 are respectively connected to the two groups of lifting mechanisms, so as to control the rising and falling of the two groups of lifting mechanisms.

[0019] In this embodiment, as Figure 1 、 Figure 2 shown, the upper end of the rotating platform 39 is composed of a multi-processor real-time simulation module, a dynamics model module, a remote control instruction processing module, a sensor simulation module, and a data relay communication module: Among them, the multi-processor architecture: ARM (responsible for control algorithms), DSP (responsible for complex calculations), and FPGA (responsible for high-speed data sharing and synchronization) work together. For example, ARM1 runs the PID algorithm as the control center, DSP1 / DSP2 respectively process the sensor and actuator models, and FPGA realizes real-time data interaction through the FIFO technology.

[0020] The dynamics model: includes orbital dynamics, attitude dynamics, and celestial body models, and is used to simulate the on-orbit motion state of the satellite and external environmental perturbations (such as earth gravity, atmospheric drag, etc.).

[0021] The communication interface: supports protocols such as 1553B bus, CAN bus, and RS422, simulates the communication link between satellite subsystems, and realizes the issuance of remote control instructions and the return of telemetry data.

[0022] In this embodiment, as Figure 1 、 Figure 2 、 Figure 3 、 Figure 4As shown in the figure, the support rod mechanism includes a triangular support rod 31. A servo motor 33 and a transverse screw rod 32 are provided at the lower end of the triangular support rod 31. The servo motor 33 is fixedly installed on the triangular support rod 31 through a connecting plate. The servo motor 33 is fixedly connected to the transverse screw rod 32 through an output shaft. A movable plate 37 is slidably sleeved on the triangular support rod 31. The transverse screw rod 32 is installed through the movable plate 37 by means of a thread. A transverse adjusting plate 34 is provided at the lower end of the movable plate 37. A hanging bracket 36 is provided at the lower end of the triangular support rod 31. The transverse adjusting plate 34 is slidably installed through the hanging bracket 36. Various sensors (such as an optical camera, a microwave radiometer, etc.) carried by the simulated satellite emit energy to the target scene on the transverse adjusting plate 34. For example, the optical sensor simulates the emission of electromagnetic waves such as visible light and infrared light, and the microwave sensor simulates the emission of microwave signals. In the support rod mechanism, the structure for adjusting the sensors is the combination of the servo motor 33 and the transverse screw rod 32. When it is necessary to adjust various sensors, the servo motor 33 can be controlled to work. The servo motor 33 drives the transverse screw rod 32 to rotate through the output shaft. The transverse screw rod 32 can control the movement of the transverse adjusting plate 34 through the threaded connection with the movable plate 37, so as to adjust the position of the sensors on the transverse adjusting plate 34. The hanging bracket 36 can provide good support for the transverse adjusting plate 34.

[0023] In this embodiment, as Figure 1 , Figure 2 , Figure 5 , Figure 8 , Figure 9 As shown in the figure, the lock mechanism includes two lock block bodies 22. L-shaped lock holes 23 are formed in both of the two lock block bodies 22. Since the shape of the triangular lock pin 41 is in the shape of an inverted hook, when the protective plate 29 is flipped to the parallel state, the triangular lock pin 41 will directly insert into the L-shaped lock hole 23 formed in the lock block body 22. The L-shaped lock hole 23 formed in the lock block body 22 is an L-shaped hole, so the triangular lock pin 41 can be engaged with the L-shaped lock hole 23 formed in the lock block body 22, so as to fix the protective plates 29 in the two groups of protection mechanisms, making them parallel to the upper end of the ejector rod 21. Then, through the reflective layer 28 electroplated at the lower end of the protective plate 29, targets with different reflectivities and scattering rates are simulated for the research on the reflection and scattering characteristics of satellite communication signals, and to assist in the optimization and testing of the satellite communication system.

[0024] In this embodiment, as Figure 1 , Figure 2 , Figure 7 , Figure 8 , Figure 9 , Figure 10As shown, the lifting mechanism includes two connecting rods 13, the lower ends of the two connecting rods 13 are fixedly installed with connecting blocks 12, the side ends of the two connecting blocks 12 are provided with T-shaped slots 16, the T-shaped slide blocks 15 are slidably installed in the T-shaped slots 16 provided in the two connecting blocks 12, and the side ends of the two T-shaped slide blocks 15 are fixedly installed with extrusion support plates 11. Since the shape of the extrusion support plate 11 is trapezoidal, and in the initial state, the extrusion support plate 11 is in the placement groove 24 provided by the top rod 21, when the two connecting rods 13 move upward, the connecting rod 13 will drive the connecting blocks 12, the T-shaped slide blocks 15 and the extrusion support plate 11 to move upward. Since the upper end of the extrusion support plate 11 is an inclined surface, it can move upward between the protective plate 29 and the top rod 21, and the trapezoidal shape of the extrusion support plate 11 will squeeze the protective plate 29 to make it move upward. When the support plate 11 is squeezed and moved to the vertex position, the protective plate 29 is in a parallel state, and the triangular locking pin 41 on the protective plate 29 is engaged with the L-shaped locking hole 23 provided in the locking block body 22, so that the protective plate 29 can be unfolded. A U-shaped unlocking block 14 is fixedly installed between the two connecting rods 13. When the installed protective plate 29 needs to be stored, the two connecting rods 13 are controlled to move downward, thereby driving the U-shaped unlocking block 14 to move downward, and the triangular locking pin 41 in the L-shaped locking hole 23 provided in the locking block body 22 can be squeezed to make it escape from the L-shaped locking hole 23 provided in the locking block body 22, so that the two protective plates 29 can be stored, and the two protective plates 29 can be flipped from the parallel state to the vertical state. When the protective plate 29 is in the vertical state, some sensors on the triangular support rod 31 can be protected.

[0025] Working principle: Core workflow of electronic core components: 1. Initialization and command input After power-on, each processor completes initialization and waits for remote control command input. The user sets simulation parameters (such as initial orbit, attitude angle, control mode, etc.) through the host computer, and the remote control command is sent to the dynamic simulation component through the communication interface (such as RS422). After analysis, the corresponding simulation unit (such as actuator or sensor) is triggered to respond.

[0026] 2. Sensor data simulation DSP1 generates sensor data (such as the attitude angle of the sun sensor and the angular velocity of the gyroscope) according to the dynamic model and shares it to ARM1 through FIFO. The sensor data includes ephemeris, environmental perturbation parameters, etc., which are used to update the current status of the satellite.

[0027] 3. Control algorithm execution and instruction generation ARM1 calculates attitude adjustment instructions based on the PID algorithm. If the parameters do not meet the requirements, it sends control instructions (such as the torque value of the magnetic torque actuator) to DSP2. DSP2 simulates the actions of the actuators (such as the change in the speed of the reaction wheel), and feeds back the results to update the satellite state in the dynamic model.

[0028] 4. Closed-loop Verification and Data Monitoring The simulation platform realizes the closed-loop transmission of control instructions and telemetry data through a data transfer module (such as TCP / IP or RS422 protocol) to ensure the real-time performance of the control logic. The host computer displays data such as attitude angles and orbit parameters in real time, and supports fault injection (such as sensor noise, communication interruption) to verify the robustness of the system.

[0029] The key technical features of the electronic core components are as follows: 1. Real-time Performance and Synchronous Control The FPGA uses the FIFO technology to achieve zero-waiting data transmission between multiple processors, and coordinates the timing logic to avoid simulation chaos. The dynamic simulation step size can reach the 10ms level, meeting the requirements of high-precision control.

[0030] 2. Model Flexibility and Expandability It supports switching different orbit parameters, types of sensors (such as star sensors / earth sensors), and actuator models through configuration files. Adopting a modular design, it can adapt to the simulation requirements of satellites in different orbits such as LEO and GEO.

[0031] 3. Multi-physical-field Coupled Simulation Combined with celestial dynamics tools such as STK to simulate the satellite orbit, and at the same time integrate physical layer models such as antenna patterns and signal attenuation to evaluate the reliability of the communication link.

[0032] The core work process of the mechanical components: In the first step, if it is necessary to adjust the position of the simulated satellite sensors (such as optical cameras, microwave radiometers, etc.) mounted on the lateral adjustment plate 34, start the servo motor 33. The servo motor 33 drives the lateral screw 32 to rotate through the output shaft. Since the lateral screw 32 is installed on the movable plate 37 through threads, and the lower end of the movable plate 37 is provided with a lateral adjustment plate 34, and the lower end of the triangular support rod 31 is provided with a hanging bracket 36, and the lateral adjustment plate 34 is slidably installed through the hanging bracket 36, when the lateral screw 32 rotates, the movable plate 37 will slide up and down along the triangular support rod 31, thereby driving the lateral adjustment plate 34 to move, realizing precise adjustment of the sensor position.

[0033] Step 2: When it is necessary to deploy the protective plate 29 for experiments such as studying the reflection and scattering characteristics of satellite communication signals, start the small motor 25 inside the ejector rod 21. The small motor 25 drives the adjusting screw rod 26 to rotate through the output shaft. The lifting rod 27 installed through the thread on the adjusting screw rod 26 will rise with the rotation of the adjusting screw rod 26. Both side ends of the lifting rod 27 are connected to two sets of lifting mechanisms. At this time, the rising of the lifting rod 27 will drive the two connecting rods 13 to move upward. A connecting block 12 is fixedly installed at the lower end of the connecting rod 13. A T-shaped sliding groove 16 is opened on the side end of the connecting block 12. A T-shaped sliding block 15 is slidably installed in the T-shaped sliding groove 16. An extrusion support plate 11 is fixedly installed at the side end of the T-shaped sliding block 15. In the initial state, the extrusion support plate 11 is located in the placement groove 24 opened on the ejector rod 21. As the connecting rod 13 moves upward, the extrusion support plate 11 will also move upward. Since the upper end of the extrusion support plate 11 is an inclined surface, when moving between the protective plate 29 and the ejector rod 21, it uses its trapezoidal shape to extrude the protective plate 29, causing the protective plate 29 to flip upward. When the extrusion support plate 11 moves upward to the vertex position, the protective plate 29 is in a parallel state. At this time, the triangular locking pin 41 fixedly installed at the separated end of the protective plate 29 will be inserted into the L-shaped locking hole 23 opened on the lock block body 22, completing the deployment and fixation of the protective plate 29. The reflection layer 28 below the protective plate 29 can simulate targets with different reflectivities and scattering rates for related research and tests.

[0034] Step 3: After the protective plate 29 is deployed, the signal generator on the upper end of the rotating platform 39 generates analog signals with different frequencies and waveforms to simulate the electromagnetic wave signals emitted by satellite sensors; the signal receiver receives the simulated reflected or radiated signals and performs preprocessing such as amplification and filtering; the data collector converts the analog signals processed by the signal receiver into digital signals and collects and stores them; the controller controls the operation of each component of the satellite remote sensing simulation platform according to external instructions; the computer host runs simulation software to process and analyze the collected data and execute various remote sensing algorithms; the power supply provides stable power for each electronic device inside the platform; the communication module realizes data transmission and communication between the platform and external devices, jointly completing the satellite simulation demonstration work.

[0035] Step 4: When the demonstration ends or it is necessary to protect the equipment, start the small motor 25 again to make it reverse, driving the adjusting screw rod 26 to reverse, and the lifting rod 27 will descend accordingly, thereby driving the two connecting rods 13 to move downward. The U-shaped unlocking block 14 fixedly installed between the connecting rods 13 will move downward with the connecting rods 13. During the downward movement of the U-shaped unlocking block 14, it squeezes the triangular locking pin 41 located in the L-shaped locking hole 23 opened on the lock block body 22, causing the triangular locking pin 41 to disengage from the L-shaped locking hole 23. At this time, the protective plate 29 loses its locking and flips from the parallel state to the vertical state under the action of gravity, protecting components such as the sensors on the triangular support rod 31.

[0036] Step 5: Turn off various precision devices and sorting devices on the upper end of the rotating platform 39 to get ready for the next use.

[0037] The embodiments of the present invention are provided for purposes of illustration and description, and are not intended to be exhaustive or to limit the invention to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are chosen and described in order to best explain the principles of the invention and its practical application, and to enable those of ordinary skill in the art to understand the invention and design various embodiments with various modifications suitable for specific purposes.

Claims

1. A physical simulation demonstration device for satellite simulation, comprising a demonstration device base (38), characterized in that: A rotating platform (39) is rotatably mounted on the demonstration device base (38), support rod mechanisms for supporting sensors are provided on both sides of the rotating platform (39), a top rod (21) connected to two groups of support rod mechanisms is provided on the rotating platform (39), protective mechanisms are provided on both sides of the top rod (21), lifting mechanisms are provided on both sides of the top rod (21), and locking mechanisms are provided on both sides of the top rod (21); The protective mechanism comprises two protective plates (29), the two protective plates (29) are hingedly mounted on the top rod (21), a reflective layer (28) is provided below the two protective plates (29), and triangular locking pins (41) are fixedly mounted on the separated ends of the two protective plates (29). A small motor (25) is fixedly mounted inside the top rod (21), an adjusting screw (26) is fixedly mounted on the small motor (25) via an output shaft, a lifting rod (27) is threadedly mounted on the adjusting screw (26), and both side ends of the lifting rod (27) are respectively connected to the two sets of lifting mechanisms, so that the rise and fall of the two sets of lifting mechanisms can be controlled.

2. A satellite simulation demonstration device as claimed in claim 1, characterized in that: The support rod mechanism comprises a triangular support rod (31), a servo motor (33) and a transverse screw rod (32) are provided at the lower end of the triangular support rod (31), and the servo motor (33) is fixedly mounted on the triangular support rod (31) via a connecting plate.

3. A satellite simulation demonstration device as claimed in claim 2, characterized in that: The servo motor (33) is fixedly connected to the transverse screw rod (32) via an output shaft, and a movable plate (37) is slidably sleeved on the triangular support rod (31).

4. A satellite simulation demonstration device as claimed in claim 3, characterized in that: The transverse screw rod (32) is installed on the movable plate (37) by means of a threaded penetration, and a transverse adjustment plate (34) is provided at the lower end of the movable plate (37).

5. A satellite simulation demonstration device as claimed in claim 4, characterized in that: A hanger (36) is provided at the lower end of the triangular support rod (31), and the transverse adjustment plate (34) is slidably installed in the hanger (36).

6. A satellite simulation demonstration device as claimed in claim 5, characterized in that: The locking mechanism comprises two locking block bodies (22), each of which is provided with an L-shaped locking hole (23), and the triangular locking pin (41) is snap-engaged in the L-shaped locking hole (23) provided in the locking block body (22).

7. A satellite simulation demonstration device as claimed in claim 6, characterized in that: The lifting mechanism comprises two connecting rods (13), and the lifting rod (27) is fixedly mounted between the two connecting rods (13).

8. A satellite simulation demonstration device as claimed in claim 7, characterized in that: A connecting block (12) is fixedly mounted on the lower ends of the two connecting rods (13), and a T-shaped sliding groove (16) is provided on the side ends of the two connecting blocks (12).

9. A satellite simulation demonstration device as claimed in claim 8, characterized in that: T-shaped sliding blocks (15) are slidably mounted in the T-shaped sliding grooves (16) formed in the two connecting blocks (12).

10. A physical simulation demonstration device for satellite simulation as claimed in claim 9, characterized in that: An extrusion support plate (11) is fixedly mounted on the side ends of the two T-shaped slide blocks (15), and a U-shaped unlocking block (14) is fixedly mounted between the two connecting rods (13).

Images