A demonstration device for physical simulation in satellite simulation

Abstract

The present invention provides a demonstration device for physical simulation in satellite simulation, which relates to the technical field of satellite simulation demonstration devices. It includes a demonstration device base, on which a rotating platform is rotatably installed. On both sides of the rotating platform, there are support rod mechanisms for supporting sensors. On the rotating platform, there is a top rod connected to the two groups of support rod mechanisms. On both sides of the top rod, there are protection mechanisms, and on both sides of the top rod, there are lifting mechanisms. In the present invention, through the L-shaped lock hole of the lock block body and the barb-like clamping connection of the triangular lock 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 reflection layer continuously and accurately simulates the target characteristics. When the protection plate is retracted to the vertical state, it can cover and protect sensors on the support rod mechanism, such as precision equipment like microwave radiometers, reducing the damage to the equipment caused by external dust and collisions, and extending the service life of the device.

Description

Technical Field

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

[0002] Satellite tracking and control is an important part of aerospace engineering. Satellite tracking and control stations are the basis for in-orbit satellite control, ground communication, data transmission, status monitoring, emergency maintenance and other tasks. However, the construction of satellite tracking and control stations is expensive and the conditions are complex. They can only be used in engineering applications, but cannot be accessed by the public, let alone meet the needs of scientific education for young people.

[0003] At present, the satellite simulation demonstration device has been found to have at least the following technical problems:

[0004] 1. Existing devices usually separate sensor protection from signal simulation functions. The protective structure (such as a fixed shell) can only provide physical protection and cannot actively participate in the simulation of the reflection and scattering characteristics of satellite communication signals. The reflective components used to simulate the electromagnetic environment are mostly independent components, which require additional installation and are inconvenient to adjust, making it difficult to link with the protective mechanism. In addition, the traditional lock and lifting mechanism is cumbersome to operate, and the manual deployment and storage of protective components can easily lead to insufficient structural stability or equipment damage, which cannot meet the requirements of efficient, safe, and accurate scene switching in satellite simulation demonstrations.

[0005] 2. At present, when satellite simulation physical simulation demonstration devices are equipped with sensors (such as optical cameras, microwave radiometers, etc.) to simulate signal transmission and reception, the sensor position adjustment mechanism is mostly manual or simple mechanical structure, with low adjustment accuracy and insufficient flexibility. For example, traditional support rod mechanisms make it difficult to achieve dynamic and accurate positioning of sensors in the horizontal or multi-angle direction, resulting in the inability to simulate signal transmission scenarios of satellites in different orbits or attitudes, limiting the simulation capabilities of complex space environments. Summary of the invention

[0006] In order to solve the above technical problems, the present invention provides a demonstration device for physical simulation of satellite simulation to solve the above problems.

[0007] The present invention provides a demonstration device for physical simulation in satellite simulation, including a base of the demonstration device. A rotating platform is rotatably installed on the base of the demonstration device. 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 of the two 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 adjusting screw rod is fixedly installed on the small motor through an output shaft. A lifting rod is installed through the adjusting screw rod by threads. 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.

[0008] 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 by threads.

[0009] Preferably, a transverse adjusting 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 adjusting plate is slidably installed through the hanger. The locking mechanism includes two lock block bodies. L-shaped lock holes are formed in both of the two 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.

[0010] 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.

[0011] Compared with the prior art, the present invention has the following beneficial effects:

[0012] In the present invention, through the inverted hook type clamping of 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 on the support rod mechanism, such as precision equipment like microwave radiometers, reducing the damage of external dust and collisions to the equipment and extending the service life of the device.

[0013] In the present invention, a reflective layer is provided below the protective plate of the protection mechanism. When unfolded, it can simulate different reflectivities and scattering rates through a special surface formed by electroplating technology, constructing a real scenario of signal reflection and scattering in satellite communication, such as signal transmission between a ground base station and a satellite. Cooperating with the triangular locking pin of the locking mechanism to be engaged 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 satellite communication systems.

[0014] Through the cooperation of the servo motor and the transverse screw in the strut 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.

[0015] In the present invention, a small motor in the ejector rod is used to drive 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 device use.

[0016] In the present invention, the ejector rod connects the strut mechanism, the protection mechanism, the lifting mechanism and the locking mechanism. Each module has a clear division of labor and is interconnected: the strut 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 integrated at the upper end of the rotating platform, such as signal generators and data collectors 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. Description of the Drawings

[0017] Figure 1 is the overall structural schematic diagram of the present invention;

[0018] Figure 2 is the structural schematic diagram of the protective plate of the present invention;

[0019] Figure 3 is the structural schematic diagram of the base of the demonstration device of the present invention;

[0020] Figure 4 is the structural schematic diagram of the triangular support rod of the present invention;

[0021] Figure 5 is the structural schematic diagram of the ejector rod of the present invention;

[0022] Figure 6It is a schematic structural diagram of the lifting rod of the present invention;

[0023] Figure 7 It is a schematic structural diagram of the connecting rod of the present invention;

[0024] Figure 8 It is the present invention Figure 5 A magnified schematic diagram of the structure at position A;

[0025] Figure 9 It is the present invention Figure 1 A magnified schematic diagram of the structure at position B;

[0026] Figure 10 It is a schematic structural diagram of the extrusion support plate of the present invention.

[0027] In the figure, the corresponding relationship between the component names and the attached drawing 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 sliding groove; 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, protection plate; 31, triangular support rod; 32, transverse screw; 33, servo motor; 34, transverse adjustment plate; 36, hanging bracket; 37, movable plate; 38, demonstration device base; 39, rotating platform; 41, triangular locking pin. Specific embodiments

[0028] The following further describes in detail the embodiments of the present invention with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention, but cannot be used to limit the scope of the present invention.

[0029] 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, a ejector rod 21 connected to the two support rod mechanisms is provided on the rotating platform 39, protection 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 protection mechanisms, and locking mechanisms are provided on both sides of the ejector rod 21;

[0030] The protection mechanism includes two protection plates 29, both of which are hingedly installed on the top rod 21. A reflective layer 28 is provided below each of the two protection plates 29. 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 rear sides of both ends of the top rod 21. The reflective 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 strut 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 reflectivity 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;

[0031] A small motor 25 is fixedly installed inside the top rod 21. An adjustment screw rod 26 is fixedly installed on the small motor 25 through an output shaft. A lifting rod 27 is installed through the adjustment 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.

[0032] 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 transfer and communication module:

[0033] 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.

[0034] Dynamics model: It 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.).

[0035] Communication interface: It 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.

[0036] 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 adjustment 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 adjustment 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 adjustment 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 adjustment plate 34 through the threaded connection with the movable plate 37, so as to adjust the position of the sensors on the transverse adjustment plate 34. The hanging bracket 36 can provide good support for the transverse adjustment plate 34.

[0037] 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 complete the clamping 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 on 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.

[0038] 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.

[0039] Working principle:

[0040] Core workflow of electronic core components:

[0041] 1. Initialization and command input

[0042] 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.

[0043] 2. Sensor data simulation

[0044] 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.

[0045] 3. Control algorithm execution and instruction generation

[0046] ARM1 calculates the attitude adjustment instruction based on the PID algorithm. If the parameters do not meet the requirements, it sends a control instruction (such as the torque value of the magnetic torquer) to DSP2. DSP2 simulates the actions of the actuator (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.

[0047] 4. Closed-loop Verification and Data Monitoring

[0048] 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 and communication interruption) to verify the robustness of the system.

[0049] The key technical features of the electronic core components are as follows:

[0050] 1. Real-time Performance and Synchronous Control

[0051] 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.

[0052] 2. Model Flexibility and Expandability

[0053] 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.

[0054] 3. Multi-physical-field Coupled Simulation

[0055] 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.

[0056] The core workflow of the mechanical components:

[0057] In the first step, if it is necessary to adjust the position of the simulated satellite sensors (such as optical cameras, microwave radiometers, etc.) carried 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 through the thread on the movable plate 37, 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 hanger 36, and the lateral adjustment plate 34 is installed through and slidably in the hanger 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 the precise adjustment of the sensor position.

[0058] In the second step, when it is necessary to unfold the protective plate 29 to conduct experiments such as research on reflection and scattering characteristics of satellite communication signals, the small motor 25 in the top rod 21 is started. The small motor 25 drives the adjusting screw 26 to rotate through the output shaft. The lifting rod 27 installed on the adjusting screw 26 through a thread will rise with the rotation of the adjusting screw 26. The two side ends of the lifting rod 27 are connected to the two sets of lifting mechanisms. At this time, the rise of the lifting rod 27 will drive the two connecting rods 13 to move upward. The lower end of the connecting rod 13 is fixedly installed with a connecting block 12, and the side end of the connecting block 12 is provided with a T-shaped slide groove 16. The T-shaped slider 15 is slidably installed in the T-shaped slide groove 16. The side end of the T-shaped slider 15 is fixedly installed with the extrusion support plate 11. In the initial state, the extrusion The support plate 11 is in the placement groove 24 opened by the top rod 21. As the connecting rod 13 moves upward, the extruded support plate 11 will also move upward. Since the upper end of the extruded support plate 11 is an inclined surface, when it moves upward between the protective plate 29 and the top rod 21, its trapezoidal shape is used to squeeze the protective plate 29, so that the protective plate 29 flips upward. When the extruded support plate 11 moves 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 in the locking block body 22, completing the deployment and fixation of the protective plate 29. The reflective layer 28 under the protective plate 29 can simulate targets with different reflectivity and scattering rates for related research and testing.

[0059] In the third step, after the protective plate 29 is unfolded, the signal generator on the top of the rotating platform 39 generates analog signals of different frequencies and waveforms to simulate the electromagnetic wave signals emitted by the satellite sensor; the signal receiver receives the simulated reflected or radiated signals and performs pre-processing 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 various components of the satellite remote sensing simulation platform according to external instructions; the computer host runs the simulation software, processes and analyzes the collected data, and executes various remote sensing algorithms; the power supply provides stable power for various electronic equipment in the platform; the communication module realizes data transmission and communication between the platform and external equipment, and jointly completes the satellite simulation demonstration work.

[0060] The fourth step, when the demonstration is over or the equipment needs to be protected, start the small motor 25 again to reverse it, drive the adjusting screw 26 to reverse, and the lifting rod 27 will drop accordingly, thereby driving the two connecting rods 13 to move downward, and 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, the triangular locking pin 41 in the L-shaped locking hole 23 opened in the locking block body 22 is squeezed, so that the triangular locking pin 41 is disengaged from the L-shaped locking hole 23. At this time, the protective plate 29 loses its lock and flips from a parallel state to a vertical state under the action of gravity, thereby protecting the sensors and other components on the triangular support rod 31.

[0061] Step 5: Turn off various precision devices and sorting devices at the upper end of the rotating platform 39 to get ready for the next use.

[0062] The embodiments of the present invention are given 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 a particular purpose.

Claims

1. A demonstration device for physical simulation in satellite simulation, comprising a demonstration device base (38), characterized in that: A rotating platform (39) is rotatably mounted on the base (38) of the demonstration device. Support rod mechanisms for supporting sensors are provided on both sides of the rotating platform (39). A push rod (21) connected to the two support rod mechanisms is provided on the rotating platform (39). Protection mechanisms are provided on both sides of the push rod (21). Lifting mechanisms are provided on both sides of the push rod (21). Locking mechanisms are provided on both sides of the push rod (21). Among them, the protection mechanism includes two protection plates (29). The two protection plates (29) are both hinged to the push rod (21). Reflective layers (28) are provided below the two protection plates (29). Triangular locking pins (41) are fixedly installed at the separated ends of the two protection plates (29). A small motor (25) is fixedly installed in the push 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) by means of a thread. The two side ends of the lifting rod (27) are respectively connected to the two lifting mechanisms, so as to control the rising and falling of the two lifting mechanisms.

2. The demonstration device for physical simulation in satellite simulation according to claim 1, wherein, 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.

3. The demonstration device for physical simulation in satellite simulation according to claim 2, characterized in that, 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).

4. The demonstration device for physical simulation in satellite simulation according to claim 3, wherein 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).

5. The demonstration device for physical simulation in satellite simulation according to claim 4, wherein A hanger (36) is provided at the lower end of the triangular support rod (31). The transverse adjusting plate (34) is slidably installed through the hanger (36).

6. The demonstration device for physical simulation in satellite simulation according to claim 5, characterized in that, The locking mechanism includes two lock block bodies (22). L-shaped lock holes (23) are formed in the two lock block bodies (22). The triangular locking pin (41) is clamped in the L-shaped lock hole (23) formed in the lock block body (22).

7. The demonstration device for physical simulation in satellite simulation according to claim 6, wherein, The lifting mechanism includes two connecting rods (13). The lifting rod (27) is fixedly installed between the two connecting rods (13).

8. The demonstration device for physical simulation in satellite simulation according to claim 7, characterized in that, Connecting blocks (12) are fixedly installed at the lower ends of the two connecting rods (13). T-shaped sliding grooves (16) are formed in the side ends of the two connecting blocks (12).

9. The demonstration device for physical simulation in satellite simulation according to claim 8, characterized in that, T-shaped sliding blocks (15) are slidably installed in the T-shaped sliding grooves (16) formed in the two connecting blocks (12).

10. The demonstration device for physical simulation in satellite simulation according to claim 9, characterized in that, Extrusion support plates (11) are fixedly installed at the side ends of the two T-shaped sliding blocks (15). A U-shaped unlocking block (14) is fixedly installed between the two connecting rods (13).

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