Spacecraft TT&C model

Abstract

The application provides a spaceflight measurement and control model, and relates to the technical field of spaceflight popular science. The spaceflight measurement and control model comprises an exhibition stand and a backboard. The first surface of the backboard is provided with a running track line. An orbit assembly is located on the side where the first surface is located. The orbit assembly comprises two groups of first and second orbit assemblies. The first orbit assembly comprises a first guide rail and a first moving part. The second orbit assembly comprises a second guide rail and a second moving part. A satellite model assembly is installed on the second moving part. The satellite model assembly comprises a plurality of functional modules for acquiring detection signals. A ground station model assembly is signal connected with the satellite model assembly. The ground station model assembly is used for receiving detection signals and acquiring position signals of the satellite model assembly. The ground station model assembly can adjust the azimuth and elevation angles of the antenna group based on the position signals of the satellite model assembly.

Description

Technical Field

[0001] This application relates to the field of aerospace science popularization technology, and in particular to an aerospace measurement and control model. Background Technology

[0002] The 2016 "Space White Paper" pointed out that exploring outer space expands our understanding of the Earth and the universe, meets the needs of economic development, scientific and technological advancement, national security, and social progress, improves the scientific and cultural literacy of the entire population, safeguards national interests, and enhances comprehensive national strength. It also emphasizes actively organizing a series of activities for "China Space Day" and fully utilizing platforms such as "World Space Week" and "National Science and Technology Week" to vigorously promote space science education, popularize space knowledge, publicize space culture, and carry forward the spirit of space exploration. This aims to inspire the enthusiasm of the entire population, especially young people, for science, exploration of the unknown, and innovation, and attract more outstanding talents to dedicate themselves to the space industry.

[0003] In existing technologies, popularizing knowledge about aerospace telemetry and control mainly includes the following approaches: First, aerospace telemetry and control popular science software, which is converted from aerospace telemetry and control application software. The overall interface presents knowledge with a high level of difficulty, making it difficult for users to understand. Second, CubeSats, which are small satellites widely used internationally in universities for aerospace scientific research and education. As a type of spacecraft, satellites are the data source for ground-based telemetry and control objects and ground application systems, and are an indispensable part of aerospace telemetry and control popular science. However, a single satellite is difficult to systematically demonstrate the entire aerospace telemetry and control system, and lacks systematicity. Third, Yagi antennas, which are end-fire antennas composed of an active dipole, a passive reflector, and several passive directors arranged in parallel. They can receive detection signals and are widely used among radio enthusiasts. They are one of the easiest devices for teenagers to experience aerospace telemetry and control. However, the use of Yagi antennas is limited by geographical conditions and the surrounding environment, and they are easily affected by external interference, resulting in poor overall operability.

[0004] Therefore, current teaching aids for popularizing aerospace telemetry and control knowledge suffer from problems such as high difficulty, lack of systematicity, and poor operability. How to provide an aerospace telemetry and control model that can demonstrate the aerospace telemetry and control process, popularize aerospace knowledge, and is less difficult, more systematic, and more operable is an urgent technical problem to be solved. Summary of the Invention

[0005] The purpose of this application is to provide an aerospace telemetry and control model to solve the technical problems of current teaching aids for popularizing aerospace telemetry and control knowledge being difficult, lacking systematicity, and having poor operability.

[0006] To address the aforementioned technical problems, this application provides the following technical solutions:

[0007] The first aspect of this application provides an aerospace telemetry and control model, which includes: a display stand and a back panel, wherein the back panel is vertically disposed on the top surface of the display stand, and a running trajectory line is disposed on the first surface of the back panel;

[0008] The track assembly, located on one side of the first surface, includes: two sets of first-direction track groups and a second-direction track group. The two sets of first-direction track groups are disposed on the top side of the booth and are respectively located on opposite sides of the first surface of the back panel in a first direction. The first-direction track group includes: a first guide rail and a first moving member. The second-direction track group includes: a second guide rail and a second moving member.

[0009] Wherein, the first guide rail extends longitudinally, the first moving member is movably disposed on the first guide rail, the second guide rail extends along the first direction and connects between the two first moving members of the two sets of first direction rail groups, and the second moving member is movably disposed on the second guide rail.

[0010] A satellite model component is installed on the second movable component. The satellite model component includes multiple functional modules for acquiring detection signals.

[0011] A ground station model component is installed on the top surface of the booth and is located on the same side of the first surface as the satellite model component. The ground station model component includes an antenna group and is signal-connected to the satellite model component. The ground station model component is used to receive detection signals and acquire the position signal of the satellite model component, and can adjust the azimuth and elevation angles of the antenna group based on the position signal of the satellite model component.

[0012] The first drive motor and the second drive motor, the first drive motor having two components and being respectively connected to two sets of first directional track groups, are used to drive the two first moving parts to move simultaneously along the corresponding first guide rails. The second drive motor is connected to the second directional track group and is used to drive the second moving parts to move along the second guide rails, so as to drive the satellite model component to move simultaneously along the longitudinal direction and the first direction to form a motion trajectory corresponding to the running trajectory line.

[0013] The first direction is in the same direction as the length direction of the back panel, and this direction is perpendicular to the longitudinal direction and parallel to the top surface of the booth.

[0014] In some modified embodiments of this application, it further includes: an installation frame, which is a frame structure composed of multiple profiles spliced ​​together and connected by multiple angle irons. The installation frame is rectangular on both sides opposite to each other in the first direction and on both sides opposite to each other in the longitudinal direction. The installation frame is vertically fixed to the top surface of the booth and surrounds the first surface of the back panel for fixing the back panel.

[0015] The two sets of first-direction track groups are respectively installed on opposite sides of the mounting frame in the first direction.

[0016] In some modified embodiments of this application, the first orbital group further includes:

[0017] A fixed base plate and a fixed top plate are located on the bottom and top sides of the first movable part, respectively, and are installed on the bottom and top of the mounting frame, respectively.

[0018] The first guide rail includes: a lead screw and at least one guide rod, which are respectively spaced apart and extend longitudinally. The top and bottom ends of the lead screw are respectively rotatably connected to the fixed top plate and the fixed top plate. The top and bottom ends of the at least one guide rod are respectively fixed to the fixed top plate and the fixed top plate.

[0019] The first moving part is provided with an adjusting nut corresponding to and adapted to the lead screw and at least one guide hole corresponding to and adapted to the at least one guide rod. The lead screw is threadedly connected to the adjusting nut, and the at least one guide rod passes through the at least one guide hole.

[0020] The first drive motor is mounted on the bottom of the fixed base plate, and the output shaft of the first drive motor passes through the fixed base plate and is coaxially connected to the lead screw.

[0021] In some modified embodiments of this application, the second orbital group further includes:

[0022] Two first fixed frames are respectively installed on two first moving parts of two sets of first guide rails, and the second guide rail is connected between the two first fixed frames;

[0023] Two second fixed brackets are respectively installed on two first moving parts of two sets of first guide rail groups. The second drive motor is installed on one of the second fixed brackets. The output shaft of the second drive motor faces the first surface and its axis is perpendicular to the first surface.

[0024] A timing belt mechanism includes: a drive pulley, a timing pulley, and a timing belt. The drive pulley is connected to the output shaft of the second drive motor. The timing pulley is rotatably mounted on another second fixed frame. The timing belt connects the drive pulley and the timing pulley and is located on the side of the second guide rail near the first surface.

[0025] The second moving part has a through hole that corresponds to and is adapted to the second guide rail, and a transmission hole that corresponds to and is adapted to the synchronous belt. The transmission hole has a transmission tooth that cooperates with the synchronous belt.

[0026] In some modified embodiments of this application, it further includes: a main controller, disposed on the display stand, and signal-connected to the first drive motor, the second drive motor and the ground station model component, for controlling the first drive motor and the second drive motor, and sending the position signal of the satellite model component to the ground station model component.

[0027] In some modified embodiments of this application, the satellite model component includes: three 1U CubeSat units, which are arranged longitudinally and adjacent to each other and connected by a structural frame. Each 1U CubeSat unit has an internal cavity. The 1U CubeSat units from bottom to top are respectively used to house: the aforementioned functional modules, control and communication modules, and power supply modules.

[0028] The plurality of functional modules include at least: a temperature and humidity sensor and a camera; the control and communication module is signal-connected to the ground station model component; and the power supply module is used to supply power to the remaining modules of the satellite model component.

[0029] In some modified embodiments of this application, a display screen is provided on the outside of the satellite model component for displaying information based on the detection signal.

[0030] In some modified embodiments of this application, the satellite model assembly is hinged with solar charging panels on both sides opposite to each other in the first direction, for supplying power to the power supply module.

[0031] In some modified embodiments of this application, the ground station model component includes:

[0032] The base is installed on the top surface of the booth;

[0033] The ground station body is installed on top of the base, and the interior of the ground station body has a first accommodating space;

[0034] A motor bracket is movably mounted on the top side of the ground station body, and the motor bracket has a second accommodating space inside;

[0035] The antenna bracket is movably mounted on the top side of the motor bracket;

[0036] The antenna assembly includes: an antenna, four connecting rods and a feed source. The antenna is mounted on the top side of the antenna bracket. One end of each of the four connecting rods is connected to the antenna, and the other end is connected to the feed source to support the feed source.

[0037] The third drive motor is installed at the bottom of the first accommodating space of the ground station body. The output shaft of the third drive motor is coaxially connected to the first rotating shaft. The top end of the first rotating shaft is connected to the motor bracket to drive the motor bracket to rotate. The axial direction of the output shaft of the third drive motor is longitudinal.

[0038] A fourth drive motor is installed in the second accommodating space. The output shaft of the fourth drive motor passes through the motor bracket and is connected to the antenna bracket. It is used to drive the antenna bracket to swing relative to the motor bracket. The axial direction of the output shaft of the fourth drive motor is perpendicular to the longitudinal direction.

[0039] In some modified embodiments of this application, the antenna bracket includes connecting portions disposed on opposite sides of the motor bracket on the axial direction of the output shaft of the fourth drive motor. One of the connecting portions is connected to the output shaft of the fourth drive motor, and the other connecting portion is rotatably connected to the motor bracket, and its rotation axis relative to the motor bracket is coaxial with the output shaft of the fourth drive motor. A counterweight module is respectively provided on the bottom side of the two connecting portions.

[0040] Compared to existing technologies, the aerospace telemetry and control model provided in this application simulates the satellite's on-orbit operation process by setting a running trajectory line on the first surface of the backplate. The first and second drive motors can cooperate with the drive track assembly to drive the satellite model assembly to move simultaneously along the longitudinal direction and the first direction to form a motion trajectory corresponding to the running trajectory line. The satellite model assembly can acquire detection signals through functional modules and can communicate with the ground station model assembly. The ground station model assembly can acquire the position signal of the satellite model assembly and adjust the elevation and azimuth angles of the antenna assembly based on the position signal, thus simulating the process of the ground station tracking the satellite. The model provided in this embodiment can comprehensively demonstrate the aerospace telemetry and control process, popularize aerospace knowledge, and has a strong systematic nature. It allows the target audience to intuitively observe and experience the model's operation process, making it easier to understand. Furthermore, the model can be displayed indoors, reducing external interference and making it highly operable. Attached Figure Description

[0041] The above and other objects, features, and advantages of exemplary embodiments of this application will become readily understood by reading the following detailed description with reference to the accompanying drawings. In the drawings, several embodiments of this application are illustrated by way of example and not limitation, with the same or corresponding reference numerals denoteing the same or corresponding parts, wherein:

[0042] Figure 1 A schematic diagram of the aerospace telemetry and control model provided in an embodiment of the present invention is shown;

[0043] Figure 2 This shows a structural schematic diagram of the aerospace telemetry and control model provided in an embodiment of the present invention from another angle;

[0044] Figure 3 This shows a schematic diagram of the structure of the backplate of the aerospace telemetry and control model provided in an embodiment of the present invention;

[0045] Figure 4 This invention provides a schematic diagram of the orbital components of an aerospace telemetry and control model.

[0046] Figure 5 This invention provides a partial structural schematic diagram of a set of first-direction orbit groups in a space telemetry and control model.

[0047] Figure 6 This invention provides a partial structural schematic diagram of another set of first-direction orbit groups in the aerospace telemetry and control model.

[0048] Figure 7 This invention provides a schematic diagram of the bottom structure of the first orbital group of the aerospace telemetry and control model.

[0049] Figure 8 This invention provides a schematic diagram of the top structure of the first orbital group of the aerospace telemetry and control model.

[0050] Figure 9 This invention illustrates a schematic diagram of the structure of the second moving component of the aerospace telemetry and control model provided in an embodiment of the invention.

[0051] Figure 10 This invention provides a schematic diagram of the structure of a satellite model component of an aerospace telemetry and control model.

[0052] Figure 11 This invention provides a schematic diagram of the satellite model component of the aerospace telemetry and control model from another angle.

[0053] Figure 12 This invention provides a schematic diagram of the internal structure of a satellite model component of a space telemetry and control model.

[0054] Figure 13This invention provides a schematic diagram of the structure of the ground station model component of the aerospace telemetry and control model.

[0055] Figure 14 This shows a structural schematic diagram of the ground station model component of the aerospace telemetry and control model provided in an embodiment of the present invention from another angle;

[0056] Figure 15 A cross-sectional structural schematic diagram of the ground station model component of the aerospace telemetry and control model provided in an embodiment of the present invention is shown;

[0057] Figure 16 It shows Figure 15 A partially enlarged structural diagram of section A in the middle;

[0058] Figure 17 A partial cross-sectional structural diagram of the ground station model component of the aerospace telemetry and control model provided in an embodiment of the present invention is shown;

[0059] Explanation of icon numbers:

[0060] Booth 1, Fixed Platform 101, Enclosure Structure 102, Back Panel 2, First Surface 201, Running Trajectory Line 202, First Track Assembly 3, First Guide Rail 301, Lead Screw 3011, Guide Rod 3012, First Moving Part 302, Guide Hole 3021, Fixed Base Plate 303, Fixed Top Plate 304, Adjusting Nut 305, Flange Bearing 306, Second Track Assembly 4, Second Guide Rail 401, Second Moving Part 402, Through Hole 4021, Conveying Hole 4022, First Fixed Frame 403, Second Fixed Frame 404, Drive Wheel 4051, Synchronous Wheel 4052, Synchronous Belt 4053, Satellite Model Components 5, Satellite Structural Frame 501, Hexagonal Nut 502, CubeSat Support 503, Satellite Outer Wall 504, Top Cover 505, Bottom Cover 506, Satellite Circuit Support Plate 507, Power Supply Module 508, Control and Communication Module 509, Temperature and Humidity Sensor 510, Camera 511, Satellite antenna model 512, Reserved hole 513, Solar charging panel 514, Connector 515, Ground station model component 6, Base 601, Control module 602, Ground station main body 603, Lower section of ground station 6031, Middle section of ground station 6032, Upper section of ground station 6033, Motor bracket 604, Upper motor bracket 6041, Lower motor bracket 6042, Antenna bracket 605, Antenna group 606, Antenna 6061, Connecting rod 6062, Feed source 6063, Third drive motor 607, Fourth drive motor 608, First rotating shaft 609, Bearing 610, Key 611, Counterweight module 612, Ladder model 613, First drive motor 7, Second drive motor 8, Main controller 9, Mounting frame 10, Profile 1001, Angle iron 1002, Coupling 11, First direction x, Longitudinal direction z. Detailed Implementation

[0061] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0062] It should be noted that, unless otherwise stated, the technical or scientific terms used in this application shall have the ordinary meaning as understood by one of ordinary skill in the art to which this application pertains.

[0063] Example 1

[0064] Reference Appendix Figure 1 -Appendix Figure 17Embodiment 1 of the present invention proposes an aerospace telemetry and control model, which includes: a platform 1 and a backplate 2. The backplate 2 is vertically disposed on the top surface of the platform 1, and a trajectory line 202 is provided on the first surface 201 of the backplate 2; an orbit assembly, located on one side of the first surface 201, including: two sets of first-direction orbit groups 3 and second-direction orbit groups 4. The two sets of first-direction orbit groups 3 are disposed on the top side of the platform 1 and are respectively located on opposite sides of the first surface 201 of the backplate 2 in the first direction x. The first-direction orbit group 3 includes: a first guide rail. The second directional orbit group 4 includes: a second guide rail 401 and a second moving member 402; wherein the first guide rail 301 extends along the longitudinal direction z, the first moving member 302 is movably disposed on the first guide rail 301, the second guide rail 401 extends along the first direction x and connects between the two first moving members 302 of the two first directional orbit groups, and the second moving member 402 is movably disposed on the second guide rail 401; a satellite model assembly 5 is installed on the second moving member 402, the satellite model assembly 5 including multiple functions. The system includes a detection module for detecting detection signals; a ground station model assembly 6, mounted on the top surface of the booth 1 and located on the same side of the first surface 201 as the satellite model assembly 5; the ground station model assembly 6 includes an antenna group 606 and is signal-connected to the satellite model assembly 5; the ground station model assembly 6 is used to receive detection signals and acquire the position signal of the satellite model assembly 5, and can adjust the azimuth and elevation angles of the antenna group 606 based on the position signal of the satellite model assembly 5; and a first drive motor 7 and a second drive motor 8. Two first drive motors 7 are connected to two sets of first-direction track groups 3, respectively, for driving two first moving parts 302 to move simultaneously along the corresponding first guide rails 301. The second drive motor 8 is connected to the second-direction track group 4, for driving the second moving part 402 to move along the second guide rail 401, thereby causing the satellite model assembly 5 to move simultaneously along the longitudinal direction z and the first direction x to form a motion trajectory corresponding to the running trajectory line 202; wherein, the first direction x is perpendicular to the longitudinal direction z and parallel to the top surface of the booth 1.

[0065] Specifically, the aerospace telemetry and control model provided in this embodiment can be used indoors in places such as schools and science museums to simulate the entire process of satellite on-orbit operation and telemetry and control. The aerospace telemetry and control model mainly includes the following parts: display stand 1 and back panel 2, track assembly, satellite model assembly 5, ground station model assembly 6, and first drive motor 7 and second drive motor 8. The display stand 1 is mainly used to install the back panel 2 and each assembly. The back panel 2 is provided with a running trajectory line 202. The first drive motor 7 and the second drive motor 8 can cooperate with the track assembly to drive the satellite model assembly 5 to move simultaneously along the longitudinal direction z and the first direction x to form a motion trajectory corresponding to the running trajectory line 202, so as to simulate the process of satellite on-orbit operation. The satellite model assembly 5 can obtain detection signals through functional modules and can communicate with the ground station model assembly 6, thereby systematically demonstrating the process of aerospace telemetry and control and popularizing aerospace knowledge.

[0066] Reference Appendix Figure 1 and attached Figure 2 The exhibition stand 1 is used to support and install various components. It includes a fixed platform 101, which is a rectangular plate structure. The first direction x can be the width direction of the fixed platform 101. The exhibition stand 1 may also include a frame structure 102 surrounding the fixed platform 101. The frame structure 102 can enclose and form an exhibition space, thereby preventing the science popularization object from approaching a certain part of the model during the exhibition and affecting the all-round display of the model. The height of the frame structure 102 can be set according to the actual situation. The top surface of the exhibition stand 1 mentioned above and below refers to the top surface of the fixed platform 101. The back panel 2 can be a rectangular plate structure, which is set perpendicular to the top surface of the fixed platform 101. The length direction of the back panel 2 is also the first direction x, and its height direction is the longitudinal direction z. The back panel 2 is set at one end of the length direction of the fixed platform 101, and the first surface 201 of the back panel 2 faces the other end of the length direction of the fixed platform 101. The first surface 201 is provided with running trajectory lines 202, as shown in the attached figure. Figure 3 As shown, the trajectory line 202 here can be, but is not limited to, the trajectory of the star point. Optimally, the trajectory line 202 can also be replaced with a different trajectory according to the needs of the demonstration, so as to meet the needs of teaching and demonstration.

[0067] Reference Appendix Figure 1 Appendix Figure 2 and appendix Figure 4The track assembly is installed on the booth 1 and faces the first surface 201. Specifically, the track assembly includes two sets of first-direction track groups 3 and one set of second-direction track groups 4. The two sets of first-direction track groups 3 correspond to opposite sides of the booth 1 in the first direction x. Each first-direction track group 3 includes a first guide rail 301 and a first moving member 302. The first guide rail 301 extends longitudinally z, and the first moving member 302 is movably mounted on the first guide rail 301, allowing it to reciprocate relative to the first guide rail 301 in its extending direction. Two first drive motors 7 are used, corresponding to the two sets of first-direction track groups 3 respectively. The two first drive motors 7 simultaneously drive the two first moving members 302 to move relative to the first guide rail 301 in the longitudinal direction z. The second-direction track group 4 includes a second guide rail 401 and a second moving member 402. The second guide rail 401 extends in the first direction x, and its two... The first moving part 302 is mounted on two first moving parts 302 respectively. The second moving part 402 is movably mounted on the second guide rail 401 and can reciprocate relative to the second guide rail 401 in its extension direction. There is one second drive motor 8, which can drive the second moving part 402 to move relative to the second guide rail 401 along the first direction x. The satellite model component 5 is mounted on the second moving part 402. Taking the motion trajectory line as the nadir point trajectory as an example, the nadir point trajectory is similar to a sine curve. The first drive motor 7 and the second drive motor 8 are driven at the same time, so that the two first moving parts 302 and the second moving part 402 can move at the same time in the corresponding direction, thereby driving the satellite to move and simulating the nadir point trajectory of the satellite. The first drive motor 7 and the second drive motor 8 can be controlled by setting a main controller 9. The main controller 9 can also be connected to the ground station model component 6.

[0068] Reference Appendix Figure 10 The satellite model component 5 is used to simulate a satellite. It is mounted on the second moving part 402 and includes multiple functional modules for acquiring different types of detection signals to simulate the functions of different types of satellites.

[0069] Reference Appendix Figure 13 The ground station model component 6 is signal-connected to the satellite model component 5 and can communicate with it, enabling the ground station model component 6 to acquire the detection signal from the satellite model component 5. This detection signal can be output to students and other science education subjects. The ground station model component 6 can also acquire the position signal of the satellite model component 5. The acquisition of the position signal can be achieved through communication between the main controller 9 and the ground station model component 6, or through the satellite model component 5's own positioning and communication with the ground station model component 6. The ground station model component 6 includes an antenna group 606. Based on the position signal of the satellite model component 5, the ground station model component 6 adjusts the elevation and azimuth angles of the antenna group 606 to simulate the process of a ground station tracking a satellite.

[0070] Based on the above, this embodiment of the invention proposes an aerospace telemetry and control model. By setting an operational trajectory line 202 on the first surface 201 of the backplate 2, the first drive motor 7 and the second drive motor 8 can cooperate with the drive track assembly to drive the satellite model assembly 5 to move simultaneously along the longitudinal direction z and the first direction x to form a motion trajectory corresponding to the operational trajectory line 202, thereby simulating the process of satellite operation in orbit. The satellite model assembly 5 can acquire detection signals through functional modules and can communicate with the ground station model assembly 6. The ground station model assembly 6 can acquire the position signal of the satellite model assembly 5 and can adjust the elevation angle and azimuth angle of the antenna group 606 based on the position signal, thereby simulating the process of the ground station tracking the satellite. The model provided in this embodiment can comprehensively and effectively demonstrate the aerospace telemetry and control process, popularize aerospace knowledge, and has strong systematicity. It allows the target audience to intuitively observe and experience the operation process of the model, making it easy to understand. Furthermore, the model can be displayed indoors, reducing external interference and making it highly operable.

[0071] Further, see attached document. Figure 4 and attached Figure 8 In a specific implementation, the aerospace telemetry and control model provided in this embodiment also includes: a mounting frame 10, which is a frame structure formed by splicing multiple profiles 1001 and connecting them with multiple angle irons 1002. The mounting frame 10 has rectangular frames on both sides opposite each other in the first direction x and on both sides opposite each other in the longitudinal direction z. The mounting frame 10 is vertically fixed to the display stand 1 and surrounds the first surface 201 of the back plate 2 for fixing the back plate 2. The two sets of first-direction track groups 3 are respectively installed on the two rectangular frames opposite each other in the first direction x of the mounting frame 10.

[0072] Specifically, to achieve the installation of the first track assembly 3 and the back panel 2, the technical solution adopted in this invention includes an installation frame 10 on the top surface of the booth 1. This frame is rectangular and its dimensions are adapted to the dimensions of the back panel 2. The installation frame 10 can be constructed from 12 aluminum profiles 1001 and 12 angle irons 1002. The angle irons 1002 are used to connect adjacent profiles 1001, and the resulting rectangular frame can enclose a cubic space. Each face of this cubic space corresponds to a rectangular frame-shaped portion. The installation frame 10 can be installed on the frame structure 102 of the booth 1. The mounting frame 10 is positioned above the fixed platform 101, and there is a certain distance between the top surface of the mounting frame 10 and the top surface of the fixed platform 101. However, it is not limited to this; the mounting frame 10 can also be directly fixed to the top surface of the fixed platform 101. The back plate 2 is fixed to the mounting frame 10, with its first surface 201 facing the mounting frame 10. Two sets of first-direction track groups 3 are respectively installed on opposite sides of the mounting frame 10 in the first direction x. The specific installation relationship is as follows: the two ends of the two sets of first-direction track groups 3 in the longitudinal z direction can be respectively fixed to the top and bottom of the mounting frame on opposite sides in the first direction x, thereby achieving reliable and stable installation of the first-direction track groups 3.

[0073] Further, see attached document. Figure 4 -Appendix Figure 8 In a specific implementation, the first guide rail assembly 3 further includes a fixed base plate 303 and a fixed top plate 304, which are located on the bottom and top sides of the first moving member 302, respectively, and are installed on the bottom and top of the mounting frame 10, respectively. The first guide rail includes a lead screw 3011 and at least one guide rod 3012, which are spaced apart and extend longitudinally along the z-axis. The top and bottom ends of the lead screw 3011 are rotatably connected to the fixed top plate 304, respectively, and the top and bottom ends of the at least one guide rod 3012 are fixed to the fixed top plate 304, respectively. The first movable member 302 is provided with an adjusting nut 305 corresponding to and adapted to the lead screw 3011 and at least one guide hole 3021 corresponding to and adapted to the at least one guide rod 3012. The lead screw 3011 is threadedly connected to the adjusting nut 305, and the at least one guide rod 3012 passes through the at least one guide hole 3021. The first drive motor 7 is installed at the bottom of the fixed base plate 303, and the output shaft of the first drive motor 7 passes through the fixed base plate 303 and is coaxially connected to the lead screw 3011.

[0074] Specifically, to fix the first guide rail 301, the first track assembly 3 further includes a fixed base plate 303 and a fixed top plate 304, which are respectively used to connect the bottom and top ends of the first guide rail 301. The fixed base plate 303 can be fixed to the profile 1001 located on the bottom side of the mounting frame 10, and similarly, the fixed top plate 304 can be fixed to the profile 1001 located on the top side of the mounting frame 10. In order to enable the first track assembly 3 to indirectly drive the satellite model assembly 5 to move along the longitudinal z direction through the second track assembly 4, in the technical solution adopted by the present invention, the first guide rail 301 of the first track assembly 3 includes a lead screw 3011 and at least one guide. The guide rod 3012, described here with two guide rods 3012, extends longitudinally (z) in the direction of both the lead screw 3011 and the guide rod 3012. The two guide rods 3012 are positioned on either side of the lead screw 3011, spaced a certain distance apart. The top and bottom ends of the lead screw 3011 are fixed to the fixed top plate 304 and the fixed bottom plate 303, respectively. The top end of the lead screw 3011 is rotatably connected to the fixed top plate 304. Here, a mounting frame 10 is installed on the frame structure 102 of the exhibition stand 1. The distance between the mounting frame 10 and the top surface of the fixed platform 101 is used to install the first drive motor 7. The output of the first drive motor 7... The shaft is coaxial with the lead screw 3011 and passes through the fixed base plate 303 to connect with the lead screw 3011, thereby driving the lead screw 3011 to rotate. The bottom end of the lead screw 3011 can be connected to the output shaft of the first drive motor 7 through the coupling 11. The first moving part 302 can be a flat plate structure with guide holes 3021 adapted to the two guide rods 3012 and a longitudinal Z-shaped opening corresponding to the lead screw 3011. An adjusting nut 305 adapted to the lead screw 3011 is installed at the longitudinal Z-shaped opening. Specifically, it can be a T-shaped adjusting nut 305. The two guide rods 3012 pass through the guide holes 3021 on the first moving part 302. The lead screw 3011 passes through the longitudinal z-shaped opening and is threadedly connected to the adjusting nut 305. When the first drive motor 7 drives its output shaft to rotate the lead screw 3011, the rotation of the first moving part 302 is restricted by the cooperation between the guide rod 3012 and the guide hole 3021. This allows the rotation of the lead screw 3011 to be converted into the linear motion of the first moving part 302, so that the first moving part 302 rises or falls relative to the lead screw 3011 along the longitudinal z-shape. This allows the satellite model assembly 5 to move along the longitudinal z-shape indirectly through the second guide rail 401 group. Furthermore, the cooperation between the lead screw 3011 and the adjusting nut 305 enables more precise adjustment of the first moving part 302.

[0075] Among them, flange bearings 306 that cooperate with the corresponding guide rods 3012 can be installed in the two guide holes 3021, thereby reducing the friction between the guide rods 3012 and the guide holes 3021 of the first moving part 302; the first drive motor 7 can be installed at the bottom end of the lead screw 3011 as described above, or at the top end of the lead screw 3011, with the same connection method. Compared with the solution of setting the first drive motor 7 at the bottom end of the lead screw 3011 and located between the mounting frame 10 and the fixed platform 101, it is more conducive to improving the aesthetics of the aerospace telemetry and control model and is easier to install.

[0076] Further, see attached document. Figure 4 -Appendix Figure 6 and appendix Figure 9 In a specific implementation, the second track group 4 further includes: two first fixed frames 403, respectively mounted on the two first moving parts 302 of the two sets of first track groups 3, and the second guide rail 401 connected between the two first fixed frames 403; two second fixed frames 404, respectively mounted on the two first moving parts 302 of the two sets of first track groups 3, and the second drive motor 8 mounted on one of the second fixed frames 404, the output shaft of the second drive motor 8 facing the first surface 201 and its axis perpendicular to the first surface 201; and a timing belt 4053 mechanism, which includes: a drive wheel 4051, a timing wheel 4052 and a timing belt 4053, the drive wheel 4051 being connected to the output shaft of the second drive motor 8, the timing wheel 4052 being rotatably mounted on the other second fixed frame 404, and the timing belt 4053 being connected to the drive wheel 4051 and the timing wheel 4052, and being able to drive the timing wheel 4052 under the drive of the drive wheel 4051. As the synchronous belt 4053 rotates, it can be driven by the teeth on its inner surface to drive the drive pulley 4051 and the synchronous pulley 4052. The synchronous belt 4053 is located on the side of the second guide rail 401 near the first surface 201. The second moving member 402 has a through hole 4021 corresponding to and adapted to the second guide rail 401, and a transmission hole 4022 corresponding to and adapted to the synchronous belt 4053. The outer surface of the synchronous belt 4053 can be provided with teeth, and the transmission hole 4022 has a tooth that corresponds to the synchronous belt. The transmission teeth of the timing belt 4053 (not shown in the figure) are engaged with the transmission hole 4022. The bottom part of the timing belt 4053 passes through the transmission hole 4022. Through the meshing relationship between the teeth on the outer surface of the timing belt 4053 and the transmission teeth on the bottom wall of the transmission hole 4053, the timing belt 4053 can drive the second moving member 402 to move linearly in the first direction x. The engagement between the timing belt 4053 and the second moving member 402 is not limited to the above method. The purpose is to enable the timing belt 4053 to drive the second moving member 402 to reciprocate linearly in the first direction x.

[0077] Specifically, to install the second guide rail 401, two first fixing frames 403 can be set on the first moving parts 302 of the two sets of first track groups 3. The first fixing frames 403 can be plate structures and are vertically set on the top surface of the first moving parts 302. The two first fixing frames 403 are arranged opposite to each other, and the two ends of the second guide rail 401 can be connected to the two first fixing frames 403 respectively. In order to enable the second track group 4 to drive the satellite model component 5 to move along the first direction x, the second track group 4 can use the same method as the first track group 3, using the cooperation of the lead screw 3011, adjusting nut 305 and guide rod 3012 to convert the rotation of the lead screw 3011 into the vertical movement of the first moving part 302. In the linear motion scheme, or in the technical solution adopted by the present invention, the two ends of the second guide rail 401 are respectively fixed to the opposing surfaces of the two first fixing frames 403, and the second track group 4 further includes: two second fixing frames 404 and a synchronous belt 4053 mechanism. The two second fixing frames 404 can also be configured as plate structures and are vertically arranged on the top surface of the first moving member 302. The arrangement directions of the first fixing frames 403 and the second fixing frames 404 can be perpendicular to each other. One of the second fixing frames 404 is used to mount the second drive motor 8. The axial direction of the output shaft of the second drive motor 8 is perpendicular to the first surface 201, and the output shaft is located on the side of the second drive motor 8 facing the first surface 201. The stepper belt 4053 mechanism includes: a drive pulley 4051, a synchronous pulley 4052, and a synchronous belt 4053. The drive pulley 4051 and the synchronous pulley 4052 have the same shape. The drive pulley 4051 is mounted on the output shaft of the second drive motor 8 to provide power. The synchronous pulley 4052 is rotatably connected to another second fixed frame 404. The connection between the drive pulley 4051 and the synchronous pulley 4052 is parallel to the first surface 201 and perpendicular to the longitudinal direction z. The synchronous belt 4053 connects the drive pulley 4051 and the driven pulley. The synchronous belt 4053 is provided with teeth (not shown in the figure) that mesh with the drive pulley 4051 and the driven pulley. Through the meshing relationship, it can rotate under the drive of the drive pulley 4051. A second guide rail is also included. Specifically, 401 can be two rod structures spaced apart in the longitudinal z direction. Correspondingly, the second moving member 402 has a through hole 4021 that corresponds to and is adapted to the second guide rail 401, and a transmission hole 4022 that corresponds to and is adapted to the synchronous belt 4053. The transmission hole 4022 has transmission teeth (not shown in the figure) that are arranged facing the teeth of the synchronous belt 4053. Through the meshing of the transmission teeth with the teeth of the synchronous belt 4053, the second moving member 402 can move in the first direction x under the drive of the synchronous belt 4053. The second guide rail 401 can play a reliable supporting and guiding role, thereby ensuring that the second moving member 402 drives the satellite model component 5 to move accurately along the first direction x.

[0078] Among them, linear motion bearings (not shown in the figure) that cooperate with the corresponding second guide rails 401 can be provided in the two second guide holes 3021 to reduce the friction between the second guide rails 401 and the second guide holes 3021 of the second moving member 402 during the movement of the second moving member 402, and bearing end caps can also be provided on opposite sides of the second moving member 402 in the first direction x.

[0079] Further, see attached document. Figure 1 Appendix Figure 2 and appendix Figure 7 In a specific implementation, the aerospace telemetry and control model provided in this embodiment also includes: a main controller 9, which is set on the display stand 1 and is signal-connected to the first drive motor 7, the second drive motor 8 and the ground station component, for controlling the first drive motor 7 and the second drive motor 8, and sending the position signal of the satellite model component 5 to the ground station model component 6.

[0080] Specifically, in order to control the first drive motor 7 and the second drive motor 8, the technical solution adopted in this invention uses a main controller 9. The main controller 9 may include a main control box and a circuit part (not shown in the figure) set inside the main control box. An opening is provided on one side of the main control box, and the box can be closed by setting a box cover at the opening. The main controller 9 can be set on the fixed platform 101 of the display stand 1, or it can be set on the outside of the frame structure 102, as long as its position does not affect the display of the model. The circuit part of the main controller 9 has a pre-edited program that can control the operation of the first drive motor 7 and the second drive motor 8 so that the satellite model component 5 can move according to the running trajectory line 202 to simulate the on-orbit operation of the satellite. The main controller 9 is signal connected to the ground station model component 6 and can send the position signal of the satellite model component 5 to the ground station model signal.

[0081] Further, see attached document. Figure 10 -Appendix Figure 12 In a specific implementation, the satellite model component 5 includes three 1U CubeSat units, which are arranged longitudinally z and connected by a structural frame. Each 1U CubeSat unit has an internal cavity. From bottom to top, the 1U CubeSat units are respectively used to house the aforementioned functional modules, a control and communication module 509, and a power supply module 508. The aforementioned functional modules include at least a temperature and humidity sensor 510 and a camera 511. The control and communication module 509 is signal-connected to the ground station model component 6, and the power supply module 508 is used to supply power to the remaining modules of the satellite model component 5.

[0082] Specifically, to achieve this, in the technical solution adopted in this invention, the cube star is divided into "U" units, where 1U refers to a standard unit cube (volume 10*10*10cm). 3 In the technical solution adopted by the present invention, the satellite model component 5 may include three 1U cubesat units, that is, the satellite model component 5 is a 3U cubesat model. Each cubesat unit includes: a satellite structural frame 501 located on the top and bottom sides, multiple hexagonal nuts 502 connecting two satellite structural frames 501, and four cubesat pillars 503. After connection, a satellite outer wall 504 is provided around the perimeter, forming a cavity inside. A top cover 505 or a bottom cover 506 can be added to the top and bottom as needed. A satellite circuit support plate 507 can be added in the middle according to function. The three 1U cubesat units are arranged along the longitudinal direction z. Adjacent 1U cubesat units are connected by connectors 515. The 1U cubesat unit located at the top is the power supply unit, and the power supply module is located on the satellite circuit support plate 507 set in its internal cavity. 508 is used to power the other modules of the satellite model assembly 5; the 1U CubeSat unit in the middle is the control unit, and the satellite circuit support plate 507 inside its cavity is the control and communication module 509. The satellite outer wall 504 on the side of the 1U CubeSat unit facing the second moving part 402 is provided with four holes for connecting the second moving part 402; the 1U CubeSat unit at the bottom is the detection unit, and a bottom cover 506 is provided at its bottom. Multiple functional modules are installed on the bottom cover 506, such as temperature and humidity sensor 510 and / or other extended sensors, camera 511, etc. A satellite antenna model 512 can also be set to make the appearance of the satellite model assembly 5 closer to that of a satellite. In order to enable the satellite model assembly 5 to have more functions, holes 513 can also be reserved on the bottom cover 506 for installing other functional modules.

[0083] Specifically, in the technical solution adopted by the present invention, a display screen (not shown in the figure) can be set on the outside of the satellite outer wall 504 on the side of the 1U CubeSat unit located in the middle that is away from the second moving part 402. The display screen is used to display the detection signal, such as temperature and humidity data measured by temperature and humidity sensor 510 and images captured by camera 511.

[0084] For details, please refer to the appendix. Figure 10 In the technical solution adopted by the present invention, the satellite model component 5 is hinged to solar charging panels 514 on both sides opposite to each other in the first direction x, for powering the power supply module 508; each solar charging panel 514 can be connected to the outer wall 504 of the satellite through two damping hinges.

[0085] Further, see attached document. Figure 13 -Appendix Figure 17In specific implementation, the ground station model component 6 includes: a base 601, installed on the top surface of the booth 1; a ground station body 603, installed on the top of the base 601, the ground station body 603 having a first accommodating space inside; a motor bracket 604, movably disposed on the top side of the ground station body 603, the motor bracket 604 having a second accommodating space inside; an antenna bracket 605, movably disposed on the top side of the motor bracket 604; and an antenna group 606, which includes: an antenna 6061, four connecting rods 6062, and a feed 6063. The antenna 6061 is installed on the top side of the antenna bracket 605, and one end of each of the four connecting rods 6062 is connected to the antenna, and the other end is connected to the feed 6063. The system includes: a support for the feed source 6063; a third drive motor 607, installed at the bottom of the first accommodating space of the ground station body 603, the output shaft of the third drive motor 607 being coaxially connected to a first rotating shaft 609, the top end of the first rotating shaft 609 being connected to the motor bracket 604, for driving the motor bracket 604 to rotate, the axial direction of the output shaft of the third drive motor 607 being longitudinal (z); and a fourth drive motor 608, installed in the second accommodating space, the output shaft of the fourth drive motor 608 passing through the motor bracket 604 and connected to the antenna bracket 605, for driving the antenna bracket 605 to swing relative to the motor bracket 604, the axial direction of the output shaft of the fourth drive motor 608 being perpendicular to longitudinal (z).

[0086] Specifically, to achieve the adjustment of the elevation and azimuth angles of the antenna group 606 of the ground station model, the technical solution adopted in this invention includes the following main components of the ground station model component 6: a base 601, a ground station body 603, a motor bracket 604, an antenna bracket 605, an antenna group 606, a third drive motor 607, and a fourth drive motor 608. The base 601 is located on the top surface of the display stand 1, serving as the bottom support structure of the ground station model component 6. The base 601 can be cubic in shape, with a hollow interior and an opening on the bottom side. A control module 602 is installed inside the base 601 to receive satellite signals. The position signal of model component 5 is used to control the third drive motor 607 and the fourth drive motor 608. The bottom of the base 601 can be closed by connecting cover plates. The shape of the ground station body 603 is close to that of an actual ground station. It has a first accommodating space inside. The ground station body 603 can include three parts connected in sequence along the longitudinal z direction, from bottom to top: the lower section 6031, the middle section 6032, and the upper section 6033. The lower section 6031 is connected to the base 601. The third drive motor 607 is installed on the ground station's first drive motor 6032. At the bottom of an accommodating space, the output shaft of the third drive motor 607 is connected to a coupling 11. The top of the coupling 11 is connected to a first rotating shaft 609. The first rotating shaft 609 and the output shaft of the third drive motor 607 are coaxially arranged. A motor bracket 604 is movably mounted on the upper section 6033 of the ground station body 603. The motor bracket 604 may include two parts: an upper motor bracket 6041 and a lower motor bracket 6042. The lower motor bracket 6042 is located at the bottom of the upper motor bracket 6041. The top of the upper section 6033 of the ground station is open and has a groove for accommodating the bearing 610. 042 is installed inside the opening of the upper section 6033 of the ground station and is connected to the upper section 6033 of the ground station via bearing 610. The center of the lower motor bracket 6042 is connected to the first rotating shaft 609 via key 611. The interior of the upper motor bracket 6041 has a second accommodating space for installing the fourth drive motor 608. The antenna bracket 605 is installed on the top side of the upper motor bracket 6041 for installing the antenna group 606. The output shaft of the fourth drive motor 608 is perpendicular to the longitudinal direction z and passes through the side wall of the upper motor bracket 6041 to connect with the antenna bracket 605, so as to drive the antenna bracket 605 to pitch and swing. See attached figure. Figure 13A ladder model 613 can be connected to the side of the motor upper bracket 6041 to make the appearance of the ground station model component 6 closer to the actual ground station; a Hall sensor can be installed on the upper section 6033 of the ground station near the position where the lower motor bracket 6042 is installed. When the azimuth angle of the antenna group 606 needs to be adjusted, the control module 602 controls the output shaft of the third drive motor 607 to drive the first rotating shaft 609 to rotate, so that the first rotating shaft 609 drives the motor bracket 604 and the antenna bracket 605 and the antenna group 606 to rotate horizontally relative to the base 601; when the elevation angle of the antenna group 606 needs to be adjusted, the control module 602 controls the output shaft of the fourth drive motor 608 to drive the antenna bracket 605 to swing in pitch, thereby driving the antenna group 606 to swing, thus completing the adjustment of the elevation angle.

[0087] For details, please refer to the appendix. Figure 13 and attached Figure 14 The antenna assembly 606 includes an antenna 6061, four connecting rods 6062, and a feed 6063. The antenna 6061 is connected to the antenna bracket 605. One end of the four connecting rods 6062 is connected to the antenna 6061, and the other ends are close together to connect to and support the feed 6063. Sensor holes are provided on the upper part of the antenna bracket 605 and the middle part of the antenna 6061 to fix the laser sensor. The laser sensor can emit a laser beam pointing at the satellite, which can intuitively determine whether the ground station model component 6 is correctly tracking the satellite.

[0088] For details, please refer to the appendix. Figure 13 and attached Figure 16 In a specific implementation, the antenna bracket 605 includes connecting portions disposed on opposite sides of the motor bracket 604 on the axial direction of the output shaft of the fourth drive motor 608. One of the connecting portions is connected to the output shaft of the fourth drive motor 608, and the other connecting portion is rotatably connected to the motor bracket 604. The axis of rotation of the other connecting portion relative to the motor bracket 604 is coaxial with the output shaft of the fourth drive motor 608. A counterweight module 612 is respectively provided on the bottom side of the two connecting portions.

[0089] It should be noted that in the description of this specification, the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention; the terms "connection," "installation," "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present invention can be understood according to the specific circumstances.

[0090] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0091] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A space telemetry and control model, characterized in that, include: The exhibition stand and the back panel, wherein the back panel is vertically installed on the top surface of the exhibition stand, and the first surface of the back panel is provided with running trajectory lines; The track assembly, located on one side of the first surface, includes: two sets of first-direction track groups and a second-direction track group. The two sets of first-direction track groups are disposed on the top side of the booth and are respectively located on opposite sides of the first surface of the back panel in a first direction. The first-direction track group includes: a first guide rail and a first moving member. The second-direction track group includes: a second guide rail and a second moving member. Wherein, the first guide rail extends longitudinally, the first moving member is movably disposed on the first guide rail, the second guide rail extends along the first direction and connects between the two first moving members of the two sets of first directional rail groups, and the second moving member is movably disposed on the second guide rail. A satellite model component is installed on the second movable component. The satellite model component includes multiple functional modules for acquiring detection signals. A ground station model component is installed on the top surface of the booth and is located on the same side of the first surface as the satellite model component. The ground station model component includes an antenna group and is signal-connected to the satellite model component. The ground station model component is used to receive detection signals and acquire the position signal of the satellite model component, and can adjust the azimuth and elevation angles of the antenna group based on the position signal of the satellite model component. The first drive motor and the second drive motor, the first drive motor having two components and being respectively connected to two sets of first directional track groups, are used to drive the two first moving parts to move simultaneously along the corresponding first guide rails. The second drive motor is connected to the second directional track group and is used to drive the second moving parts to move along the second guide rails, so as to drive the satellite model component to move simultaneously along the longitudinal direction and the first direction to form a motion trajectory corresponding to the running trajectory line. The first direction is in the same direction as the length direction of the back panel, and this direction is perpendicular to the longitudinal direction and parallel to the top surface of the display stand, further including: The mounting frame is a frame structure made of multiple profiles spliced ​​together and connected by multiple angle irons. The mounting frame is rectangular on both sides opposite each other in the first direction and on both sides opposite each other in the longitudinal direction. The mounting frame is vertically fixed to the top surface of the booth and surrounds the first surface of the back panel for fixing the back panel. The two sets of first-direction track groups are respectively installed on opposite sides of the mounting frame in the first direction; The first orbital group also includes: A fixed base plate and a fixed top plate are located on the bottom and top sides of the first movable part, respectively, and are installed on the bottom and top of the mounting frame, respectively. The first guide rail includes: a lead screw and at least one guide rod, which are respectively spaced apart and extend longitudinally. The top and bottom ends of the lead screw are respectively rotatably connected to the fixed top plate and the fixed top plate. The top and bottom ends of the at least one guide rod are respectively fixed to the fixed top plate and the fixed top plate. The first moving part is provided with an adjusting nut corresponding to and adapted to the lead screw and at least one guide hole corresponding to and adapted to the at least one guide rod. The lead screw is threadedly connected to the adjusting nut, and the at least one guide rod passes through the at least one guide hole. The first drive motor is mounted on the bottom of the fixed base plate, and the output shaft of the first drive motor passes through the fixed base plate and is coaxially connected to the lead screw.

2. The aerospace telemetry and control model according to claim 1, characterized in that, The second orbital group also includes: Two first fixed frames are respectively installed on two first moving parts of two sets of first guide rails, and the second guide rail is connected between the two first fixed frames; Two second fixed brackets are respectively installed on two first moving parts of two sets of first guide rail groups. The second drive motor is installed on one of the second fixed brackets. The output shaft of the second drive motor faces the first surface and its axis is perpendicular to the first surface. A timing belt mechanism includes: a drive pulley, a timing pulley, and a timing belt. The drive pulley is connected to the output shaft of the second drive motor. The timing pulley is rotatably mounted on another second fixed frame. The timing belt connects the drive pulley and the timing pulley and is located on the side of the second guide rail near the first surface. The second moving part has a through hole that corresponds to and is adapted to the second guide rail, and a transmission hole that corresponds to and is adapted to the synchronous belt. The transmission hole has a transmission tooth that cooperates with the synchronous belt.

3. The aerospace telemetry and control model according to claim 1 or 2, characterized in that, Also includes: The main controller, located on the exhibition stand, is signal-connected to the first drive motor, the second drive motor, and the ground station model component. It is used to control the first drive motor and the second drive motor, and to send the position signal of the satellite model component to the ground station model component.

4. The aerospace telemetry and control model according to claim 1, characterized in that, The satellite model assembly includes: three 1U cube satellite units, which are arranged longitudinally and connected by a structural frame. Each 1U cube satellite unit has an internal cavity. The 1U cube satellite units from bottom to top are respectively used to house: the aforementioned functional modules, control and communication modules, and power supply modules. The plurality of functional modules include at least: a temperature and humidity sensor and a camera; the control and communication module is signal-connected to the ground station model component; and the power supply module is used to supply power to the remaining modules of the satellite model component.

5. The aerospace telemetry and control model according to claim 4, characterized in that, The satellite model component is equipped with a display screen on its exterior for displaying information based on the detection signals.

6. The aerospace telemetry and control model according to claim 4, characterized in that, The satellite model assembly has solar charging panels hinged to its two opposite sides in the first direction, which are used to supply power to the power supply module.

7. The aerospace telemetry and control model according to claim 1, characterized in that, The ground station model components include: The base is installed on the top surface of the booth; The ground station body is installed on top of the base, and the interior of the ground station body has a first accommodating space; A motor bracket is movably mounted on the top side of the ground station body, and the motor bracket has a second accommodating space inside; The antenna bracket is movably mounted on the top side of the motor bracket; The antenna assembly includes: an antenna, four connecting rods and a feed source. The antenna is mounted on the top side of the antenna bracket. One end of each of the four connecting rods is connected to the antenna, and the other end is connected to the feed source to support the feed source. The third drive motor is installed at the bottom of the first accommodating space of the ground station body. The output shaft of the third drive motor is coaxially connected to the first rotating shaft. The top end of the first rotating shaft is connected to the motor bracket to drive the motor bracket to rotate. The axial direction of the output shaft of the third drive motor is longitudinal. A fourth drive motor is installed in the second accommodating space. The output shaft of the fourth drive motor passes through the motor bracket and is connected to the antenna bracket. It is used to drive the antenna bracket to swing relative to the motor bracket. The axial direction of the output shaft of the fourth drive motor is perpendicular to the longitudinal direction.

8. The aerospace telemetry and control model according to claim 7, characterized in that, The antenna bracket includes connecting portions disposed on opposite sides of the output shaft of the fourth drive motor on the motor bracket. One of the connecting portions is connected to the output shaft of the fourth drive motor, and the other connecting portion is rotatably connected to the motor bracket. The axis of rotation of the other connecting portion relative to the motor bracket is coaxial with the output shaft of the fourth drive motor. A counterweight module is respectively provided on the bottom side of the two connecting portions.

Images