Satellite loop simulation test system and method, electronic equipment and program product

Abstract

The invention discloses a satellite loop simulation test system and method, electronic equipment and a program product. The satellite loop simulation test system comprises a darkroom system used for simulating an electromagnetic propagation environment between a satellite and a terminal; the turntable system is deployed in the darkroom system and is used for controlling the terminal to move in the darkroom system according to the input terminal movement track; the communication system is used for sending a downlink test signal to the terminal and receiving an uplink test signal fed back by the terminal according to the input channel simulation file, and the uplink test signal and the downlink test signal are used for determining a test result of the satellite loop simulation test; and the timing system is used for generating a unified time reference for the turntable system and the communication system, and the turntable system and the communication system operate based on the time reference. The technical problem of how to construct a darkroom test environment in a low-orbit broadband satellite high-speed motion scene so as to verify the end-to-end communication performance of a terminal under a real-time tracking satellite is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite communication testing, and in particular to a satellite loop simulation testing system, method, electronic equipment and program product. Background Art

[0002] The rapid development of low-Earth orbit (LEO) broadband satellite communication technology offers new prospects for global high-speed data transmission, especially in remote areas and on mobile platforms. However, the high-speed motion of Low Earth Orbit (LEO) satellites presents significant technical challenges in verifying the end-to-end communication performance of terminals tracking LEO broadband satellites in real time.

[0003] Traditional communication test methods and systems, such as static or quasi-static darkroom testing, cannot effectively simulate the complex dynamic communication conditions between LEO satellites and ground terminals caused by the high-speed movement of satellites. In addition, the frequent link switching between LEO satellites and ground terminals caused by orbital motion and the rotation of the earth requires the test system to support high-dynamic channel modeling and real-time signal closed-loop feedback. Traditional test systems mostly use static or quasi-static simulations, which cannot reproduce the rapid changes in signal strength, delay, and Doppler effect in actual scenarios, resulting in insufficient verification of terminal functions and performance. Therefore, how to construct a darkroom test environment under the high-speed movement of low-orbit broadband satellites to verify the end-to-end communication performance of terminals under real-time tracking of satellites is one of the important technical issues in the relevant technical fields.

[0004] To address the above-mentioned problems, no effective solutions have been proposed so far. Summary of the Invention

[0005] Embodiments of the present invention provide a satellite loop simulation test system, method, electronic equipment, and program product to at least solve the technical problem of how to construct a darkroom test environment in a low-orbit broadband satellite high-speed motion scenario to verify the end-to-end communication performance of a terminal under real-time satellite tracking.

[0006] According to one aspect of an embodiment of the present invention, a satellite loop simulation test system is provided, including: a darkroom system for simulating the electromagnetic propagation environment between a satellite and a terminal; a turntable system deployed in the darkroom system, for controlling the movement of the terminal in the darkroom system according to an input terminal motion trajectory; a communication system for sending a downlink test signal to the terminal and receiving an uplink test signal fed back by the terminal according to an input channel simulation file, the uplink test signal and the downlink test signal being used to determine the test result of the satellite loop simulation test; a timing system for generating a unified time base for the turntable system and the communication system, and the turntable system and the communication system operate based on the time base.

[0007] Optionally, the communication system includes a packet filling server, a core network, a base station, a channel simulator and a frequency conversion module, wherein the packet filling server is used to send the generated test data packet to the base station through the core network, the base station is used to convert the signal format of the test data packet and send the intermediate frequency signal after format conversion to the channel simulator, the channel simulator is used to simulate the channel fading characteristics of the intermediate frequency signal in the satellite-to-ground link, and the frequency conversion module is used to convert the frequency of the signal entering the frequency conversion module.

[0008] Optionally, the darkroom system includes a darkroom, a feed antenna and a reflecting surface.

[0009] Optionally, the time system includes a global navigation satellite system simulator for generating a time reference.

[0010] According to another aspect of an embodiment of the present invention, a satellite loop simulation test method is also provided, including: obtaining ephemeris information; determining the terminal motion trajectory and channel simulation file based on the ephemeris information; inputting the terminal motion trajectory and channel simulation file into the satellite loop simulation test system described in any of the above embodiments, and using the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain test results.

[0011] Optionally, the terminal motion trajectory is determined based on the ephemeris information, including: determining the satellite position coordinates and satellite speed based on the ephemeris information, wherein the satellite position coordinates are in the geocentric earth fixed coordinate system; determining the terminal position coordinates of the terminal in the geocentric earth fixed coordinate system based on the coordinates of the terminal in the geographic coordinate system; determining the pitch angle and azimuth angle of the terminal from the satellite's perspective based on the satellite position coordinates and the terminal position coordinates; and determining the terminal motion trajectory based on the pitch angle and azimuth angle.

[0012] Optionally, the pitch angle and azimuth angle of the terminal from the satellite's perspective are determined based on the satellite position coordinates and the terminal position coordinates, including: determining a target coordinate system based on the satellite position coordinates, wherein the origin of the target coordinate system is the satellite position; determining the relative coordinates of the terminal in the target coordinate system based on the terminal position coordinates and the target coordinate system; and determining the pitch angle and azimuth angle of the terminal from the satellite's perspective based on the relative coordinates.

[0013] Optionally, determining a channel simulation file based on the ephemeris information includes: determining a channel fading model based on the ephemeris information; and determining the channel simulation file based on the channel fading model and the communication system.

[0014] Optionally, a satellite loop simulation test system is used to test the communication between the terminal and the satellite to obtain test results, including: controlling the terminal to move according to a motion trajectory based on a turntable system; sending a downlink test signal to the terminal using a communication system in response to the terminal moving along the motion trajectory; obtaining an uplink test signal fed back by the terminal based on the downlink test signal using the communication system, wherein the communication system and the turntable system operate based on a time reference issued by a timing system; and determining the test results based on the downlink test signal and the uplink test signal.

[0015] According to another aspect of an embodiment of the present invention, a test system is also provided, including: the satellite loop simulation test system described in any of the above embodiments; a host computer for obtaining ephemeris information; determining the terminal motion trajectory and channel simulation file based on the ephemeris information; inputting the terminal motion trajectory and channel simulation file into the satellite loop simulation test system, and using the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain test results.

[0016] According to another aspect of an embodiment of the present invention, an electronic device is provided, including: a memory storing an executable program; and a processor for running the executable program, wherein the executable program executes any of the above satellite loop simulation test methods when running.

[0017] According to another aspect of an embodiment of the present invention, a computer-readable storage medium is also provided, which includes a stored executable program, wherein when the executable program is running, the device where the computer-readable storage medium is located is controlled to execute any of the above-mentioned satellite loop simulation test methods.

[0018] According to another aspect of an embodiment of the present invention, a computer program product is provided, including a computer program. When the computer program is executed by a processor, the computer program implements any of the above satellite loop simulation test methods.

[0019] In an embodiment of the present invention, a darkroom system is used to simulate the electromagnetic propagation environment between a satellite and a terminal; a turntable system is deployed in the darkroom system and is used to control the movement of the terminal in the darkroom system according to an input terminal motion trajectory; a communication system is used to send a downlink test signal to the terminal and receive an uplink test signal fed back by the terminal according to an input channel simulation file, and the uplink test signal and the downlink test signal are used to determine the test results of the satellite loop simulation test; a timing system is used to generate a unified time base for the turntable system and the communication system, and the turntable system and the communication system operate based on the time base. The present invention realizes the simulation of the electromagnetic propagation environment through the darkroom system; at the same time, the turntable system enables the terminal to perform high-precision dynamic simulation according to the input trajectory data, simulating the relative position change of the terminal tracking the high-speed mobile satellite. In this way, the dynamic conditions that cannot be simulated in the traditional static test environment are effectively overcome, and the accuracy of the test is effectively improved; in addition, the communication system is used to generate and send downlink test signals according to the channel simulation file, and at the same time receive uplink test signals fed back by the terminal, so as to complete a comprehensive evaluation of the terminal communication performance; further, the time system provides a unified time base for the entire test system, ensures the synchronous operation between the turntable system and the communication system, ensures the precise alignment of all test activities, enables the test system to accurately perform the simulation task, and enhances the validity and credibility of the test results. In summary, the satellite loop simulation test system provided by the present invention constructs a highly simulated dynamic test platform by coordinating the darkroom system, turntable system, communication system and time system system. It can effectively simulate the high-speed movement scenario of low-orbit broadband satellites and conduct in-depth verification of the end-to-end communication performance of the terminal under real-time tracking of satellites, thereby solving the technical problem of how to construct a darkroom test environment under the high-speed movement scenario of low-orbit broadband satellites to verify the end-to-end communication performance of the terminal under real-time tracking of satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0021] Figure 1 is a structural block diagram of a satellite loop simulation test system according to one embodiment of the present invention;

[0022] Figure 2 is a system architecture diagram of a satellite loop simulation test system according to one embodiment of the present invention;

[0023] Figure 3 is a flow chart of a satellite loop simulation test method according to one embodiment of the present invention;

[0024] Figure 4is a schematic diagram of a target coordinate system with a satellite as the origin according to one embodiment of the present invention;

[0025] Figure 5 is a structural block diagram of a test system according to one embodiment of the present invention. DETAILED DESCRIPTION

[0026] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0027] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0028] According to an embodiment of the present invention, a satellite loop simulation test system is provided. Figure 1 FIG. 1 is a structural block diagram of a satellite loop simulation test system 100 according to one embodiment of the present invention. Figure 1 As shown, the system includes:

[0029] Anechoic chamber system 101, used to simulate the electromagnetic propagation environment between the satellite and the terminal;

[0030] The anechoic chamber system is the basic part of the test system. The purpose of building the anechoic chamber system is to simulate the real electromagnetic propagation conditions between the satellite and the terminal.

[0031] The special interior structure of the darkroom uses absorbent materials and reflective surface design to minimize external electromagnetic interference and create a closed and highly controllable electromagnetic environment.

[0032] It is understandable that the darkroom system simulates the signal propagation in the real space environment, providing a realistic background for the performance testing of the terminal.

[0033] The turntable system 102 is deployed in the darkroom system and is used to control the movement of the terminal in the darkroom system according to the input terminal movement trajectory;

[0034] The turntable system in the darkroom system is used to control the motion posture of the terminal, enabling it to simulate the dynamic process of tracking low earth orbit (LEO) satellites.

[0035] In an optional embodiment, the turntable system has high-precision control capabilities and can adjust the position and angle of the terminal in real time based on the input terminal motion trajectory data to equivalently simulate the tracking behavior of the terminal in a LEO satellite high-speed motion scenario.

[0036] It should be noted that this simulation method overcomes the limitation of traditional testing that cannot reproduce dynamic scenes. It simulates the dynamic movement of the satellite through the movement of the turntable, and realizes the comprehensive verification of the terminal tracking capability and beam pointing adjustment function.

[0037] The communication system 103 is used to send a downlink test signal to the terminal and receive an uplink test signal fed back by the terminal according to the input channel simulation file. The uplink test signal and the downlink test signal are used to determine the test result of the satellite loop simulation test;

[0038] The communication system is the core of the test system. It generates and sends downlink test signals based on the channel simulation file, and receives uplink test signals fed back by the terminal to evaluate the actual communication performance of the terminal in the simulation environment.

[0039] It should be noted that the communication system can generate a channel model that reflects parameters such as path loss, Doppler frequency deviation and propagation delay based on the channel simulation file, ensuring that the generation and processing of test signals can simulate the dynamic changes in the LEO satellite communication link.

[0040] Through closed-loop testing of uplink and downlink signals, the system can accurately evaluate the performance of the terminal in a dynamic channel environment, including data transmission rate, signal quality, and link stability, providing a scientific basis for terminal design optimization.

[0041] The time system 104 is used to generate a unified time base for the turntable system and the communication system. The turntable system and the communication system operate based on the time base.

[0042] The timing system provides a unified time base for the entire test system, which is the key to achieve accurate testing.

[0043] In an optional embodiment, the timing system can output precise time signals to ensure synchronization between the communication system and the turntable system during test execution. This synchronization mechanism is crucial for simulating channel parameter variations in high-speed motion scenarios. It ensures precise alignment of all test activities, thereby enhancing the accuracy and reliability of test results.

[0044] With the support of the time synchronization system, the communication system and turntable system can work together to provide a highly dynamic and high-precision test environment for terminal performance testing.

[0045] The present invention realizes the simulation of the electromagnetic propagation environment through the darkroom system; at the same time, the turntable system enables the terminal to perform high-precision dynamic simulation according to the input trajectory data, simulating the relative position change of the terminal tracking the high-speed mobile satellite. In this way, the dynamic conditions that cannot be simulated in the traditional static test environment are effectively overcome, and the accuracy of the test is effectively improved; in addition, the communication system is used to generate and send downlink test signals according to the channel simulation file, and at the same time receive uplink test signals fed back by the terminal, so as to complete a comprehensive evaluation of the terminal communication performance; further, the time system provides a unified time base for the entire test system, ensures the synchronous operation between the turntable system and the communication system, ensures the precise alignment of all test activities, enables the test system to accurately perform the simulation task, and enhances the validity and credibility of the test results. In summary, the satellite loop simulation test system provided by the present invention constructs a highly simulated dynamic test platform by coordinating the darkroom system, turntable system, communication system and time system system. It can effectively simulate the high-speed movement scenario of low-orbit broadband satellites and conduct in-depth verification of the end-to-end communication performance of the terminal under real-time tracking of satellites, thereby solving the technical problem of how to construct a darkroom test environment under the high-speed movement scenario of low-orbit broadband satellites to verify the end-to-end communication performance of the terminal under real-time tracking of satellites.

[0046] Figure 2 This is a system architecture diagram of a satellite loop simulation test system according to one embodiment of the present invention. Figure 2 A detailed introduction to the satellite loop simulation test system is given.

[0047] Optionally, the communication system includes a packet filling server, a core network, a base station, a channel simulator and a frequency conversion module, wherein the packet filling server is used to send the generated test data packet to the base station through the core network, the base station is used to convert the signal format of the test data packet and send the intermediate frequency signal after format conversion to the channel simulator, the channel simulator is used to simulate the channel fading characteristics of the intermediate frequency signal in the satellite-to-ground link, and the frequency conversion module is used to convert the frequency of the signal entering the frequency conversion module.

[0048] In an optional embodiment, the communication system includes Figure 2The package server, the core network, the base station, the channel simulator and the frequency conversion module shown in the figure.

[0049] Optionally, the role of the package server is to generate and send test data packets. The test data packets contain information required for transmission in the simulation communication process, such as voice, video data or control instructions. The server can automatically generate different types of data traffic according to the preset test requirements, which is used to test the processing capacity of the terminal to the signal under different business loads. The generated data packets are then sent to the base station through the core network, preparing for subsequent signal format conversion and transmission.

[0050] Optionally, the core network is responsible for the transmission and routing of test data packets at the network level in the communication system. In the embodiment of the present application, the core network plays the role of data bridge, seamlessly delivering test data packets generated by the package server to the base station, while ensuring the stability and security of transmission.

[0051] It should be noted that the design of the core network needs to take into account the special needs of LEO satellite communication, including high bandwidth, low delay and support for dynamic links, to ensure the efficient operation of the entire test system.

[0052] Optionally, the base station undertakes the task of signal format conversion, i.e. converting test data packets into intermediate frequency signals suitable for air transmission. This process involves a series of communication protocol processing such as data coding, modulation, encryption, etc., to ensure that the signal can be correctly transmitted in the space-ground link.

[0053] Optionally, the base station is also responsible for receiving uplink test signals from user terminals, performing demodulation, decoding and other reverse operations, and finally restoring the data packets and sending them back to the package server through the core network for analysis. The design of the base station needs to be compatible with multiple communication standards to meet the needs of different LEO satellite communication scenarios.

[0054] Optionally, the channel simulator is the key to simulating the real space-ground communication environment. It dynamically generates a channel fading model based on ephemeris information and channel parameters such as path loss, delay, Doppler frequency offset and spatial loss.

[0055] The channel simulator receives intermediate frequency signals from the base station, simulates various attenuations and distortions that the signal experiences in the space-ground link, making the signal closer to the real communication conditions, and then transmits the simulated signal to the frequency conversion module. In this way, the channel simulator not only verifies the terminal's ability to respond to changes in signal strength and quality, but also adds a high degree of realism and complexity to the test system.

[0056] The optional frequency conversion module converts the signal frequency, raising the intermediate frequency (IF) signal to the Ku-band, Q / V-band, or higher frequency bands to meet LEO satellite communication standards. For the downlink, the frequency conversion module upconverts the received IF signal to the specified RF signal. For the uplink, the frequency conversion module downconverts the RF signal fed back by the user terminal to the IF frequency for further processing and analysis.

[0057] The high efficiency and frequency flexibility of the frequency conversion module are crucial for testing broadband signals, ensuring the accuracy of test results.

[0058] Optionally, the darkroom system includes a darkroom, a feed antenna and a reflecting surface.

[0059] In an optional embodiment, the darkroom system includes Figure 2 The darkroom, feed source (i.e. feed antenna) and compact field reflecting surface shown in the figure.

[0060] Optionally, an anechoic chamber is used to eliminate external electromagnetic interference, ensuring the purity of the test signal and accurate signal measurement. The interior of the chamber is covered with electromagnetic absorption materials, such as conical absorbing sponges. These materials absorb most of the electromagnetic waves entering the chamber, preventing them from reflecting and interfering with the test signal, thereby creating an environment close to ideal space propagation conditions. The design and construction of the anechoic chamber require strict control to ensure low reflectivity, low residual stray signals, and good isolation. These provide the necessary physical conditions for accurately simulating satellite-to-ground links.

[0061] Optionally, the feed antenna is a signal transmission device in the darkroom system, and its function is to direct the radio frequency signal generated by the frequency conversion module into the reflecting surface. The feed antenna has the characteristics of high gain and narrow beam width, so as to accurately control the direction and intensity of the signal and ensure that the signal can be radiated or received evenly and accurately. In the test system of the embodiment of the present application, the feed antenna is used in conjunction with the reflecting surface to convert the radio frequency signal into a plane wave to simulate the long-distance propagation of the satellite signal, thereby further enhancing the authenticity of the test.

[0062] Optionally, the reflector can be designed based on a parabola or other curved surface to convert the signal emitted by the feed antenna into a uniform plane wave, mimicking free-space propagation. The curvature, dimensions, and surface accuracy of the reflector directly impact the quality and distribution of the signal. Therefore, factors such as signal frequency, power, and polarization must be considered during design to ensure that the signal maintains the expected characteristics after reflection. In the test environment, the reflector effectively simulates long-distance space propagation conditions, providing user terminals with an electromagnetic environment close to that of real-world satellite communications.

[0063] Optionally, the time system includes a global navigation satellite system simulator for generating a time reference.

[0064] In an optional embodiment, the time system includes Figure 2 The GNSS (Global Navigation Satellite System) simulator shown in .

[0065] The GNSS simulator is capable of simulating signals from global navigation satellite systems (such as GPS, GLONASS, Galileo and BeiDou) for testing and verifying the performance of equipment that relies on GNSS, particularly in terms of positioning, navigation and timing functions.

[0066] In the embodiment of the present application, the core function of the GNSS simulator is to generate a unified and highly stable time base to synchronize the operations in the turntable system, communication system and darkroom system to ensure the accuracy and reliability of the test.

[0067] In another alternative embodiment, through coordinate transformation and precise control of the turntable, the terminal is placed on the turntable, the satellite antenna is fixed, and the terminal rotates in place while the satellite remains stationary, enabling tracking of low-orbit broadband communication satellites. The satellite loop simulation test system consists of a darkroom system, a turntable system, a communication system, a timing system, and a central control system.

[0068] Specifically, the darkroom system is mainly composed of a darkroom, a feed antenna, and a reflecting surface, which are used to simulate the electromagnetic propagation environment between the actual space satellite and the terminal; the turntable system is composed of a turntable, which is used to control the rotation posture of the terminal; the communication system is mainly composed of a packet injection server, a core network, a base station, a channel simulator, a frequency converter, and a user terminal, in order to simulate the satellite-to-ground loop system; the timing system provides a time reference for the communication system equipment based on the clock signal of the GNSS simulator; the central control system generates the terminal's motion trajectory and channel simulation file based on the imported ephemeris file and coordinate system conversion algorithm, the turntable system simulates the relative position and angle relationship of the terminal when tracking the satellite based on the generated terminal trajectory, and the communication system simulates parameters such as time delay, Doppler frequency deviation and spatial path loss in the satellite-to-ground link based on the channel simulation file. Both the communication system and the turntable system carry out terminal performance testing based on the time reference provided by the timing system.

[0069] The satellite loop simulation test system achieves the following functions: a computer controls the base station to transmit the correct downlink communication signal, including parameters such as frequency, power, modulation, and ephemeris synchronization. The intermediate frequency (IF) signal from the ground-based base station passes through a channel simulator. The channel simulator calculates path loss, frequency offset, and delay based on the relative positions of the satellite and the terminal based on the ephemeris, simulating the path loss, Doppler effect, and delay experienced during actual signal transmission. After passing through the channel simulator, the signal is up-converted to the Ku-band frequency by a frequency converter. The signal is then transmitted through a feed antenna connected after the frequency converter, converted into a uniform plane wave by a reflector, and finally establishes a connection with the user terminal for communication. The user terminal then transmits the uplink Ku-band signal back through its transceiver antenna. After passing through the reflector, the signal is received by the feed antenna and then down-converted to an IF signal by a frequency converter. The IF signal again passes through the channel simulator to generate a channel fading model for the uplink signal. Signals simulating path loss, frequency offset, and delay are then added before the signal connects to the base station for communication. Different communication sequences and processes for uplink and downlink signals can be defined based on different testing requirements.

[0070] During the test, an external GNSS simulator generates a unified time base, and the base station, turntable controller, user terminal, and channel simulator simultaneously carry out test tasks based on this time.

[0071] The satellite loop simulation test system's on-orbit simulation function can simulate satellite motion trajectory and parameters by loading ephemeris data files, setting the user terminal position and selecting the satellite trajectory. The user terminal's motion trajectory and attitude changes are obtained through coordinate system conversion. This simulates the relative motion between the terminal and the satellite, and simultaneously generates turntable coordinates and channel fading models, providing a more realistic test environment for the user terminal. The user terminal's motion trajectory and coordinates are defined by using a spherical coordinate system centered on the satellite (i.e., the center point of the reflection surface) as a reference. The terminal's motion trajectory data, calculated inversely, is converted into the coordinate position and attitude corresponding to the turntable coordinate system.

[0072] According to an embodiment of the present invention, an embodiment of a satellite loop simulation test method is also provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system containing at least one set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0073] The method embodiment can also be executed in an electronic device including a memory and a processor, a similar control device, or the cloud. Taking an electronic device as an example, the electronic device may include one or more processors and a memory for storing data. Optionally, the electronic device may also include a communication device and a display device for communication functions. It will be understood by those skilled in the art that the above structural description is only illustrative and does not limit the structure of the above electronic device. For example, the electronic device may also include more or fewer components than the above structural description, or have a configuration different from the above structural description.

[0074] The processor may include one or more processing units. For example, the processor may include a central processing unit (CPU), a graphics processing unit (GPU), a digital signal processing (DSP) chip, a microcontroller unit (MCU), a programmable logic device (field-programmable gate array, FPGA), a neural network processor (NPU), a tensor processing unit (TPU), an artificial intelligence (AI) type processor, and the like. Among them, different processing units may be independent components or integrated into one or more processors. In some instances, the electronic device may also include one or more processors.

[0075] The memory can be used to store computer programs, such as the computer program corresponding to the satellite loop simulation test method in the embodiments of the present invention. The processor implements the aforementioned satellite loop simulation test method by running the computer program stored in the memory. The memory can include high-speed random access memory (RAM) and non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some examples, the memory can further include memory remotely located relative to the processor, and these remote memories can be connected to the electronic device via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof.

[0076] The communication device is used to receive or send data via a network. The specific example of the above-mentioned network may include a wireless network provided by a communication provider of the mobile terminal. In one example, the communication device includes a network adapter (network interface controller, NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the communication device can be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly. In some embodiments of the present solution, the communication device is used to connect to mobile devices such as mobile phones and tablets, and can send instructions to electronic devices through the mobile device.

[0077] The display device may be a touchscreen-type liquid crystal display (LCD) or a touch display (also referred to as a "touch screen" or "touch display"). The LCD may enable a user to interact with a user interface of the electronic device. In some embodiments, the electronic device may include a graphical user interface (GUI), and a user may interact with the GUI by touching a touch-sensitive surface with a finger and / or performing gestures. Executable instructions for performing the aforementioned human-computer interaction functions are configured / stored in a computer program product or readable storage medium executable by one or more processors.

[0078] Figure 3 FIG. 1 is a flow chart of a satellite loop simulation test method according to one embodiment of the present invention. Figure 3 As shown, the method includes the following steps:

[0079] Step S201: Obtain ephemeris information.

[0080] Optionally, ephemeris information is key data describing the satellite's orbital position and motion status, and includes at least: satellite identification, timestamp, orbital parameters, satellite position and velocity information.

[0081] Among them, the satellite identifier is used to uniquely identify the information of each satellite to distinguish different LEO satellites; the timestamp is the time corresponding to the satellite position and status information, which is crucial for achieving time synchronization; the orbital parameters include the orbital semi-major axis, orbital eccentricity, orbital inclination, etc. These parameters reflect the relative position and motion trajectory of the satellite in space; the satellite position and velocity information reflects the three-dimensional coordinates and velocity vector of the satellite at a specific point in time.

[0082] Step S202: Determine the terminal motion trajectory and channel simulation file based on the ephemeris information.

[0083] Based on the acquired ephemeris information, the relative motion between the satellite and the terminal is analyzed, and then the motion trajectory of the terminal is determined, and a channel simulation file is created to simulate the channel characteristics.

[0084] Step S203: input the terminal motion trajectory and the channel simulation file into the satellite loop simulation test system, and use the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain a test result.

[0085] The determined terminal motion trajectory and channel simulation file are input into the satellite loop simulation test system described in any of the above embodiments of the present application to perform a communication performance test between the terminal and the simulated satellite.

[0086] Optionally, the satellite loop simulation test system can be used to test the terminal's signal processing capabilities in dynamic scenarios, including tracking accuracy, demodulation performance, and anti-interference capabilities.

[0087] Optionally, determining the terminal motion trajectory based on the ephemeris information includes the following steps:

[0088] Step S2021, determining the satellite position coordinates and satellite velocity based on the ephemeris information, wherein the satellite position coordinates are in a geocentric earth-fixed coordinate system;

[0089] In an optional embodiment, the ephemeris information is imported into a computer. The ephemeris information includes the satellite ID number (i.e., satellite identification), Beidou time, orbit semi-major axis, orbit eccentricity, orbit inclination, longitude of the ascending node at the reference time, argument of perigee, and mean anomaly.

[0090] Based on the ephemeris information, six data can be obtained: the arc entry and exit time, the satellite's position coordinates (x, y, z) at a certain moment in the ECEF coordinate system, the speed Vx in the x-axis direction, the speed Vy in the y-axis direction, and the speed Vz in the z-axis direction, as shown in Formula 1:

[0091]

[0092] Where SatID represents the satellite ID number, BDT represents BeiDou time, Δa represents the semi-major axis of the orbit, e represents the orbit eccentricity, i0 represents the orbit inclination, Ω0 represents the longitude of the ascending node at the reference time, ω represents the argument of perigee, M0 represents the mean anomaly, (X sat ,Y sat ,Z sat ) represents the position coordinates of the satellite in the ECEF coordinate system, Vx sat Represents the satellite's x-axis velocity, Vy sat Represents the satellite's y-axis velocity, Vz sat Represents the speed of the satellite in the z-axis direction.

[0093] The ECEF coordinate system (Earth-Centered, Earth-Fixed coordinate system) is a three-dimensional rectangular coordinate system widely used in navigation, surveying and space fields. In the ECEF coordinate system, the origin is set at the center of mass of the Earth, i.e., the geometric center of the Earth.

[0094] In step S2022, the terminal position coordinates in the ECEF coordinate system are determined according to the terminal coordinates in the geographic coordinate system.

[0095] In an optional embodiment, the computer sets the position coordinates of the terminal in the geographic coordinate system: longitude, latitude and height, and converts the position coordinates of the terminal in the geographic coordinate system into (X, Y, Z) position coordinates in the ECEF coordinate system, as shown in formula 2:

[0096]

[0097] wherein λ UE , h UE represent the longitude, latitude and height of the terminal in the geographic coordinate system, respectively; (X UE , Y UE , Z UE ) represent the position coordinates of the terminal in the ECEF coordinate system.

[0098] It can be understood that the representation of the terminal position in the ECEF coordinate system enables intuitive understanding and calculation of the relative position relationship between the terminal and the satellite in a unified coordinate framework.

[0099] In step S2023, the elevation angle and the azimuth angle of the terminal in the satellite view are determined according to the satellite position coordinates and the terminal position coordinates.

[0100] By comparing the ECEF coordinates of the satellite and the terminal, the elevation angle and the azimuth angle of the terminal relative to the satellite are calculated, which is crucial for simulating the action of the terminal tracking the satellite. The elevation angle is the vertical angle of the line connecting the terminal and the satellite with the horizontal plane, and the azimuth angle is the angle of the horizontal projection of the line connecting the terminal and the satellite.

[0101] In step S2024, the terminal motion trajectory is determined according to the elevation angle and the azimuth angle.

[0102] Optionally, based on the calculated elevation angle and azimuth angle, the turntable is continuously adjusted so that the motion trajectory of the terminal on the turntable can accurately simulate the dynamic changes of the LEO satellite, thereby reproducing the relative motion between the terminal and the satellite in the test environment.

[0103] Optionally, determining the elevation angle and azimuth angle of the terminal from the perspective of the satellite based on the satellite position coordinates and the terminal position coordinates includes the following steps:

[0104] Step S2025, determining a target coordinate system based on the satellite position coordinates, wherein the origin of the target coordinate system is the satellite position;

[0105] In an optional embodiment, the target coordinate system is an RTN (Radial-Tangential-Normal) coordinate system. In the fields of aerospace, satellite navigation, and earth observation, this coordinate system is used to describe the local dynamic position and motion direction of a satellite relative to a point on the earth's surface.

[0106] The RTN coordinate system takes the satellite position as the origin, where the radial direction points to the center of the Earth, the tangential direction is tangent to the satellite orbit, and the vertical direction is perpendicular to the satellite orbit plane.

[0107] Construct an RTN coordinate system with the satellite as the origin. The unit radial vector, unit tangential vector, and unit normal vector of the RTN coordinate system are calculated as follows:

[0108]

[0109] in, represents the unit radial vector, r sat Represents the satellite radial vector.

[0110]

[0111] in, Represents the unit tangent vector, N = r sat ×v sat , r sat represents the satellite radial vector, v sat Represents the satellite radial velocity.

[0112]

[0113] in, represents the unit normal vector, represents the unit tangent vector, Represents the unit radial vector.

[0114] Figure 4 is a schematic diagram of a target coordinate system with a satellite as the origin according to one embodiment of the present invention. Figure 4 As shown in FIG, an RTN coordinate system is constructed with the satellite as the origin.

[0115] Step S2026, determining the relative coordinates of the terminal in the target coordinate system based on the terminal position coordinates and the target coordinate system;

[0116] Optionally, convert the terminal's position coordinates in the ECEF coordinate system to relative position coordinates in the RTN coordinate system. The conversion formula is as follows:

[0117]

[0118] Among them, R RTN Represents the relative position coordinates of the terminal in the RTN coordinate system, (X UE ,Y UE ,Z UE ) represents the position coordinates of the terminal in the ECEF coordinate system, (X sat ,Y sat ,Z sat ) represents the position coordinates of the satellite in the ECEF coordinate system.

[0119] Step S2027: Determine the elevation angle and azimuth angle of the terminal from the perspective of the satellite based on the relative coordinates.

[0120] Optionally, the elevation angle and azimuth angle of the terminal from the satellite's perspective are further calculated based on the relative coordinate information of the terminal in the RTN coordinate system. The calculation formula is as follows:

[0121]

[0122] Among them, Ele represents the pitch angle, R RTN (3) represents the third term of the RTN relative position coordinate vector, ||R RTN || represents the modulus of the relative position vector.

[0123] Azi=arctan2(R RTN (2),R RTN (1))+180° (8)

[0124] Among them, Azi represents the azimuth, R RTN (2) represents the second term of the RTN relative position coordinate vector, R RTN (1) represents the first term of the RTN relative position coordinate vector.

[0125] Optionally, determining a channel simulation file based on ephemeris information includes the following steps:

[0126] Step S2028: determining a channel fading model based on the ephemeris information;

[0127] Ephemeris information provides the orbital position and velocity of the satellite at a specific point in time, and is the basic data for building a channel fading model.

[0128] Channel fading models are used to simulate the signal transmission characteristics of satellite communication links. They include parameters such as path loss, Doppler shift, and delay variation. These parameters vary over time, reflecting the influence of relative motion between the satellite and the ground terminal.

[0129] By building a channel fading model using ephemeris information, we can simulate the fading of signals in different frequency bands and environments under high-speed satellite motion scenarios, which is crucial for evaluating the performance of ground terminals in dynamic environments.

[0130] Step S2029: Determine a channel simulation file based on the channel fading model and the communication system.

[0131] The determined channel fading model is combined with the specific requirements of the communication system to generate a configuration file for the channel simulator, namely the channel simulation file, to simulate the terminal communication performance loop test under the high-speed movement scenario of the LEO satellite.

[0132] It can be understood that the channel simulation file is used to guide the channel simulator to simulate actual dynamic channel conditions, so that the test environment is closer to the actual communication scenario, thereby being able to more realistically evaluate the performance of the terminal.

[0133] Optionally, using a satellite loop simulation test system to test the communication between the terminal and the satellite to obtain a test result includes the following steps:

[0134] Step S2031, controlling the terminal to move according to the motion trajectory based on the turntable system;

[0135] Optionally, the turntable system in the satellite loop simulation test system continuously adjusts the turntable according to the determined terminal motion trajectory, thereby achieving dynamic adjustment of the terminal, causing the terminal to move according to the motion trajectory, simulating the terminal's real-time tracking of the LEO satellite.

[0136] Step S2032, in response to the terminal moving along the motion trajectory, using the communication system to send a downlink test signal to the terminal;

[0137] When the turntable system drives the terminal to move according to the motion trajectory, the communication system sends a predefined downlink test signal to the terminal to verify the terminal's receiving capability and signal processing capability under dynamic conditions.

[0138] Step S2033: using the communication system to obtain an uplink test signal fed back by the terminal based on the downlink test signal, wherein the communication system and the turntable system operate based on a time reference issued by the time system;

[0139] Optionally, after the terminal receives and processes the downlink test signal, the terminal will feed back the uplink test signal to the communication system. The uplink test signal is used to evaluate the terminal's transmission power, modulation quality and signal integrity, as well as the bidirectional performance of the communication link, ensuring the comprehensiveness and accuracy of the test.

[0140] The timing system can output accurate time signals to ensure the time synchronization of the communication system and the turntable system when performing test tasks.

[0141] Step S2034: Determine the test result according to the downlink test signal and the uplink test signal.

[0142] After receiving the uplink test signal, the communication system analyzes the downlink and uplink test signal data to determine the terminal's communication performance indicators, such as bit error rate, throughput, latency, and tracking accuracy. The test results are used to determine whether the terminal meets design requirements and whether there are any performance bottlenecks.

[0143] In summary, the embodiments of the present invention obtain ephemeris information; determine the terminal motion trajectory and channel simulation file based on the ephemeris information; input the terminal motion trajectory and channel simulation file into the satellite loop simulation test system, and use the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain test results, thereby solving the technical problem of how to construct a darkroom test environment under the high-speed motion scenario of low-orbit broadband satellites to verify the end-to-end communication performance of the terminal under real-time tracking of satellites.

[0144] Through the description of the above embodiments, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus the necessary general hardware platform, and of course it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a number of instructions for enabling a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods described in each embodiment of the present invention.

[0145] An embodiment of the present invention further provides a testing system for implementing the above embodiments and preferred implementations.

[0146] Figure 5 FIG. 5 is a block diagram of a test system 500 according to one embodiment of the present invention. Figure 5As shown, the system comprises: a satellite loop simulation test system 100; a host computer 502 configured to acquire ephemeris information; determine a terminal motion trajectory and a channel simulation file according to the ephemeris information; input the terminal motion trajectory and the channel simulation file into the satellite loop simulation test system, and test the communication between the terminal and the satellite by using the satellite loop simulation test system to obtain a test result.

[0147] Optionally, the host computer 502 is further configured to: determine a satellite position coordinate and a satellite speed according to the ephemeris information, wherein the satellite position coordinate is in an earth-centered earth-fixed coordinate system; determine a terminal position coordinate of the terminal in the earth-centered earth-fixed coordinate system according to a coordinate of the terminal in a geographical coordinate system; determine an elevation angle and an azimuth angle of the terminal in a satellite visual angle according to the satellite position coordinate and the terminal position coordinate; and determine the terminal motion trajectory according to the elevation angle and the azimuth angle.

[0148] Optionally, the host computer 502 is further configured to: determine a target coordinate system according to the satellite position coordinate, wherein an origin of the target coordinate system is the satellite position; determine a relative coordinate of the terminal in the target coordinate system according to the terminal position coordinate and the target coordinate system; and determine the elevation angle and the azimuth angle of the terminal in the satellite visual angle according to the relative coordinate.

[0149] Optionally, the host computer 502 is further configured to: determine a channel fading model according to the ephemeris information; and determine the channel simulation file according to the channel fading model and a communication system.

[0150] Optionally, the host computer 502 is further configured to: control the terminal to move according to the motion trajectory based on a turntable system; send a downlink test signal to the terminal by using the communication system in response to the terminal moving on the motion trajectory; acquire an uplink test signal fed back by the terminal based on the downlink test signal by using the communication system, wherein the communication system and the turntable system operate based on a time reference sent by a time system; and determine the test result according to the downlink test signal and the uplink test signal.

[0151] Embodiments of the present application also provide an electronic device comprising: a memory storing an executable program; and a processor configured to run the executable program, wherein the executable program, when running, performs the satellite loop simulation test method of any of the above embodiments.

[0152] Optionally, in the present embodiment, the processor of the electronic device can be configured to run the executable program to perform the following steps:

[0153] Step S201: acquiring ephemeris information.

[0154] Step S202: determining a terminal motion trajectory and a channel simulation file according to the ephemeris information.

[0155] Step S203, inputting the terminal motion trajectory and the channel simulation file into the satellite loop simulation test system, testing the communication between the terminal and the satellite by using the satellite loop simulation test system, and obtaining a test result.

[0156] Optionally, the processor in the electronic device can be configured to run an executable program to perform the following steps: determining a satellite position coordinate and a satellite speed according to the ephemeris information, wherein the satellite position coordinate is in an earth-centered earth-fixed coordinate system; determining a terminal position coordinate of the terminal in the earth-centered earth-fixed coordinate system according to a coordinate of the terminal in a geographic coordinate system; determining an elevation angle and an azimuth angle of the terminal in a satellite visual angle according to the satellite position coordinate and the terminal position coordinate; and determining the terminal motion trajectory according to the elevation angle and the azimuth angle.

[0157] Optionally, the processor in the electronic device can be configured to run an executable program to perform the following steps: determining a target coordinate system according to the satellite position coordinate, wherein an origin of the target coordinate system is the satellite position; determining a relative coordinate of the terminal in the target coordinate system according to the terminal position coordinate and the target coordinate system; and determining the elevation angle and the azimuth angle of the terminal in the satellite visual angle according to the relative coordinate.

[0158] Optionally, the processor in the electronic device can be configured to run an executable program to perform the following steps: determining a channel fading model according to the ephemeris information; and determining the channel simulation file according to the channel fading model and the communication system.

[0159] Optionally, the processor in the electronic device can be configured to run an executable program to perform the following steps: controlling the terminal to move according to the motion trajectory based on a turntable system; sending a downlink test signal to the terminal by using the communication system in response to the terminal moving on the motion trajectory; obtaining an uplink test signal fed back by the terminal based on the downlink test signal by using the communication system, wherein the communication system and the turntable system operate based on a time reference issued by a time system; and determining a test result according to the downlink test signal and the uplink test signal.

[0160] Embodiments of the present application also provide a computer readable storage medium including a stored executable program, wherein the computer readable storage medium controls a device where the computer readable storage medium is located to perform the satellite loop simulation test method according to any one of the above embodiments when the executable program is run.

[0161] Optionally, in the present embodiment, the executable program can be configured to store an executable program for performing the following steps:

[0162] Step S201, obtaining ephemeris information.

[0163] Step S202, determining a terminal motion trajectory and a channel simulation file according to the ephemeris information.

[0164] Step S203: input the terminal motion trajectory and the channel simulation file into the satellite loop simulation test system, and use the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain a test result.

[0165] Optionally, the above-mentioned executable program can be configured to store an executable program for performing the following steps: determining the satellite position coordinates and satellite speed based on ephemeris information, wherein the satellite position coordinates are in the geocentric earth fixed coordinate system; determining the terminal position coordinates of the terminal in the geocentric earth fixed coordinate system based on the coordinates of the terminal in the geographic coordinate system; determining the pitch angle and azimuth angle of the terminal from the satellite's perspective based on the satellite position coordinates and the terminal position coordinates; and determining the terminal motion trajectory based on the pitch angle and azimuth angle.

[0166] Optionally, the above-mentioned executable program can be configured to store an executable program for performing the following steps: determining a target coordinate system based on the satellite position coordinates, wherein the origin of the target coordinate system is the satellite position; determining the relative coordinates of the terminal in the target coordinate system based on the terminal position coordinates and the target coordinate system; and determining the pitch angle and azimuth angle of the terminal from the satellite's perspective based on the relative coordinates.

[0167] Optionally, the above executable program may be configured to store an executable program for executing the following steps: determining a channel fading model based on ephemeris information; and determining a channel simulation file based on the channel fading model and the communication system.

[0168] Optionally, the above-mentioned executable program can be configured to store an executable program for executing the following steps: controlling the terminal to move according to a motion trajectory based on the turntable system; using the communication system to send a downlink test signal to the terminal in response to the terminal moving along the motion trajectory; using the communication system to obtain an uplink test signal fed back by the terminal based on the downlink test signal, wherein the communication system and the turntable system operate based on a time reference issued by the timing system; and determining the test result based on the downlink test signal and the uplink test signal.

[0169] An embodiment of the present invention further provides a computer program product, including a computer program, which implements the satellite loop simulation test method described in any of the above embodiments when executed by a processor.

[0170] Optionally, in this embodiment, the computer program implements the following steps when executed by a processor:

[0171] Step S201: Obtain ephemeris information.

[0172] Step S202: Determine the terminal motion trajectory and channel simulation file based on the ephemeris information.

[0173] Step S203: input the terminal motion trajectory and the channel simulation file into the satellite loop simulation test system, and use the satellite loop simulation test system to test the communication between the terminal and the satellite to obtain a test result.

[0174] Optionally, the above-mentioned computer program implements the following steps when executed by the processor: determining the satellite position coordinates and satellite speed based on the ephemeris information, wherein the satellite position coordinates are in the geocentric earth fixed coordinate system; determining the terminal position coordinates of the terminal in the geocentric earth fixed coordinate system based on the coordinates of the terminal in the geographic coordinate system; determining the pitch angle and azimuth angle of the terminal from the satellite's perspective based on the satellite position coordinates and the terminal position coordinates; and determining the terminal motion trajectory based on the pitch angle and azimuth angle.

[0175] Optionally, the above-mentioned computer program implements the following steps when executed by the processor: determining the target coordinate system based on the satellite position coordinates, wherein the origin of the target coordinate system is the satellite position; determining the relative coordinates of the terminal in the target coordinate system based on the terminal position coordinates and the target coordinate system; and determining the pitch angle and azimuth angle of the terminal from the satellite perspective based on the relative coordinates.

[0176] Optionally, the computer program implements the following steps when executed by a processor: determining a channel fading model based on ephemeris information; and determining a channel simulation file based on the channel fading model and the communication system.

[0177] Optionally, the above-mentioned computer program implements the following steps when executed by the processor: controlling the terminal to move according to the motion trajectory based on the turntable system; sending a downlink test signal to the terminal using the communication system in response to the terminal moving along the motion trajectory; obtaining an uplink test signal fed back by the terminal based on the downlink test signal using the communication system, wherein the communication system and the turntable system operate based on the time reference issued by the timing system; and determining the test result based on the downlink test signal and the uplink test signal.

[0178] Optionally, specific examples in this embodiment may refer to the examples described in the above embodiments and optional implementation modes, and this embodiment will not be described in detail here.

[0179] In the above embodiments of the present invention, the description of each embodiment has its own focus. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0180] In some embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the system embodiments described above are only exemplary. For example, the division of units can be a logical function division. In actual implementation, there may be other division methods, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0181] Units described as separate components may or may not be physically separate, and components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple units. Some or all of the units may be selected to achieve the purpose of the present embodiment according to actual needs.

[0182] In addition, the functional units in the various embodiments of the present invention may be integrated into a single processing unit, each unit may exist physically separately, or two or more units may be integrated into a single unit. The aforementioned integrated units may be implemented in the form of hardware or software functional units.

[0183] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, server or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, magnetic disk or optical disk, etc. Various media that can store program codes.

[0184] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A satellite loop simulation test system, characterized in that: include: Anechoic chamber system, used to simulate the electromagnetic propagation environment between satellites and terminals; a turntable system, deployed in the darkroom system, for controlling the movement of the terminal in the darkroom system according to an input terminal motion trajectory; A communication system, configured to send a downlink test signal to the terminal and receive an uplink test signal fed back by the terminal according to an input channel simulation file, wherein the uplink test signal and the downlink test signal are used to determine a test result of a satellite loop simulation test; A time system is used to generate a unified time base for the turntable system and the communication system, and the turntable system and the communication system operate based on the time base.

2. The satellite loop simulation test system according to claim 1, characterized in that: The communication system includes a packet injection server, a core network, a base station, a channel simulator and a frequency conversion module, wherein the packet injection server is used to send the generated test data packet to the base station through the core network, the base station is used to convert the signal format of the test data packet and send the intermediate frequency signal after the format conversion to the channel simulator, the channel simulator is used to simulate the channel fading characteristics of the intermediate frequency signal in the satellite-to-ground link, and the frequency conversion module is used to convert the frequency of the signal entering the frequency conversion module.

3. The satellite loop simulation test system according to claim 1, characterized in that: The darkroom system includes a darkroom, a feed antenna and a reflecting surface.

4. The satellite loop simulation test system according to claim 1, characterized in that: The timing system includes a global navigation satellite system simulator for generating the time reference.

5. A satellite loop simulation test method, characterized in that: include: Get ephemeris information; Determining a terminal motion trajectory and a channel simulation file based on the ephemeris information; The terminal motion trajectory and the channel simulation file are input into the satellite loop simulation test system according to any one of claims 1 to 4, and the communication between the terminal and the satellite is tested using the satellite loop simulation test system to obtain a test result.

6. The satellite loop simulation test method according to claim 5, characterized in that: The determining of the terminal motion trajectory according to the ephemeris information includes: Determining satellite position coordinates and satellite velocity based on the ephemeris information, wherein the satellite position coordinates are in a geocentric Earth-fixed coordinate system; Determining the terminal position coordinates of the terminal in the geocentric earth-fixed coordinate system according to the coordinates of the terminal in the geographic coordinate system; Determining the elevation angle and azimuth angle of the terminal from the perspective of the satellite according to the satellite position coordinates and the terminal position coordinates; Determine the terminal motion trajectory according to the pitch angle and the azimuth angle.

7. The satellite loop simulation test method according to claim 6, characterized in that: The determining, based on the satellite position coordinates and the terminal position coordinates, the pitch angle and the azimuth angle of the terminal from the satellite perspective, includes: Determining a target coordinate system based on the satellite position coordinates, wherein the origin of the target coordinate system is the satellite position; Determining the relative coordinates of the terminal in the target coordinate system according to the terminal position coordinates and the target coordinate system; Determine the elevation angle and azimuth angle of the terminal under the perspective of the satellite according to the relative coordinates.

8. The satellite loop simulation test method according to claim 5, characterized in that: The determining of the channel simulation file according to the ephemeris information includes: determining a channel fading model according to the ephemeris information; The channel simulation file is determined according to the channel fading model and the communication system.

9. The satellite loop simulation test method according to claim 5, characterized in that: The method of testing the communication between the terminal and the satellite using the satellite loop simulation test system to obtain a test result includes: Controlling the terminal to move according to the motion trajectory based on the turntable system; In response to the terminal moving along the motion trajectory, using a communication system, sending a downlink test signal to the terminal; Utilizing the communication system, obtaining an uplink test signal fed back by the terminal based on the downlink test signal, wherein the communication system and the turntable system operate based on a time reference issued by a time synchronization system; The test result is determined according to the downlink test signal and the uplink test signal.

10. A testing system, characterized in that: include: The satellite loop simulation test system according to any one of claims 1 to 4; Host computer, used to obtain ephemeris information; According to the ephemeris information, the terminal motion trajectory and channel simulation file are determined; the terminal motion trajectory and channel simulation file are input into the satellite loop simulation test system, and the satellite loop simulation test system is used to test the communication between the terminal and the satellite to obtain the test results.

11. An electronic device, characterized in that: include: a memory storing an executable program; A processor, configured to run the program, wherein the program, when running, executes the method according to any one of claims 5 to 9.

12. A computer-readable storage medium, characterized in that The computer-readable storage medium includes a stored executable program, wherein when the executable program is run, the device where the storage medium is located is controlled to execute the method according to any one of claims 5 to 9.

13. A computer program product, characterized in that The invention comprises a computer program which, when executed by a processor, implements the method according to any one of claims 5 to 9.

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