A method and apparatus for testing demodulation performance of an NGSO non-terrestrial network terminal

Abstract

The present application provides a kind of NGSO non-terrestrial network terminal demodulation performance test method and device, comprising: generating analog non-geostationary satellite link with simulation time variation;In response to the terminal under test accesses test equipment through analog satellite link, start the demodulation performance index test of current test round;If the simulation elevation angle reaches the second elevation angle, the test end condition has not been met, the cumulative test data is retained, the satellite orbit simulation is reset to the starting trajectory position, and the simulated satellite link is regenerated;In response to the terminal under test re-accesses test equipment through regenerated simulated satellite link, continue the demodulation performance index test until the test end condition is met, and determine the test result.The cumulative statistical length of demodulation performance index test and result determination process is no longer limited to non-geostationary orbit single-satellite visible time, and long-time demodulation performance index test that cannot obtain sufficient test data within single-satellite visible time can be completed.

Description

Technical Field

[0001] The embodiments in this specification relate to the field of satellite communication testing technology, and in particular to a method and apparatus for testing the demodulation performance of NGSO non-terrestrial network terminals. Background Technology

[0002] Non-Terrestrial Networks (NTNs) utilize non-terrestrial platforms such as satellites to provide wireless communication services. Unlike fixed base stations in terrestrial networks, NGSO (Non-Geostationary Orbit) satellites are in continuous motion relative to ground terminals, and the distance, elevation angle, and wireless propagation conditions between the satellite and the terminal change over time. To verify the communication performance of NGSO NTN terminals in this dynamic environment, test equipment can simulate satellite orbits according to preset satellite simulation trajectories and generate simulated satellite links that change over time based on the simulation results, thereby testing the demodulation performance indicators of NGSO NTN terminals.

[0003] Due to factors such as orbital altitude, terminal location, and minimum available satellite elevation angle, the visibility time of a single low-Earth orbit (LEO) satellite relative to a specific ground location is typically short. For example, the visibility time for a single LEO satellite at an altitude of approximately 1200 kilometers is about 6 to 8 minutes. Once the satellite moves out of the terminal's line of sight, the link between the terminal and the satellite cannot be maintained. Therefore, when using dynamic satellite orbit simulation for terminal testing, terminal access, test parameter configuration, and demodulation performance index testing must be completed within the corresponding satellite visibility time.

[0004] One existing method for testing non-terrestrial network terminals uses static satellite positions. Taking New Radio Non-Terrestrial Network (NR-NTN) as an example, the testing equipment can provide the terminal with a fixed satellite ephemeris and maintain the simulated satellite's position unchanged during the test. This method allows selecting a satellite position that remains continuously within the terminal's line of sight, thus preventing the satellite from moving out of the terminal's line of sight during the test. However, static satellite positions cannot reflect the continuous motion characteristics of low-Earth orbit satellites, nor can they fully demonstrate the changes in link parameters such as propagation delay, Doppler shift, and path loss as the satellite position changes.

[0005] Furthermore, some demodulation performance tests require the continuous collection of substantial amounts of test data until the data meets specified statistical or confidence level requirements before a test result can be determined. The result determination process for this type of test is also unsuitable for splitting the results into multiple independent test results based on a single satellite visibility time. When the test duration required to determine the result exceeds the visibility time of a single satellite, the simulated satellite may move out of the terminal's line of sight before the test ends, causing the terminal under test to lose the satellite link and resulting in an interruption of the demodulation performance test.

[0006] Furthermore, some related technologies extend the time a terminal can maintain a satellite link by simulating multiple satellites and switching between them. However, multi-satellite switching requires configuring the simulated trajectories and link parameters of multiple satellites, and processing the terminal status and test data during the satellite switching period. Whether to pause demodulation performance testing during switching, how to determine the pause period, and how to process test data before and after switching all require establishing corresponding control rules, making the test implementation quite complex. In addition, it is difficult to avoid switching failures of the tested terminal, and the statistical time window for pausing demodulation performance test data during switching is difficult to standardize and determine, making it difficult to reproduce and compare test results, and the test methods are not easy to standardize.

[0007] Therefore, there is a need to provide a demodulation performance testing scheme for NGSO non-terrestrial network terminals that is suitable for NGSO dynamic satellite orbit simulation environment, so that the demodulation performance index test can be completed and the test results can be determined under the limitation of the duration of the single satellite orbit simulation segment. Summary of the Invention

[0008] This specification provides an NGSO non-terrestrial network terminal demodulation performance testing method, apparatus, and equipment to enable the cumulative statistical duration and result determination process of demodulation performance index testing to no longer be limited by the visibility time of a single satellite, and to complete long-term demodulation performance index testing where sufficient test data cannot be obtained within the visibility time of a single satellite.

[0009] One aspect of this specification provides a method for testing the demodulation performance of NGSO (Non-Terrestrial Network) terminals, applied to test equipment, including: According to the preset non-geostationary orbit NGSO satellite simulation trajectory, the satellite orbit simulation is started from the starting trajectory position with the simulated elevation angle of the first elevation angle on the preset satellite simulation trajectory, and the simulated satellite link changes with the simulation time. In response to the terminal under test accessing the test equipment through the simulated satellite link, the demodulation performance index test of the current test round is started. During the demodulation performance index test, the simulated elevation angle generated by the satellite orbit simulation is obtained, the cumulative test data is updated according to the test data generated in the current test round, and it is determined whether the test termination condition is met based on the updated cumulative test data. If the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, the demodulation performance index test is terminated, and the test result is determined based on the cumulative test data. If the test termination condition is not met when the simulated elevation angle reaches the second elevation angle, the test is paused, the connection between the terminal under test and the simulated satellite link is disconnected, the accumulated test data is retained, the satellite orbit simulation is reset to the starting trajectory position, and the satellite orbit simulation is restarted from the starting trajectory position to regenerate the simulated satellite link. In response to the terminal under test reconnecting to the test equipment via the regenerated simulated satellite link, the demodulation performance index test continues. The test data is accumulated based on the previous round of accumulated test data. This process is repeated in a loop until the accumulated test data meets the test termination condition. The test ends and the test result is determined based on the latest accumulated test data. Wherein, the first elevation angle and the second elevation angle are used to define the orbit simulation section corresponding to a single test round. The first elevation angle is the starting boundary elevation angle of the orbit simulation section, and the second elevation angle is the ending boundary elevation angle of the orbit simulation section. The ending trajectory position corresponding to the second elevation angle is located after the starting trajectory position corresponding to the first elevation angle according to the simulation time sequence of the preset satellite simulation trajectory.

[0010] Furthermore, the demodulation performance indicators were tested in each test round using the same preset satellite simulated trajectory, first elevation angle, second elevation angle, and preset test parameters.

[0011] Furthermore, the method also includes: dynamically updating the cumulative confidence level as the demodulation performance index test data included in the cumulative test data increases in multiple rounds of testing; the test termination condition includes the cumulative confidence level reaching a preset confidence threshold.

[0012] Furthermore, generating the simulated satellite link that changes with simulation time includes: dynamically determining the link parameters of the simulated satellite link based on the preset satellite simulated trajectory and the simulated elevation angle generated by the satellite orbit simulation, wherein the link parameters include propagation delay, Doppler shift and path loss.

[0013] Furthermore, before the satellite orbit simulation is started for the first time, preset test parameters for generating the simulated satellite link are configured, the preset test parameters including at least one of non-terrestrial network tap delay line channel model parameters and signal-to-noise ratio parameters.

[0014] Furthermore, the first elevation angle and the second elevation angle are determined based on the correspondence between the satellite link status and the satellite elevation angle recorded by the terminal during actual use or pre-testing; wherein, the first elevation angle is determined based on a first reference elevation angle, which is the satellite elevation angle corresponding to the satellite link changing from an unavailable state to an available state; the second elevation angle is determined based on a second reference elevation angle, which is the satellite elevation angle corresponding to the satellite link changing from an available state to an unavailable state after the satellite link changes from an unavailable state to an available state.

[0015] Furthermore, the method further includes: determining the first elevation angle based on the first reference elevation angle and the first preset elevation angle margin, and determining the second elevation angle based on the second reference elevation angle and the second preset elevation angle margin, so that the starting trajectory position corresponding to the first elevation angle and the ending trajectory position corresponding to the second elevation angle are located within the available range of the satellite link.

[0016] Another aspect of this specification provides an NGSO non-terrestrial network terminal demodulation performance testing device, applied to testing equipment, comprising: The generation module is used to simulate satellite orbits from the starting position of the preset satellite simulation trajectory with a simulated elevation angle of the first elevation angle, according to the preset non-geostationary orbit NGSO satellite simulation trajectory, and generate a simulated satellite link that changes with the simulation time. The startup module is used to respond to the terminal under test accessing the test equipment through the simulated satellite link, start the demodulation performance index test of the current test round, and during the demodulation performance index test, obtain the simulated elevation angle generated by the satellite orbit simulation, update the cumulative test data according to the test data generated in the current test round, and determine whether the test termination condition is met based on the updated cumulative test data. The first test module is used to terminate the demodulation performance index test if the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, and to determine the test result based on the cumulative test data. The reset module is used to pause the test, disconnect the connection between the terminal under test and the simulated satellite link, retain the accumulated test data, reset the satellite orbit simulation to the starting trajectory position, and restart the satellite orbit simulation from the starting trajectory position to regenerate the simulated satellite link if the test end condition is not met when the simulated elevation angle reaches the second elevation angle. The second test module is used to respond to the terminal under test reconnecting to the test equipment through the regenerated simulated satellite link, continue to test demodulation performance indicators, continue to accumulate test data based on the accumulated test data of the previous round, and repeat the test rounds in this way until the accumulated test data meets the test termination condition, then end the test and determine the test result based on the latest accumulated test data. Wherein, the first elevation angle and the second elevation angle are used to define the orbit simulation section corresponding to a single test round. The first elevation angle is the starting boundary elevation angle of the orbit simulation section, and the second elevation angle is the ending boundary elevation angle of the orbit simulation section. The ending trajectory position corresponding to the second elevation angle is located after the starting trajectory position corresponding to the first elevation angle according to the simulation time sequence of the preset satellite simulation trajectory.

[0017] Another aspect of this specification provides an electronic device including at least one processor and a memory; the memory stores a computer program or instruction set; at least one of the processors executes the computer program or instruction set stored in the memory, such that at least one of the processors performs the method described in any of the foregoing embodiments.

[0018] This specification also provides a computer-readable storage medium storing a computer program or instruction set that, when executed by a processor, performs the method described in any of the foregoing embodiments.

[0019] This specification also provides a computer program product comprising a computer program that, when executed by a processor, implements the method described in any of the foregoing embodiments.

[0020] Compared with the prior art, the method provided in the embodiments of this specification has at least the following beneficial effects: Each test cycle is completed within the orbit simulation segment defined by the first and second elevation angles, and does not exceed the single-satellite visibility duration corresponding to that orbit simulation segment. The cumulative statistical process for the same demodulation performance index test can span multiple test cycles. The satellite orbit simulation is reset between each test cycle, while the cumulative test data is retained and continuously updated between test cycles, enabling the demodulation performance index test data generated from multiple test cycles to be used together to determine whether the test termination conditions are met and to determine the same test result.

[0021] For demodulation performance index tests where the required testing time to complete statistical result determination exceeds the single satellite's visible duration, the necessary demodulation performance index test data can be obtained across multiple test rounds, rather than forming multiple independent test results. These results are then accumulated according to the same statistical rules until the accumulated test data meets the test termination criteria. Therefore, the cumulative statistical time and result determination process for demodulation performance index testing are no longer limited by the visible duration of a single satellite, enabling long-term demodulation performance index tests where sufficient test data cannot be obtained within the visible time of a single satellite.

[0022] Furthermore, by repeatedly using the same preset satellite simulation trajectory and resetting the satellite orbit simulation between each test round, continuous accumulation of demodulation performance index test data can be achieved. This eliminates the need to configure multiple simulation satellites or perform satellite switching to extend the cumulative test duration, thereby reducing the need for trajectory configuration, link configuration, and switching control of multiple satellites. It also avoids the inability to complete demodulation performance testing due to terminal switching failure. In addition, it avoids the problem of difficulty in standardizing and determining the time window for pausing demodulation performance test data statistics during switching. It is an executable, reproducible, comparable, standardized, and easy-to-implement test method.

[0023] In addition to the technical problems solved by at least one embodiment of this application, the technical features constituting the technical solution, and the beneficial effects brought about by the technical features of these technical solutions as described above, other technical problems that can be solved by at least one embodiment of this application, other technical features included in the technical solution, and the beneficial effects brought about by these technical features will be further described in detail in the specific embodiments. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings: Figure 1 A schematic diagram illustrating the satellite visibility time relationship between a ground terminal and a service satellite as provided in the embodiments of this specification; Figure 2 This is a flowchart illustrating a method for testing the demodulation performance of a non-terrestrial network terminal provided in an embodiment of this specification. Figure 3 A flowchart illustrating the determination of the first elevation angle and the second elevation angle provided for embodiments of this specification; Figure 4 A schematic diagram of a demodulation performance testing device for a non-terrestrial network terminal provided in the embodiments of this specification; Figure 5 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this specification.

[0025] [Explanation of Figure Markers]: 401. Generation Module; 402. Startup module; 403. First test module; 404, Module Reset; 405. Second Test Module; 502. Computer equipment; 504. Processing equipment; 506. Storage resources; 508. Drive mechanism; 510. Input / output module; 512. Input devices; 514. Output devices; 516. Presentation equipment; 518. Graphical User Interface; 520. Network interface; 522. Communication link; 524. Communication bus. Detailed Implementation

[0026] The present specification will now be described in detail with reference to the specific embodiments shown in the accompanying drawings. However, these embodiments do not limit the scope of this specification, and any structural, methodological, or functional modifications made by those skilled in the art based on these embodiments are included within the scope of protection of this specification.

[0027] It should be understood that in the description of the specific embodiments in this specification, terms such as "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature.

[0028] In the specific embodiments described in this specification, unless otherwise explicitly stated and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a movable connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this specification according to the specific circumstances.

[0029] In the specific embodiments described herein, unless otherwise expressly specified and limited, "above" or "below" a second feature may include direct contact between the first and second features, or contact between the first and second features not in direct contact but through another feature between them. In the specific embodiments described herein, unless otherwise expressly specified and limited, the term "more" means two or more.

[0030] This specification provides the operational steps of the methods described in the embodiments or flowcharts, but based on conventional or non-inventive labor, more or fewer operational steps may be included. The order of steps listed in the embodiments is merely one possible execution order among many and does not represent the only possible execution order. In actual system or device products, the methods shown in the embodiments or drawings can be executed sequentially or in parallel.

[0031] To facilitate understanding the apparent time of a single low-Earth orbit satellite relative to a specific ground location, combined with Figure 1 Please provide an explanation. For example... Figure 1 As shown, Figure 1 The diagram illustrates the satellite visibility time relationship between the ground terminal and the serving satellite. The serving satellite moves relative to the ground along its orbit, while the ground terminal is located on the ground. A satellite communication link is established between the serving satellite and the ground terminal, allowing the ground terminal to connect to the serving base station via the serving satellite.

[0032] With the horizontal plane at the location of the ground terminal as a reference, as the elevation angle of the service satellite rises from about +30° to about 90° and then falls to about -30°, the service satellite is within the line of sight of the ground terminal for which satellite communication with guaranteed quality can be carried out. The line of sight time for a single service satellite within this line of sight is about 6 to 8 minutes. Figure 1 The service satellite orbit in the upper middle section represents the trajectory of the service satellite, and the service satellite and its beam coverage area in the orbit represent the satellite communication coverage provided by the service satellite to the ground terminal. Figure 1 The ground terminal in the lower center represents the terminal to be accessed or the test object located on the ground. As the service satellite moves along its orbit, the elevation angle of the service satellite relative to the ground terminal, the relative position between the satellite and the ground terminal, and the satellite communication coverage area change over time. When the service satellite leaves the line of sight of the ground terminal, the ground terminal may not be able to maintain the satellite communication link with the service satellite.

[0033] In the existing technology, there is a lack of a non-terrestrial network terminal demodulation performance testing scheme suitable for dynamic satellite orbit simulation environment, so as to break through the limitation of single satellite visibility time.

[0034] To address the technical problems existing in the prior art, this specification provides a method, apparatus, and device for testing the demodulation performance of non-terrestrial network terminals. The technical solution of this specification will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] Figure 2 This is a flowchart illustrating a method for testing the demodulation performance of a non-terrestrial network terminal provided in an embodiment of this specification. The subject executing this method can be a test device.

[0036] The test equipment described in this manual is capable of performing satellite orbit simulation, generating simulated satellite links, and conducting demodulation performance index tests. The test equipment can be a single test instrument integrating these functions, or it can consist of an orbit simulation module, a non-terrestrial network base station simulation module, a channel simulation module, and a demodulation performance index test module. Different modules can be housed in the same hardware device, or they can be housed in multiple hardware devices capable of data communication and synchronization control.

[0037] The terminal under test (DUT) is a terminal device that supports communication via non-terrestrial networks. The DUT can perform system information reception, random access, and wireless connection establishment via a simulated satellite link generated by the test equipment, and then perform demodulation performance testing after completing the access.

[0038] A preset satellite simulation trajectory describes the relationship between the position of the simulated satellite and the measured terminal over simulation time. The preset satellite simulation trajectory can be determined based on information such as satellite orbital parameters, satellite ephemeris, the geographical location of the measured terminal, and the preset simulation time. The satellite orbit simulation operates according to the preset satellite simulation trajectory and generates satellite position, distance between the satellite and the measured terminal, simulated elevation angle, and other simulation parameters related to orbital motion.

[0039] The simulated elevation angle is generated by satellite orbit simulation and is used to represent the position of the simulated satellite relative to the terminal under test. The simulated elevation angle can change as the satellite orbit simulation progresses. In the embodiments of this specification, the first elevation angle and the second elevation angle are used to define the orbit simulation segment corresponding to a single test cycle that meets the test environment conditions. The first elevation angle is the starting boundary elevation angle of the orbit simulation segment, and the second elevation angle is the ending boundary elevation angle of the orbit simulation segment. See below for details.

[0040] like Figure 2 As shown, the method may include the following steps: Step 201: According to the preset non-geostationary orbit NGSO satellite simulation trajectory, start the satellite orbit simulation from the starting trajectory position with the simulated elevation angle of the first elevation angle on the preset satellite simulation trajectory, and generate a simulated satellite link that changes with the simulation time.

[0041] Specifically, the test equipment loads a preset satellite simulation trajectory before starting the test. The preset satellite simulation trajectory includes multiple trajectory positions arranged in simulation time sequence. Each trajectory position can correspond to a simulation time and orbit simulation parameters such as the satellite position, the distance between the satellite and the terminal under test, and the simulated elevation angle at that simulation time.

[0042] The testing equipment determines the starting trajectory position with the first elevation angle on the preset satellite simulation trajectory, based on the first elevation angle. The starting trajectory position is used to determine the trajectory starting point when satellite orbit simulation begins in each test round.

[0043] When the preset satellite simulation trajectory includes both ascent and descent segments, the same elevation angle value may correspond to two or more trajectory positions. The testing equipment can determine the starting trajectory position from multiple trajectory positions corresponding to the first elevation angle based on the preset simulation direction and simulation timing. For example, the position on the preset satellite simulation trajectory that first enters the predetermined link availability range according to the simulation timing can be determined as the starting trajectory position. Therefore, the starting trajectory position is determined not only by the value of the first elevation angle but also by the specific position within the preset satellite simulation trajectory and the simulation timing.

[0044] The test equipment advances the simulation time from the initial trajectory position and continuously updates the position and elevation angle of the simulated satellite according to the preset satellite simulation trajectory. The test equipment generates a simulated satellite link based on the orbit simulation parameters generated from the satellite orbit simulation. The simulated satellite link may include the radio frequency signal between the test equipment and the terminal under test, as well as the non-terrestrial network channel characteristics applied to this radio frequency signal.

[0045] For example, the test equipment can update the propagation delay, Doppler shift, and path loss of the simulated satellite link according to the relative position and relative motion state between the satellite and the terminal under test. The test equipment can also provide the terminal under test with satellite ephemeris, common timing advance, or non-terrestrial network cell configuration information through system information, enabling the terminal under test to receive and process simulated satellite links according to the non-terrestrial network communication process.

[0046] In one example, the test equipment simulates a low-Earth orbit satellite according to a preset satellite trajectory. Starting from the initial trajectory position, the simulated satellite gradually enters the link availability range corresponding to the terminal under test and moves along the preset satellite trajectory to the termination trajectory position. During this period, the simulated satellite link generated by the test equipment changes with the simulation time, rather than maintaining a fixed satellite position and a fixed link state throughout the entire test.

[0047] Step 202: In response to the terminal under test accessing the test equipment through the simulated satellite link, start the demodulation performance index test for the current test round. During the demodulation performance index test, obtain the simulated elevation angle generated by the satellite orbit simulation, update the cumulative test data according to the test data generated in the current test round, and determine whether the test termination condition is met based on the updated cumulative test data.

[0048] After generating a simulated satellite link, the test equipment transmits downlink signals for terminal access via the simulated satellite link. These downlink signals may include synchronization signals, broadcast channel signals, and system information. The terminal under test synchronizes itself based on the received downlink signals, reads the corresponding system information, and performs random access and wireless connection establishment procedures.

[0049] The test equipment can determine whether the terminal under test (DUT) has successfully connected to the test equipment via a simulated satellite link based on the access signaling received from the DUT, or based on the terminal connection status provided by the network simulation module within the test equipment. Terminal access completion can include the DUT completing random access, establishing a radio resource control (RRC) connection, or entering a communication state capable of performing demodulation performance index tests. The specific access completion condition can be determined based on the test items to be performed and the corresponding test specifications.

[0050] The test equipment initiates the demodulation performance index test for the current test round in response to the terminal under test completing the connection. Therefore, the terminal connection process is distinguished from the demodulation performance index test process; the demodulation performance index test for the current test round is performed after the terminal completes the connection.

[0051] Demodulation performance index test data refers to the data obtained during the demodulation performance index testing process, used to calculate demodulation performance indicators and determine whether the test termination conditions are met. It corresponds to the test data for the Key Performance Indicator (KPI) of demodulation performance. Demodulation performance index test data may include at least one of the following: the number of data sent by the test equipment, the number of data correctly demodulated by the tested terminal, the number of data incorrectly demodulated by the tested terminal, the number of data that the tested terminal failed to demodulate, and the corresponding number of data transmissions. Depending on the statistical unit used for the demodulation performance index, the above data quantities may be the number of data blocks, transport blocks, bits, code blocks, data packets, or symbols.

[0052] For example, demodulation performance metrics may include at least one of Block Error Rate (BLER), Bit Error Rate (BER), Code Block Error Rate, Packet Error Rate, Demodulation Success Rate, and Throughput. Accordingly, demodulation performance metric test data may include at least one of the following: For block error rate, demodulation performance test data can include the total number of transport blocks and the number of erroneous transport blocks. The block error rate can be determined based on the ratio of the number of erroneous transport blocks to the total number of transport blocks. For bit error rate, demodulation performance test data can include the total number of transmitted bits and the number of erroneous bits. The bit error rate can be determined based on the ratio of the number of erroneous bits to the total number of transmitted bits. For code block error rate, demodulation performance test data can include the total number of code blocks and the number of erroneous code blocks. The code block error rate can be determined based on the ratio of the number of erroneous code blocks to the total number of code blocks. For packet error rate, demodulation performance test data can include the total number of data packets and the number of erroneous data packets. The packet error rate can be determined based on the ratio of the number of erroneous data packets to the total number of data packets. For demodulation success rate, demodulation performance test data can include the total amount of demodulated data and the amount of correctly demodulated data. The demodulation success rate can be determined based on the ratio of the amount of correctly demodulated data to the total amount of demodulated data. For throughput, demodulation performance test data can include the amount of data correctly demodulated by the tested terminal within the effective test time and the corresponding effective test time. The throughput can be determined based on the amount of correctly demodulated data and the effective test time.

[0053] The cumulative test data includes test data generated in the current test round and test data generated and retained in previous test rounds. At the start of the first test round, the cumulative test data can be initialized to a null value, a zero value, or the initial statistical value of the corresponding demodulation performance indicator. During the first test round, the test equipment updates the cumulative test data based on the continuously generated test data. In the second and subsequent test rounds, the test equipment continues to include the test data generated in the current test round, based on the cumulative test data retained from the previous test round.

[0054] It is understandable that updating cumulative test data is not limited to simply adding multiple test values ​​together. Test equipment can perform cumulative processing according to the statistical rules corresponding to the demodulation performance metrics. For example, it can accumulate the number of samples and erroneous samples obtained in each test round, or it can merge valid test data from different test rounds and recalculate the demodulation performance metrics. The method of accumulation can be determined based on the definition of the demodulation performance metrics and the corresponding test specifications.

[0055] While performing demodulation performance tests, the test equipment acquires the simulated elevation angle generated by the satellite orbit simulation. The simulated elevation angle can be periodically output by the orbit simulation module, or it can be calculated by the test equipment based on the satellite position and the position of the terminal under test at the current simulation time. The test equipment can read the simulated elevation angle according to a preset sampling period and compare it with a second elevation angle to determine whether the satellite orbit simulation has reached the termination boundary of the orbit simulation segment.

[0056] The testing equipment also determines whether the test termination condition is met based on the updated cumulative test data. The test termination condition is used to determine whether the cumulative test data is sufficient to form the test result for the current demodulation performance index. The test termination condition can be determined according to the test specifications, test items, or user configuration. For example, the test termination condition may include the cumulative confidence level corresponding to the cumulative test data reaching a preset confidence threshold, or it may include the cumulative number of valid samples reaching a preset number of samples. When the test termination condition includes multiple sub-conditions, it can be determined that the test termination condition is met when all sub-conditions are satisfied, or multiple sub-conditions can be combined and judged according to preset logic.

[0057] Therefore, the testing equipment monitors two aspects simultaneously during the demodulation performance index test: firstly, it monitors whether the simulated elevation angle has reached the second elevation angle; secondly, it monitors whether the accumulated test data meets the test termination conditions. Based on the two monitoring results, the testing equipment determines whether to end the entire demodulation performance index test or end the current test round and continue to execute the next test round.

[0058] Step 203: If the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, the demodulation performance index test is terminated, and the test result is determined based on the cumulative test data.

[0059] Specifically, the testing equipment continuously updates the cumulative test data in the current test round and performs test termination condition judgment on the updated cumulative test data. When the simulated elevation angle has not yet reached the second elevation angle, if the testing equipment determines that the cumulative test data has met the test termination condition, it stops generating data for the current demodulation performance index test, ends the demodulation performance index test, and determines the test result based on the current cumulative test data.

[0060] When the simulated elevation angle reaches the second elevation angle, if the updated cumulative test data meets the test termination condition, the test equipment also ends the demodulation performance index test and determines the test result based on the cumulative test data. This processing method covers the case where the test termination condition is met exactly at the termination boundary of the track simulation section.

[0061] Test results can include demodulation performance index values ​​determined based on accumulated test data, or comparison results between demodulation performance index values ​​and preset acceptance criteria. For example, the test equipment can calculate the corresponding demodulation performance index value based on accumulated test data and determine whether the demodulation performance index value meets the limit requirements specified in the test specification. The test equipment can also record information such as the accumulated test data, test duration, number of test rounds, first elevation angle, second elevation angle, and the identifier of the preset satellite simulated trajectory corresponding to the test results, in order to verify the test process and test results.

[0062] If the test termination conditions are met within the first test round, the test equipment does not need to reset the satellite orbit simulation, nor does it need to start the next test round. In this case, the demodulation performance index test can be completed within one orbit simulation segment.

[0063] If the test termination conditions are met in the second or subsequent test rounds, the test equipment determines the test result based on the latest cumulative test data obtained up to that test round. This cumulative test data includes test data retained from previous test rounds and newly generated test data from the current test round.

[0064] Step 204: If the test termination condition is not met when the simulated elevation angle reaches the second elevation angle, the test is paused, the connection between the terminal under test and the simulated satellite link is disconnected, the accumulated test data is retained, the satellite orbit simulation is reset to the starting trajectory position, and the satellite orbit simulation is restarted from the starting trajectory position to regenerate the simulated satellite link.

[0065] In the current test round, if the satellite orbit simulation reaches the termination trajectory position corresponding to the second elevation angle, and the updated cumulative test data has not yet met the test termination conditions, the test equipment disconnects the connection between the terminal under test and the simulated satellite link, pausing the demodulation performance index test of the current test round.

[0066] Pausing the current test round means ceasing the inclusion of newly generated data within the current orbital simulation segment in the demodulation performance index test. Pausing the current test round does not mean deleting previously obtained test data, nor does it imply making an independent judgment on the test results obtained up to the current test round.

[0067] The test equipment retains the cumulative test data obtained up to the current test round. The cumulative test data can be stored in association with the test task identifier, test round identifier, and test parameters so that the cumulative test data corresponding to the same test task can be updated in the next test round.

[0068] The testing equipment resets the satellite orbit simulation to the starting trajectory position. Resetting the satellite orbit simulation means adjusting the current trajectory position of the satellite orbit simulation from the ending trajectory position to the starting trajectory position corresponding to the first elevation angle, so that the next test round will still start from the same trajectory position. When resetting the satellite orbit simulation, the testing equipment retains the accumulated test data and does not restore the accumulated test data to the initial value.

[0069] After the satellite orbit simulation is reset, the test equipment restarts the satellite orbit simulation from the initial trajectory position and regenerates the simulated satellite link that changes over time. The regenerated simulated satellite link uses the same preset satellite simulation trajectory and test conditions as the previous test round, so that the test data generated in different test rounds can be accumulated according to the same statistical rules for demodulation performance indicators.

[0070] During the satellite orbit simulation reset process, the original simulated satellite link was interrupted, and the terminal under test changed from an connected state to an unconnected state. The next test round will not directly use the terminal's connected state from the previous test round, but will wait for the terminal under test to reconnect to the test equipment through the newly generated simulated satellite link.

[0071] Step 205: In response to the terminal under test reconnecting to the test equipment through the regenerated simulated satellite link, continue demodulation performance index testing, continue to accumulate test data based on the accumulated test data of the previous round, and repeat the test rounds in this way until the accumulated test data meets the test termination condition, end the test, and determine the test result based on the latest accumulated test data.

[0072] After the test equipment restarts the satellite orbit simulation from the initial trajectory position, it generates a simulated satellite link in the same manner as the previous test round, and sends the signals and system information required for the terminal under test to access the system through the newly generated simulated satellite link.

[0073] The terminal under test detects the regenerated simulated satellite link and performs cell search, synchronization, system information reading, and access procedures. Based on the access signaling sent by the terminal under test or the terminal's connection status, the test equipment determines that the terminal under test has reconnected to the test equipment via the regenerated simulated satellite link.

[0074] In response to the tested terminal successfully reconnecting, the test equipment initiates the next test round of demodulation performance testing. The next test round can use the same demodulation performance metrics, data transmission configuration, and statistical rules as the current test round. In the next test round, the test equipment generates new test data and updates the cumulative test data retained from the previous test round based on this new data.

[0075] For example, at the end of the first test round, the first cumulative test data is retained. After the second test round begins, the testing equipment adds the test data generated in the second test round to the first cumulative test data, obtaining the second cumulative test data. If the second cumulative test data still does not meet the test termination condition, the testing equipment stops the second test round at the second elevation angle, retains the second cumulative test data, and resets the satellite orbit simulation to the initial trajectory position again. After the third test round begins, the testing equipment continues to update the second cumulative test data based on the test data generated in the third test round.

[0076] Each test round corresponds to the same test task. Each test round only provides test data generated within the simulated track section, and does not determine independent final test results for each test round. The testing equipment accumulates the test data generated from multiple test rounds as data in a continuous statistical process, and determines whether the test termination conditions are met based on the accumulated data.

[0077] Specifically, after the next test round starts, the test equipment continues to acquire the simulated elevation angle generated by the satellite orbit simulation, updates the cumulative test data based on the test data generated in the next test round, and determines whether the test termination conditions are met based on the updated cumulative test data.

[0078] If the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, the test equipment will end the demodulation performance index test and determine the test result based on the latest cumulative test data.

[0079] If the test termination condition is not met when the simulated elevation angle reaches the second elevation angle, the test equipment will stop the current test cycle again, retain the latest cumulative test data, reset the satellite orbit simulation to the starting trajectory position, and wait for the terminal under test to reconnect through the newly generated simulated satellite link. After the terminal under test successfully reconnects, the test equipment will start the subsequent test cycles and continue to update the retained cumulative test data.

[0080] The above process can be executed two or more times until the accumulated test data meets the test termination criteria. The test equipment determines the test result based on the latest accumulated test data when the test termination criteria are met, and then terminates the current test task.

[0081] In this embodiment, the orbit simulation segment corresponding to a single test cycle refers to the trajectory segment formed according to the preset simulation time sequence of the satellite simulated trajectory, from the starting trajectory position corresponding to the first elevation angle to the ending trajectory position corresponding to the second elevation angle. The ending trajectory position corresponding to the second elevation angle is located after the starting trajectory position corresponding to the first elevation angle in the simulation time sequence.

[0082] The first elevation angle and the second elevation angle do not necessarily have a fixed absolute numerical relationship. For example, when the orbit simulation section is located in the trajectory phase where the satellite's elevation angle gradually increases, the second elevation angle can be greater than the first elevation angle; when the orbit simulation section includes the trajectory phase where the satellite gradually moves away from the tested terminal after passing the maximum elevation angle, the second elevation angle can be smaller than the first elevation angle. Even when the first and second elevation angles have the same absolute value, they can correspond to different trajectory positions on the preset satellite simulation trajectory. The testing equipment distinguishes between the two based on the starting trajectory position, the ending trajectory position, and the simulation timing, rather than determining the orbit simulation section solely based on the absolute value of the elevation angle.

[0083] Using the embodiments in this specification, a single test cycle is completed within the orbit simulation segment defined by the first and second elevation angles, and does not exceed the single-satellite visibility duration corresponding to that orbit simulation segment; the cumulative statistical process of the same demodulation performance index test can span multiple test cycles. The satellite orbit simulation is reset between each test cycle, while the cumulative test data is retained and continuously updated between each test cycle, enabling the demodulation performance index test data generated from multiple test cycles to be used together to determine whether the test termination conditions are met and to determine the same test result.

[0084] For demodulation performance index tests where the required testing time to complete statistical result determination exceeds the single satellite's visible duration, the necessary demodulation performance index test data can be obtained across multiple test rounds, rather than forming multiple independent test results. These results are then accumulated according to the same statistical rules until the accumulated test data meets the test termination criteria. Therefore, the cumulative statistical time and result determination process for demodulation performance index testing are no longer limited by the visible duration of a single satellite, enabling long-term demodulation performance index tests where sufficient test data cannot be obtained within the visible time of a single satellite.

[0085] Furthermore, by reusing the same preset satellite simulation trajectory and resetting the satellite orbit simulation between each test round, the demodulation performance index test data can be continuously accumulated. This eliminates the need to configure multiple simulation satellites or perform satellite switching in order to extend the cumulative test duration. It can reduce the trajectory configuration, link configuration, and switching control of multiple satellites, and also avoid the inability to complete the demodulation performance test due to terminal switching failure. In addition, it also avoids the problem of difficulty in standardizing and determining the time window for pausing demodulation performance test data statistics during switching.

[0086] In some embodiments of this specification, the process for determining the first elevation angle and the second elevation angle can be found in [reference needed]. Figure 3 ,like Figure 3 As shown, it includes the following steps: Step 301: Record the satellite link status and satellite elevation angle of the terminal during actual use or pre-testing.

[0087] Specifically, the test equipment acquires the satellite link status of the terminal during actual use or pre-testing and records the correspondence between the satellite link status and the satellite elevation angle.

[0088] In practical use, this can be the process of a terminal establishing and maintaining a satellite link with a serving satellite in a real non-terrestrial network. During practical use, the terminal's satellite link status can be recorded according to a preset sampling period, and the satellite elevation angle corresponding to each satellite link status can be determined based on the serving satellite's ephemeris information, the terminal's geographical location, and the sampling time. The data recorded during practical use can be pre-stored and provided to the testing equipment during configuration.

[0089] The pre-testing process can be a procedure where the test equipment determines the satellite link availability range of the terminal before formally performing demodulation performance tests. During pre-testing, the test equipment simulates a satellite orbit according to a preset satellite simulation trajectory, generating a simulated satellite link that changes over time, and then initiates a terminal connection to the test equipment via this simulated satellite link. The test equipment acquires the simulated elevation angle generated by the satellite orbit simulation at a preset sampling period, and simultaneously acquires the terminal's access status, connection status, synchronization status, or wireless link status, thereby establishing a correspondence between the satellite link status and the satellite elevation angle.

[0090] Satellite link status includes at least an available state and an unavailable state. A satellite link being available means that the satellite link is in a state sufficient to support terminal access and maintain the execution of the scheduled communication processes; a satellite link being unavailable means that the satellite link is in a state insufficient to support terminal access or maintain the execution of the scheduled communication processes.

[0091] For the pre-testing process, the satellite elevation angle can be the simulated elevation angle generated by satellite orbit simulation; for the actual use process, the satellite elevation angle can be determined based on the position of the actual serving satellite and the position of the terminal.

[0092] Step 302: Determine the first reference elevation angle based on the correspondence between the satellite link status and the satellite elevation angle.

[0093] Specifically, the testing equipment identifies the moment when the satellite link changes from an unavailable state to an available state based on the satellite link status, such as satellite signal strength and signal-to-noise ratio, and determines the satellite elevation angle corresponding to that moment as the first reference elevation angle.

[0094] By performing multiple actual usage records or multiple pre-tests, multiple candidate values ​​for the first reference elevation angle can be obtained. The test equipment can determine the first reference elevation angle used for formal testing based on the average, median, or preset statistical range of the multiple candidate values ​​for the first reference elevation angle.

[0095] Step 303: Determine the second reference elevation angle based on the correspondence between the satellite link status and the satellite elevation angle.

[0096] Specifically, the testing equipment identifies the moment when the satellite link changes from an available state to an unavailable state based on the satellite link status, such as satellite signal strength and signal-to-noise ratio, and determines the satellite elevation angle corresponding to that moment as the second reference elevation angle.

[0097] The second reference elevation angle should correspond to the satellite link state transition after which the first reference elevation angle was determined. Specifically, an event that transitions from an unavailable state to an available state can be considered the starting point of a continuous satellite link available period, and the first confirmed transition from an available state to an unavailable state after that event can be considered the ending point of that continuous satellite link available period. Thus, the first reference elevation angle and the second reference elevation angle correspond to the same continuous satellite link available period during the same satellite transit.

[0098] Multiple candidate values ​​for the second reference elevation angle can be obtained by performing multiple actual usage records or multiple pre-tests. The test equipment can perform statistical processing on the multiple candidate values ​​for the second reference elevation angle and determine the second reference elevation angle based on the average value, median value, etc.

[0099] Step 304: Determine the first elevation angle based on the first reference elevation angle and the first preset elevation angle margin, and determine the second elevation angle based on the second reference elevation angle and the second preset elevation angle margin.

[0100] Specifically, the test equipment determines the first elevation angle based on the first reference elevation angle and the first preset elevation angle margin, and determines the second elevation angle based on the second reference elevation angle and the second preset elevation angle margin, so that the starting trajectory position corresponding to the first elevation angle and the ending trajectory position corresponding to the second elevation angle are both within the available range of the satellite link.

[0101] The available range of the satellite link can be a continuous trajectory range on a preset satellite simulation trajectory where the terminal can complete access and maintain the corresponding connection status through the satellite link.

[0102] The first preset elevation angle margin is used to adjust the boundary corresponding to the first reference elevation angle, so that the starting trajectory position corresponding to the first elevation angle is within the available range of the satellite link. The second preset elevation angle margin is used to adjust the boundary corresponding to the second reference elevation angle, so that the ending trajectory position corresponding to the second elevation angle is within the available range of the satellite link, and maintains a corresponding interval from the boundary where the satellite link changes from an available state to an unavailable state.

[0103] For example, based on a first preset elevation angle margin, starting from the first reference trajectory position corresponding to the first reference elevation angle, a starting trajectory position can be selected within the available range of the satellite link along the simulation timing of the preset satellite simulated trajectory, and the simulated elevation angle corresponding to the selected starting trajectory position can be determined as the first elevation angle. Thus, the satellite link conditions at the starting trajectory position are within the available range determined during pre-testing or actual use, and the terminal under test can perform access through the simulated satellite link generated from that position.

[0104] Accordingly, based on the second preset elevation angle margin, starting from the second reference trajectory position corresponding to the second reference elevation angle, a termination trajectory position can be selected within the available range of the satellite link in the opposite direction to the simulation timing, and the simulated elevation angle corresponding to the selected termination trajectory position can be determined as the second elevation angle. Thus, the test equipment stops the current test cycle before the satellite link becomes unavailable, retains the accumulated test data, and resets the satellite orbit simulation.

[0105] The first and second preset elevation angle margins can be directly adopted from preset angle values. For example, the corresponding angle margins can be set according to the pre-test results. The first and second preset elevation angle margins can also be calculated based on the preset time margin and the elevation angle change rate of the corresponding trajectory stage.

[0106] Once the first and second elevation angles are determined, they can be stored in the test equipment as configuration parameters for formal testing. Each test round in the formal test begins satellite orbit simulation from the starting trajectory position corresponding to the first elevation angle, and the ending trajectory position corresponding to the second elevation angle is used as the end boundary of that test round. If the accumulated test data has not met the test termination condition when reaching the ending trajectory position, the current test round is stopped, the accumulated test data is retained, and the satellite orbit simulation is reset to the starting trajectory position.

[0107] It should be noted that the above embodiments describe how to determine the first elevation angle and the second elevation angle based on the correspondence between the satellite link status and the satellite elevation angle recorded by the terminal during actual use or pre-testing. In some embodiments, the configuration of the test personnel can also be received directly to determine the first elevation angle and the second elevation angle. That is, the embodiments in this specification do not specifically limit the method of determining the first elevation angle and the second elevation angle.

[0108] By employing the above implementation method, the first reference elevation angle and the second reference elevation angle can be determined based on the satellite link status exhibited by the terminal during actual use or pre-testing. Therefore, the determination of the reference elevation angle, based on the satellite link status, can reflect the terminal's access capability and link maintenance capability under corresponding satellite link conditions.

[0109] Furthermore, by adjusting the starting and ending trajectory positions within the available range of the satellite link according to the first and second preset elevation angle margins, each test round can start from a trajectory position available on the satellite link and stop the current test round before the satellite link becomes unavailable.

[0110] In some embodiments of this specification, before the satellite orbit simulation is first initiated, the test equipment is configured to generate preset test parameters for simulating the satellite link. The preset test parameters include at least one of the following: non-terrestrial network tapped delay line channel model (NTN-TDL channel model) parameters and signal-to-noise ratio parameters.

[0111] The non-terrestrial network tapped delay line channel model parameters are used to configure the multipath propagation characteristics of simulated satellite links. The non-terrestrial network tapped delay line channel model can include multiple taps, each corresponding to a specific propagation path. The parameters can include at least one of the following: the number of taps, the relative delay of each tap, delay spread parameters, and Doppler spread parameters. Specific parameters can be determined based on the demodulation performance test to be performed and the corresponding test specifications.

[0112] The test equipment can use the channel simulation module to perform channel processing on the signal to be sent to the terminal under test according to the channel model parameters of the non-terrestrial network tap delay line, and add noise or adjust the signal power to the channel-processed signal according to the signal-to-noise ratio parameters to generate a simulated satellite link that meets the preset test conditions.

[0113] After configuring the preset test parameters, the test equipment performs satellite orbit simulation from the starting trajectory position corresponding to the first elevation angle, following the preset satellite simulation trajectory, and generates a simulated satellite link based on the preset test parameters. In subsequent test rounds, the test equipment can continue to use the preset test parameters configured before the initial satellite orbit simulation, without needing to reconfigure them each time the satellite orbit simulation is reset.

[0114] As can be seen, in this embodiment, configuring the non-terrestrial network tap delay line channel model parameters before the initial satellite orbit simulation allows the simulated satellite link to possess multipath propagation and delay spread characteristics corresponding to the test items. Configuring the signal-to-noise ratio (SNR) parameters enables the terminal under test (DUT) to perform demodulation performance index testing under specified signal and noise conditions. Pre-configuring the test parameters before the satellite orbit simulation begins ensures that the simulated satellite link used by the DUT during access corresponds to the link conditions used in the demodulation performance index testing, and also avoids changing the test conditions during test rounds.

[0115] In some embodiments of this specification, the same preset satellite simulation trajectory, first elevation angle, second elevation angle, and preset test parameters are used to test demodulation performance indicators in each test round.

[0116] The same preset satellite simulation trajectory means that each test round uses the same set of satellite orbit parameters or the same set of trajectory data arranged according to the simulation time sequence. After the test equipment reaches the termination trajectory position corresponding to the second elevation angle in the current test round, it resets the satellite orbit simulation to the starting trajectory position corresponding to the first elevation angle. The next test round will still follow the same preset satellite simulation trajectory, performing satellite orbit simulation from the same starting trajectory position to the same termination trajectory position.

[0117] The use of the same first and second elevation angles in each test round means that each test round has the same orbital simulation segment. For the same preset satellite simulation trajectory, the starting trajectory position corresponding to the first elevation angle and the ending trajectory position corresponding to the second elevation angle remain unchanged in each test round. Therefore, each test round has the same simulation start and simulation end points.

[0118] Using the same preset test parameters in each test round means keeping the test conditions such as the non-terrestrial network tap delay line channel model parameters and signal-to-noise ratio parameters unchanged in different test rounds.

[0119] In some embodiments, each test round may also employ the same demodulation performance metrics, modulation scheme, encoding scheme, transport block size, data transmission configuration, and test data statistical rules. These parameters can be stored in the test equipment as configuration content for the same test task and repeatedly invoked in each test round.

[0120] By employing the above implementation method, each test round uses the same preset satellite simulation trajectory, first elevation angle, and second elevation angle, ensuring that each test round corresponds to the same orbit simulation segment. Using the same preset test parameters in each test round allows different test rounds to be conducted under the same target channel conditions and signal-to-noise ratio conditions. Therefore, the test data generated by different test rounds have consistent test conditions, enabling the cumulative test data to be updated according to the same statistical rules for demodulation performance indicators. Ultimately, the test results are obtained based on the cumulative test data from multiple test rounds, overcoming the limitation of single-satellite visibility time.

[0121] In some embodiments of this specification, as the demodulation performance index test data included in the cumulative test data increases, the test equipment dynamically updates the cumulative confidence level. Test termination conditions include the cumulative confidence level reaching a preset confidence threshold.

[0122] Specifically, the cumulative confidence level indicates the degree to which the demodulation performance index test results determined based on the current cumulative test data meet predetermined statistical requirements. The cumulative confidence level corresponds to the cumulative test data, rather than to each individual test round. When the test equipment executes multiple test rounds, the demodulation performance index test data generated in the current test round is included in the previously retained cumulative test data, and the cumulative confidence level is also re-determined based on the updated cumulative test data.

[0123] For example, during a demodulation performance index test in one test round, the test equipment can update the cumulative test data according to a preset time interval and a preset data volume interval, and update the cumulative confidence level based on the updated cumulative test data. The specific calculation method for the cumulative confidence level can be determined according to the statistical method or test specification corresponding to the demodulation performance index.

[0124] For example, demodulation performance test data may include at least one of the following: cumulative number of transmitted data blocks, cumulative number of erroneous data blocks, cumulative number of transmitted bits, cumulative number of erroneous bits, cumulative number of transmitted data packets, and cumulative number of erroneous data packets. The test equipment can determine the corresponding demodulation performance index based on the aforementioned cumulative count data and determine the cumulative confidence level according to the statistical method corresponding to that demodulation performance index.

[0125] The preset confidence threshold can be pre-configured according to the corresponding test specifications or determined based on the demodulation performance index test to be performed. The test equipment compares the dynamically updated cumulative confidence with the preset confidence threshold. When the cumulative confidence reaches the preset confidence threshold, the test termination condition is determined to be met; when the cumulative confidence has not yet reached the preset confidence threshold, the test termination condition is determined to be not yet met.

[0126] If the cumulative confidence score has not reached the preset confidence threshold when the current test round reaches the termination trajectory position corresponding to the second elevation angle, the test equipment stops the current test round and retains the cumulative test data. After the terminal under test reconnects to the test equipment through the regenerated simulated satellite link, the demodulation performance index test data generated in the next test round will continue to be included in the retained cumulative test data, and the cumulative confidence score will also continue to be updated based on the updated cumulative test data.

[0127] By applying the above implementation method, the cumulative confidence level is dynamically updated based on accumulated test data. This allows for the joint determination of whether the test meets the prescribed statistical requirements using test data obtained from multiple test rounds. Even if the test data generated in a single test round is insufficient to raise the cumulative confidence level to a preset confidence threshold, test data can continue to accumulate in subsequent test rounds. Using the cumulative confidence level reaching the preset confidence threshold as the test termination condition allows the testing equipment to determine whether to end the test based on the accumulated test data already obtained, without needing to pre-fix the number of test rounds. When the accumulated test data reaches the corresponding statistical requirements, the testing equipment can terminate the demodulation performance index test and determine the test results.

[0128] In some embodiments of this specification, the test equipment dynamically determines the link parameters of the simulated satellite link based on a preset simulated satellite trajectory and a simulated elevation angle generated by satellite orbit simulation. The link parameters include propagation delay, Doppler shift, and path loss.

[0129] The preset satellite simulation trajectory is used to determine the position and motion state of the simulated satellite at different simulation moments. Based on the preset satellite simulation trajectory, the test equipment can obtain the relative position, relative distance, and relative velocity between the simulated satellite and the terminal under test. The simulated elevation angle represents the elevation angle of the simulated satellite relative to the location of the terminal under test and can be used as one of the input parameters for determining link parameters.

[0130] The propagation delay can be determined based on the relative distance between the simulated satellite and the tested terminal. As the satellite orbit simulation progresses, the relative distance changes, and the test equipment updates the propagation delay accordingly, applying the updated propagation delay to the simulated satellite link.

[0131] The Doppler shift can be determined based on the radial relative velocity between the simulated satellite and the terminal under test (DUT) and the carrier frequency used in the simulated satellite link. The test equipment can determine the radial relative velocity according to a preset simulated satellite trajectory and update the Doppler shift over time. The Doppler shift can be applied to the radio frequency signal transmitted to the DUT to simulate the frequency changes caused by the motion of the simulated satellite.

[0132] Path loss can be determined based on the relative distance between the simulated satellite and the terminal under test, the carrier frequency, and the simulated elevation angle. For example, the test equipment can determine the free-space path loss based on the carrier frequency and relative distance, and adjust the free-space path loss according to the additional loss corresponding to the simulated elevation angle. The test equipment then adjusts the signal power or attenuation of the simulated satellite link based on the updated path loss.

[0133] The testing equipment can dynamically determine the aforementioned link parameters according to a preset update cycle. The preset update cycle can be the same as the time step of the satellite orbit simulation, or it can be set according to the processing capacity of the testing equipment and the requirements of the test project. At each update moment, the testing equipment reads the current trajectory position and simulated elevation angle, determines the link parameters corresponding to the current simulation moment, and generates a simulated satellite link based on these link parameters.

[0134] When the satellite orbit simulation is reset to the initial trajectory position, the propagation delay, Doppler shift, and path loss also revert to the parameter values ​​corresponding to that initial trajectory position. In the next test run, running on the same preset satellite simulation trajectory, the aforementioned link parameters are updated over time according to the same changing relationship as in the previous test run.

[0135] It should be noted that during the testing process, the simulated satellite link can be generated by combining the dynamic link parameters and the preset test parameters mentioned in the aforementioned embodiments. The preset test parameters are used to configure test conditions such as the non-terrestrial network tap delay line channel model and signal-to-noise ratio, while the dynamic link parameters are used to reflect the changes in propagation delay, Doppler shift, and path loss generated when the simulated satellite moves along the preset simulated satellite trajectory.

[0136] By applying the above implementation method, during the testing process, propagation delay, Doppler shift, and path loss are dynamically determined based on the preset simulated satellite trajectory and simulated elevation angle. This allows the relevant parameters of the simulated satellite link to change with the position and motion state of the simulated satellite. Compared to methods that keep the satellite position and link parameters constant during testing, this provides dynamic satellite link conditions. After the satellite orbit simulation is reset, each link parameter restarts its change from the parameter value corresponding to the initial trajectory position. This allows different test rounds to use the same link parameter change process, facilitating the accumulation of test data generated in each test round.

[0137] Based on the same inventive concept, embodiments of this specification also provide a demodulation performance testing device for a non-terrestrial network terminal, such as... Figure 4 As shown, the device includes: The generation module 401 is used to perform satellite orbit simulation from the starting trajectory position with a simulated elevation angle of the first elevation angle on the preset non-geostationary orbit NGSO satellite simulation trajectory, and generate a simulated satellite link that changes with the simulation time. The startup module 402 is used to respond to the terminal under test accessing the test equipment through the simulated satellite link, start the demodulation performance index test of the current test round, and during the demodulation performance index test, obtain the simulated elevation angle generated by the satellite orbit simulation, update the cumulative test data according to the test data generated in the current test round, and determine whether the test end condition is met based on the updated cumulative test data. The first test module 403 is used to terminate the demodulation performance index test if the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, and to determine the test result based on the cumulative test data. The reset module 404 is used to pause the test, disconnect the connection between the terminal under test and the simulated satellite link, retain the accumulated test data, reset the satellite orbit simulation to the starting trajectory position, and restart the satellite orbit simulation from the starting trajectory position to regenerate the simulated satellite link if the test end condition is not met when the simulated elevation angle reaches the second elevation angle. The second test module 405 is used to respond to the terminal under test reconnecting to the test equipment through the regenerated simulated satellite link, continue to test demodulation performance indicators, continue to accumulate test data based on the accumulated test data of the previous round, and repeat the test rounds in this way until the accumulated test data meets the test termination condition, then end the test and determine the test result based on the latest accumulated test data.

[0138] The beneficial effects obtained by the above-described device are the same as those obtained by the above-described method, and will not be described in detail in the embodiments of this specification.

[0139] like Figure 5 The diagram shows a schematic of the computer device according to an embodiment of this specification. The computer device in this embodiment is capable of executing the NGSO non-terrestrial network terminal demodulation performance testing method described in this specification. The computer device 502 may include one or more processing devices 504, such as one or more central processing units (CPUs), each of which may implement one or more hardware threads. The computer device 502 may also include any storage resource 506 for storing any kind of information, such as code, settings, data, etc. Without limitation, for example, the storage resource 506 may include any type of RAM, any type of ROM, flash memory, hard disk, optical disk, etc. More generally, any storage resource can use any technology to store information. Furthermore, any storage resource may provide volatile or non-volatile retention of information. Furthermore, any storage resource may represent a fixed or removable component of the computer device 502. In one case, when the processing device 504 executes associated instructions stored in any storage resource or combination of storage resources, the computer device 502 may perform any operation of the associated instructions. The computer device 502 also includes one or more drive mechanisms 508 for interacting with any storage resource, such as hard disk drive mechanism, optical disk drive mechanism, etc.

[0140] Computer device 502 may also include an input / output module 510 (I / O) for receiving various inputs (via input device 512) and providing various outputs (via output device 514). A specific output mechanism may include a presentation device 516 and an associated graphical user interface (GUI) 518. In other embodiments, the input / output module 510 (I / O), input device 512, and output device 514 may be omitted, and the device may function solely as a computer device within a network. Computer device 502 may also include one or more network interfaces 520 for exchanging data with other devices via one or more communication links 522. One or more communication buses 524 couple the components described above together.

[0141] Communication link 522 can be implemented in any way, such as via a local area network, a wide area network (e.g., the Internet), a point-to-point connection, or any combination thereof. Communication link 522 may include any combination of hardwired links, wireless links, routers, gateway functions, name servers, etc., governed by any protocol or combination of protocols.

[0142] This specification also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method.

[0143] This specification also provides computer-readable instructions, wherein when a processor executes the instructions, the program therein causes the processor to perform the above-described method.

[0144] It should be understood that in the various embodiments of this specification, the sequence number of each process does not imply the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of this specification.

[0145] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed in this specification can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of each example have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this specification.

[0146] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0147] In the several embodiments provided in this specification, it should be understood that the disclosed systems, apparatuses, and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the couplings or direct couplings or communication connections shown or discussed may be indirect couplings or communication connections through some interfaces, devices, or units, or they may be electrical, mechanical, or other forms of connection.

[0148] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of the embodiments described in this specification, depending on actual needs.

[0149] Furthermore, the functional units in the various embodiments of this specification can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0150] If the integrated unit is implemented as 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 this specification, in essence, 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. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this specification. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0151] This specification uses specific embodiments to illustrate the principles and implementation methods of this specification. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this specification. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this specification. Therefore, the content of this specification should not be construed as a limitation of this specification.

Claims

1. A method for testing the demodulation performance of NGSO non-terrestrial network terminals, characterized in that, Applied to testing equipment, including: According to the preset non-geostationary orbit NGSO satellite simulation trajectory, the satellite orbit simulation is started from the starting trajectory position with the simulated elevation angle of the first elevation angle on the preset satellite simulation trajectory, and the simulated satellite link changes with the simulation time. In response to the terminal under test accessing the test equipment through the simulated satellite link, the demodulation performance index test of the current test round is started. During the demodulation performance index test, the simulated elevation angle generated by the satellite orbit simulation is obtained, the cumulative test data is updated according to the test data generated in the current test round, and it is determined whether the test termination condition is met based on the updated cumulative test data. If the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, the demodulation performance index test is terminated, and the test result is determined based on the cumulative test data. If the test termination condition is not met when the simulated elevation angle reaches the second elevation angle, the test is paused, the connection between the terminal under test and the simulated satellite link is disconnected, the accumulated test data is retained, the satellite orbit simulation is reset to the starting trajectory position, and the satellite orbit simulation is restarted from the starting trajectory position to regenerate the simulated satellite link. In response to the terminal under test reconnecting to the test equipment via the regenerated simulated satellite link, the demodulation performance index test continues. The test data is accumulated based on the previous round of accumulated test data. This process is repeated in a loop until the accumulated test data meets the test termination condition. The test ends and the test result is determined based on the latest accumulated test data. Wherein, the first elevation angle and the second elevation angle are used to define the orbit simulation section corresponding to a single test round. The first elevation angle is the starting boundary elevation angle of the orbit simulation section, and the second elevation angle is the ending boundary elevation angle of the orbit simulation section. The ending trajectory position corresponding to the second elevation angle is located after the starting trajectory position corresponding to the first elevation angle according to the simulation time sequence of the preset satellite simulation trajectory.

2. The method according to claim 1, characterized in that, Each test round uses the same preset satellite simulation trajectory, first elevation angle, second elevation angle, and preset test parameters to test the demodulation performance indicators.

3. The method according to claim 1, characterized in that, The method further includes: As the demodulation performance index test data included in the cumulative test data increases across multiple rounds of testing, the cumulative confidence level is dynamically updated; the test termination condition includes the cumulative confidence level reaching a preset confidence threshold.

4. The method according to claim 1, characterized in that, The generation of the simulated satellite link that varies with simulation time includes: Based on the preset satellite simulated trajectory and the simulated elevation angle generated by the satellite orbit simulation, the link parameters of the simulated satellite link are dynamically determined. The link parameters include propagation delay, Doppler shift, and path loss.

5. The method according to claim 1, characterized in that, Before the satellite orbit simulation is started for the first time, preset test parameters for generating the simulated satellite link are configured. The preset test parameters include at least one of non-terrestrial network tap delay line channel model parameters and signal-to-noise ratio parameters.

6. The method according to claim 1, characterized in that, The first elevation angle and the second elevation angle are determined based on the correspondence between the satellite link status and the satellite elevation angle recorded by the terminal during actual use or pre-testing; wherein, the first elevation angle is determined based on a first reference elevation angle, which is the satellite elevation angle corresponding to the satellite link changing from an unavailable state to an available state; the second elevation angle is determined based on a second reference elevation angle, which is the satellite elevation angle corresponding to the satellite link changing from an available state to an unavailable state after the satellite link changes from an unavailable state to an available state.

7. The method according to claim 6, characterized in that, The method further includes: The first elevation angle is determined based on the first reference elevation angle and the first preset elevation angle margin, and the second elevation angle is determined based on the second reference elevation angle and the second preset elevation angle margin, so that the starting trajectory position corresponding to the first elevation angle and the ending trajectory position corresponding to the second elevation angle are located within the available range of the satellite link.

8. A device for testing the demodulation performance of NGSO non-terrestrial network terminals, characterized in that, Applied to testing equipment, including: The generation module is used to simulate satellite orbits from the starting position of the preset satellite simulation trajectory with a simulated elevation angle of the first elevation angle, according to the preset non-geostationary orbit NGSO satellite simulation trajectory, and generate a simulated satellite link that changes with the simulation time. The startup module is used to respond to the terminal under test accessing the test equipment through the simulated satellite link, start the demodulation performance index test of the current test round, and during the demodulation performance index test, obtain the simulated elevation angle generated by the satellite orbit simulation, update the cumulative test data according to the test data generated in the current test round, and determine whether the test termination condition is met based on the updated cumulative test data. The first test module is used to terminate the demodulation performance index test if the test termination condition is met before or when the simulated elevation angle reaches the second elevation angle, and to determine the test result based on the cumulative test data. The reset module is used to pause the test, disconnect the connection between the terminal under test and the simulated satellite link, retain the accumulated test data, reset the satellite orbit simulation to the starting trajectory position, and restart the satellite orbit simulation from the starting trajectory position to regenerate the simulated satellite link if the test end condition is not met when the simulated elevation angle reaches the second elevation angle. The second test module is used to respond to the terminal under test reconnecting to the test equipment through the regenerated simulated satellite link, continue to test demodulation performance indicators, continue to accumulate test data based on the accumulated test data of the previous round, and repeat the test rounds in this way until the accumulated test data meets the test termination condition, then end the test and determine the test result based on the latest accumulated test data. Wherein, the first elevation angle and the second elevation angle are used to define the orbit simulation section corresponding to a single test round. The first elevation angle is the starting boundary elevation angle of the orbit simulation section, and the second elevation angle is the ending boundary elevation angle of the orbit simulation section. The ending trajectory position corresponding to the second elevation angle is located after the starting trajectory position corresponding to the first elevation angle according to the simulation time sequence of the preset satellite simulation trajectory.

9. An electronic device, characterized in that, It includes at least one processor and a memory; the memory stores a computer program or instruction set; at least one of the processors executes the computer program or instruction set stored in the memory, such that at least one of the processors performs the method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program or instruction set, which, when executed by a processor, implements the method as described in any one of claims 1 to 7.

11. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the method described in any one of claims 1 to 7.

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