A fast OTA test method for a satellite communication terminal

Abstract

This invention discloses a rapid OTA testing method and system for satellite communication terminals, relating to the field of satellite communication testing technology. It solves the technical problem of excessively long OTA testing times and extremely low efficiency for satellite terminals, making it difficult to meet the needs of large-scale industry testing. The method includes: establishing a signaling connection between a satellite simulator and the terminal under test (DUT), and disabling the DUT's ephemeris consistency check and position check functions; configuring the reference positions of the DUT and the target satellite using the satellite simulator to obtain multiple optimized test scenarios; generating a test signal containing the ephemeris information of the target satellite based on the multiple test scenarios; selecting the target test scenario from the optimized test scenario and the standard test scenario to perform OTA performance testing on the DUT, and disabling the uplink filling function of the DUT during the OTA reception performance test. This invention significantly shortens the OTA testing time for satellite communication terminals, improves testing efficiency, and meets the needs of large-scale testing.

Description

Technical Field

[0001] This invention relates to the field of satellite communication testing technology, and in particular to a rapid OTA testing method for satellite communication terminals. Background Technology

[0002] In NTN (Non-Terrestrial Network) related communication systems (including NTN LTECategory NB1, NTN NR, etc.), the communication latency is significantly higher than that of terrestrial wireless communication networks. The core reason lies in the difference in node altitude and propagation distance caused by its non-terrestrial deployment architecture. Terrestrial network base stations are mostly deployed on the ground or in low altitude, with a distance of only 1-5 kilometers from the terminal. The one-way signal propagation delay is only 0.003-0.017 milliseconds, and the basic latency is at an extremely low level. However, the core communication nodes of NTN (satellites, HAPS, etc.) need to be deployed in the stratosphere to space orbit. Since the signal propagation delay is positively correlated with the transmission distance, the high-altitude / space deployment mode adopted by NTN nodes to achieve wide-area coverage results in a signal propagation distance that is much greater than that of terrestrial networks. This directly leads to a significant increase in the basic propagation delay, which in turn makes the OTA test (Over-The-Air Testing, a standard for testing the radiation performance of wireless communication terminals, which evaluates the transmission and reception performance of equipment through passive and active testing methods) time of NTN terminals significantly longer than that of traditional terrestrial communication network terminals.

[0003] According to the current 3GPP NTN terminal air interface performance test specifications, for the radio frequency transceiver and demodulation test items (applicable to geostationary orbit GSO constellations or non-geostationary orbit NGSO constellation scenarios), the reference positions of the terminal under test and the target satellite during the test process are defined as shown in Table 1.

[0004] Table 1 Definitions of the reference position of the terminal under test and the reference position of the target satellite

[0005]

[0006] Based on the aforementioned reference location settings, the 3GPP reference location definition not only fully aligns with the orbital altitude characteristics of different types of satellites in actual deployment scenarios but also matches the actual usage location and altitude conditions of the terminal in typical application scenarios. Based on this standard reference configuration, TIS (Total Isotropic Sensitivity) tests were conducted on multiple satellite terminals in GSO scenarios, and the test duration statistics are shown in Table 2.

[0007] Table 2 Comparison of TIS test durations for different terminals under test in GSO standard test scenarios / configurations

[0008]

[0009] The test results above show that, compared to OTA testing of terrestrial terminals (whose typical TIS test takes about 1 hour), the current OTA testing methods for satellite terminals suffer from the core problem of excessively long testing times. With the continuous iteration and application of new standards, new frequency bands, and multi-band combination technologies in the satellite communication field, the shortcomings of existing testing solutions in terms of testing time and efficiency will become increasingly apparent, making it difficult to meet the actual needs of large-scale industry testing.

[0010] In the process of realizing this invention, the inventors discovered at least the following problems in the prior art:

[0011] The existing OTA testing time for satellite terminals is too long and the efficiency is extremely low, making it difficult to meet the needs of large-scale testing in the industry. Summary of the Invention

[0012] The purpose of this invention is to provide a rapid OTA testing method for satellite communication terminals, thereby solving the technical problems of excessively long OTA testing times and extremely low efficiency in existing technologies, which make it difficult to meet the needs of large-scale industry testing. The various technical effects of the preferred solutions among the many technical solutions provided by this invention are detailed below.

[0013] To achieve the above objectives, the present invention provides the following technical solution:

[0014] This invention provides a rapid OTA testing method for a satellite communication terminal, comprising the following steps: S100: establishing a signaling connection between a satellite simulator and the terminal under test (DUT), and disabling the ephemeris consistency check and position check functions of the DUT; S200: configuring the reference position of the DUT and the reference position of the target satellite through the satellite simulator, and obtaining multiple optimized test scenarios that can reduce the round-trip transmission delay K-offset between the DUT and the target satellite based on multiple sets of DUT reference positions and target satellite reference positions; S300: generating a test signal containing the ephemeris information of the target satellite based on the multiple optimized test scenarios; S400: configuring the DUT through the satellite simulator, selecting a target test scenario from the multiple optimized test scenarios and standard test scenarios, and performing OTA performance testing on the DUT based on the target test scenario and the corresponding test signal, disabling the uplink filling function of the DUT during the OTA reception performance test.

[0015] Preferably, in step S400, the optimized test scenario includes the GSO optimized test scenario and the NGSO optimized test scenario, the standard test scenario includes the GSO standard test scenario and the NGSO standard test scenario, and the target test scenario includes the GSO target test scenario and the NGSO target test scenario.

[0016] Preferably, the GSO optimization test scenario includes a first GSO optimization test scenario, a second GSO optimization test scenario, a third GSO optimization test scenario, and a fourth GSO optimization test scenario; in the first and second GSO optimization test scenarios, the reference position of the terminal under test and the reference position of the target satellite are both set to the same spatial position; in the third and fourth GSO optimization test scenarios, the longitude and latitude of the reference position of the terminal under test and the reference position of the target satellite are the same, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the LEO altitude.

[0017] Preferably, in the first GSO optimization test scenario, the altitudes of the reference position of the terminal under test and the reference position of the target satellite are both geostationary orbit altitudes; in the second GSO optimization test scenario, the altitudes of the reference position of the terminal under test and the reference position of the target satellite are both 0m; in the third GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is a first low Earth orbit (LEO) altitude; in the fourth GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is a second low Earth orbit (LEO) altitude; the first LEO altitude is lower than the second LEO altitude.

[0018] Preferably, in step S400, the GSO target test scenario is generated in the following way:

[0019] S410a: Using the reference position of the terminal under test (DUT) and the reference position of the geostationary orbit GSO target satellite in the default 3GPP GSO scenario as the standard GSO test scenario, the equivalent isotropic radiated power of the DUT is measured within the standard GSO test scenario. The test yielded the GSO standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the first, second, third, and fourth GSO optimized test scenarios, respectively. The tests yielded the first equivalent isotropic radiated power. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power ;

[0020] S420a: Calculate the first equivalent isotropic radiated power respectively. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power Equivalent Isotropic Radiated Power of GSO Standard The difference between them yields the difference for the first GSO optimization test scenario. The difference in the second GSO optimization test scenario The difference in the third GSO optimization test scenario The fourth GSO optimization test scenario difference :

[0021] ,

[0022] ,

[0023] ,

[0024] ;

[0025] S430a: Setting the equivalent isotropic radiation power First reference limit ;

[0026] S440a: If Select either the first GSO optimization test scenario or the second GSO optimization test scenario as the target test scenario; if and Select the third GSO optimized test scenario as the target test scenario; if and Select the fourth GSO optimization test scenario as the target test scenario; if If so, the GSO standard test scenario is selected as the GSO target test scenario.

[0027] Preferably, the NGSO optimized test scenarios include the NGSO LEO-600 optimized test scenario and the NGSO LEO-1200 optimized test scenario; the NGSO standard test scenarios include the NGSO LEO-600 standard test scenario and the NGSO LEO-1200 standard test scenario; and the NGSO target test scenarios include the NGSO LEO-600 target test scenario and the NGSO LEO-1200 target test scenario. In the NGSO LEO-600 optimized test scenario, the reference position of the terminal under test and the reference position of the target satellite are the same spatial position, and the altitude of this spatial position is the third low Earth orbit (LEO) altitude. In the NGSO LEO-1200 optimized test scenario, the reference position of the terminal under test and the reference position of the target satellite are the same spatial position, and the altitude of this spatial position is the fourth low Earth orbit (LEO) altitude. The third low Earth orbit (LEO) altitude is lower than the fourth low Earth orbit (LEO) altitude.

[0028] Preferably, in step S400, the NGSO LEO-600 target test scenario is generated in the following manner: S410b: The reference position of the terminal under test and the reference position of the target satellite under the 3GPP default NGSO LEO-600 scenario are used as the NGSO LEO-600 standard test scenario, and the equivalent isotropic radiated power of the terminal under test is measured in the NGSO LEO-600 standard test scenario. The test yielded the NGSO LEO-600 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSOLEO-600 optimized test scenario. The fifth equivalent isotropic radiated power was obtained from the test. S420b: Calculate the NGSO LEO-600 standard equivalent isotropic radiated power. With the fifth equivalent isotropic radiated power The difference between them yields the NGSO LEO-600 test scenario difference. S430b: Setting the equivalent isotropic radiation power Second reference limit S440b: If If the conditions are met, the NGSO LEO-600 optimized test scenario is selected as the target test scenario; otherwise, the NGSO LEO-600 standard test scenario is selected as the target test scenario.

[0029] Preferably, in step S400, the NGSO LEO-1200 target test scenario is generated in the following manner: S410c: The reference position of the terminal under test and the reference position of the target satellite under the 3GPP default NGSO LEO-1200 scenario are used as the NGSO LEO-1200 standard test scenario, and the equivalent isotropic radiated power of the terminal under test is measured in the NGSO LEO-1200 standard test scenario. The test yielded the NGSO LEO-1200 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSO LEO-1200 optimized test scenario. The sixth equivalent isotropic radiated power was obtained from the test. S420c: Calculate the NGSO LEO-1200 standard equivalent isotropic radiated power. With the sixth equivalent isotropic radiated power The difference between them yields the NGSO LEO-1200 test scenario difference. S430c: Set equivalent isotropic radiated power The third reference limit S440c: If If the conditions are met, the NGSO LEO-1200 optimized test scenario is selected as the target test scenario; otherwise, the NGSO LEO-1200 standard test scenario is selected as the target test scenario.

[0030] Preferably, the maximum equivalent isotropic radiated power in the upper hemisphere of the terminal under test is... The equivalent isotropic radiated power of the terminal under test is measured at the location of the value. test.

[0031] Implementing one of the above-described technical solutions of the present invention has the following advantages or beneficial effects:

[0032] This invention significantly shortens the OTA test time of the satellite communication terminal under test and improves test efficiency by disabling the ephemeris consistency check and position check functions of the terminal under test and the target satellite during the test process to reduce the round-trip transmission delay K-offset, and disabling the uplink filling function of the terminal under test during the receiving test. At the same time, it maintains the accuracy and consistency of the test results and meets the needs of large-scale testing. Attached Figure Description

[0033] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments 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:

[0034] Figure 1 This is a flowchart of a fast OTA testing method for a satellite communication terminal according to Embodiment 1 of the present invention;

[0035] Figure 2 This is a flowchart illustrating the generation of the GSO target test scenario in a rapid OTA test method for a satellite communication terminal according to Embodiment 1 of the present invention.

[0036] Figure 3 This is a flowchart illustrating the generation of the NGSO LEO-600 target test scenario in a rapid OTA testing method for a satellite communication terminal according to Embodiment 1 of the present invention.

[0037] Figure 4 This is a flowchart illustrating the generation of the NGSO LEO-1200 target test scenario in a rapid OTA test method for a satellite communication terminal according to Embodiment 1 of the present invention. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of the present invention clearer, various exemplary embodiments described below will be referenced to the accompanying drawings, which constitute a part of the exemplary embodiments, illustrating various exemplary embodiments that may be used to implement the present invention. Unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this disclosure. It should be understood that they are merely examples of processes, methods, and apparatuses consistent with some aspects of the present invention disclosed as detailed in the appended claims, and other embodiments may be used, or structural and functional modifications may be made to the embodiments listed herein without departing from the scope and spirit of the present invention.

[0039] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," etc., indicate the orientation or positional relationship based on the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the referred element must have a specific orientation, or be constructed and operated in a specific orientation. The terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. The term "multiple" means two or more. The terms "connected" and "linked" should be interpreted broadly, for example, they can be fixed connections, detachable connections, integral connections, mechanical connections, electrical connections, communication connections, direct connections, indirect connections through an intermediate medium, and can be the internal connection of two elements or the interaction relationship between two elements. The term "and / or" includes any and all combinations of one or more of the related listed items. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] To illustrate the technical solution described in this invention, specific embodiments are described below, showing only the parts related to the embodiments of this invention.

[0041] Example 1:

[0042] like Figure 1As shown, this invention provides a rapid OTA testing method for satellite communication terminals, including the following steps: S100: Establish a signaling connection between the satellite simulator and the terminal under test, and disable the ephemeris consistency verification and location verification functions of the terminal under test; Traditional 3GPP RF (including OTA) performance testing requires, according to the test scenario (GSO / NGSO), specifying the reference positions (longitude, latitude, altitude, see Tables 1 and 2 in the background technology) of the target satellite and the terminal under test according to the 3GPP specifications, and generating a test signal containing the corresponding ephemeris information based on the reference position, and conducting the test. During the test, the terminal under test will by default perform consistency verification of the reference position and ephemeris information under the target test scenario according to the corresponding 3GPP test specifications. Disabling the above verification function can avoid interference with the subsequent test process of custom configuring the reference position of the target satellite and the terminal under test. S200: Configure the reference position of the terminal under test (DUT) and the target satellite reference position using a satellite simulator. Based on multiple sets of DUT and target satellite reference positions, these reference positions are used to shorten the distance between the DUT and the target satellite, and even achieve co-location (setting them to the same spatial location), thereby obtaining multiple optimized test scenarios that can reduce the round-trip transmission delay (K-offset) between the DUT and the target satellite. S300: Based on multiple optimized test scenarios, the satellite simulator generates a test signal containing the ephemeris information of the target satellite. S400: The satellite simulator configures the DUT and selects the target test scenario from multiple optimized and standard test scenarios. Based on the target test scenario and the corresponding test signal, OTA performance testing of the DUT is performed. During the OTA reception performance test, the uplink padding function of the DUT is disabled. Uplink padding typically refers to adding padding bits in uplink transmission to meet the frame length or timing requirements specified by the protocol, ensuring the integrity of data transmission. During OTA (Over-The-Air) reception performance testing of satellite terminals, uplink padding (UL Padding) transmission increases the test duration of reception performance (EIS / TIS). Disabling uplink padding will stop the terminal from transmitting the Physical Uplink Shared Channel (PUSCH), thus shortening the test duration. Specifically, this includes setting RU=0 (completely disabling uplink padding) or RU=1 (enabling uplink padding and using a specific indexed RU, or a padding length of 1 unit). In this embodiment, by disabling the ephemeris consistency check and position check functions of the satellite communication terminal under test, configuring the reference positions of the terminal under test and the target satellite during the test to reduce the round-trip transmission delay (K-offset), and disabling the uplink padding function of the terminal under test during reception performance testing, the OTA test duration of the satellite communication terminal under test can be significantly shortened, test efficiency improved, and the accuracy and consistency of test results maintained, meeting the needs of large-scale testing.

[0043] As an optional implementation, in step S200, the optimized test scenarios include GSO optimized test scenarios and NGSO optimized test scenarios; the standard test scenarios include GSO standard test scenarios and NGSO standard test scenarios; and the target test scenarios include GSO target test scenarios and NGSO target test scenarios. This allows for testing of all types of satellites at different altitudes, thus broadening the scope of application. This embodiment provides multiple pre-configured test scenario combinations, including different orbital altitudes for geostationary orbit GSO and non-geostationary orbit NGSO satellites, as well as co-location configuration options for the target satellite and the terminal under test, allowing the test system to flexibly select the appropriate scenarios.

[0044] As an optional implementation, the GSO optimization test scenarios include a first GSO optimization test scenario, a second GSO optimization test scenario, a third GSO optimization test scenario, and a fourth GSO optimization test scenario. In the first and second GSO optimization test scenarios, the reference position of the terminal under test and the reference position of the target satellite are set to the same spatial location. In the third and fourth GSO optimization test scenarios, the longitude and latitude of the reference position of the terminal under test and the reference position of the target satellite are the same, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the LEO altitude. Specifically, as shown in Table 3, in the first GSO optimization test scenario, the altitude of both the reference position of the terminal under test and the reference position of the target satellite is the geostationary orbit altitude, i.e., 35,786,361.2 meters; its longitude and latitude are set to the standard default longitude and latitude of the GSO target satellite reference position. The first GSO optimized test scenario is the most preferred option in this embodiment. Its core is to set the reference position of the terminal under test (DUT) to the reference position of the target GSO satellite. This setting can minimize the additional propagation delay compensation error introduced by position deviation. In the second GSO optimized test scenario, the altitude of both the reference position of the DUT and the reference position of the target satellite is 0m. The second GSO optimized test scenario is theoretically equivalent to the first GSO optimized test scenario, but it is only enabled under specific constraints: when the DUT has a factory-preset altitude configuration upper limit and cannot match the satellite orbital-level altitude parameters, the reference position of the target GSO satellite needs to be adjusted in reverse to match the reference position of the DUT, thereby avoiding the configuration problem caused by the terminal exceeding the parameter limit. In the third GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the first low Earth orbit (LEO) altitude. Both have a longitude of 121.56303 degrees and a latitude of 25.05009 degrees. In the fourth GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the second low Earth orbit (LEO) altitude. Both have a longitude of 121.57637 degrees and a latitude of 25.01201 degrees. The third and fourth GSO optimization test scenarios... The test scenarios are alternative test scenarios to the first and second GSO optimized test scenarios. When the first and second GSO optimized test scenarios cannot be run, the third or fourth GSO optimized test scenarios can be selected as alternatives. Although these two test scenarios have a longer round-trip transmission delay K-offset than the first and second GSO optimized test scenarios, they are significantly lower than the round-trip transmission delay K-offset of the 3GPP default standard test scenario, and can also improve the OTA test efficiency to a certain extent.Specifically, the altitude of the first low Earth orbit (LEO) is lower than that of the second low Earth orbit (LEO). In this embodiment, the altitude of the first LEO is 608,964.7 meters, which corresponds to LEO-600, and the altitude of the second LEO is 1,210,865.1 meters, which corresponds to LEO-1200.

[0045] Table 3 Reference position settings for different GSO optimization test scenarios

[0046]

[0047] As an optional implementation method, such as Figure 2 As shown, in step S400, the GSO target test scenario is generated in the following way: S410a: The reference position of the terminal under test (DUT) and the reference position of the geostationary orbit GSO target satellite under the default GSO scenario of 3GPP are used as the standard GSO test scenario. The equivalent isotropic radiated power of the DUT is measured in the standard GSO test scenario (i.e., the GSO test parameter configuration explicitly defined in the 3GPP specification). The test yielded the GSO standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the first, second, third, and fourth GSO optimized test scenarios, respectively. The tests yielded the first equivalent isotropic radiated power. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power S420a: Calculate the first equivalent isotropic radiated power respectively. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power Equivalent Isotropic Radiated Power of GSO Standard The difference between them yields the difference for the first GSO optimization test scenario. The difference in the second GSO optimization test scenario The difference in the third GSO optimization test scenario The fourth GSO optimization test scenario difference :

[0048] ,

[0049] ,

[0050] ,

[0051] ;

[0052] S430a: Setting the equivalent isotropic radiation power First reference limit The specific value should be set according to the test requirements, so as to ensure that the OTA test can be completed successfully.

[0053] S440a: If That is, the first, second, third, and fourth GSO optimized test scenarios can all meet the accuracy requirements of OTA testing. The first or second GSO optimized test scenario is selected as the target test scenario, with the first GSO optimized test scenario being preferred, thus achieving a better effect in reducing the round-trip transmission latency (K-offset). and Both the third and fourth GSO optimized test scenarios meet the OTA testing accuracy requirements, but the third GSO optimized test scenario has a lower altitude and a smaller round-trip transmission delay (K-offset). Therefore, the third GSO optimized test scenario is selected as the target test scenario. and At this point, only the fourth GSO optimized test scenario meets the OTA test accuracy requirements. To reduce the round-trip transmission latency K-offset, the fourth GSO optimized test scenario is selected as the target test scenario; if If none of the first, second, third, and fourth GSO optimized test scenarios meet the OTA test accuracy requirements, then the standard GSO test scenario is selected as the GSO target test scenario.

[0054] As an optional implementation, as shown in Table 4, the NGSO optimized test scenarios include the NGSO LEO-600 optimized test scenario and the NGSO LEO-1200 optimized test scenario; the NGSO standard test scenarios include the NGSO LEO-600 standard test scenario and the NGSO LEO-1200 standard test scenario; and the NGSO target test scenarios include the NGSO LEO-600 target test scenario and the NGSO LEO-1200 target test scenario. In the NGSO LEO-600 optimized test scenario, the altitude of both the reference position of the terminal under test and the reference position of the target satellite is the third low Earth orbit (LEO) altitude, specifically 608,964.7 meters in this embodiment, which is equal to the first low Earth orbit (LEO) altitude. In the LEO-1200 optimized test scenario, the altitudes of the reference positions of the terminal under test and the target satellite are both the fourth low Earth orbit (LEO) altitude, specifically 1,210,865.1 meters in this embodiment, which is equal to the second low Earth orbit (LEO) altitude. The third low Earth orbit (LEO) altitude is lower than the fourth low Earth orbit (LEO) altitude, thereby enabling LEO satellite communication tests at different altitudes.

[0055] Table 4. Reference position settings for different NGSO optimization test scenarios

[0056]

[0057] As an optional implementation method, such as Figure 3 As shown in step S400, the NGSO LEO-600 target test scenario is generated in the following way: S410b: The reference position of the terminal under test and the reference position of the target satellite under the 3GPP default NGSO LEO-600 scenario are used as the NGSO LEO-600 standard test scenario (i.e., the NGSO LEO-600 test parameter configuration explicitly defined by the 3GPP specification), and the equivalent isotropic radiated power of the terminal under test is measured in the NGSO LEO-600 standard test scenario. The test yielded the NGSO LEO-600 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSO LEO-600 optimized test scenario. The fifth equivalent isotropic radiated power was obtained from the test. S420b: Calculate the NGSO LEO-600 standard equivalent isotropic radiated power. With the fifth equivalent isotropic radiated power The difference between them yields the NGSO LEO-600 test scenario difference. S430b: Setting the equivalent isotropic radiation power Second reference limit The specific value should be set according to the test requirements, such as the first reference limit. Equal, based on the ability to successfully complete OTA testing; S440b: If If the NGSO LEO-600 optimized test scenario is selected as the target test scenario, then the NGSO LEO-600 optimized test scenario is selected as the target test scenario. Otherwise, if the NGSO LEO-600 optimized test scenario cannot meet the OTA test accuracy requirements, the NGSO LEO-600 standard test scenario is selected as the target test scenario.

[0058] As an optional implementation method, such as Figure 4 As shown, in step S400, the NGSO LEO-1200 target test scenario is generated in the following way: S410c: The reference position of the terminal under test and the reference position of the target satellite under the 3GPP default NGSO LEO-1200 scenario are used as the NGSO LEO-1200 standard test scenario (i.e., the NGSO LEO-1200 test parameter configuration explicitly defined by the 3GPP specification), and the equivalent isotropic radiated power of the terminal under test is measured in the NGSO LEO-1200 standard test scenario. The test yielded the NGSO LEO-1200 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSO LEO-1200 optimized test scenario. The sixth equivalent isotropic radiated power was obtained from the test. S420c: Calculate the NGSO LEO-1200 standard equivalent isotropic radiated power. With the sixth equivalent isotropic radiated power The difference between them yields the NGSO LEO-1200 test scenario difference. S430c: Set equivalent isotropic radiated power The third reference limit The specific value should be set according to the test requirements, such as the first reference limit. Or second reference limit Equal, based on the ability to successfully complete OTA testing; S440c: If If the NGSO LEO-1200 optimized test scenario is selected as the target test scenario, then the NGSO LEO-1200 optimized test scenario is selected as the target test scenario. Otherwise, if the NGSO LEO-1200 optimized test scenario cannot meet the OTA test accuracy requirements, the NGSO LEO-1200 standard test scenario is selected as the NGSOLEO-1200 target test scenario.

[0059] As an optional implementation, the maximum equivalent isotropic radiated power in the upper hemisphere of the terminal under test is... The equivalent isotropic radiated power of the terminal under test is measured at the location of the value. Tests are conducted to reduce the equivalent isotropic radiated power. The impact of test errors.

[0060] Table 5 shows a comparison of test results for a fast OTA testing method for a satellite communication terminal using this embodiment in a GSO optimized test scenario. Regardless of whether there are 67 or 500 samples, completely disabling uplink padding or setting uplink padding RU=1 significantly reduces the OTA test time. Setting the test terminal to co-locate with the target satellite also significantly reduces the OTA test time. Combining these two methods (co-location + completely disabling uplink padding) minimizes the test time. In the 67 samples, the test times for test prototypes 1 and 2 decreased from 61.2 seconds and 55.5 seconds to 6.4 seconds and 6.2 seconds, respectively. In the 500 samples, the test times for test prototypes 1 and 2 decreased from 467.1 seconds and 357.4 seconds to 38.8 seconds and 35.6 seconds, respectively, significantly reducing the test time and greatly improving test efficiency.

[0061] Table 5. Comparison of test results for various test configurations in the GSO optimization test scenario using this method.

[0062]

[0063] The embodiment is merely a specific example and does not indicate that the present invention is only implemented in this way.

[0064] Example 2:

[0065] A rapid OTA testing system for satellite communication terminals is provided for running the rapid OTA testing method for a satellite communication terminal described in Embodiment 1. This system significantly shortens the OTA testing time of the satellite communication terminal under test and improves testing efficiency by disabling the ephemeris consistency check and position check functions of the terminal under test, configuring the reference positions of the terminal under test and the target satellite during the testing process to reduce the round-trip transmission delay (K-offset), and disabling the uplink padding function of the terminal under test during the reception performance test. This also maintains the accuracy and consistency of the test results.

[0066] The above description is merely a preferred embodiment of the present invention. Those skilled in the art will understand that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the present invention. Furthermore, under the teachings of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of the present invention.

Claims

1. A method for fast OTA testing of a satellite communication terminal, characterized in that, Includes the following steps: S100: Establish a signaling connection between the satellite simulator and the terminal under test, and disable the ephemeris consistency check and position check functions of the terminal under test; S200: Configure the reference position of the terminal under test and the reference position of the target satellite through the satellite simulator respectively. Based on multiple sets of reference positions of the terminal under test and the target satellite, by setting the reference position of the terminal under test to be the same as the reference position of the target satellite, or setting the altitude of the reference position of the target satellite at the same longitude and latitude to be lower than the altitude of the reference position of the standard test scenario, multiple optimized test scenarios that can reduce the round-trip transmission delay K-offset between the terminal under test and the target satellite are obtained. S300: Based on multiple optimized test scenarios, the satellite simulator generates a test signal containing the ephemeris information of the target satellite; S400: The satellite simulator configures the terminal under test and selects a target test scenario from multiple optimized test scenarios and standard test scenarios. Based on the target test scenario and the corresponding test signal under the target test scenario, the OTA performance test of the terminal under test is performed. During the OTA reception performance test, the uplink filling function of the terminal under test is turned off.

2. The method of claim 1, wherein, In step S400, the optimized test scenarios include GSO optimized test scenarios and NGSO optimized test scenarios; the standard test scenarios include GSO standard test scenarios and NGSO standard test scenarios; and the target test scenarios include GSO target test scenarios and NGSO target test scenarios.

3. The method of claim 2, wherein, The GSO optimization test scenarios include a first GSO optimization test scenario, a second GSO optimization test scenario, a third GSO optimization test scenario, and a fourth GSO optimization test scenario. In the first and second GSO optimization test scenarios, the reference position of the terminal under test and the reference position of the target satellite are set to the same spatial position. In the third and fourth GSO optimization test scenarios, the longitude and latitude of the reference position of the terminal under test and the reference position of the target satellite are the same, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the LEO altitude.

4. The method of claim 3, wherein, In the first GSO optimization test scenario, the altitudes of the reference positions of the terminal under test and the target satellite are both geostationary orbit altitudes; in the second GSO optimization test scenario, the altitudes of the reference positions of the terminal under test and the target satellite are both 0m; in the third GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the first low Earth orbit (LEO) altitude. In the fourth GSO optimization test scenario, the altitude of the reference position of the terminal under test is 0m, and the altitude of the reference position of the target satellite is the second low Earth orbit (LEO) altitude; the first LEO altitude is lower than the second LEO altitude.

5. The method of claim 4, wherein, In step S400, the GSO target test scenario is generated in the following way: S410a: Using the reference position of the terminal under test (DUT) and the reference position of the geostationary orbit GSO target satellite in the default 3GPP GSO scenario as the standard GSO test scenario, the equivalent isotropic radiated power of the DUT is measured within the standard GSO test scenario. The test yielded the GSO standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the first, second, third, and fourth GSO optimized test scenarios, respectively. The tests yielded the first equivalent isotropic radiated power. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power ; S420a: Calculate the first equivalent isotropic radiated power respectively. Second equivalent isotropic radiated power Third equivalent isotropic radiated power Fourth equivalent isotropic radiated power Equivalent Isotropic Radiated Power of GSO Standard The difference between them yields the difference for the first GSO optimization test scenario. The difference in the second GSO optimization test scenario The difference in the third GSO optimization test scenario The fourth GSO optimization test scenario difference : ， ， ， ； S430a: Setting the equivalent isotropic radiation power First reference limit ; S440a: If Select either the first GSO optimization test scenario or the second GSO optimization test scenario as the GSO target test scenario; if and Select the third GSO optimization test scenario as the GSO target test scenario; if and Select the fourth GSO optimization test scenario as the GSO target test scenario; if If so, the GSO standard test scenario is selected as the GSO target test scenario.

6. The rapid OTA testing method for a satellite communication terminal according to claim 2, characterized in that, The NGSO optimized test scenarios include the NGSO LEO-600 optimized test scenario and the NGSO LEO-1200 optimized test scenario. The NGSO standard test scenarios include the NGSO LEO-600 standard test scenario and the NGSO LEO-1200 standard test scenario. The NGSO target test scenarios include the NGSO LEO-600 target test scenario and the NGSO LEO-1200 target test scenario. In the NGSO LEO-600 optimized test scenario, the reference position of the terminal under test and the reference position of the target satellite are the same spatial position, and the altitude at this spatial position is the third low Earth orbit (LEO) altitude. In the NGSO LEO-1200 optimized test scenario, the reference position of the terminal under test and the reference position of the target satellite are the same spatial position, and the altitude at this spatial position is the fourth low Earth orbit (LEO) altitude. The third low Earth orbit (LEO) altitude is lower than the fourth low Earth orbit (LEO) altitude.

7. The rapid OTA testing method for a satellite communication terminal according to claim 6, characterized in that, In step S400, the NGSO LEO-600 target test scenario is generated in the following way: S410b: Using the 3GPP default NGSO LEO-600 scenario as the reference position of the terminal under test and the target satellite reference position, the equivalent isotropic radiated power of the terminal under test is measured within the NGSO LEO-600 standard test scenario. The test yielded the NGSO LEO-600 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSO LEO-600 optimized test scenario. The fifth equivalent isotropic radiated power was obtained from the test. ; S420b: Calculate the equivalent isotropic radiated power according to the NGSO LEO-600 standard. With the fifth equivalent isotropic radiated power The difference between them yields the NGSO LEO-600 test scenario difference. ; S430b: Setting equivalent isotropic radiation power Second reference limit ; S440b: If If the condition is met, the NGSO LEO-600 optimized test scenario is selected as the NGSO LEO-600 target test scenario; otherwise, the NGSO LEO-600 standard test scenario is selected as the NGSO LEO-600 target test scenario.

8. A rapid OTA testing method for a satellite communication terminal according to claim 6, characterized in that, In step S400, the NGSO LEO-1200 target test scenario is generated in the following way: S410c: Using the 3GPP default NGSO LEO-1200 scenario as the reference position of the terminal under test and the target satellite reference position, the equivalent isotropic radiated power of the terminal under test is measured within the NGSO LEO-1200 standard test scenario. The test yielded the NGSO LEO-1200 standard equivalent isotropic radiated power. The equivalent isotropic radiated power of the terminal under test was measured in the NGSO LEO-1200 optimized test scenario. The sixth equivalent isotropic radiated power was obtained from the test. ; S420c: Calculate the NGSO LEO-1200 standard equivalent isotropic radiated power With the sixth equivalent isotropic radiated power The difference between them yields the NGSO LEO-1200 test scenario difference. ; S430c: Setting equivalent isotropic radiated power The third reference limit ; S440c: If If the condition is met, the NGSO LEO-1200 optimized test scenario is selected as the NGSO LEO-1200 target test scenario; otherwise, the NGSO LEO-1200 standard test scenario is selected as the NGSO LEO-1200 target test scenario.

9. A rapid OTA testing method for a satellite communication terminal according to any one of claims 5, 7, and 8, characterized in that, Maximum equivalent isotropic radiated power in the upper hemisphere of the terminal under test The equivalent isotropic radiated power of the terminal under test is measured at the location of the value. test.

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