Satellite carrier signal equivalent isotropically radiated power test method, device and system

Abstract

The application discloses a satellite carrier signal equivalent isotropic radiated power test method, device and system, the method comprises the following steps: in the link calibration stage, the wideband carrier signal test link compensation term is calculated through the standard satellite link, the standard satellite link is established through the standard gain antenna, the compact field reflector and the feed antenna; in the satellite performance test stage, the satellite load is controlled to emit the satellite carrier signal, and the multi-degree-of-freedom platform is controlled to drive the satellite load to move, so that the beam of the satellite carrier signal is real-time pointed to the compact field reflector in the satellite load movement process; after the satellite carrier signal passes through the compact field reflector and reaches the feed antenna, the in-band power value of the satellite carrier signal of the satellite load at each track point and the wideband carrier signal test link compensation term are used to calculate the dynamic equivalent isotropic radiated power value of each track point. The application can simulate the dynamic working condition, and adapt to the high-precision dynamic test process of the equivalent isotropic radiated power of the wideband carrier characteristics.

Description

Technical Field

[0001] This application relates to the field of satellite communication testing technology, and in particular to a method, apparatus and system for testing the equivalent omnidirectional radiated power of satellite carrier signals. Background Technology

[0002] This section is intended to provide background or context for the embodiments of this application set forth in the claims. The description herein is not an admission that it is prior art simply because it is included in this section.

[0003] In satellite communication systems, the equivalent isotropic radiated power (EIRP) is a key indicator for measuring the transmission performance of satellite antennas, and its value directly determines the coverage and communication quality of satellite signals.

[0004] In the field of satellite communication testing, far-field testing is a common method for testing equivalent isotropic radiated power. Its principle is to receive and analyze signals in the far-field region of the antenna, and the test results directly reflect the far-field radiation characteristics of the antenna. However, this method has significant drawbacks: First, far-field testing requires meeting a far-field distance condition, i.e., the test distance must reach 2D² / λ of the antenna's maximum size (D is the antenna aperture, and λ is the operating wavelength). For large-aperture satellite antennas (e.g., diameter greater than 5 meters), the far-field distance may exceed several kilometers, meaning a dedicated large-scale test site is required, which is not only costly to construct but also difficult to deploy in space-constrained areas such as urban peripheries. Second, the far-field test environment at long distances is usually outdoors, easily affected by environmental factors such as atmospheric attenuation, ground reflection, and electromagnetic interference. For example, above the Ku band, rainfall attenuation can reach over 20 dB, severely affecting test accuracy. Furthermore, far-field testing is inefficient, with a single test taking several hours, making it difficult to meet the rapid testing requirements of mass-produced satellites.

[0005] Compact field testing technology converts the spherical wave emitted by the feed antenna into a plane wave through a compact field reflecting surface (usually a parabola or cylinder), simulating the far-field testing environment in a small space, and has been widely used in the field of antenna testing.

[0006] Existing compact-field testing methods lack simulation of dynamic scenarios in dynamic EIRP testing of satellite carrier signals: In traditional compact-field testing, the satellite payload or antenna is fixedly installed, and only the EIRP value under static beam pointing can be tested. However, in actual satellite operation, to achieve continuous coverage of ground targets, the beam needs to scan at a certain speed (e.g., 5° / s), and the dynamic changes in beam pointing cause the EIRP value to fluctuate over time. Traditional methods cannot simulate such dynamic conditions, resulting in test results that deviate from the actual operating performance of the satellite.

[0007] With single constellations now containing over ten thousand satellites, these satellites need to achieve dynamic coverage of massive numbers of users through beam scanning. The accuracy of EIRP dynamic testing directly impacts the accuracy of link budget. Therefore, there is an urgent need for a high-precision dynamic testing method for equivalent isotropic radiated power that can simulate dynamic operating conditions and adapt to the characteristics of broadband carriers. Summary of the Invention

[0008] This application provides a method for testing the equivalent isotropic radiated power of a satellite carrier signal, used to simulate dynamic operating conditions and adapt to the characteristics of broadband carriers, enabling high-precision dynamic testing of the equivalent isotropic radiated power. The method includes:

[0009] During the link calibration phase, the broadband carrier signal test link compensation term is calculated using a standard satellite link, which is established through a standard gain antenna, a compact field reflector, and a feed antenna.

[0010] During the satellite performance testing phase, the satellite payload is controlled to transmit satellite carrier signals, and a multi-degree-of-freedom platform is controlled to drive the satellite payload to move, so that the beam of the satellite carrier signal is pointed to the compact field reflector in real time during the movement of the satellite payload.

[0011] After the satellite carrier signal reaches the feed antenna through the compacted field reflector, the dynamic equivalent isotropic radiated power value of each trajectory point is calculated based on the in-band power value of the satellite carrier signal and the broadband carrier signal test link compensation term of the satellite payload at each trajectory point.

[0012] This application also provides a satellite carrier signal equivalent isotropic radiated power testing device to simulate dynamic operating conditions and adapt to the characteristics of broadband carriers, enabling high-precision dynamic testing of equivalent isotropic radiated power. The device includes:

[0013] The calibration module is used to calculate the broadband carrier signal test link compensation term during the link calibration phase using a standard satellite link established by a standard gain antenna, a compacted field reflector, and a feed antenna.

[0014] The control module is used to control the satellite payload to transmit satellite carrier signals during the satellite performance testing phase, and to control the multi-degree-of-freedom platform to drive the satellite payload to move, so that the beam of the satellite carrier signal is pointed to the compact field reflector in real time during the movement of the satellite payload.

[0015] The calculation module is used to calculate the dynamic equivalent isotropic radiated power value of each trajectory point after the satellite carrier signal reaches the feed antenna through the compacted field reflector, based on the in-band power value of the satellite carrier signal and the broadband carrier signal test link compensation term of the satellite payload at each trajectory point.

[0016] This application provides a satellite carrier signal equivalent omnidirectional radiated power testing system to simulate dynamic operating conditions and adapt to the characteristics of broadband carriers for high-precision dynamic testing of equivalent omnidirectional radiated power. The system includes: the aforementioned dynamic testing device for equivalent omnidirectional radiated power, a multi-degree-of-freedom platform, a satellite payload mounted on the multi-degree-of-freedom platform, a feed turntable, a feed antenna mounted on the feed turntable, a compact field reflector, a beamformer, and a spectrum analyzer.

[0017] The satellite carrier signal equivalent omnidirectional radiated power testing device is also used to: trigger the beamformer to adjust the beam pointing of the satellite carrier signal to the compact field reflector in real time during the movement of the satellite payload;

[0018] The spectrum analyzer is used to: receive the satellite carrier signal arriving at the feed antenna and analyze the in-band power value of the satellite carrier signal.

[0019] This application also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the above-described method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0020] This application also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0021] This application also provides a computer program product, which includes a computer program that, when executed by a processor, implements the above-described method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0022] The beneficial effects of the embodiments of this application are as follows:

[0023] I. Improve the accuracy of dynamic EIRP testing and eliminate link error interference.

[0024] Pre-calibration of link compensation terms: By establishing a standard satellite link through a standard gain antenna during the link calibration phase, the broadband carrier signal test link compensation terms are pre-calculated, which can accurately correct the inherent errors of the test link itself and avoid the errors being superimposed on the dynamic EIRP calculation results of the satellite payload, thus significantly improving the reliability of the measurement data.

[0025] Accurate trajectory point sampling and calculation: For each trajectory point during the satellite payload's motion, the in-band power value of the satellite carrier signal is collected separately and combined with the compensation term to calculate the dynamic EIRP. This can truly reflect the radiated power characteristics of the satellite under different motion attitudes, avoid local errors caused by overall estimation, and meet the requirements of high-precision testing.

[0026] II. The test results accurately reflect real-world satellite orbit scenarios and are relevant to practical applications.

[0027] Simulate on-orbit motion trajectory: By using a multi-degree-of-freedom platform to drive the satellite payload to move, the changing trajectory of the satellite relative to the ground test station when it is in orbit is reproduced. This breaks through the limitation of traditional static testing that cannot simulate dynamic working conditions, and makes the test scenario highly consistent with the actual operating environment of the satellite.

[0028] Real-time beam tracking of the reflector: During the movement of the satellite payload, the beam is controlled to point to the compact field reflector in real time, ensuring the stability of the signal transmission path at each trajectory point and avoiding signal attenuation or loss due to beam offset. This truly restores the coordinated working state of the satellite's motion and beam adjustment when it is in orbit, and the test results can directly guide the optimization of the satellite's on-orbit performance.

[0029] Third, optimize the efficiency of the testing process, making it highly universal and operable.

[0030] The process is highly efficient and well-organized: "Link calibration" and "dynamic testing" are divided into two independent but interconnected stages. The standard link in the calibration stage can be reused (without the need for recalibration for each test), while the dynamic testing stage only needs to focus on the motion control and data acquisition of the satellite payload, reducing repetitive operations, shortening the overall testing cycle, and reducing manpower and time costs.

[0031] Universality and adaptability to multiple scenarios: The testing method does not depend on specific satellite payloads or compact field equipment. Through the angle adjustment and beam tracking mechanism of the multi-degree-of-freedom platform, it supports the simulation of different satellite on-orbit trajectories. It is suitable for the dynamic EIRP testing needs of various low-Earth orbit and medium-Earth orbit satellites and has a wide range of applications.

[0032] IV. Reduce the complexity of the testing system, balancing technical feasibility and cost control.

[0033] There is no need to build a complex on-orbit test environment (such as a real-time communication link between the ground station and the on-orbit satellite). Dynamic scene simulation can be achieved simply by using a ground compact field, a multi-degree-of-freedom platform and a standard gain antenna. While ensuring test performance, the construction cost and operation and maintenance difficulty of the test system are greatly reduced, which makes it easy to promote and apply on a large scale in the laboratory environment. Attached Figure Description

[0034] To more clearly illustrate the technical solutions in the embodiments of this application 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 this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0035] Figure 1 This is a flowchart of the method for testing the equivalent isotropic radiated power of satellite carrier signals in the embodiments of this application;

[0036] Figure 2 This is a schematic diagram of the structure of the satellite carrier signal equivalent isotropic radiated power testing device in the embodiments of this application;

[0037] Figure 3 This is a schematic diagram of the structure of the satellite carrier signal equivalent isotropic radiated power testing system in the embodiments of this application;

[0038] Figure 4 This is another schematic diagram of the equivalent isotropic radiated power testing system for satellite carrier signals in this application embodiment;

[0039] Figure 5 This is a schematic diagram of the dynamic EIRP curve obtained by the equivalent isotropic radiated power test method of satellite carrier signal in the embodiments of this application;

[0040] Figure 6 This is a schematic diagram of a computer device in an embodiment of this application. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the embodiments of this application will be further described in detail below with reference to the accompanying drawings. Here, the illustrative embodiments and descriptions of this application are used to explain this application, but are not intended to limit this application.

[0042] Figure 1 This is a flowchart of the method for testing the equivalent isotropic radiated power of a satellite carrier signal in this application, including:

[0043] Step 101: In the link calibration phase, calculate the broadband carrier signal test link compensation term using a standard satellite link, which is established using a standard gain antenna, a compacted field reflector, and a feed antenna.

[0044] Step 102: During the satellite performance testing phase, control the satellite payload to transmit satellite carrier signals and control the multi-degree-of-freedom platform to drive the satellite payload to move, so that the beam of the satellite carrier signal points to the compact field reflector in real time during the movement of the satellite payload.

[0045] Step 103: After the satellite carrier signal reaches the feed antenna through the compacted field reflector, calculate the dynamic equivalent omnidirectional radiated power value of each trajectory point based on the in-band power value of the satellite carrier signal and the broadband carrier signal test link compensation term of the satellite payload at each trajectory point.

[0046] Figure 2This is a schematic diagram of the structure of the satellite carrier signal equivalent isotropic radiated power testing device in the embodiments of this application, including:

[0047] The calibration module 201 is used to calculate the broadband carrier signal test link compensation term through a standard satellite link during the link calibration phase. The standard satellite link is established through a standard gain antenna, a compacted field reflector, and a feed antenna.

[0048] The control module 202 is used to control the satellite payload to transmit satellite carrier signals during the satellite performance testing phase, and to control the multi-degree-of-freedom platform to drive the satellite payload to move, so that the beam of the satellite carrier signal points to the compact field reflector in real time during the movement of the satellite payload.

[0049] The calculation module 203 is used to calculate the dynamic equivalent isotropic radiated power value of each trajectory point after the satellite carrier signal reaches the feed antenna through the compacted field reflector, based on the in-band power value of the satellite carrier signal and the broadband carrier signal test link compensation term of the satellite payload at each trajectory point.

[0050] Figure 3 This is a schematic diagram of the structure of the satellite carrier signal equivalent omnidirectional radiated power test system in this application embodiment, including: the aforementioned satellite carrier signal equivalent omnidirectional radiated power test device, a multi-degree-of-freedom platform, a satellite payload installed on the multi-degree-of-freedom platform, a feed turntable, a feed antenna installed on the feed turntable, a compact field reflector, a beamformer, and a spectrum analyzer;

[0051] The satellite carrier signal equivalent omnidirectional radiated power testing device is also used to: trigger the beamformer to adjust the beam pointing of the satellite carrier signal to the compact field reflector in real time during the movement of the satellite payload;

[0052] The spectrum analyzer is used to: receive the satellite carrier signal arriving at the feed antenna and analyze the in-band power value of the satellite carrier signal.

[0053] In the above embodiments, multiple modules work together to achieve trajectory simulation and beam tracking: the system uses a combination of a "multi-degree-of-freedom platform + beamformer" structure. The multi-degree-of-freedom platform drives the satellite payload to replicate its on-orbit trajectory, while the dynamic testing device synchronously triggers the beamformer to adjust the beam direction, ensuring that the beam is always accurately aligned with the compacted field reflector during the satellite payload's movement. This avoids signal transmission errors caused by beam offset and provides a stable signal source foundation for subsequent in-band power analysis and EIRP calculation. The feed turntable and spectrum analyzer optimize the signal reception link: the feed antenna is mounted on the feed turntable, which can flexibly adjust its attitude to adapt to the signal reflection path of the compacted field reflector. Combined with the spectrum analyzer, it accurately receives and analyzes the in-band power value of the satellite carrier signal, reducing signal loss and interference in the signal reception stage, further improving the accuracy of the test data and ensuring the reliability of the dynamic EIRP calculation results. Integrated Core Test Components: The system integrates core components such as satellite payload, multi-degree-of-freedom platform, beamformer, compact field reflector, and spectrum analyzer, forming a complete test chain of "signal transmission - trajectory simulation - beam adjustment - signal reception - data analysis." This eliminates the need for additional external auxiliary equipment, avoids compatibility issues between multiple devices, significantly simplifies the setup and debugging process of the test system, and shortens the test preparation cycle. Unified Control Logic for Dynamic Test Devices: The dynamic test device not only undertakes the core functions of EIRP testing but also triggers the beamformer to adjust the beam direction, achieving unified scheduling of "trajectory simulation" and "beam control." This avoids timing deviations caused by independent control of multiple devices, ensures the synchronization of satellite payload movement, beam adjustment, and signal acquisition, and improves the smoothness and efficiency of the overall test process. Multi-DOF platform and feed turntable enhance scenario adaptability: The multi-DOF platform can simulate the motion trajectory of satellites in different orbits (LEO, MEO, etc.) based on satellite ephemeris files. The feed turntable can adjust the feed antenna attitude to adapt to satellite payloads with different frequency bands and beam characteristics. This allows the system to meet the dynamic EIRP testing requirements of various satellite carrier signals without changing the core structure, reducing the cost of scenario switching. Compact field reflector ensures test environment stability: The compact field reflector can construct a near-plane wave signal transmission environment, unaffected by external space environment interference. This allows the system to operate stably in a laboratory environment and can also adjust the reflector parameters to adapt to different test accuracy requirements, further expanding the system's application scenarios (such as performance verification during satellite payload development and quality inspection before delivery). Modular structure facilitates maintenance and upgrades: The system's components (multi-degree-of-freedom platform, feed turntable, spectrum analyzer, etc.) adopt a modular design. If a component fails, it can be repaired or replaced individually without disassembling the entire system, reducing maintenance difficulty and cost. At the same time, individual components can be upgraded in the future according to technological developments (such as replacing with a higher-precision spectrum analyzer or expanding the motion range of the multi-degree-of-freedom platform), extending the system's service life.Stable signal transmission links reduce test rework: Through real-time adjustment of the beamformer and signal optimization of the compact field reflector, the system can ensure the stability of signal transmission during the test, reduce test rework caused by signal interruption or deviation, reduce the manpower and time costs of repeated tests, and improve the reliability and economic benefits of test work.

[0054] In one embodiment, the polarization of the standard gain antenna, the feed antenna, and the satellite payload antenna are kept consistent.

[0055] In the embodiments of this application, keeping the polarization of the standard gain antenna, the feed antenna and the satellite payload antenna consistent means that when the satellite payload antenna is linearly polarized, the standard gain antenna and the feed antenna use the same linearly polarized antenna, and the polarization direction deviation must be less than 5°, otherwise polarization loss will be introduced; when the satellite payload antenna is circularly polarized, the standard gain antenna and the feed antenna use the same circularly polarized antenna, and the polarization axis ratio of the antenna must be less than 3dB.

[0056] In one embodiment, the motion angles of the multi-degree-of-freedom platform include at least pitch angle, azimuth angle, polarization angle, and forward / backward translation angle.

[0057] In this embodiment, step 101 is the execution step of the link calibration stage, and steps 102-103 are the execution steps of the satellite performance testing stage. During the test, the broadband carrier signal test link compensation item is required, and the broadband carrier signal test link compensation item is obtained in the link calibration stage. The structure and execution steps of the satellite carrier signal equivalent omnidirectional radiated power test system in the link calibration stage are given below.

[0058] Figure 4 This is another schematic diagram of the equivalent omnidirectional radiated power test system for satellite carrier signals in this application embodiment, which also includes a vector signal generator, a laser collimator, and a standard gain antenna mounted on a multi-degree-of-freedom platform;

[0059] A vector signal generator is used to generate carrier signals and send them to a standard gain antenna;

[0060] A laser collimator is used to adjust the standard gain antenna to align with the center of the compacted field reflector.

[0061] In this embodiment, a standardized carrier signal is generated by a vector signal generator and sent to a standard gain antenna. This allows for precise control of parameters such as bandwidth, modulation type (e.g., QPSK), and power of the calibration signal, avoiding calibration errors caused by signal source instability. It provides a unified and reliable "reference signal source" for subsequent calculation of compensation terms for the broadband carrier signal test link, ensuring that the compensation terms accurately reflect the inherent loss characteristics of the test link. The gain of the standard gain antenna is a known fixed parameter, and its polarization characteristics can be consistent with those of the satellite payload antenna. The calibration link built using this antenna effectively isolates interference between "antenna characteristics" and "link transmission characteristics," allowing the calculation of the link compensation terms to focus solely on the loss of the test link (e.g., a compact field reflector or feed antenna), further improving compensation accuracy. Laser collimators can control the pointing error of standard gain antennas to ≤0.05°, ensuring that the antenna beam center is precisely aligned with the center of the compact field reflector, avoiding uneven signal reflection loss caused by antenna offset. If the antenna pointing is off, the signal transmission path during calibration will be inconsistent with the path during dynamic testing, causing the link compensation terms to fail to match the actual test scenario. The introduction of laser collimators solves this problem at its source, ensuring "path consistency" between the calibration and testing links. The precise alignment method of laser collimators for standard gain antennas can be transferred to the alignment process of satellite payload antennas (such as adjusting the satellite payload antenna pointing via a laser tracker), forming a "standardized alignment methodology." This avoids errors caused by operational differences in the alignment process of different antennas, improving the operational standardization and result repeatability of the entire testing system. The newly added vector signal generator, laser collimator, and standard gain antenna fill the gap in the original system's "core equipment for the link calibration phase," upgrading the system from "only capable of dynamic testing" to a complete closed loop that "can autonomously complete link calibration + dynamic testing." This eliminates reliance on external calibration equipment, reduces compatibility issues with multiple devices, and significantly improves the independence and convenience of the testing process. Through the high-precision alignment of the laser collimator and the standardized signal output of the vector signal generator, the system can stably reproduce calibration and testing scenarios in a laboratory environment, without relying on the "natural alignment conditions" of large outdoor testing grounds (such as the actual alignment of the satellite and ground station). This reduces the system's dependence on external space, weather, and other environmental factors, expanding its applicability to various scenarios (such as indoor R&D testing and factory inspection). The parameters of the vector signal generator can be accurately recorded (such as signal bandwidth of 100MHz and modulation type), the alignment error of the laser collimator can be quantified (≤0.05°), and the parameters of the standard gain antenna can be traced. These components enable each step of the link calibration process to have clear quantitative indicators. If it is necessary to verify or reproduce the test results later, the calibration scenario can be quickly restored by tracing back the calibration parameters, thereby improving the traceability of the test results.Based on the test results of precise calibration links and high-precision alignment, the dynamic EIRP characteristics of satellite payloads can be more realistically reflected. When a satellite is in orbit, the antenna pointing accuracy and signal link loss directly affect its communication performance. This system, through the optimized calibration and alignment process with added components, can ensure that the deviation between the test results and the actual performance of the satellite in orbit is minimized. This provides authoritative data support for the research and development optimization and performance acceptance of satellite payloads, and accelerates the application of the technology.

[0062] In one embodiment, the polarization axis ratio of the standard gain antenna to the feed antenna is less than a preset ratio.

[0063] For example, taking a 4-DOF platform as an example, the 4-DOF platform has the ability to adjust the pitch angle, azimuth angle, polarization angle, and forward and backward translation. The pitch angle adjustment range is ±65°, the azimuth angle adjustment range is ±180°, the polarization adjustment range is ±90°, and the translation adjustment range is ±500mm. The pitch and azimuth angle accuracy is better than 0.02°, and the angle resolution is better than 0.01°. The standard gain antenna is aligned with the center of the compact field reflector by a laser collimator, and the alignment error is ≤0.05°, avoiding EIRP test errors caused by pointing deviation (when the beam pointing deviation is 1°, the EIRP test error can reach more than 0.5dB). The feed antenna is installed on the feed turntable. The satellite payload antenna is right-hand circularly polarized. The polarization of both the standard gain antenna and the feed antenna is right-hand circularly polarized. The polarization axis ratio of the standard gain antenna and the feed antenna is ≤2dB.

[0064] During the link calibration phase, the vector signal generator generates a broadband carrier signal and sends it to the standard gain antenna. For example, the carrier signal has a bandwidth of 100MHz and a modulation type of QPSK. The carrier signal reaches the feed antenna after passing through the compact field reflector. The signal is received by the spectrum analyzer and then sent to the host computer, which calculates the broadband carrier signal test link compensation term. In another embodiment, the spectrum analyzer can also perform the calculation of the broadband carrier signal test link compensation term. There is no limitation here.

[0065] The vector signal generator generates a carrier signal with a bandwidth of 40~1600MHz, and the modulation types include QPSK, 8PSK, 16APSK, 32APSK, 16QAM and 32QAM.

[0066] In one embodiment, calculating the broadband carrier signal test link compensation term using a standard satellite link includes:

[0067] After the carrier signal passes through the standard satellite link, the broadband carrier signal test link compensation term is calculated based on the in-band amplitude unevenness and group delay of the satellite carrier signal.

[0068] The standard satellite link consists of a carrier signal that passes sequentially through a standard gain antenna, a compacted field reflector, and a feed antenna.

[0069] In one embodiment, the broadband carrier signal test link compensation term is calculated based on the in-band amplitude unevenness and group delay of the satellite carrier signal, including:

[0070] Calculate the amplitude calibration factor based on the in-band amplitude unevenness;

[0071] Calculate the phase calibration factor based on the group delay;

[0072] Calculate the integrated channel calibration coefficient based on the amplitude calibration factor and the phase calibration factor;

[0073] Calculate the broadband carrier signal test link compensation term based on the comprehensive channel calibration coefficient.

[0074] In one embodiment, the broadband carrier signal test link compensation term is calculated based on the in-band amplitude unevenness and group delay of the satellite carrier signal, including:

[0075] The following formula is used to determine the in-band amplitude unevenness. Calculate the amplitude calibration factor : ;

[0076] The following formula is used, based on group delay. Calculate the phase calibration factor : ;

[0077] The integrated channel calibration coefficient is calculated using the following formula, based on the amplitude calibration factor and the phase calibration factor. : ;

[0078] The following formula is used to calculate the broadband carrier signal test link compensation term based on the integrated channel calibration coefficient: : .

[0079] After obtaining the broadband carrier signal test link compensation item, the satellite performance testing phase can begin. In this phase, the satellite payload is mounted on a multi-degree-of-freedom platform, with its antenna aligned with the center of the compacted field reflector. The antenna pointing is adjusted using a laser tracker to ensure the beam center is aligned with the compacted field reflector, with an alignment error ≤0.05°. Optionally, the satellite payload can operate in S-band, C-band, X-band, Ku-band, Ka-band, or QV-band.

[0080] In the above embodiments, by calculating the amplitude calibration factor and the phase calibration factor separately, the two core errors of "amplitude loss" and "phase offset" in the test link are accurately separated. Traditional compensation methods often use "overall average loss" estimation, which cannot distinguish the independent effects of amplitude and phase. However, this solution, through dimensional calibration, can specifically correct amplitude fluctuations (such as more significant amplitude attenuation in a certain frequency band within the band) and phase delays (such as signal phase distortion caused by group delay) at different frequency points, making the compensation terms more consistent with the actual error characteristics of the link. The signal transmission path of the standard satellite link (standard gain antenna → compact field reflector → feed antenna) is completely consistent with the path of subsequent satellite payload testing. Moreover, the gain and polarization characteristics of the standard gain antenna are known fixed parameters, which can effectively eliminate the interference of "antenna performance differences" on link errors. This ensures that the compensation terms only focus on the losses of common links such as "compact field reflector, feed antenna, and transmission space," avoiding compensation deviations caused by antenna characteristic confusion and further improving compensation accuracy. From "amplitude / phase calibration factor" to "comprehensive channel calibration coefficient," and then to "wideband carrier signal test link compensation term," a hierarchical and progressive calculation logic is adopted. Each step of the calculation has a clear physical meaning and quantitative basis (such as amplitude calibration factor and phase calibration factor), rather than a vague "empirical formula." This logic makes the calculation process of the compensation term decomposable and verifiable. If it is necessary to trace the source of error later, the problem can be quickly located by reverse derivation of each calculation link (such as the compensation deviation at a certain frequency point originating from the amplitude unevenness measurement error). Addressing the "frequency-dependent" error of wideband carrier signals (differences in amplitude unevenness and group delay at different frequency points), this scheme introduces a frequency variable f to construct calibration factors and calibration coefficients, enabling the compensation term to cover the error across the entire signal bandwidth. This avoids the limitation of traditional "narrowband compensation" being only applicable to a single frequency and unable to adapt to wideband signals, thus meeting the testing requirements of wideband carrier signals for satellite payloads. The standard satellite link and the satellite payload test link (satellite payload → compacted field reflector → feed antenna) share core transmission components such as the compacted field reflector and feed antenna, and their signal transmission paths are completely identical. This ensures that the compensation terms calculated based on the standard link accurately match the error characteristics of the actual test link. If there are differences in the paths, the compensation terms will not be able to effectively correct the test errors. This solution, through link path consistency design, ensures the "effectiveness" of the compensation terms from the source, avoiding the cumulative effect of errors on the dynamic EIRP calculation results. Once the compensation terms for the broadband carrier signal test link are determined through standard link calculation, they can be used as a fixed benchmark for the dynamic EIRP calculation of all subsequent trajectory points, avoiding deviations caused by recalculating the compensation terms for each test. This also ensures the comparability of results from different satellite payloads and different test batches, improving the reliability and repeatability of test results and providing authoritative data support for satellite payload performance verification and quality control.From error parameter acquisition (amplitude unevenness, group delay) to final compensation term output, each step has clear logic and quantifiable steps. It does not rely on complex algorithm models or specialized equipment. Testers can complete parameter acquisition using conventional equipment such as spectrum analyzers and then calculate the compensation term using standardized formulas, lowering the operational threshold and facilitating large-scale application in laboratories, factories, and other scenarios. Adaptable to multiple frequency bands and carrier signal types: This calculation scheme only relies on two common link parameters, "amplitude unevenness" and "group delay," and is not bound to specific signal frequency bands (such as S-band and Ku-band) or modulation types (such as QPSK and FSK). Whether it's the S-band signal commonly used in satellite payloads or broadband carrier signals in other frequency bands, this method can calculate the appropriate link compensation term, significantly improving the method's universality and reducing the cost of adjusting the scheme in different scenarios.

[0081] In one embodiment, controlling the multi-degree-of-freedom platform to drive the satellite payload motion includes:

[0082] Analyze satellite ephemeris files to obtain the motion angles for controlling a multi-degree-of-freedom platform;

[0083] The multi-degree-of-freedom platform is controlled to move the satellite payload when it moves according to the stated motion angle.

[0084] In one embodiment, parsing satellite ephemeris files to obtain the motion angles for controlling a multi-degree-of-freedom platform includes:

[0085] By analyzing the ephemeris file, the azimuth and elevation angles of the satellite relative to the test station over time are obtained according to the satellite's on-orbit trajectory.

[0086] Based on the aforementioned change curve, the motion angles of the control multi-degree-of-freedom platform are obtained.

[0087] In this embodiment, the test station refers to the fixed site where the satellite carrier signal equivalent omnidirectional radiated power test system is located, which can be understood as the ground reference point of the entire compact field test system. During the test, the host computer triggers the beamformer to adjust the beam direction towards the compact field reflector in real time during the movement of the satellite payload, ensuring that the beam tracking error is ≤0.1.

[0088] In this embodiment, by parsing satellite ephemeris files to obtain the satellite's on-orbit trajectory, the orbital characteristics of the satellite during actual operation can be accurately reproduced (such as the rapid changes in azimuth / pitch angles of low-orbit satellites and the periodic trajectory patterns of medium-orbit satellites). This breaks through the limitations of the traditional "manually set fixed trajectory" method—manual trajectories cannot fully match the actual motion state of the satellite in orbit. Ephemeris files contain core parameters such as the satellite's latitude, longitude, altitude, and velocity in orbit, ensuring that the motion trajectory simulated by the multi-degree-of-freedom platform driving the satellite payload is highly consistent with the actual on-orbit trajectory of the satellite. This makes the dynamic EIRP test results more consistent with the satellite's on-orbit application scenarios. When analyzing ephemeris files, the azimuth and elevation angles of the satellite relative to the test station are explicitly used as core parameters to generate change curves. This perspective is completely consistent with the actual scenario of the ground test station receiving satellite signals when the satellite is in orbit. It can realistically simulate the relative motion relationship between the satellite and the ground station (such as the process of the azimuth angle increasing from 0° to 180° and the elevation angle first increasing and then decreasing when the satellite passes overhead). This avoids the test scenario from deviating from the actual application scenario due to perspective deviation, and further enhances the reference value of the test results. The "azimuth and elevation angle change curves over time" parsed from the ephemeris file provide a clear quantitative control basis for the motion angle of the multi-degree-of-freedom platform, rather than relying on vague "empirical values." For example, if the ephemeris file shows that the azimuth angle of the satellite relative to the test station is 30° and the elevation angle is 45° at a certain moment, the multi-degree-of-freedom platform can be precisely adjusted to that angle to ensure that the motion attitude of the satellite payload is completely matched with the satellite's on-orbit attitude. This avoids beam offset caused by angle control deviation (such as the beam not being able to align with the compact field reflector), and ensures the stability of the signal transmission link. Motion angle control based on ephemeris files can be precisely synchronized with the signal transmission timing of the satellite payload. After parsing the ephemeris file, the host computer can simultaneously output "platform motion control commands" and "satellite payload signal transmission commands," ensuring that the satellite payload's attitude is completely consistent with its on-orbit state when transmitting signals at specific motion angles (such as the elevation angle simulating the satellite's overhead pass). This avoids test data distortion caused by asynchrony between motion and signal transmission, improving the accuracy of dynamic EIRP calculation results. Test personnel do not need to manually calculate or set the motion angles of the multi-degree-of-freedom platform; simply importing the satellite ephemeris file allows the system to automatically parse and generate platform motion control commands. This significantly reduces manual intervention (such as manually adjusting angles and manually recording timing), lowers the operational threshold and reduces human error (such as angle setting deviations and timing recording errors), improving the automation and efficiency of the testing process.This solution is not tied to a specific satellite model. For different satellites (such as communication satellites and navigation satellites), only the corresponding ephemeris file needs to be replaced. The appropriate platform motion angles can be generated by parsing the file, without modifying the hardware structure or control logic of the multi-degree-of-freedom platform. This significantly improves the method's versatility and can meet the dynamic EIRP testing needs throughout the entire lifecycle of satellite R&D, production, and testing, reducing the cost of adjusting the testing scheme for different satellite models. The ephemeris file, as the original basis for the platform's motion angles, can be stored long-term and traced back. If the validity of the test results needs to be verified later, the corresponding ephemeris file can be retrieved, the motion trajectory of the multi-degree-of-freedom platform can be re-analyzed and reproduced, ensuring the traceability of the testing process, avoiding disputes caused by "unrecorded motion parameters," and enhancing the authority of the test data. The platform control method based on ephemeris files can form a unified "standard process for satellite dynamic simulation testing." When different laboratories and testing institutions adopt this method, they only need to follow the standardized steps of "ephemeris file parsing → motion angle generation → platform control" to ensure the consistency of the testing process, avoid incomparable results due to differences in testing methods, provide technical support for the industry standardization of satellite dynamic EIRP testing, and accelerate the promotion and application of the technology in the industry.

[0089] In this application example, it is necessary to ensure that the carrier signal beam is scanned in real time during the movement of the satellite payload, and that the beam always points to the compact field reflector. Real-time beam scanning control is the core of dynamic testing. Through the beamforming network inside the satellite payload (such as the T / R component of the phased array antenna), the beam pointing of the satellite carrier signal is adjusted in real time according to the motion angle of the multi-degree-of-freedom platform to ensure that the beam center is always aligned with the compact field reflector (deviation ≤0.1°) during the movement of the multi-degree-of-freedom platform, and to avoid the attenuation of received power due to beam offset.

[0090] In this embodiment, the in-band power value of the satellite carrier signal at each trajectory point can be obtained by a spectrum analyzer or by analysis by a host computer; there is no limitation here. The analysis process involves discretizing and sampling the satellite carrier signal to obtain the in-band power value of the satellite carrier signal at each trajectory point. To balance test accuracy and efficiency, the time interval for trajectory discretization sampling is typically set to 0.1~1s (adjusted according to the beam scanning speed, such as 0.2s interval at 5° / s, corresponding to 1° angular resolution). The aforementioned in-band power value can be (optionally, after calibration factor compensation) the average in-band power of the carrier.

[0091] In one embodiment, the method further includes:

[0092] After the satellite carrier signal passes through the standard satellite link, the gain of the standard gain antenna and the link loss are obtained.

[0093] Based on the in-band power value of the satellite carrier signal and the broadband carrier signal test link compensation term of the satellite payload at each trajectory point, the dynamic equivalent isotropic radiated power value of each trajectory point is calculated, including:

[0094] Based on the in-band power value of the satellite carrier signal of the satellite payload at each trajectory point, the broadband carrier signal test link compensation term, the gain of the standard gain antenna, and the link loss, calculate the dynamic equivalent isotropic radiated power value of each trajectory point.

[0095] In one embodiment, the dynamic equivalent isotropic radiated power value of each trajectory point is calculated using the following formula. :

[0096]

[0097] in, The in-band power value for each trajectory point, The gain of a standard gain antenna. For link loss, This is a link compensation item for broadband carrier signal testing.

[0098] The above Given a known quantity, such as 20 dBi, the physical meaning of this formula is: the satellite's EIRP value equals the power measured at the receiver, plus the link loss and broadband compensation term, minus the receiver antenna gain (to offset the influence of the receiver gain on the measurement result).

[0099] In this embodiment, by introducing the "gain of the standard gain antenna" into the formula, the interference of the "standard gain antenna's own gain" in the receiving link on the measurement results can be accurately offset. The gain of the standard gain antenna is an inherent parameter of the receiver signal amplification; if this factor is not eliminated, the calculated EIRP will include the "receiver gain contribution," rather than the actual transmitted radiated power of the satellite payload. The formula "subtracts..." The design, from a physical perspective, replicates the actual launch characteristics of the satellite payload, ensuring that the results are consistent with the actual EIRP of the satellite in orbit. Link loss and compensation terms are added to correct for end-to-end errors: the formula simultaneously incorporates "link loss". "and "Broadband carrier signal test link compensation item" The former corrects for inherent losses during signal transmission (such as attenuation from the compacted field reflector and feed antenna loss), while the latter corrects for amplitude unevenness and group delay error in broadband signals. The combination of both achieves complete compensation for the entire link error from signal transmission to signal characteristics, avoiding calculation deviations caused by the omission of a single error term (such as compensating only for link loss while ignoring broadband signal phase distortion), making the EIRP calculation results more realistic. Secondly, the formula logic is strongly bound to its physical meaning, ensuring the calculation process is traceable and verifiable. The clear physical meaning avoids empirical estimation: each parameter in the formula corresponds to a clear physical scenario— It is the actual measured received power. It is the receiver gain, It is transmission loss, This is a link characteristic compensation formula. The calculation logic perfectly matches the physical process of "received power → restored transmit power" (received power = transmit EIRP - link loss - compensation term + receive gain, EIRP is derived by reverse derivation), rather than relying on vague empirical formulas. This ensures the calculation process has a clear physical basis, facilitating subsequent verification and reproduction. Parameters are quantifiable and traceable, improving the reliability of the results: all parameters in the formula are quantifiable known quantities or measured values. These are the calibration parameters for a standard gain antenna. and These are the measured and calculated values ​​from the link calibration phase. This data is sampled from a spectrum analyzer, and the source of each parameter can be traced through the original records (such as calibration reports and sampling logs). If it is necessary to verify the accuracy of EIRP results, the authenticity of each parameter can be verified in reverse, avoiding disputes caused by ambiguous parameters and greatly enhancing the authority of the test data.

[0100] Figure 5 This is a schematic diagram of the dynamic EIRP curve obtained by the equivalent isotropic radiated power test method of satellite carrier signal in the embodiments of this application. The horizontal axis is time (0~600s), and the vertical axis is EIRP value (51.83~53.81dBW). It simulates the EIRP values ​​obtained by testing the satellite at different trajectory points (corresponding to different times). The curve fluctuations reflect the changes in EIRP values ​​during the beam scanning process. Table 1 shows... Figure 5 Example of corresponding EIRP value.

[0101] Table 1

[0102]

[0103] In one embodiment, the control module is used to:

[0104] Analyze satellite ephemeris files to obtain the motion angles for controlling a multi-degree-of-freedom platform;

[0105] The multi-degree-of-freedom platform is controlled to move the satellite payload when it moves according to the stated motion angle.

[0106] In one embodiment, the control module is used to:

[0107] By analyzing the ephemeris file, the azimuth and elevation angles of the satellite relative to the test station over time are obtained according to the satellite's on-orbit trajectory.

[0108] Based on the aforementioned change curve, the motion angles of the control multi-degree-of-freedom platform are obtained.

[0109] In one embodiment, the calibration module is used for:

[0110] After the carrier signal passes through the standard satellite link, the broadband carrier signal test link compensation term is calculated based on the in-band amplitude unevenness and group delay of the satellite carrier signal.

[0111] In one embodiment, the calibration module is further configured to:

[0112] Calculate the amplitude calibration factor based on the in-band amplitude unevenness;

[0113] Calculate the phase calibration factor based on the group delay;

[0114] Calculate the integrated channel calibration coefficient based on the amplitude calibration factor and the phase calibration factor;

[0115] Calculate the broadband carrier signal test link compensation term based on the comprehensive channel calibration coefficient.

[0116] In one embodiment, the calibration module is further configured to:

[0117] The following formula is used to determine the in-band amplitude unevenness. Calculate the amplitude calibration factor : ;

[0118] The following formula is used, based on group delay. Calculate the phase calibration factor : ;

[0119] The integrated channel calibration coefficient is calculated using the following formula, based on the amplitude calibration factor and the phase calibration factor. : ;

[0120] The following formula is used to calculate the broadband carrier signal test link compensation term based on the integrated channel calibration coefficient: : .

[0121] In one embodiment, the calibration module is further configured to:

[0122] After the satellite carrier signal passes through the standard satellite link, the gain of the standard gain antenna and the link loss are obtained.

[0123] The calculation module is also used for:

[0124] Based on the in-band power value of the satellite carrier signal of the satellite payload at each trajectory point, the broadband carrier signal test link compensation term, the gain of the standard gain antenna, and the link loss, calculate the dynamic equivalent isotropic radiated power value of each trajectory point.

[0125] In one embodiment, the computing module is further configured to:

[0126] The dynamic equivalent isotropic radiated power value of each trajectory point is calculated using the following formula. :

[0127]

[0128] in, The in-band power value for each trajectory point, The gain of a standard gain antenna. For link loss, This is a link compensation item for broadband carrier signal testing.

[0129] In summary, the beneficial effects achieved by the method and apparatus proposed in the embodiments of this application are as follows:

[0130] I. Improve the accuracy of dynamic EIRP testing and eliminate link error interference.

[0131] Pre-calibration of link compensation terms: By establishing a standard satellite link through a standard gain antenna during the link calibration phase, the test link compensation terms for the broadband carrier signal are pre-calculated. This can accurately correct inherent errors such as loss, amplitude unevenness, and group delay of the test link itself, avoiding the superposition of errors into the dynamic EIRP calculation results of the satellite payload, and significantly improving the reliability of the measurement data.

[0132] Accurate trajectory point sampling and calculation: For each trajectory point during the satellite payload's motion, the in-band power value of the satellite carrier signal is collected separately and combined with the compensation term to calculate the dynamic EIRP. This can truly reflect the radiated power characteristics of the satellite under different motion attitudes, avoid local errors caused by overall estimation, and meet the requirements of high-precision testing.

[0133] II. The test results accurately reflect real-world satellite orbit scenarios and are relevant to practical applications.

[0134] Simulate on-orbit motion trajectory: By using a multi-degree-of-freedom platform to drive the satellite payload to move, the trajectory of the satellite's azimuth and pitch angle changes relative to the ground test station when it is in orbit is reproduced. This breaks through the limitation of traditional static testing that cannot simulate dynamic working conditions, and makes the test scenario highly consistent with the actual operating environment of the satellite.

[0135] Real-time beam tracking of the reflector: During the movement of the satellite payload, the beam is controlled to point to the compact field reflector in real time, ensuring the stability of the signal transmission path at each trajectory point and avoiding signal attenuation or loss due to beam offset. This truly restores the coordinated working state of the satellite's motion and beam adjustment when it is in orbit, and the test results can directly guide the optimization of the satellite's on-orbit performance.

[0136] Third, optimize the efficiency of the testing process, making it highly universal and operable.

[0137] The process is highly efficient and well-organized: "Link calibration" and "dynamic testing" are divided into two independent but interconnected stages. The standard link in the calibration stage can be reused (without the need for recalibration for each test), while the dynamic testing stage only needs to focus on the motion control and data acquisition of the satellite payload, reducing repetitive operations, shortening the overall testing cycle, and reducing manpower and time costs.

[0138] Universal applicability to multiple scenarios: The testing method does not depend on specific satellite payloads or compact field equipment. Through the angle adjustment and beam tracking mechanism of the multi-degree-of-freedom platform, it can be adapted to payload testing of S-band and other commonly used satellite operating frequency bands. At the same time, it supports the simulation of different satellite on-orbit trajectories (achieved by importing different ephemeris files), and is suitable for the dynamic EIRP testing needs of various low-Earth orbit and medium-Earth orbit satellites, with a wide range of applications.

[0139] IV. Reduce the complexity of the testing system, balancing technical feasibility and cost control.

[0140] There is no need to build a complex on-orbit test environment (such as a real-time communication link between the ground station and the on-orbit satellite). Dynamic scene simulation can be achieved simply by using a ground compact field, a multi-degree-of-freedom platform and a standard gain antenna. While ensuring test performance, the construction cost and operation and maintenance difficulty of the test system are greatly reduced, which makes it easy to promote and apply on a large scale in the laboratory environment.

[0141] This application also provides a computer device. Figure 6 This is a schematic diagram of a computer device in an embodiment of this application. The computer device 600 includes a memory 610, a processor 620, and a computer program 630 stored in the memory 610 and executable on the processor 620. When the processor 620 executes the computer program 630, it implements the above-mentioned method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0142] This application also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0143] This application also provides a computer program product, which includes a computer program that, when executed by a processor, implements the above-described method for testing the equivalent omnidirectional radiated power of satellite carrier signals.

[0144] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product embodied on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0145] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0146] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0147] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0148] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this application. It should be understood that the above descriptions are merely specific embodiments of this application and are not intended to limit the scope of protection of this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. A method of testing the equivalent isotropically radiated power of a satellite carrier signal, characterized by, include: During the link calibration phase, the broadband carrier signal test link compensation term is calculated using a standard satellite link established through a standard gain antenna, a compacted field reflector, and a feed antenna. After the satellite carrier signal passes through the standard satellite link, the gain of the standard gain antenna and the link loss are obtained. The following formula is used to calculate the in-band amplitude unevenness of the satellite carrier signal after it passes through the standard satellite link. Calculate the amplitude calibration factor : The following formula is used, based on the group delay of the satellite carrier signal. Calculate the phase calibration factor : The integrated channel calibration coefficient is calculated using the following formula, based on the amplitude calibration factor and the phase calibration factor. : The following formula is used to calculate the broadband carrier signal test link compensation term based on the integrated channel calibration coefficient. : ; During the satellite performance testing phase, the satellite payload is controlled to transmit satellite carrier signals, and a multi-degree-of-freedom platform is controlled to drive the satellite payload to move, so that the beam of the satellite carrier signal is pointed to the compact field reflector in real time during the movement of the satellite payload. After the satellite carrier signal reaches the feed antenna through the compacted field reflector, the dynamic equivalent isotropic radiated power value of each trajectory point is calculated based on the in-band power value of the satellite carrier signal at each trajectory point, the broadband carrier signal test link compensation term, the gain of the standard gain antenna, and the link loss.

2. The method as described in claim 1, characterized in that, The polarization type of the standard gain antenna, feed antenna, and satellite payload antenna is consistent.

3. The method as described in claim 1, characterized in that, The motion angles of a multi-degree-of-freedom platform include at least pitch angle, azimuth angle, polarization angle, and forward / backward translation angle.

4. The method as described in claim 1, characterized in that, The polarization axis ratio of the standard gain antenna to the feed antenna is less than the preset ratio.

5. The method as described in claim 1, characterized in that, Controlling the multi-degree-of-freedom platform to drive the movement of the satellite payload includes: Analyze satellite ephemeris files to obtain the motion angles for controlling a multi-degree-of-freedom platform; The multi-degree-of-freedom platform is controlled to move the satellite payload when it moves according to the stated motion angle.

6. The method as described in claim 5, characterized in that, Parse satellite ephemeris files to obtain the motion angles for controlling the multi-degree-of-freedom platform, including: By analyzing the ephemeris file, the azimuth and elevation angles of the satellite relative to the test station over time are obtained according to the satellite's on-orbit trajectory. Based on the aforementioned change curve, the motion angles of the control multi-degree-of-freedom platform are obtained.

7. The method as described in claim 1, characterized in that, The dynamic equivalent isotropic radiated power value of each trajectory point is calculated using the following formula. : in, The in-band power value for each trajectory point, The gain of a standard gain antenna. For link loss, This is a link compensation item for broadband carrier signal testing.

8. A device for testing the equivalent isotropic radiated power of a satellite carrier signal, characterized in that, include: The calibration module is used during the link calibration phase to calculate the test link compensation term for the broadband carrier signal using a standard satellite link established through a standard gain antenna, a compacted field reflector, and a feed antenna. After the satellite carrier signal passes through the standard satellite link, the gain of the standard gain antenna and the link loss are obtained. The following formula is used to calculate the in-band amplitude unevenness of the satellite carrier signal after it passes through the standard satellite link. Calculate the amplitude calibration factor : The following formula is used, based on the group delay of the satellite carrier signal. Calculate the phase calibration factor : The integrated channel calibration coefficient is calculated using the following formula, based on the amplitude calibration factor and the phase calibration factor. : The following formula is used to calculate the broadband carrier signal test link compensation term based on the integrated channel calibration coefficient: : ; The control module is used to control the satellite payload to transmit satellite carrier signals during the satellite performance testing phase, and to control the multi-degree-of-freedom platform to drive the satellite payload to move, so that the beam of the satellite carrier signal is pointed to the compact field reflector in real time during the movement of the satellite payload. The calculation module is used to calculate the dynamic equivalent isotropic radiated power value of each trajectory point after the satellite carrier signal reaches the feed antenna through the compacted field reflector, based on the in-band power value of the satellite carrier signal at each trajectory point, the broadband carrier signal test link compensation term, the gain of the standard gain antenna, and the link loss.

9. A system for testing the equivalent isotropic radiated power of a satellite carrier signal, characterized in that, include: The satellite carrier signal equivalent omnidirectional radiated power test device, multi-degree-of-freedom platform, satellite payload installed on the multi-degree-of-freedom platform, feed turntable, feed antenna installed on the feed turntable, compact field reflector, beamformer and spectrum analyzer as described in claim 8. The satellite carrier signal equivalent omnidirectional radiated power testing device is also used to: trigger the beamformer to adjust the beam pointing of the satellite carrier signal to the compact field reflector in real time during the movement of the satellite payload; The spectrum analyzer is used to: receive the satellite carrier signal arriving at the feed antenna and analyze the in-band power value of the satellite carrier signal.

10. The system as described in claim 9, characterized in that, It also includes a vector signal generator, a laser collimator, and a standard gain antenna mounted on a multi-degree-of-freedom platform; A vector signal generator is used to generate carrier signals and send them to a standard gain antenna; A laser collimator is used to adjust the standard gain antenna to align with the center of the compacted field reflector.

11. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method of any one of claims 1 to 7.

12. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the method of any one of claims 1 to 7.

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

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