Satellite beam control method and apparatus, storage medium and electronic device

Abstract

The embodiment of the application provides a satellite beam control method and device, a storage medium and an electronic device, wherein the method comprises the following steps: determining an electronic fence of a low-orbit satellite according to communication parameter information corresponding to each relative position information in a group of relative position information; in the case that a specified low-orbit satellite exists, adjusting the pointing direction of the beam of the specified low-orbit satellite, so that the beam of the specified low-orbit satellite points to the external area of the outer fence of the specified low-orbit satellite, wherein the specified low-orbit satellite is a low-orbit satellite indicated by the position information to enter the inner fence of the specified low-orbit satellite. Through the application, the problem that the fixed area range in the related art may cause an excessively large protection area and thus waste communication resources is solved, the communication quality between the low-orbit satellite and the low-orbit earth station thereof is ensured, interference to the high-orbit earth station is effectively avoided, and the resource utilization efficiency of the entire satellite system is improved.

Description

TECHNICAL FIELD

[0001] Embodiments of the present application relate to the technical field of satellite communication, in particular, to a satellite beam control method and device, a storage medium and an electronic device. BACKGROUND

[0002] In the current field of satellite communication, co-sites between low-orbit earth stations of low-orbit satellites and high-orbit earth stations of high-orbit satellites, due to the low-orbit characteristics of low-earth-orbit (LEO) satellites, the signals of the low-orbit satellites may unintentionally interfere with the communication of the high-orbit earth stations.

[0003] In the related art, a fixed area range is usually established with the high-orbit earth station as the center to control all low-orbit satellites in the satellite system to avoid entering the area range, thereby reducing the interference with the high-orbit earth station. However, this fixed area range method cannot effectively handle the relative changes and interference conditions between different low-orbit satellites and high-orbit earth stations. Especially when the low-orbit satellites are constantly moving, the fixed area range may result in an excessively large protection area, thereby wasting communication resources. SUMMARY

[0004] Embodiments of the present application provide a satellite beam control method and device, a storage medium and an electronic device to at least solve the technical problem that a fixed area range may result in an excessively large protection area, thereby wasting communication resources in the related art.

[0005] According to an aspect of embodiments of the present application, a satellite beam control method is provided, applied to a satellite system, a low-orbit earth station of a low-orbit satellite in the satellite system and a high-orbit earth station of a high-orbit satellite are located at the same geographical position, and the method comprises:

[0006] According to ephemeris data of the low-orbit satellite, a set of relative position information between the low-orbit satellite and the high-orbit earth station is obtained;

[0007] According to communication parameter information corresponding to each relative position information in the set of relative position information, an electronic fence of the low-orbit satellite is determined, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence is centered on the geographical position of the high-orbit earth station;

[0008] In the case where a specified low-orbit satellite exists, the pointing direction of the beam of the specified low-orbit satellite is adjusted to make the beam of the specified low-orbit satellite point to an outer region of the outer fence of the specified low-orbit satellite, wherein the specified low-orbit satellite is a low-orbit satellite whose position information indicates that it enters the inner fence of the specified low-orbit satellite.

[0009] According to another aspect of the embodiments of the present application, a satellite beam control device is also provided, which is applied to a satellite system, a low-orbit earth station of a low-orbit satellite in the satellite system is located at the same geographical position as a high-orbit earth station of a high-orbit satellite, and the device comprises:

[0010] an acquisition unit configured to acquire a set of relative position information between the low-orbit satellite and the high-orbit earth station according to ephemeris data of the low-orbit satellite;

[0011] a determination unit configured to determine an electronic fence of the low-orbit satellite according to communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence is centered at the geographical position of the high-orbit earth station;

[0012] an adjustment unit configured to, in a case where a specified low-orbit satellite exists, adjust a pointing direction of a beam of the specified low-orbit satellite so that the beam of the specified low-orbit satellite points to an outer region of the outer fence of the specified low-orbit satellite, wherein the specified low-orbit satellite is a low-orbit satellite whose position information indicates that the low-orbit satellite enters the inner fence of the specified low-orbit satellite.

[0013] In one example embodiment, the communication parameter information comprises a beam pointing angle; and the determination unit comprises:

[0014] a calculation module configured to calculate a set of signal index values according to the communication parameter information corresponding to each relative position information in the set of relative position information, wherein the set of signal index values comprises a signal index value corresponding to each relative position information;

[0015] a first determination module configured to determine the inner fence of the low-orbit satellite according to relative position information corresponding to a specified signal index value, wherein the specified signal index value is a signal index value closest to a first preset signal index value selected from the set of signal index values;

[0016] an adjustment module configured to adjust the beam pointing angle in the communication parameter information corresponding to a specified position information so that a signal index value corresponding to the specified position information is less than a second preset signal index value, wherein the specified position information is position information when the low-orbit satellite, the high-orbit satellite and the high-orbit earth station are collinear in the set of relative position information, and the first preset signal index value is greater than or equal to the second preset signal index value;

[0017] a second determination module configured to determine the outer fence of the low-orbit satellite according to a specified beam pointing angle, wherein the specified beam pointing angle is a beam pointing angle when the signal index value corresponding to the specified position information is less than the second preset signal index value.

[0018] In an example embodiment, the computing module is further configured to: input the communication parameter information corresponding to each relative position information into a preset index model, and output a set of index values corresponding to each relative position information; and perform weighted summation on the set of index values corresponding to each relative position information using a set of weight values to obtain a signal index value corresponding to each relative position information.

[0019] In an example embodiment, the first determining module is further configured to: calculate a specified subsatellite point of the low-orbit satellite according to the relative position information corresponding to the specified signal index value, wherein the specified subsatellite point is a position point of the low-orbit satellite projected onto a plane on which the high-orbit earth station is located at the relative position information corresponding to the specified signal index value; and determine a distance between the specified subsatellite point of the low-orbit satellite and the high-orbit earth station as a radius of an inner fence of the low-orbit satellite.

[0020] In an example embodiment, the first determining module is further configured to: in a case where there is an index value greater than a preset index threshold value in the set of index values corresponding to the specified signal index value, increase the radius of the inner fence of the low-orbit satellite.

[0021] In an example embodiment, the second determining module is further configured to: calculate a beam main axis landing point of the low-orbit satellite according to the altitude information of the low-orbit satellite and the specified beam pointing angle, wherein the beam main axis landing point is a projection point of a beam main axis of the low-orbit satellite on a plane on which the high-orbit earth station is located; and determine a distance between the beam main axis landing point of the low-orbit satellite and the high-orbit earth station as a radius of an outer fence of the low-orbit satellite.

[0022] In an example embodiment, the satellite beam control apparatus further includes:

[0023] a prediction unit configured to input specified ephemeris data of the low-orbit satellite into a pre-trained orbit dynamics model, and output predicted orbit state information of the low-orbit satellite;

[0024] an updating unit configured to, in a case where the predicted orbit state information indicates that an orbit altitude change value of the low-orbit satellite is greater than a preset altitude difference value, update the electronic fence of the low-orbit satellite.

[0025] According to another aspect of the embodiments of the present application, a computer readable storage medium is provided, and the computer readable storage medium stores a computer program. The computer program is configured to perform the steps in any of the method embodiments described above when executed by a processor.

[0026] According to a further aspect of the embodiments of the present application, a computer program product or computer program is provided, which comprises computer instructions stored in a computer readable storage medium. A processor of a computer device reads the computer instructions from the computer readable storage medium, and the processor executes the computer instructions to cause the computer device to perform the steps in any of the method embodiments described above.

[0027] According to a further aspect of the embodiments of the present application, an electronic device is also provided, which comprises a memory and a processor, wherein the memory stores a computer program, and the processor is configured to execute the steps in any of the method embodiments described above by using the computer program.

[0028] According to the embodiments of the present application, a set of relative position information between a low-orbit satellite and a high-orbit earth station is obtained according to ephemeris data of the low-orbit satellite; an electronic fence of the low-orbit satellite is determined according to communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence is centered at a geographical position of the high-orbit earth station; in the case that a specified low-orbit satellite exists, a pointing direction of a beam of the specified low-orbit satellite is adjusted so as to make the beam of the specified low-orbit satellite point to an outer region of the outer fence of the specified low-orbit satellite, which realizes dynamic adjustment of the electronic fence of the low-orbit satellite, avoids setting of an excessively large protection region, reduces resource waste, solves the problem that a fixed region range in the related art may cause an excessively large protection region, thereby wasting communication resources, and guarantees communication quality between the low-orbit satellite and the low-orbit earth station thereof, effectively avoids interference to the high earth station, and improves resource utilization efficiency of the entire satellite system. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is a flowchart of an optional satellite beam control method according to an embodiment of the present application.

[0030] Figure 2 is a schematic diagram of an optional satellite system according to an embodiment of the present application.

[0031] Figure 3 is a schematic diagram of an inner fence of an electronic fence according to an embodiment of the present application.

[0032] Figure 4 is a schematic diagram of an outer fence of an electronic fence according to an embodiment of the present application.

[0033] Figure 5 is a flowchart of another optional satellite beam control method according to an embodiment of the present application.

[0034] Figure 6is a structural block diagram of an optional satellite beam control device according to an embodiment of the present application.

[0035] Figure 7 is a computer system structural block diagram of an optional electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0036] In order to enable persons skilled in the art to better understand the scheme of the present application, the technical scheme in the embodiments of the present application will be clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by persons skilled in the art without creative labor should fall within the scope of protection of the present application.

[0037] It should be noted that the terms "first", "second", and the like in the specification and claims of the present application and the above-described drawings are used to distinguish similar objects, and do not necessarily have to describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device that includes a series of steps or units does not have to be limited to only those steps or units clearly listed, but can include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0038] According to an aspect of an embodiment of the present application, a satellite beam control method is provided. The method is applied to a satellite system, Figure 1 is a flowchart of an optional satellite beam control method according to an embodiment of the present application, as Figure 2 shown, the flow of the method can include the following steps:

[0039] Step S102, according to the ephemeris data of the low-orbit satellite, a set of relative position information between the low-orbit satellite and the high-orbit earth station is obtained;

[0040] Step S104, according to the communication parameter information corresponding to each relative position information in the set of relative position information, the electronic fence of the low-orbit satellite is determined, wherein the electronic fence includes an inner fence and an outer fence, and the electronic fence is centered on the geographical position of the high-orbit earth station;

[0041] Step S106, in the presence of a specified low-orbit satellite, adjusting the pointing direction of the beam of the specified low-orbit satellite so that the beam of the specified low-orbit satellite points to the outer region of the outer enclosure of the specified low-orbit satellite, wherein the specified low-orbit satellite indicates a low-orbit satellite entering the inner enclosure of the specified low-orbit satellite in the position information.

[0042] The satellite beam control method in the embodiment can be applied to the field of satellite communication, especially to the co-sited communication scenario of a Low Earth Orbit (LEO) satellite system and a Geostationary Earth Orbit (GEO) satellite system. In the co-sited communication scenario, the ground stations (LEO ground station and GEO ground station) of the LEO system and the GEO system are located at the same geographical position, but the rapid movement and lower orbit height of the LEO satellite can interfere with the GEO ground station below and affect the normal communication of the GEO satellite.

[0043] In the related art, a fixed area is usually established with the GEO ground station as the center to control all LEO satellites in the satellite system to avoid entering the area range, thereby reducing the interference with the GEO ground station. However, this fixed area method cannot effectively handle the relative changes and interference conditions between different LEO satellites and GEO ground stations. Especially when the orbit parameters and communication environment of the LEO satellite are constantly changing, the fixed area can result in an excessively large protection area, thereby wasting communication resources. Therefore, the fixed area range in the related art can result in an excessively large protection area, thereby wasting communication resources.

[0044] To at least partially solve the above technical problems, in the embodiment, a set of relative position information between the LEO satellite and the GEO ground station is obtained according to the ephemeris data of the LEO satellite; an electronic fence of the LEO satellite is determined according to the communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence includes an inner enclosure and an outer enclosure, and in the presence of a specified LEO satellite, the pointing direction of the beam of the specified LEO satellite is adjusted so that the beam of the specified LEO satellite points to the outer region of the outer enclosure of the specified LEO satellite, which realizes dynamic adjustment of the electronic fence of the LEO satellite, avoids excessively large protection area setting, reduces resource waste, solves the problem of excessively large protection area caused by the fixed area range in the related art, thereby wasting communication resources, guarantees the communication quality between the LEO satellite and its LEO ground station, effectively avoids interference with the GEO ground station, and improves the resource utilization efficiency of the entire satellite system.

[0045] It should be noted that the satellite system includes a group of low-orbit satellites, a group of high-orbit satellites, a low-orbit earth station, and a high-orbit earth station. Among them, the low-orbit earth station can be an earth station of a group of low-orbit satellites, and the high-orbit earth station can be an earth station of a group of high-orbit satellites. The low-orbit earth station of the low-orbit satellite and the high-orbit earth station of the high-orbit satellite are located at the same geographical position, that is, the co-site between the low-orbit earth station of the low-orbit satellite and the high-orbit earth station of the high-orbit satellite. Generally, the high-orbit satellite in the satellite system is generally deployed in the geostationary orbit (GEO), and the orbit inclination i = 0° and the eccentricity e ≈ 0. The pointing accuracy and the earth station accuracy are consistent, and the high-orbit satellite is always located in the zenith direction of the high-orbit earth station.

[0046] The ephemeris data of the low-orbit satellite is time series data about the satellite position and motion state of the low-orbit satellite. The ephemeris data of the low-orbit satellite can describe the motion trajectory of the low-orbit satellite in space, and can include orbit parameters of the low-orbit satellite such as orbit height, eccentricity, inclination, etc., as well as instantaneous position information and velocity information, which can be recorded by the satellite operator and the ground monitoring station.

[0047] Optionally, according to the ephemeris data of the low-orbit satellite, the relative position information of the low-orbit satellite at a preset number of time points in the visible range of the earth station can be obtained. The relative position information refers to the geometric relationship between the low-orbit satellite and the high-orbit earth station, including but not limited to the distance, azimuth, elevation angle, etc. between the two, which is a key parameter for determining the interference degree and taking evasive measures.

[0048] Optionally, the communication parameter information corresponding to the relative position information can refer to the related parameters of the communication link characteristics between the low-orbit satellite and the high-orbit earth station at a specific relative position (i.e. this relative position information). These parameters directly reflect the quality of the communication link and the possible interference level.

[0049] Optionally, according to the relative position information between the low-orbit satellite and the high-orbit earth station, the communication parameter information corresponding to the relative position information can be directly or indirectly determined. The communication parameter information can include a plurality of different types of communication link characteristic parameters. The plurality of different types of communication link characteristic parameters can include but are not limited to: transmit power, antenna gain, path loss, thermal noise power, etc. Among them, the transmit power can be the power of the transmitted signal of the low-orbit satellite, which can be dynamically adjusted as the distance between the low-orbit satellite and the high-orbit earth station increases or decreases to ensure communication quality or reduce interference. The antenna gain can refer to the signal strength enhancement ratio of the satellite antenna of the low-orbit satellite in the beam pointing direction. As the relative position of the low-orbit satellite and the high-orbit earth station changes, the antenna gain also needs to be adjusted accordingly. The path loss can be the strength of the signal reduced due to factors such as distance and atmospheric influence during the propagation of the signal from the low-orbit satellite to the ground station. The path loss is closely related to the distance between the low-orbit satellite and the high-orbit earth station.

[0050] Optionally, during the operation of the low-orbit satellite, a preset communication parameter calculation formula can be used to calculate the communication parameter information corresponding to different positions during the operation and record it to evaluate the communication quality of the low-orbit satellite. Specifically, a sampling period can be set to record the communication parameter information of each sampling point according to the sampling period.

[0051] Optionally, during the operation of the low-orbit satellite, the default beam of the low-orbit satellite can generally always point to a specified direction. For example, the beam of the low-orbit satellite can point to the earth station corresponding to the low-orbit satellite.

[0052] Optionally, the electronic fence can be a virtual protection area that can be used to limit the coverage range of the beam of the low-orbit satellite to prevent interference with a specific area on the ground or other satellite systems. The electronic fence is divided into an inner fence and an outer fence. For each low-orbit satellite, there is an electronic fence corresponding to it, which can be adaptively adjusted according to the relative position information between the low-orbit satellite and the high-orbit earth station and the communication parameter information corresponding to the relative position information. The communication parameter information corresponding to the relative position information is used to indicate the communication link characteristics between the low-orbit satellite and the high-orbit earth station under the relative position information.

[0053] The electronic fence is centered on the geographical position of the high-orbit earth station and is divided into an inner fence and an outer fence. Optionally, the inner fence can be a boundary for interference determination, and once the LEO satellite beam touches or enters this area, the beam switching mechanism will be automatically triggered to avoid direct interference with the GEO earth station. The outer fence can be a safety boundary that defines the pointing direction of the satellite beam after beam switching, ensuring that the communication activities of the LEO satellite do not pose a threat to the GEO earth station, while leaving room for the beam to directly point to the GEO earth station.

[0054] The designated LEO satellite can be a LEO satellite that has entered or is about to enter the inner fence of the electronic fence. The outer region of the outer fence of the designated LEO satellite can be a region outside the outer fence of the electronic fence, a region to which the LEO satellite beam can be safely directed, and which does not interfere with or affect the communication quality of the GEO earth station. Of course, in specific practice, the LEO satellite beam can also be directly controlled to point to the region of the outer fence of the electronic fence.

[0055] Optionally, adjusting the pointing direction of the beam of the designated LEO satellite can be controlled by the LEO satellite by changing the direction of the antenna beam, and the adjustment mode can be achieved by mechanical movement or electronic control of the antenna.

[0056] According to the embodiments provided in the present application, a set of relative position information between the LEO satellite and the GEO earth station is obtained according to the ephemeris data of the LEO satellite; and an electronic fence of the LEO satellite is determined according to the communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence includes an inner fence and an outer fence, and the electronic fence is centered on the geographical position of the GEO earth station. In the case of a designated LEO satellite, the pointing direction of the beam of the designated LEO satellite is adjusted so that the beam of the designated LEO satellite points to the outer region of the outer fence of the designated LEO satellite. This realizes dynamic adjustment of the electronic fence of the LEO satellite, avoids excessive setting of the protection region, reduces resource waste, solves the problem in the related art that a fixed region range can result in an excessively large protection region, thereby wasting communication resources, and guarantees the communication quality between the LEO satellite and its LEO earth station, effectively avoids interference with the GEO earth station, and improves the resource utilization efficiency of the entire satellite system.

[0057] In an example embodiment, the communication parameter information comprises a beam pointing angle; and determining the electronic fence of the low earth orbit satellite according to the communication parameter information corresponding to each of the set of relative position information comprises: calculating a set of signal indicator values according to the communication parameter information corresponding to each of the set of relative position information, wherein the set of signal indicator values comprises a signal indicator value corresponding to each of the set of relative position information; determining an inner fence of the low earth orbit satellite according to relative position information corresponding to a specified signal indicator value, wherein the specified signal indicator value is a signal indicator value closest to a first preset signal indicator value selected from the set of signal indicator values; adjusting the beam pointing angle in the communication parameter information corresponding to a specified position information, so that a signal indicator value corresponding to the specified position information is less than a second preset signal indicator value, wherein the specified position information is position information when the low earth orbit satellite, the high earth orbit satellite and the high earth orbit station are collinear in the set of relative position information, and the first preset signal indicator value is greater than or equal to the second preset signal indicator value; and determining an outer fence of the low earth orbit satellite according to a specified beam pointing angle, wherein the specified beam pointing angle is a beam pointing angle when the signal indicator value corresponding to the specified position information is less than the second preset signal indicator value.

[0058] It should be noted that the relative position information can be used to describe the geometric position information of the low earth orbit satellite relative to the high earth orbit station, and can include but is not limited to distance, azimuth angle, elevation angle, etc. The communication parameter information can include but is not limited to transmit power, antenna gain, beam pointing angle and free space loss. The beam pointing angle can refer to the pointing angle of the antenna beam of the low earth orbit satellite relative to a specific coordinate system (such as the Earth-Centered Inertial frame (ECI)), which determines the spatial range covered by the beam and directly affects the communication quality and interference level between the LEO satellite and the GEO earth station.

[0059] The specified signal indicator value can be a threshold signal indicator selected from the set of calculated signal indicator values for determining whether the beam of the low earth orbit satellite is close to the high earth orbit station. The value is closest to the first preset signal indicator value, which is used to determine the boundary of the inner fence. The first preset signal indicator value and the second preset signal indicator value can be preset signal indicator thresholds, which can be used to define the boundary of the electronic fence and the switching condition of the beam direction. The first preset signal indicator value and the second preset signal indicator value can be determined based on the standard of the tolerance of interference in the satellite communication system. For example, -12.2 dB. Alternatively, the first preset signal indicator value and the second preset signal indicator value can be determined according to the working frequency band of the low earth orbit satellite. Specifically, by monitoring the influence of signal indicator values at different working frequency bands on actual interference, the first preset signal indicator value and the second preset signal indicator value are determined. For each working frequency band, the first preset signal indicator value and the second preset signal indicator value can be set respectively.

[0060] Optionally, based on a set of relative position information, the signal indicator value between the low-orbit satellite and the high-orbit earth station under each relative position information can be calculated. Specifically, by monitoring the orbit data of the low-orbit satellite, the position information of the high-orbit earth station and the communication parameter information in real time, the signal indicator value under the relative position information is calculated by using mathematical model and algorithm.

[0061] From the calculated set of signal indicator values, the value closest to the first preset signal indicator value is selected, and the relative position information corresponding to the value defines the boundary of the inner fence.

[0062] In an example, for example, the relative position of the low-orbit satellite A and the high-orbit earth station changes at different time points, obtaining a set of relative position information, according to the set of relative position information and the communication parameter information (such as the transmission power, the antenna gain, the path loss, etc.), the signal indicator value under each relative position information is calculated, in order to select the relative position information corresponding to the value closest to the first preset signal indicator value, to determine the inner fence. Assuming that the first preset signal indicator value is set to -12.0 dB (I / N value), the system selects the value closest to -12.0 dB from the calculated signal indicator value as the specified signal indicator value, for example -12.2 dB, and the distance and angle information between the low-orbit satellite and the high-orbit earth station corresponding to the value defines the boundary of the inner fence. This means that when the relative position of the low-orbit satellite A and the high-orbit earth station causes I / N to reach -12.2 dB, the beam switching mechanism will be triggered to avoid further approaching the high-orbit earth station causing interference.

[0063] Optionally, as shown in Figure 2 , Figure 2 is a schematic diagram of an optional satellite system according to an embodiment of the present application, in Figure 2 , the low-orbit earth station and the high-orbit earth station in the satellite system are co-located (so Figure 2 , the high-orbit satellite in the satellite system is generally deployed in the geostationary orbit (GEO), and its orbit inclination i = 0°, eccentricity e ≈ 0, fixed point longitude consistent with the earth station, to ensure that the high-orbit satellite is always located in the zenith direction of the high-orbit earth station. When the low-orbit satellite runs in the low-orbit orbit, the relative position information between the low-orbit satellite and the high-orbit earth station can include the relative angle Figure 2 in and , and the signal indicator value corresponding to the relative position information is calculated, in order to select the relative position information corresponding to the signal indicator value closest to the first preset signal indicator value, to determine the inner fence of the electronic fence of the low-orbit satellite.

[0064] To ensure that the interference remains within the safe range even in the most adverse conditions, a specified position information can be set, which is the position information when the low-orbit satellite, the high-orbit satellite, and the high-orbit earth station are collinear. In the case where the signal index value corresponding to the specified position information does not satisfy the preset condition, i.e., is not less than the second preset signal index value, the beam pointing angle at the specified position information is adjusted to obtain a specified beam pointing angle, thereby determining the outer fence of the electronic fence of the low-orbit satellite.

[0065] Optionally, in the process of adjusting the beam pointing angle at the specified position information, the beam pointing angle corresponding to the signal index value closest to the second preset signal index value and less than the second preset signal index value can be selected as the specified beam pointing angle, so as to determine the outer fence of the low-orbit satellite according to the specified beam pointing angle.

[0066] Optionally, in the process of adjusting the beam pointing angle in the collinear case, if the signal index value is still higher than the second preset signal index value. At this time, the pointing flexibility of the antenna beam can be considered to be increased, and a multi-beam switching, a smart antenna array, or the like is adopted to further reduce the signal index value and ensure the communication safety in the collinear case. For example, in addition to offsetting the beam by 5°, a more complex beam shape can be formed by dynamically adjusting the element phase in the antenna array, so as to achieve the target of being lower than the second preset signal index value at the specified position information.

[0067] Through the embodiment, by adjusting the beam pointing angle in real time to ensure that the signal index value is less than the second preset signal index value, the boundary of the electronic fence can be accurately calculated and dynamically adjusted, and the accuracy and flexibility of the interference avoidance of the low-orbit satellite when approaching the high-orbit earth station are significantly improved. Moreover, through the reasonable design of the outer fence, unnecessary beam switching and adjustment are avoided, resource waste is reduced, and communication efficiency is improved.

[0068] In one example embodiment, a set of signal index values is calculated according to the communication parameter information corresponding to each relative position information in a set of relative position information, including: inputting the communication parameter information corresponding to each relative position information into a preset index model to output a set of index values corresponding to each relative position information; and performing weighted summation on the set of index values corresponding to each relative position information using a set of weight values to obtain a signal index value corresponding to each relative position information.

[0069] It should be noted that the preset index model can be a mathematical model for quantifying the communication link quality and the potential interference degree. A set of index values can be calculated based on the communication parameter information through a series of algorithms to evaluate the interference risk of the low-orbit satellite beam to the high-orbit earth station.

[0070] Optionally, the preset index model may include the interference-to-noise ratio (I / N), signal-to-noise ratio (SNR), bit error rate (BER), and carrier-to-interference-and-noise ratio (CNR). The calculation logic for metrics such as interference-to-noise ratio (I / N), signal-to-noise ratio (SNR), and bit error rate (BER) is explained. A set of metric values ​​may contain one or more values. When a set of metric values ​​contains only one value, it can be used for parameters such as interference-to-noise ratio (I / N), signal-to-noise ratio (SNR), and bit error rate (BER). Any one of these metrics, when there are multiple metric values ​​in a set, can be the interference-to-noise ratio (I / N), signal-to-noise ratio (SNR), or bit error rate (BER). At least one of the following.

[0071] Specifically, taking the interference signal-to-noise ratio as an example, the formula for calculating the interference signal-to-noise ratio can be as follows: (1)

[0072] (1)

[0073] in, For the interference-to-noise ratio, Transmission power refers to the energy level at which a satellite transmitter sends a signal to a ground station or another satellite. This indicates the antenna gain in the beam pointing direction, which is the direction of the antenna's maximum output signal strength. Generally, the beam pointing direction is towards the earth station by default. Free space loss refers to the degree of natural attenuation of a signal as it travels from the transmitter to the receiver in an ideal, open environment due to increased distance. KTB represents thermal noise power, which is the noise power calculated based on the Boltzmann constant (K), system temperature (T), and bandwidth (B). This represents the gain corresponding to the relative position information.

[0074] Optionally, an antenna gain table can be used, which records a set of antenna gains and a set of relative position information to record the gain corresponding to each relative position. During the operation of the low-Earth orbit (LEO) satellite, the real-time position information between the LEO satellite and the earth station is acquired to obtain the relative position information of the LEO satellite. Based on the parameters corresponding to the relative position information, the corresponding antenna gain value can be queried.

[0075] Alternatively, the value of each weight in a set of weights can be assigned based on the entropy weighting method, as shown in formula (2):

[0076] (2)

[0077] wherein, is a signal index value; , , and is a set of weight values, which can be dynamically adjusted according to the characteristics of the operating frequency band of the low-orbit satellite and the service priority.

[0078] Optionally, the I / N value, SNR dynamic range, BER statistical curve, CINR fluctuation threshold and spectral energy distribution characteristics of the target frequency band can be monitored in real time to establish a time series monitoring database, so as to obtain the communication parameter information recorded in the time series monitoring database according to the time point corresponding to the relative position information of the low-orbit satellite in the ephemeris data.

[0079] Similarly, taking the interference signal-to-noise ratio as an example, the calculation process of the specified beam pointing angle can be shown in formula (3):

[0080] (3)

[0081] wherein, is a beam pointing angle, is the corresponding when the high-orbit satellite, the low-orbit satellite and the high-orbit earth station are collinear. The antenna gain is 0. At this time, by adjusting , so that is less than a second preset signal index value, the specified beam pointing angle is obtained.

[0082] Similarly, can also be determined by another gain table. Different beam pointing angles correspond to different adjustment gain values, and the gain table is established based on the antenna directional diagram and specific design parameters. The gain values of the antenna at different beam deviation angles are recorded through simulation software or actual test. During the operation of the low-orbit satellite, the size of is determined according to the beam deviation angle.

[0083] In an example, it is assumed that at a certain moment, the relative position information between the LEO satellite and the GEO earth station is a distance of 4000 kilometers, an azimuth angle of 30 degrees and a pitch angle of 45 degrees; the corresponding communication parameter information is: LEO satellite transmitting power 20dBW, antenna gain 15dBi, GEO receiving antenna gain 10dBi, free space loss 150dB, signal bandwidth 20MHz. After inputting these information into the preset index model, the obtained I / N is -13dB, the SNR is 12dB, and the BER is In practice, the BER value can be converted and processed to calculate the signal indicator value.

[0084] This embodiment, by integrating and evaluating multiple signal indicators, provides a more comprehensive understanding of the satellite communication link status, rather than relying solely on a single indicator. This helps avoid global communication interruptions caused by poor local signal quality. Furthermore, it allows for the rational allocation of beam resources, avoiding unnecessary beam pointing adjustments and electronic fence expansion, thereby improving the efficiency of communication resource utilization between LEO satellites and GEO earth stations.

[0085] In an exemplary embodiment, determining the inner perimeter fence of a low-Earth orbit (LEO) satellite based on the relative position information corresponding to a specified signal index value includes: calculating a specified nadir point of the LEO satellite based on the relative position information corresponding to the specified signal index value, wherein the specified nadir point is the position point of the LEO satellite projected onto the plane where the high-Earth orbit (HEO) earth station is located under the relative position information corresponding to the specified signal index value; and determining the distance between the specified nadir point of the LEO satellite and the HEO earth station as the radius of the inner perimeter fence of the LEO satellite.

[0086] It should be noted that the specified signal index value is the signal index value closest to the first preset signal index value. The specified nadir point can be the intersection of the LEO satellite beam and the plane where the GEO earth station is located when the LEO satellite reaches the specified signal index value. This point is the boundary position where the LEO satellite beam may cause interference to the GEO earth station.

[0087] Optionally, a designated nadir point for the LEO satellite can be calculated using a pre-defined computational model (e.g., a geometric model). After determining the designated nadir point, the distance between this point and the GEO earth station can be used to determine the radius of the inner perimeter fence for the LEO satellite. This ensures that when the LEO satellite approaches or enters the inner perimeter fence, beam adjustment or switching strategies can be initiated promptly to avoid interference with the GEO earth station. Specifically, such as... Figure 3 As shown, in Figure 3 In the process, the angle indicated in the relative position information corresponding to the specified signal index value is determined as... The distance from the designated nadir point of the low-orbit satellite to the earth station is... This refers to the radius of the inner perimeter of a low-Earth orbit satellite. This can be called the threshold off-axis angle of the earth station receiving antenna. Based on the orbital parameters of the low-Earth orbit satellite and the threshold off-axis angle of the earth station receiving antenna, the intersection point on the corresponding orbit can be determined.

[0088] Optionally, according to the coordinate information of the specified subsatellite point, in combination with the coordinate position of the high-orbit earth station, the distance between the two points is accurately calculated to determine the radius of the inner fence of the low-orbit satellite. By determining the radius of the inner fence, the system can set a clear boundary. If the LEO satellite approaches this boundary during communication, it will react in advance to adjust the beam pointing direction to ensure the safety of the GEO earth station communication is not affected. At the same time, this also provides a basis for the next beam switching mechanism, that is, when the subsatellite point of the LEO satellite enters the inner fence, the system will automatically perform beam switching to avoid interference.

[0089] Through this embodiment, by calculating the specified subsatellite point and determining the radius of the inner fence, the interference boundary can be accurately determined. When the LEO satellite approaches or enters this range, measures are immediately taken to adjust the beam to avoid interfering with the GEO earth station, thereby improving the accuracy of interference avoidance. By determining the radius of the inner fence, the strategy of overprotection is avoided, unnecessary beam adjustment is reduced, and the utilization efficiency of the communication resources of the LEO satellite is optimized.

[0090] In one example embodiment, the above method further comprises: in the case that there is an index value greater than the preset index threshold value in the group of index values corresponding to the specified signal index value, increasing the radius of the inner fence of the low-orbit satellite.

[0091] It should be noted that the group of index values corresponding to the specified signal index value can include but is not limited to I / N, SNR (signal-to-noise ratio), BER (bit error rate), etc., for comprehensive evaluation of the state of the current communication link. The preset index threshold value is a limit value set for each signal index, which is used to determine whether the quality of the current communication link or the interference risk is within an acceptable range. If the signal index value between the low-orbit satellite and the high-orbit earth station exceeds these threshold values, it indicates that the current beam pointing direction may have potential interference risks.

[0092] When a certain index value between the low-orbit satellite and the high-orbit earth station exceeds the preset index threshold value, the radius of the inner fence of the low-orbit satellite is dynamically increased to expand the activation range of the beam switching mechanism and strengthen the protection of the high-orbit earth station. Optionally, an adjustment curve corresponding to each index value can be set in advance. The adjustment curve can record the difference between the index value and its corresponding preset index threshold value and the proportion of the radius adjustment amplitude, so as to determine the adjustment amplitude of the radius of the inner fence in the case that the index value is greater than the corresponding preset index threshold value, thereby increasing the radius of the inner fence of the low-orbit satellite.

[0093] In specific practice, in the case where the number of index values is multiple, different interference early warnings can be set, for example, a threshold value corresponding to each index value is set, and a threshold value of the comprehensive signal index value, when a single index value exceeds the threshold value, a primary early warning can be triggered, when the comprehensive signal index value is lower than the threshold value of the comprehensive signal index value, a middle early warning is triggered, and the like. Different levels of early warnings can take different early warning response measures. For example, a avoidance strategy library is set to determine the response measures corresponding to different types of early warnings from the avoidance strategy library, when SNR drops sharply accompanied by CINR degradation, the beam pointing angle is adjusted in priority (step precision ≤ 0.1°) during the operation of the low-orbit satellite; when the BER continuously exceeds the standard and the comprehensive signal index value is lower than the threshold, a coordinated scheme of antenna gain adaptive tuning (for example, dynamic adjustment range ≥ 15 dB) and electronic fence boundary expansion (the maximum expansion radius can reach 120% of the preset value) is adopted, of course, Kalman filtering can also be introduced to predict the interference motion trajectory to optimize the fence shape parameters.

[0094] Through the embodiment, by dynamically adjusting the radius of the inner circle fence, the protection area can be timely expanded according to the real-time monitored signal index value change, and the interference risk of the LEO satellite to the GEO earth station is effectively reduced.

[0095] In one example embodiment, according to the specified beam pointing angle, the outer circle fence of the low-orbit satellite is determined, including: according to the height information of the low-orbit satellite and the specified beam pointing angle, the beam main axis landing point of the low-orbit satellite is calculated, wherein the beam main axis landing point is the projection point of the beam main axis of the low-orbit satellite on the plane where the high-orbit earth station is located; the distance between the beam main axis landing point of the low-orbit satellite and the high-orbit earth station is determined as the radius of the outer circle fence of the low-orbit satellite.

[0096] It should be noted that the height information of the low-orbit satellite can be the vertical height of the low-orbit satellite from the earth's surface, which is a dynamically changing value and depends on its orbit characteristics. The specified beam pointing angle is determined by adjusting the beam pointing angle corresponding to the specified position information. Specifically, in the case where the signal index value corresponding to the specified position information is not less than the second preset signal index value, the beam pointing angle under the specified position information is adjusted to obtain the specified beam pointing angle, thereby determining the outer circle fence of the electronic fence of the low-orbit satellite.

[0097] The beam main axis landing point can refer to the projection point of the main axis (i.e. the maximum radiation direction) of the antenna beam of the low-orbit satellite on the plane where the high-orbit earth station is located. The plane where the high-orbit earth station is located can be a plane perpendicular to the line connecting the high-orbit earth station and the high-orbit satellite, as shown in Figure 4 The earth station, the low-orbit satellite and the high-orbit satellite are collinear, wherein the specified beam pointing angle is , and the angle is 90 degrees; the altitude information of the low-orbit satellite is denoted by h, the distance between the beam principal axis falling point of the low-orbit satellite and the high-orbit earth station, i.e., the radius of the outer fence of the low-orbit satellite.

[0098] Optionally, according to the altitude information of the low-orbit satellite and the specified beam pointing angle, the radius of the outer fence of the low-orbit satellite is calculated using a trigonometric formula. Specifically, the trigonometric formula can be as shown in formula (4):

[0099] (4)

[0100] wherein, the specified beam pointing angle, the altitude information of the low-orbit satellite, the radius of the outer fence of the low-orbit satellite.

[0101] Through the embodiment, the beam principal axis falling point is accurately calculated according to the altitude information of the low-orbit satellite and the specified beam pointing angle, a more accurate and flexible outer fence radius can be set to adapt to the interference avoidance requirements under different low-orbit satellite orbit characteristics and communication environments. The dynamic adjustment mechanism of the outer fence can better adapt to the changes in the orbit altitude of the low-orbit satellite, and improve the adaptability and robustness of the system in complex environments.

[0102] In an example embodiment, the above method further comprises: inputting the specified ephemeris data of the low-orbit satellite into a pre-trained orbit dynamics model to output predicted orbit state information of the low-orbit satellite; and updating the electronic fence of the low-orbit satellite in a case where the predicted orbit state information indicates that the orbit altitude change value of the low-orbit satellite is greater than a preset altitude difference value.

[0103] It should be noted that the specified ephemeris data can refer to the accurate orbit parameter information of the low-orbit satellite at a specific time point, including but not limited to position, velocity, orbit inclination, ascending node right ascension, perigee angular distance, orbit period, etc., for describing the actual orbit state of the satellite. For example, the specified ephemeris data can be ephemeris data of a preset time period before the current time.

[0104] The orbit dynamics model is a mathematical model that can predict the motion state of the low-orbit satellite in orbit, including the changes in position and velocity, and the long-term evolution of orbit parameters, through numerical simulation or analytical methods. The model can consider the influence of the earth's gravitational field, the gravity of the sun and the moon, atmospheric drag, solar radiation pressure, etc. on the orbit state of the satellite.

[0105] To determine whether the change in the orbital height of the low earth orbit satellite reaches the level that requires adjustment of the corresponding electronic fence, a threshold value, i.e., a preset height difference value, can be set. When the predicted change in the orbital height of the LEO satellite exceeds the threshold value, the system will update the settings of the electronic fence to adapt to the new orbital conditions.

[0106] In one example, the specified ephemeris data (e.g., position coordinates, velocity vector, etc.) of the LEO satellite is input into a pre-trained orbital dynamics model. Based on the input ephemeris data and the laws of dynamics, the orbital dynamics model outputs the predicted orbital state information of the LEO satellite for a future period of time, including position, velocity, and change in orbital height. In the case where the change in the orbital height is greater than the preset height threshold, the radii of the inner and outer fences are recalculated. Specifically, the radii of the inner and outer fences can be recalculated based on the predicted orbital state information of the LEO satellite.

[0107] Through this embodiment, by dynamically monitoring the orbital state of the LEO satellite and updating the electronic fence when the change in the orbital height is significant, the randomness and variability of the LEO satellite orbit can be better adapted, and the precision and flexibility of interference avoidance are improved. The electronic fence update based on LEO satellite orbit prediction can make the decision of beam adjustment or switching more reasonable, avoid unnecessary resource waste, and improve the communication efficiency between LEO satellites and GEO earth stations.

[0108] Figure 5 is a flowchart of the satellite beam control method in this optional example, as shown in Figure 5 The flow of the satellite beam control method can include the following steps:

[0109] Step 1, input the position of the earth station.

[0110] Specifically, the high-orbit earth station is co-located with the low-orbit earth station, so it is simply referred to as the earth station. The position information of the earth station includes latitude and longitude coordinates and altitude.

[0111] Step 2, import ephemeris to obtain the positions of low earth orbit satellites within the visible range of the earth station;

[0112] Specifically, the ephemeris data of the LEO satellite is obtained from the satellite operation center or control platform, which can include the position, velocity, and orbital parameters of the low earth orbit satellite at the time point within the visible range of the earth station.

[0113] Step 3, determine Imax1;

[0114] Specifically, by calculating the signal indicator value corresponding to each relative position information, the signal indicator value closest to the first preset signal indicator value is selected from the set of signal indicator values. Imax1 is the signal indicator value closest to the first preset signal indicator value from the set of signal indicator values, i.e. the designated signal indicator value.

[0115] Step 4, solving ;

[0116] Specifically, according to Imax1, it is determined that . Wherein, the relative position information corresponding to the designated signal indicator value is determined.

[0117] Step 5, determining the inner circle radius R1;

[0118] Step 6, determining Imax2;

[0119] Specifically, the beam pointing angle in the communication parameter information corresponding to the designated position information is adjusted so that the signal indicator value corresponding to the designated position information is less than the second preset signal indicator value, wherein the designated position information is the position information when the low-orbit satellite, the high-orbit satellite and the high-orbit earth station are collinear in the set of relative position information.

[0120] Step 7: solving ;

[0121] Specifically, the designated beam pointing angle is the beam pointing angle when the signal indicator value corresponding to the designated position information is less than the second preset signal indicator value.

[0122] Step 8, determining the outer circle radius R2.

[0123] Specifically, according to the height information of the low-orbit satellite and the designated beam pointing angle, the beam main axis landing point of the low-orbit satellite is calculated, and the distance between the beam main axis landing point of the low-orbit satellite and the high-orbit earth station is determined as the radius of the outer fence of the low-orbit satellite.

[0124] Step 9, determining the electronic fence range.

[0125] Step 10, judging whether the sub-satellite point position of the low-orbit satellite enters the inner circle range of the fence;

[0126] Specifically, by monitoring the sub-satellite point position of the LEO satellite, it is judged whether it is close to the inner circle electronic fence; in the case that the sub-satellite point position of the low-orbit satellite enters the inner circle range of the fence, jump to step 11.

[0127] Step 11, switching the low-orbit satellite beam pointing to the outer edge of the circle and the point outside the circle to avoid interference.

[0128] Specifically, the communication parameters and relative position information between the low-orbit satellite and the high-orbit earth station can also be predicted by a pre-trained beam adjustment model to predict the beam amplitude that needs to be adjusted in advance to perform beam adjustment. Alternatively, the pre-trained beam adjustment model can learn the interference characteristics between the low-orbit satellite and the high-orbit earth station through historical data to predict the interference. By introducing an intelligent interference prediction mechanism, the occurrence of interference events can be more accurately predicted, and preventive measures can be taken in advance to improve the response speed and accuracy of avoidance.

[0129] Through this optional example, by dynamically monitoring the real-time position information of the low-orbit satellite and combining the preset signal index threshold, it can be accurately determined when the LEO satellite poses a real threat to the GEO earth station. By adjusting the range of the electronic fence in real time, the beam switching mechanism is activated when necessary, and resource waste caused by overprotection is avoided. This dynamic adjustment strategy based on real-time data can effectively avoid interference while ensuring the communication efficiency of the LEO satellite is not affected.

[0130] It should be noted that for the foregoing method embodiments, in order to simply describe, they are all expressed as a series of action combinations, but those skilled in the art should know that the present application is not limited by the order of the described actions, because according to the present application, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the present application.

[0131] From the above description of the embodiments, those skilled in the art can clearly understand that the method according to the above embodiments can be realized by means of software and the necessary general hardware platform, and of course it can also be realized by hardware, but in many cases the former is a better implementation. Based on such understanding, the technical solutions of the present application can be embodied in the form of a software product in essence or in the form of a software product that contributes to the prior art. The computer software product is stored in a storage medium (such as a read-only memory (ROM) / random access memory (RAM), a magnetic disk, an optical disk), and includes a number of instructions for causing an end device (which can be a mobile phone, a computer, a server, or a network device, etc.) to execute the methods described in each embodiment of the present application.

[0132] According to another aspect of the embodiments of the present application, a satellite beam control apparatus is also provided, which can be used to implement the satellite beam control method provided in the above-described embodiments, and will not be described again. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the apparatus described in the following embodiments is preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.

[0133] Figure 6 is a structural block diagram of an optional satellite beam control apparatus according to an embodiment of the present application, as shown in Figure 6 The satellite beam control apparatus comprises:

[0134] An acquisition unit 602 is configured to acquire a set of relative position information between a low-orbit satellite and a high-orbit earth station according to ephemeris data of the low-orbit satellite.

[0135] A determination unit 604 is configured to determine an electronic fence of the low-orbit satellite according to communication parameter information corresponding to each of the set of relative position information, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence is centered at a geographical position of the high-orbit earth station.

[0136] An adjustment unit 606 is configured to, in a case where there is a designated low-orbit satellite, adjust a pointing direction of a beam of the designated low-orbit satellite so as to make the beam of the designated low-orbit satellite point to an outer region of the outer fence of the designated low-orbit satellite, wherein the designated low-orbit satellite is a low-orbit satellite indicated by the position information to enter the inner fence of the designated low-orbit satellite.

[0137] It should be noted that the acquisition unit 602 in this embodiment can be configured to perform the above step S102, the determination unit 604 in this embodiment can be configured to perform the above step S104, and the adjustment unit 606 in this embodiment can be configured to perform the above step S106.

[0138] According to the embodiments provided in the application, a set of relative position information between a low-orbit satellite and a high-orbit earth station is obtained according to ephemeris data of the low-orbit satellite; an electronic fence of the low-orbit satellite is determined according to communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence includes an inner fence and an outer fence, and the electronic fence is centered on the geographic position of the high-orbit earth station; in the case that a specified low-orbit satellite exists, the pointing direction of the beam of the specified low-orbit satellite is adjusted so that the beam of the specified low-orbit satellite points to an external region of the outer fence of the specified low-orbit satellite, which realizes dynamic adjustment of the electronic fence of the low-orbit satellite, avoids excessive setting of a protection region, reduces resource waste, solves the problem that a fixed region range in the related art may cause an excessively large protection region, thereby wasting communication resources, guarantees the communication quality between the low-orbit satellite and its low-orbit earth station, effectively avoids interference to the high-orbit earth station, and improves the resource utilization efficiency of the entire satellite system.

[0139] In an example embodiment, the communication parameter information includes a beam pointing angle; the determining unit 604 includes:

[0140] The computing module is configured to calculate a set of signal indicator values according to the communication parameter information corresponding to each relative position information in the set of relative position information, wherein the set of signal indicator values includes a signal indicator value corresponding to each relative position information.

[0141] The first determining module is configured to determine the inner fence of the low-orbit satellite according to the relative position information corresponding to the specified signal indicator value, wherein the specified signal indicator value is a signal indicator value closest to a first preset signal indicator value selected from the set of signal indicator values.

[0142] The adjusting module is configured to adjust the beam pointing angle in the communication parameter information corresponding to the specified position information, so that the signal indicator value corresponding to the specified position information is less than a second preset signal indicator value, wherein the specified position information is position information when the low-orbit satellite, the high-orbit satellite, and the high-orbit earth station are collinear in the set of relative position information, and the first preset signal indicator value is greater than or equal to the second preset signal indicator value.

[0143] The second determining module is configured to determine the outer fence of the low-orbit satellite according to the specified beam pointing angle, wherein the specified beam pointing angle is a beam pointing angle when the signal indicator value corresponding to the specified position information is less than the second preset signal indicator value.

[0144] In an example embodiment, the computing module is further configured to: input the communication parameter information corresponding to each relative position information into a preset indicator model to output a set of indicator values corresponding to each relative position information; and perform weighted summation on the set of indicator values corresponding to each relative position information using a set of weight values to obtain the signal indicator value corresponding to each relative position information.

[0145] In an example embodiment, the first determining module is further configured to: calculate a specified subsatellite point of the low-orbit satellite according to the relative position information corresponding to the specified signal indicator value, wherein the specified subsatellite point is a position point of the low-orbit satellite projected to a plane on which the high-orbit earth station is located under the relative position information corresponding to the specified signal indicator value; and determine a distance between the specified subsatellite point of the low-orbit satellite and the high-orbit earth station as a radius of an inner enclosure of the low-orbit satellite.

[0146] In an example embodiment, the first determining module is further configured to: in a case where there is an indicator value greater than a preset indicator threshold in the group of indicator values corresponding to the specified signal indicator value, increase the radius of the inner enclosure of the low-orbit satellite.

[0147] In an example embodiment, the second determining module is further configured to: calculate a beam main axis landing point of the low-orbit satellite according to the altitude information of the low-orbit satellite and the specified beam pointing angle, wherein the beam main axis landing point is a projection point of the beam main axis of the low-orbit satellite on the plane on which the high-orbit earth station is located; and determine a distance between the beam main axis landing point of the low-orbit satellite and the high-orbit earth station as a radius of an outer enclosure of the low-orbit satellite.

[0148] In an example embodiment, the satellite beam control apparatus further includes:

[0149] The prediction unit is configured to input the specified ephemeris data of the low-orbit satellite into a pre-trained orbit dynamics model, and output predicted orbit state information of the low-orbit satellite.

[0150] The updating unit is configured to update the electronic fence of the low-orbit satellite in a case where the predicted orbit state information indicates that an orbit altitude change value of the low-orbit satellite is greater than a preset altitude difference value.

[0151] It should be noted that the above modules can be implemented by software or hardware, and for the latter, the following implementation manners can be used, but are not limited thereto: the above modules are located in the same processor; or the above modules are located in different processors in any combination.

[0152] According to another aspect of the embodiments of the present application, a computer readable storage medium is provided, which includes a stored program, wherein the program performs the steps in any of the above method embodiments when running.

[0153] In an example embodiment, the above computer readable storage medium can include, but is not limited to, a U disk, a ROM, a RAM, a mobile hard disk, a magnetic disk or an optical disk, and various computer program storage media.

[0154] According to yet another aspect of the embodiments of the present application, an electronic device is provided, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, the processor being configured to perform the steps of any of the method embodiments described above by means of the computer program. In one exemplary embodiment, the electronic device can further include a transmission device connected to the processor, and an input / output device connected to the processor.

[0155] The specific examples in the embodiments can refer to the examples described in the above embodiments and exemplary implementation manners, which will not be repeated here.

[0156] According to yet another aspect of the embodiments of the present application, a computer program product is also provided, which includes computer programs / instructions containing program codes for executing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network by means of the communication part 709, and / or installed from the detachable medium 711. When the computer program is executed by the central processor 701, various functions provided by the embodiments of the present application are performed. The above-mentioned serial numbers of the embodiments of the present application are only for description, and do not represent the advantages or disadvantages of the embodiments.

[0157] Figure 7 The computer system structure block diagram of the electronic device for implementing the embodiments of the present application is schematically shown. As shown in the figure, Figure 7 The computer system 700 includes a central processor (CPU) 701, which can perform various appropriate actions and processes according to the programs stored in the ROM 702 or the programs loaded from the storage part 708 into the RAM 703. In the random access memory 703, various programs and data required for system operation are also stored. The central processor 701, the read-only memory 702, and the random access memory 703 are connected to each other through the bus 704. The input / output (I / O) interface 705 is also connected to the bus 704.

[0158] The following components are connected to the I / O interface 705: an input part 706 including a keyboard, a mouse, and the like; an output part 707 including a display such as a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, and a speaker, and the like; a storage part 708 including a hard disk, and the like; and a communication part 709 including a network interface card such as a LAN card, a modem, and the like. The communication part 709 performs communication processing via a network such as the Internet. A drive 710 is also connected to the input / output interface 705 as necessary. A removable media 711 such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, and the like is attached to the drive 710 as necessary, so that a computer program read therefrom is installed in the storage part 708 as necessary.

[0159] In particular, according to embodiments of the present application, the processes described in the various method flowcharts can be implemented as a computer software program. For example, embodiments of the present application include a computer program product comprising a computer program carried on a computer readable medium, the computer program containing program code for executing the methods illustrated by the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via the communication part 709, and / or installed from the removable media 711. When the computer program is executed by the central processing unit 701, various functions defined in the system of the present application are performed.

[0160] It should be noted that, Figure 7 The computer system 700 of the electronic device shown is merely an example and should not impose any limitation on the functions and usage range of embodiments of the present application.

[0161] Obviously, those skilled in the art should understand that the above-mentioned modules or steps of the present application can be realized by general computing devices, which can be centralized on a single computing device or distributed on a network composed of multiple computing devices, and can be realized by program codes executable by the computing devices, so that they can be stored in storage devices and executed by the computing devices, and in some cases, the steps shown or described can be executed in different orders, or they can be manufactured into individual integrated circuit modules or multiple modules or steps can be manufactured into a single integrated circuit module. Thus, the present application is not limited to any particular combination of hardware and software.

[0162] The above merely describes the preferred embodiments of the present application and should not impose any limitation on the present application. Those skilled in the art can make various modifications and changes to the present application. Any modification, equivalent replacement, improvement, and the like within the principles of the present application should be included in the protection scope of the present application.

Claims

1. A method of satellite beam control, characterized by, The method is applied to a satellite system, a low-orbit earth station of a low-orbit satellite in the satellite system is located at the same geographical position as a high-orbit earth station of a high-orbit satellite, and the method comprises: obtaining a set of relative position information between the low-orbit satellite and the high-orbit earth station according to ephemeris data of the low-orbit satellite; determining an electronic fence of the low-orbit satellite according to communication parameter information corresponding to each relative position information in the set of relative position information, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence is centered on the geographical position of the high-orbit earth station; in the case that a specified low-orbit satellite exists, adjusting a pointing direction of a beam of the specified low-orbit satellite so that the beam of the specified low-orbit satellite points to an outer region of an outer fence of the specified low-orbit satellite, wherein the specified low-orbit satellite is a low-orbit satellite whose position information indicates that the low-orbit satellite enters an inner fence of the specified low-orbit satellite; wherein the communication parameter information comprises a beam pointing angle; and the determining of the electronic fence of the low-orbit satellite according to the communication parameter information corresponding to each relative position information in the set of relative position information comprises: calculating a set of signal index values according to the communication parameter information corresponding to each relative position information in the set of relative position information, wherein the set of signal index values comprises a signal index value corresponding to each relative position information; determining an inner fence of the low-orbit satellite according to relative position information corresponding to a specified signal index value, wherein the specified signal index value is a signal index value closest to a first preset signal index value selected from the set of signal index values; adjusting the beam pointing angle in the communication parameter information corresponding to specified position information so that a signal index value corresponding to the specified position information is less than a second preset signal index value, wherein the specified position information is position information when the low-orbit satellite, the high-orbit satellite, and the high-orbit earth station are collinear in the set of relative position information, and the first preset signal index value is greater than or equal to the second preset signal index value; determining an outer fence of the low-orbit satellite according to a specified beam pointing angle, wherein the specified beam pointing angle is a beam pointing angle when the signal index value corresponding to the specified position information is less than the second preset signal index value.

2. The method of claim 1, wherein, the calculating of the set of signal index values according to the communication parameter information corresponding to each relative position information in the set of relative position information comprises: inputting the communication parameter information corresponding to each relative position information into a preset index model to output a set of index values corresponding to each relative position information; performing weighted summation on the set of index values corresponding to each relative position information by using a set of weight values to obtain a signal index value corresponding to each relative position information.

3. The method of claim 2, wherein, the determining of the inner fence of the low-orbit satellite according to relative position information corresponding to a specified signal index value comprises: According to the relative position information corresponding to the specified signal index value, a specified subsatellite point of the low-orbit satellite is calculated, wherein the specified subsatellite point is a position point of the low-orbit satellite projected onto a plane where the high-orbit earth station is located under the relative position information corresponding to the specified signal index value; The distance between the specified subsatellite point of the low-orbit satellite and the high-orbit earth station is determined as the radius of the inner fence of the low-orbit satellite.

4. The method of claim 3, wherein, The method further comprises: In a case where there is an index value greater than a preset index threshold in the group of index values corresponding to the specified signal index value, the radius of the inner fence of the low-orbit satellite is increased.

5. The method of claim 1, wherein, The method further comprises: According to the height information of the low-orbit satellite and the specified beam pointing angle, a beam main axis landing point of the low-orbit satellite is calculated, wherein the beam main axis landing point is a projection point of the beam main axis of the low-orbit satellite on the plane where the high-orbit earth station is located; The distance between the beam main axis landing point of the low-orbit satellite and the high-orbit earth station is determined as the radius of the outer fence of the low-orbit satellite.

6. The method according to any one of claims 1 to 5, characterized in that, The method further comprises: The specified ephemeris data of the low-orbit satellite is input into a pre-trained orbit dynamics model, and predicted orbit state information of the low-orbit satellite is output; In a case where the predicted orbit state information indicates that the orbit height change value of the low-orbit satellite is greater than a preset height difference value, the electronic fence of the low-orbit satellite is updated.

7. A satellite beam steering apparatus, characterized by, The device is applied to a satellite system, a low-orbit earth station of a low-orbit satellite in the satellite system and a high-orbit earth station of a high-orbit satellite are located at the same geographical position, and the device comprises: An acquisition unit is configured to acquire a group of relative position information between the low-orbit satellite and the high-orbit earth station according to ephemeris data of the low-orbit satellite; A determination unit is configured to determine an electronic fence of the low-orbit satellite according to communication parameter information corresponding to each relative position information in the group of relative position information, wherein the electronic fence comprises an inner fence and an outer fence, and the electronic fence takes the geographical position of the high-orbit earth station as the center; An adjustment unit is configured to, in a case where there is a specified low-orbit satellite, adjust a pointing direction of a beam of the specified low-orbit satellite, so that the beam of the specified low-orbit satellite points to an outer region of the outer fence of the specified low-orbit satellite, wherein the specified low-orbit satellite is a low-orbit satellite whose position information indicates that the low-orbit satellite enters the inner fence of the specified low-orbit satellite. The communication parameter information comprises a beam pointing angle; and the determination unit comprises: A calculation module is configured to calculate a group of signal index values according to the communication parameter information corresponding to each relative position information in the group of relative position information, wherein the group of signal index values comprises a signal index value corresponding to each relative position information; A first determination module is configured to determine an inner fence of the low-orbit satellite according to relative position information corresponding to a specified signal index value, wherein the specified signal index value is a signal index value closest to a first preset signal index value selected from the group of signal index values. The adjusting module is configured to adjust a beam pointing angle in the communication parameter information corresponding to the specified position information, so that a signal index value corresponding to the specified position information is less than a second preset signal index value, wherein the specified position information is position information when the low-orbit satellite, the high-orbit satellite, and the high-orbit earth station are collinear in the set of relative position information, and the first preset signal index value is greater than or equal to the second preset signal index value. The second determining module is configured to determine an outer circle fence of the low-orbit satellite according to a specified beam pointing angle, wherein the specified beam pointing angle is a beam pointing angle when the signal index value corresponding to the specified position information is less than the second preset signal index value.

8. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, and the computer program is executed by the processor to implement the steps of the method in any one of claims 1 to 6.

9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor executes the computer program to implement the steps of the method in any one of claims 1 to 6.

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