Low-orbit satellite link interference avoidance method and device for high-orbit satellite

Abstract

This application discloses a method and apparatus for avoiding interference from low-Earth orbit (LEO) satellite links to high-Earth orbit (HEO) satellites. It belongs to the field of satellite communications. The method involves: real-time calculation of the LEO satellite's azimuth coordinates to determine if it has entered the HEO satellite's coverage area; if it has, determining whether the downlink data transmission frequency bands of the two satellites are the same; if they are the same frequency band, determining whether the LEO satellite's coverage area covers the gateway station receiving the HEO satellite's downlink data; if it covers the gateway station, determining whether to establish a communication connection with the gateway station based on the power and delay of both satellites; and if a connection is established, receiving downlink data from the HEO satellite and forwarding it to the gateway station. Therefore, this application avoids interference from LEO satellite co-frequency signals to the HEO satellite gateway station's reception without adjusting the LEO satellite's orbit or shutting down its core communication frequency band, thus ensuring the LEO satellite's operational flexibility and communication coverage capability.

Description

Technical Field

[0001] This application relates to the field of satellite communications, and in particular to a method and apparatus for avoiding interference between low-Earth orbit satellites and high-Earth orbit satellite links. Background Technology

[0002] In the field of satellite communications, based on their orbital altitude, communication satellites are mainly divided into two categories: high-Earth orbit (HEO) satellites and low-Earth orbit (LEO) satellites. HEO satellites typically operate in geosynchronous orbit at an altitude of approximately 36,000 kilometers. This orbit has an orbital period that matches the Earth's rotation period, allowing the satellite to maintain a fixed position relative to the ground. This results in a significant advantage of wide coverage, enabling continuous communication coverage of specific areas. LEO satellites, on the other hand, operate in low-Earth orbit at an altitude of 500-1200 kilometers, with a much smaller coverage area than HEO satellites.

[0003] For example, CN113708826A, entitled "An On-orbit Verification Method for a Shared Ka-Band Interference Avoidance Strategy," discloses an on-orbit verification method for a shared Ka-band interference avoidance strategy, relating to the field of satellite system interference avoidance technology. It includes steps such as spectrum usage monitoring, electromagnetic environment interference analysis, generating interference avoidance strategies, executing the interference avoidance strategies, and monitoring the results. This invention addresses the problem of Ka-band frequency sharing and interference between high-Earth orbit and low-Earth orbit satellite systems. Based on the different uplink and downlink interference situations caused by low-Earth orbit satellite systems to high-Earth orbit satellite systems, it proposes a targeted on-orbit verification method for interference avoidance strategies, fundamentally solving problems such as the scarcity of Ka-band resources and the difficulty of high-Earth orbit frequency coordination based on traditional all-digital and semi-physical simulation interference analysis.

[0004] For example, CN113691332A, entitled "A Method and Apparatus for Characterizing Co-channel Interference in a Low-Earth Orbit Satellite Communication System," discloses a method and apparatus for characterizing co-channel interference in a low-Earth orbit satellite communication system. The method includes: constructing a low-Earth orbit satellite communication system model; wherein the low-Earth orbit satellite communication system model includes multiple satellites and multiple ground terminals, and the multiple satellites are divided into multiple layers according to their orbital altitude; establishing a spatiotemporal position model matrix for each layer of satellites using the position information of individual satellites as matrix elements; determining satellites that may cause co-channel interference to the target terminal based on the spatiotemporal position model matrix and the position information of the target terminal, thus obtaining a set of satellites that may cause interference to the target terminal; calculating the access capacity of the target terminal; and simultaneously studying the co-channel interference of the terminal uplink to the satellite within the satellite coverage area, providing a definition of the interference factor to characterize the co-channel interference of the terminal uplink within the coverage area, and calculating the average capacity of the satellites. This invention can provide guidance for research on technologies such as constellation interference avoidance, system frequency usage rules, and constellation design.

[0005] As a crucial node connecting satellites and terrestrial communication networks, the stability of the received signals from gateway stations directly impacts the overall operational quality of the communication system. In practical applications, high-orbit satellites typically establish stable communication links with pre-deployed ground gateway stations, transmitting data to the gateway stations via downlink. When low-orbit satellites enter the coverage area of ​​a gateway station during operation, and these low-orbit satellites use the same communication frequency band as the high-orbit satellites, the co-frequency signals emitted by the low-orbit satellites directly interfere with the gateway stations' reception of downlink signals from the high-orbit satellites. This leads to an increased bit error rate in the data received by the gateway stations, and in severe cases, may even cause communication link interruptions, affecting the normal operation of the high-orbit satellite communication system.

[0006] To address the aforementioned co-channel interference problem, existing technologies primarily employ regional avoidance or beam avoidance strategies. Regional avoidance involves adjusting the trajectory of low-Earth orbit (LEO) satellites using satellite orbit control technology to deflect them away from the specific area where the gateway station is located, thus preventing LEO satellites from entering the gateway station's coverage area. Beam avoidance, on the other hand, involves controlling LEO satellites to cease using the same frequency band as high-Earth orbit (HEO) satellites when they unavoidably enter the gateway station's coverage area, switching to other non-interfering frequency bands or disabling the beam in that band. However, both strategies have significant limitations: regional avoidance severely restricts the orbital flexibility of LEO satellites, shrinking their effective communication coverage area; beam avoidance prevents LEO satellites from using core communication frequency bands in specific areas, significantly reducing their communication capacity and service capabilities. Ultimately, both strategies severely limit the normal operation of LEO satellites, making it difficult to meet the application requirements of efficient and widespread coverage for LEO satellite communication systems.

[0007] To address the technical problems in the existing technologies mentioned above, the use of regional avoidance or beam avoidance strategies to avoid co-channel interference from low-Earth orbit satellites to high-Earth orbit satellite gateway stations would severely limit the operational flexibility of low-Earth orbit satellites, reduce coverage areas, or decrease communication capacity, making it difficult to balance interference control with the operational efficiency of low-Earth orbit satellites. Currently, no effective solution has been proposed. Summary of the Invention

[0008] The embodiments of this disclosure provide a method and apparatus for avoiding interference from low-Earth orbit (LEO) satellites to high-Earth orbit (HEO) satellite links, thereby at least solving the technical problem in the prior art where the use of regional avoidance or beam avoidance strategies to avoid co-channel interference from LEO satellites to HEO satellite gateway stations would greatly limit the operational flexibility of LEO satellites, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference control and LEO satellite operational efficiency.

[0009] According to one aspect of the present disclosure, a method for avoiding link interference between a low-Earth orbit (LEO) satellite and a high-Earth orbit (HEO) satellite is provided. The method includes: calculating the LEO satellite's own azimuth coordinates in real time and determining whether it has entered the HEO satellite's coverage area; if it has entered the HEO satellite's coverage area, determining whether the downlink data transmission signal bands of the HEO satellite and the LEO satellite are the same; if the downlink data transmission signal bands of the HEO satellite and the LEO satellite are the same, determining in real time whether the LEO satellite's coverage area covers a gateway station receiving downlink data from the HEO satellite; if the LEO satellite's coverage area covers the gateway station, determining whether to establish a communication connection with the gateway station based on the power and delay of the HEO satellite and the LEO satellite; and if a communication connection with the gateway station is established, receiving downlink data from the HEO satellite and transmitting the downlink data to the gateway station.

[0010] According to another aspect of the present disclosure, a storage medium is also provided, the storage medium including a stored program, wherein, when the program is executed, a processor performs any of the methods described above.

[0011] According to another aspect of the present disclosure, an interference avoidance device for low-Earth orbit (LEO) satellite links to high-Earth orbit (HEO) satellites is also provided. The device includes: a calculation module for real-time calculation of the LEO satellite's own azimuth coordinates and determining whether it has entered the HEO satellite's coverage area; a sameness determination module for determining whether, if it has entered the HEO satellite's coverage area, the signal frequency bands for downlink data transmission between the HEO satellite and the LEO satellite are the same; a coverage determination module for determining, if the signal frequency bands for downlink data transmission between the HEO satellite and the LEO satellite are the same, whether, in real-time, the coverage area of ​​the LEO satellite covers a gateway station receiving downlink data from the HEO satellite; a connection determination module for determining, if the coverage area of ​​the LEO satellite covers the gateway station, whether to establish a communication connection with the gateway station based on the power and delay of the HEO satellite and the LEO satellite; and a transmission module for receiving downlink data from the HEO satellite and transmitting the downlink data to the gateway station if a communication connection is established with the gateway station.

[0012] According to another aspect of the present disclosure, an apparatus for avoiding link interference between a low-Earth orbit (LEO) satellite and a high-Earth orbit (HEO) satellite is also provided. This apparatus is for a LEO satellite and includes: a processor; and a memory connected to the processor, configured to provide the processor with instructions to perform the following processing steps: real-time calculation of the LEO satellite's own azimuth coordinates; determining whether it has entered the HEO satellite's coverage area; if it has entered the HEO satellite's coverage area, determining whether the downlink data transmission signal bands of the HEO satellite and the LEO satellite are the same; if the downlink data transmission signal bands of the HEO satellite and the LEO satellite are the same, real-time determination whether the LEO satellite's coverage area covers a gateway station receiving downlink data from the HEO satellite; if the LEO satellite's coverage area covers the gateway station, determining whether to establish a communication connection with the gateway station based on the power and delay of the HEO satellite and the LEO satellite; and if a communication connection with the gateway station is established, receiving downlink data from the HEO satellite and transmitting the downlink data to the gateway station.

[0013] This application provides a method for avoiding interference from low-Earth orbit (LEO) satellite links to high-Earth orbit (HEO) satellites. Specifically, it is implemented through a multi-step judgment and operation process executed collaboratively by a processor: First, the LEO satellite's own azimuth coordinates are calculated in real time using an onboard positioning system and orbital dynamics algorithms. Then, a coverage area entry determination is made based on a pre-defined HEO satellite coverage area model. If entry is determined, the frequency band parameters of the downlink data transmission between the HEO and LEO satellites are retrieved for overlap comparison to determine if they are on the same frequency band. If they are on the same frequency band, the coverage area of ​​the LEO satellite is further calculated and compared with the reception range of the HEO satellite gateway station to determine if it covers the gateway station. If coverage is achieved, the signal power ratio and transmission delay difference between the HEO and LEO satellites are calculated to determine whether a communication connection should be established. If an establishment is determined, the LEO satellite receives downlink data from the HEO satellite and forwards it to the gateway station, thus achieving interference avoidance and stable data transmission. Therefore, this application avoids interference from low-Earth orbit (LEO) satellite co-channel signals with high-Earth orbit (HEO) satellite gateway station reception without adjusting the LEO satellite's orbit or shutting down the core communication frequency band, thus ensuring the operational flexibility and communication coverage of LEO satellites. Furthermore, it solves the technical problem in the prior art where using regional avoidance or beam avoidance strategies to avoid LEO satellite co-channel interference to HEO satellite gateway stations would greatly limit the operational flexibility of LEO satellites, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference control and LEO satellite operational efficiency. Attached Figure Description

[0014] The accompanying drawings, which are included to provide a further understanding of this disclosure and form part of this application, illustrate exemplary embodiments of this disclosure and are used to explain this disclosure, but do not constitute an undue limitation of this disclosure. In the drawings:

[0015] Figure 1 This is a hardware structure block diagram of a computing device for implementing the method described in Embodiment 1 of this disclosure;

[0016] Figure 2 This is a schematic diagram of a system for avoiding interference between low-orbit satellites and high-orbit satellite links according to Embodiment 1 of this disclosure;

[0017] Figure 3 This is a flowchart illustrating the method for avoiding interference between low-orbit satellites and high-orbit satellite links according to Embodiment 1 of this disclosure.

[0018] Figure 4 This is a schematic diagram of a low-Earth orbit satellite coverage gateway station according to the method for avoiding interference between low-Earth orbit satellite links and high-Earth orbit satellites as described in Embodiment 1 of this disclosure.

[0019] Figure 5 This is a schematic diagram of a low-orbit satellite leaving a gateway station according to the method for avoiding interference between low-orbit satellite links and high-orbit satellites as described in Embodiment 1 of this disclosure.

[0020] Figure 6 This is a schematic diagram of a device for avoiding interference between low-orbit satellites and high-orbit satellite links according to Embodiment 2 of this disclosure;

[0021] Figure 7 This is a schematic diagram of a device for avoiding interference between low-orbit satellites and high-orbit satellite links, according to Embodiment 3 of this disclosure. Detailed Implementation

[0022] To enable those skilled in the art to better understand the technical solutions of this disclosure, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this disclosure.

[0023] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this disclosure are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this disclosure described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0024] Example 1

[0025] According to this embodiment, an embodiment of a method for avoiding interference between low-orbit satellites and high-orbit satellite links is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0026] Figure 1 This is a schematic diagram of the hardware architecture of satellite system 10. (Reference) Figure 1 As shown, satellite system 10 includes an integrated electronic system, which includes a processor, a memory, a bus management module, and a communication interface. The memory is connected to the processor, allowing the processor to access the memory, read program instructions stored in the memory, read data from the memory, or write data to the memory. The bus management module is connected to the processor and also to a bus such as a CAN bus. Thus, the processor can communicate with onboard peripherals connected to the bus through the bus managed by the bus management module. These onboard peripherals include: onboard peripheral 1 (GNSS module), onboard peripheral 2 (fiber optic gyroscope), ..., onboard peripheral n (torque flywheel). Furthermore, the processor also communicates with devices such as cameras, star sensors, telemetry and control transponders, and data transmission equipment via the communication interface. Those skilled in the art will understand that... Figure 1 The structure shown is for illustrative purposes only and does not limit the structure of the aforementioned electronic device. For example, a satellite system may also include... Figure 1 The more or fewer components shown, or having the same Figure 1 The different configurations shown.

[0027] It should be noted that, Figure 1 One or more processors and / or other data processing circuits shown herein may generally be referred to as "data processing circuitry". This data processing circuitry may be embodied, in whole or in part, in software, hardware, firmware, or any other combination thereof. Furthermore, the data processing circuitry may be a single, independent processing module, or may be integrated, in whole or in part, into any other element in a computing device. As involved in embodiments of this disclosure, the data processing circuitry serves as processor control (e.g., selection of a variable resistor termination path connected to an interface).

[0028] Figure 1The memory shown can be used to store software programs and modules of application software, such as the program instructions / data storage device corresponding to the method for determining the communication frequency band corresponding to the beam in the embodiments of this disclosure. The processor executes various functional applications and data processing by running the software programs and modules stored in the memory, that is, to implement the above-mentioned method for determining the communication frequency band corresponding to the beam in the application program. The memory may include high-speed random access memory, and may also include non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory.

[0029] It should be noted here that, in some optional embodiments, the above... Figure 1 The device shown may include hardware elements (including circuitry), software elements (including computer code stored on a computer-readable medium), or a combination of both hardware and software elements. It should be noted that... Figure 1 This is only one instance of a specific particular instance, and is intended to illustrate the types of components that may exist in the aforementioned devices.

[0030] Figure 2 This is a schematic diagram of a system for avoiding interference between low-Earth orbit satellites and high-Earth orbit satellite links in a satellite communication scenario according to this embodiment. (Refer to...) Figure 2 As shown, the system includes a high-orbit satellite 101, a low-orbit satellite 102, and a gateway station 103. The high-orbit satellite 101 transmits downlink data to the ground gateway station 103 and simultaneously establishes a second downlink link upon request from the low-orbit satellite 102, enabling synchronous transmission of downlink data to the low-orbit satellite 102. The low-orbit satellite 102 determines in real time whether it has entered the coverage area of ​​the high-orbit satellite 101, whether it shares the same frequency band as the high-orbit satellite 101, and whether it covers the gateway station 103. When the conditions for establishing a communication connection are met, it receives downlink data from the high-orbit satellite 101 and forwards it to the gateway station 103, without needing to adjust its orbit or shut down its core frequency band, ensuring its operational flexibility. The gateway station 103 receives both the direct transmission from the high-orbit satellite 101 and the forwarded data from the low-orbit satellite 102, ensuring transmission integrity through data verification and preventing interference from the low-orbit satellite 102's co-frequency signal to the direct transmission link of the high-orbit satellite 101, thus maintaining the stable operation of the overall communication system.

[0031] Under the aforementioned operating environment, according to the first aspect of this embodiment, a method for avoiding interference between low-Earth orbit satellites and high-Earth orbit satellite links is provided. This method comprises... Figure 2 The high-orbit satellite 101, low-orbit satellite 102, and gateway station 103 shown in the figure work together to achieve this. Figure 3 A flowchart illustrating the method is shown below. (Refer to...) Figure 3 As shown, the method includes:

[0032] S302: Calculates the azimuth coordinates of the low-orbit satellite in real time to determine whether it has entered the coverage area of ​​the high-orbit satellite;

[0033] S304: When it is determined that the satellite has entered the coverage area of ​​a high-orbit satellite, determine whether the downlink data transmission signal frequency band of the high-orbit satellite and the low-orbit satellite is the same;

[0034] S306: When it is determined that the downlink data transmission signal frequency bands of the high-orbit satellite and the low-orbit satellite are the same, it is determined in real time whether the coverage area of ​​the low-orbit satellite covers the gateway station receiving the downlink data of the high-orbit satellite.

[0035] S308: When it is determined that the coverage area of ​​a low-Earth orbit satellite covers the gateway station, determine whether to establish a communication connection with the gateway station based on the power and delay of the high-Earth orbit and low-Earth orbit satellites; and

[0036] S310: Upon determining that a communication connection has been established with the gateway station, receive downlink data from the high-orbit satellite and transmit the downlink data to the gateway station.

[0037] Specifically, the real-time calculation of the azimuth coordinates of the low-Earth orbit satellite 102 first requires the satellite to continuously receive external positioning signals (such as GNSS satellite timestamps and orbital parameters) and its own state data (such as orbital altitude change rate, flight speed, and attitude angles). Then, based on a pre-set orbital calculation model (such as the Kepler orbital model combined with atmospheric perturbation correction algorithms), the above data is converted into standardized spatial coordinates (usually using a geocentric rectangular coordinate system or a latitude-longitude-altitude coordinate system) to ensure the real-time nature and accuracy of the azimuth data, providing an accurate positional reference for subsequent spatial range determination.

[0038] Secondly, the determination of the coverage area of ​​the high-orbit satellite 101 needs to be based on a preset coverage area model: the low-orbit satellite 102 retrieves the coverage area model parameters of the target high-orbit satellite 101 through the local storage module or the downlink of the ground control center. This model is jointly constructed by the orbital altitude of the high-orbit satellite 101, the antenna beam half-power angle, the beam pointing angle (including azimuth and elevation angles), and the Earth curvature parameters. It can clearly define the spatial range of the effective coverage of the high-orbit satellite 101 signal (represented as a circular area with a specific radius centered on the nadir point of the high-orbit satellite 101, the radius of which is calculated from the beam half-power angle and the orbital altitude), and convert it into spatial range data (such as latitude and longitude boundaries and altitude ranges) consistent with the azimuth coordinate format of the low-orbit satellite 102.

[0039] Finally, spatial location matching is used to determine whether the low-orbit satellite 102 has entered the coverage area of ​​the high-orbit satellite 101 (corresponding to step S302): The low-orbit satellite 102 substitutes its real-time calculated azimuth coordinates into the spatial range data of the high-orbit satellite 101 coverage area model. Through coordinate boundary comparison (e.g., determining whether the latitude and longitude of the low-orbit satellite 102 are within the latitude and longitude boundaries of the high-orbit satellite 101 coverage area, and whether its altitude is within the altitude range covered by the high-orbit satellite 101 signal) and spatial distance calculation (e.g., calculating the straight-line distance between the low-orbit satellite 102 and the nadir point of the high-orbit satellite 101, and determining whether it is less than the radius of the high-orbit coverage area), if any of the above determination conditions are met, it is determined that it has entered the coverage area of ​​the high-orbit satellite 101, triggering the subsequent frequency band consistency determination process; if any of the above determination conditions are not met, it is determined that it has not entered the coverage area of ​​the high-orbit satellite 101, the low-orbit satellite 102 maintains its current communication state, and continuously updates its own azimuth coordinates to repeat the above determination, ensuring timely capture of spatial location changes.

[0040] Then, after confirming that the low-Earth orbit satellite 102 has entered the coverage area of ​​the high-Earth orbit satellite 101, it is determined whether the downlink data transmission signal frequency bands of the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 are the same (corresponding to step S304). The low-Earth orbit satellite 102 first retrieves two types of frequency band parameters from its local storage module or the database issued by the ground control center. One type is the working frequency band parameters (including the start frequency, end frequency and signal bandwidth) of its current transmission of downlink data to the coverage area. The other type is the reference frequency band parameters (the parameters are fixed frequency bands preset by the communication system of the high-Earth orbit satellite 101, such as Ku band 11.7-12.7GHz and Ka band 17.7-21.2GHz) of the high-Earth orbit satellite 101.

[0041] Next, a comparison is performed using frequency band overlap calculation: If the bandwidth of the overlapping portion of the downlink frequency band of the low-Earth orbit satellite 102 and the downlink frequency band of the high-Earth orbit satellite 101 is greater than or equal to a preset interference bandwidth threshold, then it is determined that the signal frequency bands for downlink data transmission between the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 are the same, and subsequent coverage determination of the gateway station 103 can continue to avoid interference. If the two frequency bands do not overlap or the overlap bandwidth is less than the interference bandwidth threshold, then it is determined that the signal frequency bands for downlink data transmission between the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 are not the same, and there is no risk of co-channel interference. The low-Earth orbit satellite 102 maintains its current downlink data transmission status while continuously monitoring its relative position to the coverage area of ​​the high-Earth orbit satellite 101.

[0042] Furthermore, after confirming that the high-orbit satellite 101 and the low-orbit satellite 102 are transmitting at the same frequency, it is determined in real time whether the coverage area of ​​the low-orbit satellite 102 covers the gateway station 103 receiving downlink data from the high-orbit satellite 101 (corresponding to step S306). That is, the low-orbit satellite 102 first needs to calculate the ground area that it can cover in the current downlink signal, forming coverage range data (such as latitude and longitude boundaries) consistent with the coordinate format of the gateway station 103. Then, the coverage range of the low-orbit satellite 102 is spatially compared with the position coordinates of the gateway station 103. If the position coordinates of the gateway station 103 are within the coverage area of ​​the low-orbit satellite 102, it is determined that the coverage area of ​​the low-orbit satellite 102 covers the gateway station 103 receiving downlink data from the high-orbit satellite 101, and subsequent communication connection determination needs to be initiated to avoid interference; otherwise, it is determined that the coverage area of ​​the low-orbit satellite 102 does not cover the gateway station 103 receiving downlink data from the high-orbit satellite 101, there is no risk of interference, and the low-orbit satellite maintains its current transmission state.

[0043] Subsequently, reference Figure 4 As shown, when the low-Earth orbit satellite 102 determines in real time that it is covering the gateway station 103, it determines in real time whether to establish a communication connection with the gateway station 103 (corresponding to step S308). First, the downlink signal power of the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 is acquired in real time. Then, the transmission delay difference between the gateway station 103 and the high-Earth orbit satellite 101 (directly connected) or the gateway station 103 (retransmitted via the low-Earth orbit satellite 102) is calculated (to avoid data asynchrony). Based on these two indicators, it is determined whether to establish a communication connection with the gateway station 103.

[0044] Finally, after confirming that a communication connection can be established with the gateway station 103, the low-Earth orbit satellite 102 first sends a request to the high-Earth orbit satellite 101 to establish a downlink according to the preset communication protocol. After the high-Earth orbit satellite 101 confirms, while maintaining its direct downlink data transmission with the gateway station 103, it also sends the same downlink data to the low-Earth orbit satellite 102 through the newly established link. After receiving the downlink data from the high-Earth orbit satellite 101, the low-Earth orbit satellite 102 forwards the data to the gateway station 103 according to the transmission format agreed upon with the gateway station 103 (such as modulation and demodulation method, data frame structure) (corresponding to step S310). At this time, the gateway station 103 simultaneously receives two downlink data streams: one directly transmitted from the high-Earth orbit satellite 101 and the other forwarded by the low-Earth orbit satellite 102. By comparing and verifying the two downlink data streams, data transmission errors caused by interference from the low-Earth orbit satellite 102's co-frequency signal to the high-Earth orbit direct transmission link can be avoided, ensuring the stability and integrity of data transmission.

[0045] As described in the background section, in the field of satellite communication, a high-orbit satellite 101 typically establishes a stable communication link with a pre-deployed ground gateway station 103, transmitting data to the gateway station 103 via a downlink. When a low-orbit satellite 102 enters the coverage area of ​​the gateway station 103 during operation, and the low-orbit satellite 102 uses the same communication frequency band as the high-orbit satellite 101, the co-channel signal emitted by the low-orbit satellite 102 directly interferes with the gateway station 103's reception of the high-orbit satellite 101's downlink signal. This leads to an increase in the bit error rate of the data received by the gateway station 103, and in severe cases, may even cause a communication link interruption, affecting the normal operation of the high-orbit satellite 101 communication system. To solve the aforementioned co-channel interference problem, existing technologies mainly employ regional avoidance or beam avoidance strategies. However, both strategies have significant limitations: regional avoidance greatly restricts the operational orbital flexibility of LEO satellite 102 and reduces its effective communication coverage area; beam avoidance will prevent LEO satellite 102 from using core communication frequency bands in specific areas, significantly reducing its communication capacity and service capabilities. Ultimately, both greatly restrict the normal operation of LEO satellite 102 and make it difficult to meet the application requirements of efficient and wide coverage of the LEO satellite 102 communication system.

[0046] In view of this, this application provides a method for avoiding link interference between a low-Earth orbit satellite 102 and a high-Earth orbit satellite 101. Specifically, this is achieved through coordinated execution of multiple steps of judgment and operation: First, the low-Earth orbit satellite 102 calculates its own azimuth coordinates in real time using the onboard positioning system and orbital dynamics algorithm, and then determines whether it enters the coverage area by combining the preset coverage area model of the high-Earth orbit satellite 101. If entry is determined, the frequency band parameters of downlink data transmission of the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 are retrieved and compared for overlap to determine whether they are in the same frequency band. If they are in the same frequency band, the coverage area of ​​the low-Earth orbit satellite 102 is further calculated and compared with the receiving range of the gateway station 103 of the high-Earth orbit satellite 101 to determine whether it covers the gateway station 103. If it covers the gateway station 103, the signal power ratio and transmission delay difference of the high-Earth orbit and low-Earth orbit satellites 102 are calculated to determine whether a communication connection is established. If the connection is established, the low-Earth orbit satellite 102 receives downlink data from the high-Earth orbit satellite 101 and forwards it to the gateway station 103. Gateway station 103 simultaneously receives two downlink data streams: one directly transmitted from high-orbit satellite 101 and the other relayed from low-orbit satellite 102. By comparing and verifying the two downlink data streams, data transmission errors caused by interference from the co-frequency signal of low-orbit satellite 102 on the high-orbit direct transmission link can be avoided, ensuring the stability and integrity of data transmission. This achieves interference avoidance and stable data transmission. Therefore, this application avoids interference from the co-frequency signal of low-orbit satellite 102 on the reception of gateway station 103 for high-orbit satellite 101 without adjusting the orbit of low-orbit satellite 102 or shutting down the core communication frequency band, ensuring the operational flexibility and communication coverage of low-orbit satellite 102. Furthermore, it solves the technical problem in the prior art where using regional avoidance or beam avoidance strategies to avoid co-frequency interference from low-orbit satellite 102 on high-orbit satellite 101 gateway station 103 would severely limit the operational flexibility of low-orbit satellite 102, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference control and the operational efficiency of low-orbit satellite 102.

[0047] Optionally, the operation of receiving downlink data from a high-orbit satellite and transmitting the downlink data to a gateway station includes: sending a communication request to the gateway station to establish a first downlink according to a preset protocol; if the gateway station confirms that the first downlink can be established, sending a communication request to the high-orbit satellite to establish a second downlink from the high-orbit satellite to the low-orbit satellite; if the high-orbit satellite confirms that the second downlink can be established, receiving downlink data from the high-orbit satellite via the second downlink and transmitting the downlink data to the gateway station via the first downlink.

[0048] Specifically, the low-orbit satellite 102 sends a communication request to the gateway station 103 to establish a first downlink according to a pre-set protocol that matches the gateway station 103 (e.g., through time division multiplexing or frequency division multiplexing).

[0049] After the gateway station 103 confirms through signal quality detection and frequency band conflict investigation that the first downlink (i.e., the downlink from the low-Earth orbit satellite 102 to the gateway station 103) can be established by the low-Earth orbit satellite 102, it will generate communication confirmation information including link coordination parameters (such as modulation mode and transmission bandwidth) and send the confirmation information to the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102 respectively, and simultaneously inform them of the preparation instructions for the subsequent link establishment.

[0050] After receiving the confirmation information from the gateway station 103, the low-Earth orbit satellite 102 sends a communication request to the high-Earth orbit satellite 101 to establish a second downlink (i.e., a downlink from the high-Earth orbit satellite 101 to the low-Earth orbit satellite 102) based on the link coordination parameters in the confirmation information. The communication request includes key parameters such as the current azimuth coordinates and signal reception capability of the low-Earth orbit satellite 102. After receiving the communication request, the high-Earth orbit satellite 101 evaluates its own orbital status and downlink load. If it confirms that the second downlink can be established, it sends a link establishment permission to the low-Earth orbit satellite 102 and completes parameter negotiation and establishment of the second downlink with the low-Earth orbit satellite 102.

[0051] During this process, the high-orbit satellite 101 maintains normal downlink transmission with the gateway station 103 via the first downlink link (i.e., the downlink link from high-orbit satellite 101 to gateway station 103). Simultaneously, it transmits the same downlink data synchronously to the low-orbit satellite 102 via the newly established second downlink link. After receiving the downlink data transmitted by the high-orbit satellite 101, the low-orbit satellite 102 forwards the data to the gateway station 103 via the first downlink link according to the transmission protocol agreed upon with the gateway station 103. The gateway station 103 receives both downlink data streams directly transmitted from the high-orbit satellite 101 (first downlink) and forwarded from the low-orbit satellite 102 (second downlink + first downlink). It verifies the consistency of the two data streams through methods such as data checksum comparison or transmission timing synchronization to ensure the integrity and accuracy of data transmission, thus completing the entire link establishment and data transmission process.

[0052] The above method achieves synchronous transmission of downlink data through dual downlinks (a first link directly connecting the high-orbit satellite to the gateway station, and a second link relayed from the high-orbit satellite to the gateway station via a low-orbit satellite), avoiding interference from co-frequency signals from the low-orbit satellite on the high-orbit direct transmission link. Furthermore, the gateway station verifies both data streams to ensure transmission integrity. Simultaneously, it eliminates the need to adjust the low-orbit satellite's orbit or shut down its core frequency band. While ensuring the stability of high-orbit satellite communication, it fully preserves the operational flexibility and communication coverage capabilities of the low-orbit satellite, effectively overcoming the limitations of existing area avoidance and beam avoidance strategies.

[0053] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite includes: determining a first power parameter, which reflects the ratio of the signal power of the low-orbit satellite to the signal power of the high-orbit satellite; determining a first delay parameter, wherein the first delay parameter reflects the ratio between a first delay of the high-orbit satellite transmitting downlink data to the gateway station via the low-orbit satellite and a second delay of the high-orbit satellite directly transmitting downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0054] Specifically, determining the first power parameter requires the low-Earth orbit satellite 102 to monitor in real time the signal power P1 of the high-Earth orbit satellite 101 transmitting downlink data to the gateway station 103, and simultaneously retrieve the signal power P2 of its own downlink data transmission to the gateway station 103. Then, the low-Earth orbit satellite 102 calculates the first power parameter based on the signal power P1 and the signal power P2. The calculation formula is as follows:

[0055] (1)

[0056] It should be noted that k P (k) P ≥-1) is used to indicate the degree of deviation between the signal power P2 of low-Earth orbit satellite 102 and the signal power P1 of high-Earth orbit satellite 101. Where, k P The closer k is to -1, the smaller P2 is to P1, and the less co-channel interference caused by low-Earth orbit satellite 102 to the downlink from high-Earth orbit satellite 101 to gateway station 103. Conversely, when k P If the value is greater than the preset negative value (e.g., -0.3), it indicates that the gap between P2 and P1 has narrowed, and the low-orbit satellite 102 may cause co-channel interference to the downlink from the high-orbit satellite 101 to the gateway station 103.

[0057] Simultaneously, while calculating the first power parameter, low-Earth orbit satellite 102 calculates the same parameter, and high-Earth orbit satellite 101 transmits the parameter via low-Earth orbit satellite 102 (i.e., via...). Figure 4 The first delay in the transmission path L1 (in the forwarding transmission path) to the gateway station 103 for transmitting downlink data is... The high-orbit satellite 101 transmits downlink data directly to the gateway station 103 (i.e., via...). Figure 4 The second delay of the direct transmission path L2 in the middle ,in:

[0058] (2)

[0059] (3)

[0060] In the formula, C represents the signal propagation speed.

[0061] Furthermore, the first delay parameter k is calculated based on the first delay τ1 and the second delay τ2. τ :

[0062] (4)

[0063] Where the first delay parameter k τ Used to indicate the severity of the delay deviation when transmitting downlink data via forwarding transmission path L1 relative to the direct transmission path L2. τ The smaller the value, the smaller the difference in delay between the two transmissions, and the stronger the synchronization of subsequent data reception; k τ The larger the value, the greater the difference in delay between the two transmissions, and the weaker the synchronization of subsequent data reception.

[0064] Through the above methods, low-orbit satellite 102 can utilize the first power parameter k. P Determine the risk level of co-channel interference by using the first delay parameter k. τ Understanding the latency and synchronization of data transmission provides a quantitative basis for determining whether to establish a communication connection with gateway station 103. This allows for precise control of the timing of establishing a connection with low-orbit satellite 102 while ensuring the stability of the downlink of high-orbit satellite 101, thus avoiding interference problems caused by blind connection establishment.

[0065] Optionally, the operation of determining the first delay parameter includes: calculating in real time the first distance between the low-Earth orbit satellite and the high-Earth orbit satellite and the second distance between the low-Earth orbit satellite and the gateway station, and determining the first delay based on the first distance and the second distance; calculating in real time the third distance between the high-Earth orbit satellite and the gateway station, and calculating the second delay based on the third distance; and determining the first delay parameter based on the first delay and the second delay.

[0066] Specifically, after determining that the low-Earth orbit satellite 102 has entered the coverage area of ​​the high-Earth orbit satellite 101 and that both operate on the same frequency band, in order to further assess the feasibility of the communication connection, the azimuth coordinates (x2, y2, z2) of the high-Earth orbit satellite 101 are determined in real time, and the following calculations are performed in real time based on the azimuth coordinates (x0, y0, z0) of the gateway station, the azimuth coordinates (x1, y1, z1) of the low-Earth orbit satellite 102, and the azimuth coordinates (x2, y2, z2) of the high-Earth orbit satellite 101:

[0067] The first distance between low-orbit satellite 102 and high-orbit satellite 101

[0068] (5)

[0069] This first distance is used to subsequently deduce the path length L1 of the transmission path for forwarding downlink data from high-orbit satellite 101 via low-orbit satellite 102.

[0070] The second distance D2 between low-Earth orbit satellite 102 and gateway station 103:

[0071] (6)

[0072] This second distance provides a basis for the path length of L1, the forwarding transmission path from low-orbit satellite 102 to gateway station 103 for forwarding downlink data; and

[0073] The third distance D3 between high-orbit satellite 101 and the gateway station:

[0074] (7)

[0075] This third distance corresponds to the direct transmission path L2 from the high-orbit satellite 101 to the gateway station 103 for downlink data.

[0076] In this case, since the path for transmitting downlink data from high-orbit satellite 101 to gateway station 103 via low-orbit satellite 102 is "high-orbit satellite 101 → low-orbit satellite 102 → gateway station 103", its total path length (forwarding transmission path L1) is equal to the first distance. With the second distance The sum of these, therefore, combined with the signal propagation speed C (speed of light, approximately 3 × 10⁻⁶), 8 (m / s), the first delay can be determined by the following formula. :

[0077] (8)

[0078] Because the path length (direct transmission path L2) of the high-orbit satellite 101 directly transmitting downlink data to the gateway station 103 is the third distance. Therefore, the second delay is calculated using the following formula. :

[0079] (9)

[0080] After obtaining the first delay With the second delay Then, the degree of delay deviation is quantified based on the difference between the two, for example, by formula (4) (or other reasonable formulas set according to actual communication synchronization requirements) to determine the first delay parameter k. τ This parameter can intuitively reflect the severity of the delay deviation between the transmission path relayed by low-Earth orbit satellites and the direct transmission path of high-Earth orbit satellites. It provides a quantitative basis for subsequent determination of whether to establish a communication connection and avoid data reception asynchrony, thus closely linking the spatial distance parameter with the delay determination logic to form a complete parameter derivation closed loop.

[0081] In this way, on the one hand, basic data is provided for subsequent calculation of the first delay and the second delay, and on the other hand, it can help verify whether the spatial positional relationship between the high-orbit satellite 101 and the low-orbit satellite 102 and the gateway station 103 meets the conditions for interference-free communication, providing complete spatial dimension support for subsequent connection establishment based on power and delay, and ensuring the accuracy of interference avoidance decisions.

[0082] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter includes: using a pre-trained logistic regression algorithm model to determine whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0083] Specifically, in obtaining the first power parameter k P With the first delay parameter k τ Subsequently, the low-orbit satellite 102 uses a pre-set logistic regression algorithm to quantitatively assess the feasibility of establishing a communication connection with the gateway station 103.

[0084] (10)

[0085] (11)

[0086] Among them, the low-orbit satellite 102 calls the pre-trained logistic regression algorithm model to calculate and obtain the probability output value L(u) with a value range between [0,1]. When L(u)≥0.5, a communication connection is established; otherwise, a communication connection is not established (or the communication connection is disconnected if a communication connection has already been established).

[0087] It should be noted that this logistic regression algorithm model uses the first power parameter k. P and the first delay parameter k τ As input features, a linear prediction value u is calculated, where α0 is the model intercept term, and α1 and α2 are k... P and k τ The weighting coefficients (which are generated by training with historical interference scenario data and communication quality test data, and have been pre-stored in the local module of the low-orbit satellite 102, and can be dynamically calibrated by those skilled in the art according to actual needs).

[0088] Using the above methods, k P and k τ These two key parameters are transformed into clear criteria for connection establishment decisions, enabling quantitative assessment of interference risks and transmission quality, and ensuring the scientific and accurate nature of connection establishment decisions.

[0089] Optionally, it further includes: when the low-Earth orbit satellite determines in real time that the coverage area is leaving the gateway station, determining whether to disconnect the communication connection with the gateway station based on the power and delay of the high-Earth orbit satellite and the low-Earth orbit satellite; and disconnecting the communication connection with the high-Earth orbit satellite and the gateway station when it is determined that the communication connection with the gateway station has been disconnected; wherein the operation of determining whether to disconnect the communication connection with the gateway station based on the power and delay of the high-Earth orbit satellite and the low-Earth orbit satellite includes: determining a second power parameter, the second power parameter reflecting the ratio of the signal power of the low-Earth orbit satellite to the signal power of the high-Earth orbit satellite; determining a second delay parameter, wherein the second delay parameter reflects the ratio between the third delay of the high-Earth orbit satellite transmitting downlink data to the gateway station via the low-Earth orbit satellite and the fourth delay of the high-Earth orbit satellite directly transmitting downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station using a logistic regression algorithm model based on the second power parameter and the second delay parameter.

[0090] Specifically, refer to Figure 5 As shown, when the low-orbit satellite 102 determines, through real-time coordinate monitoring and coverage calculation, that its coverage area is gradually moving away from the gateway station 103 (e.g., the overlapping area between the two continues to decrease and falls below a preset threshold), it needs to first determine whether to trigger the communication disconnection process through dynamic evaluation of power parameters and delay parameters. The specific operation is as follows:

[0091] First, the low-orbit satellite 102 re-acquires in real time the downlink signal power P1' transmitted from the high-orbit satellite 101 to the gateway station and its own current signal transmission power P2' towards the gateway station 103, and calculates the second power parameter using a preset formula. :

[0092] (12)

[0093] Meanwhile, based on its own, high-orbit satellite 101, and gateway station 103's real-time updated azimuth coordinates, low-orbit satellite 102 recalculates the delays for two types of transmission paths: one is the third delay for high-orbit satellite 101 transmitting downlink data to gateway station 103 via low-orbit satellite 102. :

[0094] (13)

[0095] In the formula, This represents the current distance between high-orbit satellite 101 and low-orbit satellite 102. ' represents the current distance between low-orbit satellite 102 and gateway station 103, and C represents the signal propagation speed.

[0096] Another type is the fourth delay in the direct transmission of downlink data from high-orbit satellite 101 to gateway station 103. :

[0097] (14)

[0098] Given the current distance between high-orbit satellite 101 and gateway station 103, the second delay parameter k is then calculated using the formula. τ ':

[0099] (15)

[0100] Then, based on the logistic regression algorithm, it is determined whether to disconnect the communication connection: Low-Earth Orbit Satellite 102 will send the second power parameter With the second delay parameter k τ 'Substitute the preset logistic regression algorithm model (consistent with the model used when establishing the connection to ensure consistent judgment criteria), first calculate the linear prediction value u':

[0101] (16)

[0102] In the formula, α0 is the intercept term, and α1 and α2 are preset weight coefficients.

[0103] The probability value L(u') is then obtained using the Sigmoid function:

[0104] L(u') (17)

[0105] If L(u') < 0.5, it indicates that the communication connection with gateway station 103 needs to be disconnected; if L(u') ≥ 0.5, it is determined that the communication connection will not be disconnected temporarily, and parameter changes will be continuously monitored.

[0106] By employing the above methods, interference risks and synchronization changes can be captured in real time using the second power parameter and the second delay parameter. Furthermore, the consistent logistic regression algorithm model used in the connection establishment phase ensures unified judgment criteria, avoiding interference residue and data loss caused by blind disconnection or delayed disconnection. This further enhances the dynamic prevention and control capabilities against co-frequency interference between high-orbit satellite 101 and low-orbit satellite 102, while minimizing the impact on the operational flexibility of low-orbit satellite 102.

[0107] Optionally, the operation of disconnecting the communication connection with the high-orbit satellite and the gateway station includes: sending a request to disconnect the communication connection to the high-orbit satellite; after confirmation by the high-orbit satellite, the low-orbit satellite disconnects the downlink between itself and the high-orbit satellite; after the low-orbit satellite completes all downlink data transmission, it sends a request to the gateway station to disconnect the communication connection; and if the gateway station confirms that the communication connection can be disconnected, the low-orbit satellite disconnects the downlink between itself and the gateway station.

[0108] Specifically, when the low-Earth orbit satellite 102 determines that the communication connection needs to be disconnected based on the logistic regression algorithm model, the low-Earth orbit satellite 102 first sends a disconnection request, including the current link status and data transmission progress, to the high-Earth orbit satellite 101 through the established second downlink link (the link between the high-Earth orbit satellite 101 and the low-Earth orbit satellite 102). After the high-Earth orbit satellite 101 sends back confirmation of the disconnection, the low-Earth orbit satellite 102 immediately terminates signal transmission and reception on the second downlink link with the high-Earth orbit satellite 101, completing the disconnection of the link with the high-Earth orbit satellite 101. Subsequently, the low-Earth orbit satellite 102 prioritizes processing downlink data that has been received but not forwarded to the gateway station 103. After all downlink data has been completely transmitted to the gateway station 103 through the first downlink link (the link between the low-Earth orbit satellite 102 and the gateway station 103), a request to disconnect the communication connection with the gateway station 103 is generated. This request includes confirmation of data transmission completion and a link release instruction, and is sent to the gateway station 103.

[0109] After the gateway station 103 confirms through data verification that it has fully received all downlink data forwarded by the low-Earth orbit satellite 102, and that its direct transmission link (first downlink) with the high-Earth orbit satellite 101 is operating normally and there is no risk of interference, and sends back a confirmation message that the communication connection has been disconnected, the low-Earth orbit satellite 102 stops sending signals to the gateway station 103 and closes the first downlink.

[0110] By using the above methods, the entire link is finally disconnected, ensuring the integrity of data transmission while avoiding additional interference during the disconnection process.

[0111] In addition, refer to Figure 1 As shown, according to a second aspect of this embodiment, a storage medium is provided. The storage medium includes a stored program, wherein, when the program is executed, a processor performs any of the methods described above.

[0112] Therefore, according to this embodiment, this application avoids interference from low-Earth orbit satellite co-channel signals with high-Earth orbit satellite gateway station reception without adjusting the low-Earth orbit satellite's operating orbit or shutting down the core communication frequency band, thus ensuring the operational flexibility and communication coverage capability of the low-Earth orbit satellite. Furthermore, it solves the technical problem in the prior art where using regional avoidance or beam avoidance strategies to avoid co-channel interference from low-Earth orbit satellites to high-Earth orbit satellite gateway stations would greatly limit the operational flexibility of low-Earth orbit satellites, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference prevention and control with the operational efficiency of low-Earth orbit satellites.

[0113] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that the present invention is not limited to the described order of actions, because according to the present invention, some steps can be performed in other orders or simultaneously. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to the present invention.

[0114] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods according to the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) and includes several instructions to cause a terminal device (which may be a mobile phone, computer, server, or network device, etc.) to execute the methods described in the various embodiments of the present invention.

[0115] Example 2

[0116] Figure 6 An interference avoidance device for low-Earth orbit (LEO) satellite links to high-Earth orbit (HEO) satellites according to this embodiment is shown. This device corresponds to the method described in Embodiment 1. (Reference) Figure 6 As shown, the device includes: a calculation module 610, used to calculate the azimuth coordinates of the low-orbit satellite in real time and determine whether it has entered the coverage area of ​​the high-orbit satellite; a sameness determination module 620, used to determine whether the signal frequency bands for downlink data transmission between the high-orbit satellite and the low-orbit satellite are the same when it is determined that it has entered the coverage area of ​​the high-orbit satellite; a coverage determination module 630, used to determine in real time whether the coverage area of ​​the low-orbit satellite covers the gateway station receiving downlink data from the high-orbit satellite when it is determined that the signal frequency bands for downlink data transmission between the high-orbit satellite and the low-orbit satellite are the same; a connection determination module 640, used to determine whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite when it is determined that the coverage area of ​​the low-orbit satellite covers the gateway station; and a transmission module 650, used to receive downlink data from the high-orbit satellite and transmit the downlink data to the gateway station when it is determined that a communication connection has been established with the gateway station.

[0117] Optionally, the operation of receiving downlink data from a high-orbit satellite and transmitting the downlink data to a gateway station includes: sending a communication request to the gateway station to establish a first downlink according to a preset protocol; if the gateway station confirms that the first downlink can be established, sending a communication request to the high-orbit satellite to establish a second downlink from the high-orbit satellite to the low-orbit satellite; if the high-orbit satellite confirms that the second downlink can be established, receiving downlink data from the high-orbit satellite via the second downlink and transmitting the downlink data to the gateway station via the first downlink.

[0118] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite includes: determining a first power parameter, which reflects the ratio of the signal power of the low-orbit satellite to the signal power of the high-orbit satellite; determining a first delay parameter, wherein the first delay parameter reflects the ratio between a first delay of the high-orbit satellite transmitting downlink data to the gateway station via the low-orbit satellite and a second delay of the high-orbit satellite directly transmitting downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0119] Optionally, the operation of determining the first delay parameter includes: calculating in real time the first distance between the low-Earth orbit satellite and the high-Earth orbit satellite and the second distance between the low-Earth orbit satellite and the gateway station, and determining the first delay based on the first distance and the second distance; calculating in real time the third distance between the high-Earth orbit satellite and the gateway station, and calculating the second delay based on the third distance; and determining the first delay parameter based on the first delay and the second delay.

[0120] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter includes: using a pre-trained logistic regression algorithm model to determine whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0121] Optionally, the device further includes a connection determination module, used to determine whether the low-Earth orbit (LEO) satellite has lost communication with the gateway station through the following steps: when the LEO satellite determines in real time that its coverage area is leaving the gateway station, determining whether to lose communication with the gateway station based on the power and delay of the high-Earth orbit (HEO) satellite and the LEO satellite; and when it is determined that the communication connection with the gateway station has been lost, disconnecting the communication connection with the HEO satellite and the gateway station; wherein, the operation of determining whether to lose communication with the gateway station based on the power and delay of the HEO satellite and the LEO satellite includes: determining a second power parameter, the second power parameter reflecting the ratio of the signal power of the LEO satellite to the signal power of the HEO satellite; determining a second delay parameter, wherein the second delay parameter reflects the ratio between the third delay of the HEO satellite transmitting downlink data to the gateway station via the LEO satellite and the fourth delay of the HEO satellite directly transmitting downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station using a logistic regression algorithm model based on the second power parameter and the second delay parameter.

[0122] Optionally, the operation of disconnecting the communication connection with the high-orbit satellite and the gateway station includes: sending a request to disconnect the communication connection to the high-orbit satellite; after confirmation by the high-orbit satellite, the low-orbit satellite disconnects the downlink between itself and the high-orbit satellite; after the low-orbit satellite completes all downlink data transmission, it sends a request to the gateway station to disconnect the communication connection; and if the gateway station confirms that the communication connection can be disconnected, the low-orbit satellite disconnects the downlink between itself and the gateway station.

[0123] Therefore, according to this embodiment, this application avoids interference from low-Earth orbit satellite co-channel signals with high-Earth orbit satellite gateway station reception without adjusting the low-Earth orbit satellite's operating orbit or shutting down the core communication frequency band, thus ensuring the operational flexibility and communication coverage capability of the low-Earth orbit satellite. Furthermore, it solves the technical problem in the prior art where using regional avoidance or beam avoidance strategies to avoid co-channel interference from low-Earth orbit satellites to high-Earth orbit satellite gateway stations would greatly limit the operational flexibility of low-Earth orbit satellites, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference prevention and control with the operational efficiency of low-Earth orbit satellites.

[0124] Example 3

[0125] Figure 7 An interference avoidance device for low-Earth orbit (LEO) satellite links to high-Earth orbit (HEO) satellites according to this embodiment is shown. This device corresponds to the method described in Embodiment 1. (Reference) Figure 7As shown, the device includes: a processor 710; and a memory 720 connected to the processor 710, used to provide the processor 710 with instructions to process the following steps: calculating the azimuth coordinates of the low-Earth orbit satellite in real time and determining whether it has entered the coverage area of ​​the high-Earth orbit satellite; if it is determined that it has entered the coverage area of ​​the high-Earth orbit satellite, determining whether the signal frequency band for downlink data transmission between the high-Earth orbit satellite and the low-Earth orbit satellite is the same frequency band; if it is determined that the signal frequency band for downlink data transmission between the high-Earth orbit satellite and the low-Earth orbit satellite is the same frequency band, determining in real time whether the coverage area of ​​the low-Earth orbit satellite covers the gateway station receiving downlink data from the high-Earth orbit satellite; if it is determined that the coverage area of ​​the low-Earth orbit satellite covers the gateway station, determining whether to establish a communication connection with the gateway station based on the power and delay of the high-Earth orbit satellite and the low-Earth orbit satellite; and if it is determined that a communication connection has been established with the gateway station, receiving downlink data from the high-Earth orbit satellite and transmitting the downlink data to the gateway station.

[0126] Optionally, the operation of receiving downlink data from a high-orbit satellite and transmitting the downlink data to a gateway station includes: sending a communication request to the gateway station to establish a first downlink according to a preset protocol; if the gateway station confirms that the first downlink can be established, sending a communication request to the high-orbit satellite to establish a second downlink from the high-orbit satellite to the low-orbit satellite; if the high-orbit satellite confirms that the second downlink can be established, receiving downlink data from the high-orbit satellite via the second downlink and transmitting the downlink data to the gateway station via the first downlink.

[0127] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite includes: determining a first power parameter, which reflects the ratio of the signal power of the low-orbit satellite to the signal power of the high-orbit satellite; determining a first delay parameter, wherein the first delay parameter reflects the ratio between a first delay of the high-orbit satellite transmitting downlink data to the gateway station via the low-orbit satellite and a second delay of the high-orbit satellite directly transmitting downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0128] Optionally, the operation of determining the first delay parameter includes: calculating in real time the first distance between the low-Earth orbit satellite and the high-Earth orbit satellite and the second distance between the low-Earth orbit satellite and the gateway station, and determining the first delay based on the first distance and the second distance; calculating in real time the third distance between the high-Earth orbit satellite and the gateway station, and calculating the second delay based on the third distance; and determining the first delay parameter based on the first delay and the second delay.

[0129] Optionally, the operation of determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter includes: using a pre-trained logistic regression algorithm model to determine whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

[0130] Optionally, the memory 720 is further configured to provide the processor 710 with instructions to process the following steps: when a low-Earth orbit satellite determines in real time that its coverage area is leaving the gateway station, determining whether to disconnect the communication connection with the gateway station based on the power and delay of the high-Earth orbit satellite and the low-Earth orbit satellite; and when it is determined that the communication connection with the gateway station is disconnected, disconnecting the communication connection with the high-Earth orbit satellite and the gateway station; wherein the operation of determining whether to disconnect the communication connection with the gateway station based on the power and delay of the high-Earth orbit satellite and the low-Earth orbit satellite includes: determining a second power parameter, the second power parameter reflecting the ratio of the signal power of the low-Earth orbit satellite to the signal power of the high-Earth orbit satellite; determining a second delay parameter, wherein the second delay parameter reflects the ratio between a third delay in which the high-Earth orbit satellite transmits downlink data to the gateway station via the low-Earth orbit satellite and a fourth delay in which the high-Earth orbit satellite directly transmits downlink data to the gateway station; and determining whether to establish a communication connection with the gateway station using a logistic regression algorithm model based on the second power parameter and the second delay parameter.

[0131] Optionally, the operation of disconnecting the communication connection with the high-orbit satellite and the gateway station includes: sending a request to disconnect the communication connection to the high-orbit satellite; after confirmation by the high-orbit satellite, the low-orbit satellite disconnects the downlink between itself and the high-orbit satellite; after the low-orbit satellite completes all downlink data transmission, it sends a request to the gateway station to disconnect the communication connection; and if the gateway station confirms that the communication connection can be disconnected, the low-orbit satellite disconnects the downlink between itself and the gateway station.

[0132] Therefore, according to this embodiment, this application avoids interference from low-Earth orbit satellite co-channel signals with high-Earth orbit satellite gateway station reception without adjusting the low-Earth orbit satellite's operating orbit or shutting down the core communication frequency band, thus ensuring the operational flexibility and communication coverage capability of the low-Earth orbit satellite. Furthermore, it solves the technical problem in the prior art where using regional avoidance or beam avoidance strategies to avoid co-channel interference from low-Earth orbit satellites to high-Earth orbit satellite gateway stations would greatly limit the operational flexibility of low-Earth orbit satellites, reduce the coverage area, or decrease communication capacity, making it difficult to balance interference prevention and control with the operational efficiency of low-Earth orbit satellites.

[0133] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0134] In the above embodiments of the present invention, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0135] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual coupling, direct coupling, or communication connection may be through some interfaces; the indirect coupling or communication connection between units or modules may be electrical or other forms.

[0136] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0137] Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0138] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0139] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for avoiding link interference between low-Earth orbit (LEO) satellites and high-Earth orbit (HEO) satellites, characterized in that, include: Calculate the low-orbit satellite's own azimuth coordinates in real time to determine whether it has entered the coverage area of ​​the high-orbit satellite; If it is determined that the high-orbit satellite has entered the coverage area of ​​the high-orbit satellite, it is determined whether the downlink data transmission signal frequency band of the high-orbit satellite and the low-orbit satellite is the same frequency band; If it is determined that the downlink data transmission signal frequency band of the high-orbit satellite and the low-orbit satellite is the same, it is determined in real time whether the coverage area of ​​the low-orbit satellite covers the gateway station receiving the downlink data of the high-orbit satellite; If it is determined that the coverage area of ​​the low-orbit satellite covers the gateway station, a decision is made on whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite. as well as If a communication connection is established with the gateway station, the downlink data is received from the high-orbit satellite and transmitted to the gateway station. The gateway station receives two downlink data streams, one directly transmitted from the high-orbit satellite and the other relayed from the low-orbit satellite, and verifies the consistency of the two downlink data streams by comparing data check codes or synchronizing transmission timing.

2. The method according to claim 1, characterized in that, The operation of receiving downlink data from the high-orbit satellite and transmitting the downlink data to the gateway station includes: A communication request to establish a first downlink is sent to the gateway station according to a preset protocol; If the gateway station confirms the establishment of the first downlink, it sends a communication request to the high-orbit satellite to establish a second downlink from the high-orbit satellite to the low-orbit satellite. If the high-orbit satellite confirms the establishment of the second downlink, the downlink data is received from the high-orbit satellite via the second downlink, and the downlink data is transmitted to the gateway station via the first downlink.

3. The method according to claim 1, characterized in that, The operation of determining whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite includes: A first power parameter is determined, which reflects the ratio of the signal power of the low-orbit satellite to the signal power of the high-orbit satellite; A first delay parameter is determined, wherein the first delay parameter reflects the ratio between a first delay in the transmission of downlink data from the high-orbit satellite to the gateway station via the low-orbit satellite and a second delay in the transmission of downlink data directly from the high-orbit satellite to the gateway station; and Based on the first power parameter and the first delay parameter, determine whether to establish a communication connection with the gateway station.

4. The method according to claim 3, characterized in that, The operation of determining the first delay parameter includes: The first distance between the low-Earth orbit satellite and the high-Earth orbit satellite and the second distance between the low-Earth orbit satellite and the gateway station are calculated in real time, and the first delay is determined based on the first distance and the second distance. Calculate the third distance between the high-orbit satellite and the gateway station in real time, and calculate the second delay based on the third distance; and The first delay parameter is determined based on the first delay and the second delay.

5. The method according to claim 3, characterized in that, The operation of determining whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter includes: Using a pre-trained logistic regression algorithm model, a decision is made on whether to establish a communication connection with the gateway station based on the first power parameter and the first delay parameter.

6. The method according to claim 5, characterized in that, Also includes: If a low-orbit satellite determines in real time that the coverage area is leaving the gateway station, it determines whether to disconnect the communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite. as well as If it is determined that the communication connection with the gateway station has been lost, the communication connection with the high-orbit satellite and the gateway station shall be lost. The operation of determining whether to disconnect the communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite includes: A second power parameter is determined, which reflects the ratio of the signal power of the low-orbit satellite to the signal power of the high-orbit satellite; A second delay parameter is determined, wherein the second delay parameter reflects the ratio between a third delay in the transmission of downlink data from the high-orbit satellite to the gateway station via the low-orbit satellite and a fourth delay in the transmission of downlink data directly from the high-orbit satellite to the gateway station; and Based on the second power parameter and the second delay parameter, the logistic regression algorithm model is used to determine whether to disconnect the communication connection with the gateway station.

7. The method according to claim 6, characterized in that, The operation of disconnecting the communication connection with the high-orbit satellite and the gateway station includes: Send a request to disconnect the communication connection to the high-orbit satellite; After the high-orbit satellite is confirmed, the low-orbit satellite disconnects the downlink from the high-orbit satellite. After completing all downlink data transmissions, the low-orbit satellite sends a request to the gateway station to disconnect the communication connection; and If the gateway station confirms that the communication connection has been lost, the low-orbit satellite will disconnect the downlink between itself and the gateway station.

8. A storage medium, characterized in that, The storage medium includes a stored program, wherein, when the program is executed, the method described in any one of claims 1 to 7 is performed by a processor.

9. A device for avoiding interference between low-Earth orbit (LEO) satellite links and high-Earth orbit (HEO) satellites, used for LEO satellites, characterized in that, include: The calculation module is used to calculate the low-orbit satellite's own azimuth coordinates in real time and determine whether it has entered the coverage area of ​​the high-orbit satellite. The same determination module is used to determine whether the downlink data transmission signal frequency bands of the high-orbit satellite and the low-orbit satellite are the same when it is determined that the high-orbit satellite has entered the coverage area of ​​the high-orbit satellite. The coverage determination module is used to determine in real time whether the coverage area of ​​the low-orbit satellite covers the gateway station receiving the downlink data from the high-orbit satellite when the signal frequency band for downlink data transmission between the high-orbit satellite and the low-orbit satellite is the same. The connection determination module is used to determine whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite when it is determined that the coverage area of ​​the low-orbit satellite covers the gateway station. as well as The transmission module is used to receive downlink data from the high-orbit satellite and transmit the downlink data to the gateway station when it is determined that a communication connection has been established with the gateway station; the gateway station receives two downlink data streams respectively from the direct transmission from the high-orbit satellite and the relay from the low-orbit satellite, and performs consistency verification on the two downlink data streams by comparing data check codes or by synchronizing transmission timing.

10. A device for avoiding interference between low-Earth orbit (LEO) satellite links and high-Earth orbit (HEO) satellites, used for LEO satellites, characterized in that, include: processor; as well as A memory, connected to the processor, for providing the processor with instructions to perform the following processing steps: Calculate the low-orbit satellite's own azimuth coordinates in real time to determine whether it has entered the coverage area of ​​the high-orbit satellite; If it is determined that the high-orbit satellite has entered the coverage area of ​​the high-orbit satellite, it is determined whether the downlink data transmission signal frequency band of the high-orbit satellite and the low-orbit satellite is the same frequency band; If it is determined that the downlink data transmission signal frequency band of the high-orbit satellite and the low-orbit satellite is the same, it is determined in real time whether the coverage area of ​​the low-orbit satellite covers the gateway station receiving the downlink data of the high-orbit satellite; If it is determined that the coverage area of ​​the low-orbit satellite covers the gateway station, a decision is made on whether to establish a communication connection with the gateway station based on the power and delay of the high-orbit satellite and the low-orbit satellite. as well as If a communication connection is established with the gateway station, the downlink data is received from the high-orbit satellite and transmitted to the gateway station. The gateway station receives two downlink data streams, one directly transmitted from the high-orbit satellite and the other relayed from the low-orbit satellite, and verifies the consistency of the two downlink data streams by comparing data check codes or synchronizing transmission timing.

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