Method, system and electronic device for coordinating interference

Abstract

The present application discloses a method, system and electronic device for coordinating interference. The method includes: detecting the real-time trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; sending an assist sensing instruction to a second low earth orbit satellite when it is detected that the first low earth orbit satellite is operating in an interference area where interference exists with a geostationary orbit satellite; receiving the sensing result returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate a sensing result; determining the operating state of the first low earth orbit satellite based on the sensing result, wherein the operating state at least includes: the transmission power of the first low earth orbit satellite. The present application solves the technical problem that the overall performance is poor due to the low frequency resource utilization and throughput of satellites in the related technology, and the mutual interference of signals between satellites.

Description

Technical Field

[0001] The present application relates to the field of satellite communication networks, and in particular, to a method, system and electronic equipment for coordinating interference. Background Art

[0002] In the future 6G mobile communication system, there will be many challenges and changes. In recent years, the satellite-to-ground network has achieved vigorous development. The space information network has broken the unfavorable situation of repeated construction and independent operation of various systems, and has promoted the unified, orderly and efficient allocation and use of various resources such as frequency resources and space orbit resources, playing an important role in all aspects of people's lives. However, with the rapid increase in people's demand for wireless communication services, available frequency resources are becoming increasingly scarce. At the same time, due to the existence of interference between satellites and the ground and between satellites, the overall performance has been reduced in serious cases.

[0003] At present, the global satellite communication system is still dominated by geostationary orbit (GSO) satellites. Many frequency bands adopt interference protection strategies for GSO as the main users. The development of low-orbit Internet constellations is bound to pose severe challenges to the co-frequency coexistence of existing GSO.

[0004] To address the above-mentioned problems, no effective solution has been proposed yet. Summary of the invention

[0005] The embodiments of the present application provide a method, system and electronic device for coordinating interference to at least solve the technical problems in the related art of low frequency resource utilization and throughput of satellites, and signal interference between satellites, resulting in poor overall performance.

[0006] According to one aspect of an embodiment of the present application, a method for coordinating interference is provided, including: detecting a real-time operating trajectory of a first low-Earth orbit satellite, wherein the first low-Earth orbit satellite is used to transmit data; in the case of detecting that the first low-Earth orbit satellite is operating into an interference area where interference exists with a geostationary orbit satellite, sending an assist sensing instruction to a second low-Earth orbit satellite; receiving sensing results returned by the second low-Earth orbit satellite, wherein the second low-Earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate sensing results; and determining the operating status of the first low-Earth orbit satellite based on the sensing results, wherein the operating status includes at least: the transmission power of the first low-Earth orbit satellite.

[0007] Optionally, determining the operating state of the first low earth orbit satellite based on the sensing result includes: when the sensing result indicates that the channel state of the geostationary orbit satellite is an idle state, determining that the operating mode of the first low earth orbit satellite is a coverage mode, and the transmission power is set to a first transmission power

[0008] Optionally, when the sensing result indicates that the channel state of the geostationary orbit satellite is busy, the working mode of the first low earth orbit satellite is determined to be the substrate mode, and the transmission power is set to the second transmission power in,

[0009] Optionally, determining the operating status of the first low-Earth orbit satellite based on the perception result includes: detecting whether the channel status of the geostationary orbit satellite remains in an idle state or a busy state for a consecutive predetermined number of time slots to obtain a detection result; when the detection result indicates that the channel status remains in an idle state or a busy state for a consecutive predetermined number of time slots, determining the operating status of the first low-Earth orbit satellite based on the perception result.

[0010] Optionally, when the detection result indicates that there is a change in the channel state in a continuous predetermined number of time slots, the data throughput of the first low earth orbit satellite is optimized.

[0011] Optionally, optimizing the data throughput of the first low earth orbit satellite includes: generating an optimization problem, wherein a first expression P1 of the optimization problem is:

[0012]

[0013]

[0014]

[0015]

[0016]

[0017] C5:T min ≤T s ≤Θτ-T t

[0018] C6: 1≤Θ≤Θ max ;

[0019] in, When the objective function is maximized, Perception duration T of the perception stage s And the value of the spectrum sensing interval Θ, represents the average throughput of the first low earth orbit satellite. Constraint (C1) requires that the minimum throughput rate of the first low earth orbit satellite is greater than the target threshold. Constraint (C2) limits the total transmit power of the first low earth orbit satellite to a predetermined value Constraints (C3) and (C4) are the average interference under the substrate model at the GEO system and transient interference Limit to a predetermined threshold Constraints (C5) and (C6) are used to limit the sensing duration and sensing interval, respectively, where τ represents the time slot, T t represents the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process; and solves the optimization problem.

[0020] Optionally, solving the optimization problem includes: solving the expression of the optimization problem using a two-dimensional line search method to obtain the optimal Θ and T s ; The optimal Θ and T s As given Θ and T s , transform the second expression of the optimization problem into the second expression P2: determine the convex optimization technique to solve P2, determine the dual function of P2; determine that the Karush-Kuhn-Tucker (KKT) condition is a necessary and sufficient condition for the global optimality of P2, and determine the optimal primal solution and dual solution of P2.

[0021] According to another aspect of an embodiment of the present application, a system for coordinating interference is also provided, the system comprising: a first low Earth orbit satellite for transmitting data, wherein the first low Earth orbit satellite is used to detect its own real-time operating trajectory, and when it is detected that the first low Earth orbit satellite is operating into an interference area where interference exists with a geostationary orbit satellite, the first low Earth orbit satellite sends an assisting sensing instruction to a second low Earth orbit satellite, receives sensing results returned by the second low Earth orbit satellite, and determines the operating state of the first low Earth orbit satellite based on the sensing results, wherein the operating state includes at least: the transmission power of the first low Earth orbit satellite; and a second low Earth orbit satellite, used to receive the assisting sensing instruction, perform spectrum sensing on the geostationary orbit satellite to generate sensing results, and send the sensing results to the first low Earth orbit satellite.

[0022] According to another aspect of an embodiment of the present application, there is also provided a device for coordinating interference, including: a detection module for detecting the real-time operating trajectory of a first low-Earth orbit satellite, wherein the first low-Earth orbit satellite is used to transmit data; a sending module for sending an assisting sensing instruction to a second low-Earth orbit satellite when it is detected that the first low-Earth orbit satellite is operating into an interference area where interference exists with a geostationary orbit satellite; a receiving module for receiving the sensing result returned by the second low-Earth orbit satellite, wherein the second low-Earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate a sensing result; a determining module for determining the operating status of the first low-Earth orbit satellite based on the sensing result, wherein the operating status includes at least: the transmission power of the first low-Earth orbit satellite.

[0023] According to another aspect of an embodiment of the present application, a non-volatile storage medium is further provided, the storage medium including a stored program, wherein when the program is running, a device where the storage medium is located is controlled to execute any one of the methods for coordinating interference.

[0024] According to another aspect of an embodiment of the present application, there is also provided an electronic device, comprising: a processor; and a memory for storing instructions executable by the processor; wherein the processor is configured to execute the instructions to implement any one of the methods for coordinating interference.

[0025] In an embodiment of the present application, a spectrum sharing framework of a space information network consisting of a geostationary orbit (GEO) satellite and two low earth orbit (LEO) satellites is adopted, one of which is a spectrum sensing LEO (SLEO, i.e., the second low earth orbit satellite) used to sense the spectrum occupancy status of GEO, and the other is a data transmission LEO (DLEO, i.e., the first low earth orbit satellite), which is allowed to access the shared spectrum of GEO with the help of SLEO. In order to improve the throughput of DLEO satellites, a spectrum sharing framework based on two stages is constructed, thereby achieving the technical effect of considering from the perspective of low-orbit satellites, coordinating their interference with high-orbit satellites and the ground, and maximizing the throughput of low-orbit satellites without interfering with the two nodes of high-orbit satellites and the ground, thereby solving the technical problem of poor overall performance due to the low frequency resource utilization and throughput of satellites in related technologies, and the mutual interference of signals between satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0027] Figure 1 is a flowchart of an optional method for coordinating interference according to an embodiment of the present application;

[0028] Figure 2 A schematic diagram of a satellite system model and an interference analysis model between a GEO satellite and a LEO satellite in an embodiment of the present application;

[0029] Figure 3 This is a schematic diagram of the process flow of the GEO satellite and LEO satellite spectrum sharing optimization problem in an embodiment of the present application;

[0030] Figure 4 This is a diagram of the interference analysis model between satellite and ground networks in an embodiment of the present application;

[0031] Figure 5 This is a flow chart of satellite-to-ground network spectrum sharing in an embodiment of the present application;

[0032] Figure 6 It is a schematic diagram of the structure of an optional device for coordinating interference according to an embodiment of the present application. DETAILED DESCRIPTION

[0033] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0034] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0035] According to an embodiment of the present application, an embodiment of a method for coordinating interference is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0036] Figure 1is a method for coordinating interference according to an embodiment of the present application, such as Figure 1 As shown, the method comprises the following steps:

[0037] Step S102, detecting a real-time running trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; the first low earth orbit satellite is a DLEO;

[0038] Step S104, when it is detected that the first low earth orbit satellite moves into an interference area where interference exists with the geostationary orbit satellite, an assist sensing instruction is sent to a second low earth orbit satellite, namely, SLEO;

[0039] Step S106, receiving a sensing result returned by a second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on a spectrum occupancy state of a geostationary orbit satellite to generate a sensing result, and the geostationary orbit satellite is GEO;

[0040] Step S108, determining the operating status of the first low earth orbit satellite based on the sensing result, wherein the operating status at least includes: the transmission power of the first low earth orbit satellite.

[0041] In the method for coordinating interference, the real-time operation trajectory of a first low earth orbit satellite is detected, wherein the first low earth orbit satellite is used to transmit data; when it is detected that the first low earth orbit satellite is operating in an interference area where interference exists with a geostationary orbit satellite, an assist sensing instruction is sent to a second low earth orbit satellite; the sensing result returned by the second low earth orbit satellite is received, wherein the second low earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate a sensing result; and the operation state of the first low earth orbit satellite is determined based on the sensing result, wherein the operation state includes at least: the transmission power of the first low earth orbit satellite, thereby achieving the technical effect of coordinating the interference with the high orbit satellite and the ground from the perspective of the low earth orbit satellite, and maximizing the throughput of the low earth orbit satellite without interfering with the two nodes of the high orbit satellite and the ground, thereby solving the technical problem of poor overall performance due to low frequency resource utilization and throughput of satellites in related technologies and mutual signal interference between satellites.

[0042] It can be understood that in the embodiment of the present application, a spectrum sharing framework of a space information network consisting of a geostationary orbit (GEO) satellite and two low earth orbit (LEO) satellites is adopted, one of which is a spectrum sensing LEO (SLEO, i.e., the second low earth orbit satellite) used to sense the spectrum occupancy status of GEO, and the other is a data transmission LEO (DLEO, i.e., the first low earth orbit satellite), which is allowed to access the shared spectrum of GEO with the help of SLEO. In order to improve the throughput of DLEO satellites, a spectrum sharing framework based on two stages is constructed.

[0043] In some embodiments of the present application, determining the operating state of the first low earth orbit satellite based on the sensing result includes: when the sensing result indicates that the channel state of the geostationary orbit satellite is idle, determining that the operating mode of the first low earth orbit satellite is a coverage mode, and the transmission power is set to the first transmission power

[0044] In some other embodiments of the present application, when the sensing result indicates that the channel state of the geostationary orbit satellite is busy, the working mode of the first low earth orbit satellite is determined to be the substrate mode, and the transmission power is set to the second transmission power in,

[0045] As an optional implementation, the operating status of the first low-Earth orbit satellite is determined based on the perception result, and the detection result can also be obtained by detecting whether the channel status of the geostationary orbit satellite remains idle or busy for a consecutive predetermined number of time slots; when the detection result indicates that the channel status remains idle or busy for a consecutive predetermined number of time slots, the operating status of the first low-Earth orbit satellite is determined based on the perception result.

[0046] Optionally, when the detection result indicates that there is a change in the channel state in a continuous predetermined number of time slots, the data throughput of the first low earth orbit satellite is optimized.

[0047] Specifically, optimizing the data throughput of the first low earth orbit satellite includes: generating an optimization problem, wherein a first expression P1 of the optimization problem is:

[0048]

[0049]

[0050]

[0051]

[0052]

[0053] C5:T min ≤T s ≤Θτ-T t

[0054] C6: 1≤Θ≤Θ max ;

[0055] in, When the objective function is maximized, Perception duration T of the perception stage s And the value of the spectrum sensing interval Θ, represents the average throughput of the first low earth orbit satellite. Constraint (C1) requires that the minimum throughput rate of the first low earth orbit satellite is greater than the target threshold. Constraint (C2) limits the total transmit power of the first low earth orbit satellite to a predetermined value Constraints (C3) and (C4) are the average interference under the substrate model at the GEO system and transient interference Limit to a predetermined threshold Constraints (C5) and (C6) are used to limit the sensing duration and sensing interval, respectively, where τ represents the time slot, T t represents the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process; and solves the optimization problem.

[0056] In some optional embodiments of the present application, solving the optimization problem can be achieved by the following steps: using a two-dimensional line search method to solve the expression of the optimization problem to obtain the optimal Θ and T s ; The optimal Θ and T s As given Θ and T s , transform the second expression of the optimization problem into the second expression P2: determine the convex optimization technique to solve P2, determine the dual function of P2; determine that the Karush-Kuhn-Tucker (KKT) condition is a necessary and sufficient condition for the global optimality of P2, and determine the optimal primal solution and dual solution of P2.

[0057] According to another aspect of an embodiment of the present application, a system for coordinating interference is also provided, the system comprising: a first low Earth orbit satellite for transmitting data, wherein the first low Earth orbit satellite is used to detect its own real-time operating trajectory, and when it is detected that the first low Earth orbit satellite is operating into an interference area where interference exists with a geostationary orbit satellite, the first low Earth orbit satellite sends an assisting sensing instruction to a second low Earth orbit satellite, receives sensing results returned by the second low Earth orbit satellite, and determines the operating state of the first low Earth orbit satellite based on the sensing results, wherein the operating state includes at least: the transmission power of the first low Earth orbit satellite; and a second low Earth orbit satellite, used to receive the assisting sensing instruction, perform spectrum sensing on the geostationary orbit satellite to generate sensing results, and send the sensing results to the first low Earth orbit satellite.

[0058] The specific implementation methods of the present application are described in detail below in conjunction with the accompanying drawings, but it should be understood that the protection scope of the present application is not limited by the specific implementation methods.

[0059] Figure 2 Satellite system model and interference analysis model between GEO satellite and LEO satellite, including:

[0060] Only when the DLEO satellite moves into the interference area will the received signal-to-noise ratio of the DLEO and GEO satellites change significantly. This means that the DLEO satellite cannot transmit signals at will when it enters the interference area, so as not to interfere with the GEO system. Therefore, a spectrum sharing framework that relies on two stages to improve the throughput of DLEO satellites is envisioned, in which the DLEO satellite is able to access the shared spectrum with the help of SLEO. Specifically, in the first stage, SLEO is called for spectrum sensing to detect spectrum holes of the GEO system, and the DLEO satellite can access the shared spectrum in overlay mode and underlay mode under the second stage.

[0061] ① Satellite system model - Spectrum sharing between LEO and GEO system models is considered. GEO system, as the primary user, has priority to use the frequency. LEO satellites act as secondary systems and should be coordinated to avoid disrupting the existing geosynchronous orbit system. Figure 2 As shown, spectrum sensing LEO (SLEO) is used to sense the spectrum occupancy status of GEO and allow data transmission LEO (DLEO) satellites to access the shared spectrum of GEO with the help of SLEO. In addition, in this cognitive satellite network, it is assumed that the ground stations of the three systems are connected by high-speed lossless optical fibers and exchange satellite ephemeris with each other.

[0062] The model includes a DLEO satellite and its ground station, recorded as S3 and E3, a GEO satellite and its ground station, recorded as S2 and E2, and a SLEO satellite and its ground station, recorded as S1 and E1. Without loss of generality, S2 and its ground station E2 are located on the same line as the origin of the earth. In addition, the relative positions of E1, E2, and E3 are also crucial factors in interference analysis. Let σ E1→E2 , σ E2→E3 They represent the geocentric angles between E1 and E2, and between E2 and E3, respectively. Generally speaking, these two angles can be used as constants in the next step of interference analysis. Ei→Ej |i∈(1,2,3),j∈(1,2,3)} represents the distance between Ei and Ej, {d Si→Sj |i∈(1,2,3),j∈(1,2,3)}, represents the distance between Si and Sj, and {d Ei→Sj |i∈(1, 2, 3) ，j ∈(1, 2, 3)}, represents the distance between Ei and Sj. θ1~θ6 are the off-axis angles of E2 toward S3, S3 toward E2, S3 toward E3, E3 toward S2, S2 toward E3, and E2 toward S1, respectively. Let β represent the geocentric angle between S2 and S3, and α represent the geocentric angle between S1 and S2. Obviously, a and β will change as the LEO satellite moves. In addition, the distance d s3→E2 ,d S2→S2 ,d S3→E3 is a function of β, the distance d S1→E2 ,d S1→S2 is a function of α and can be rewritten as

[0063]

[0064]

[0065]

[0066]

[0067]

[0068] Where R is the radius of the Earth, d S1 ,d S2 ,d S3 Respectively represent the distances from S1, S2, and S3 to the center of the earth. In addition, the angles θ1 to θ6 can be derived as follows

[0069]

[0070]

[0071]

[0072]

[0073]

[0074]

[0075] in

[0076]

[0077] ②Interference analysis - such as Figure 2 As shown in the figure, the GEO ground station and GEO satellite will be interfered by the DLEO satellite in the downlink and the DLEO ground station in the uplink, respectively. At the same time, the DLEO ground station and DLEO satellite will also be interfered by the high-orbit satellite system. The analysis method of interference in the downlink is similar to that in the uplink. In this scheme, only the interference in the uplink scenario is discussed.

[0078] The DLEO ground station sends the signal to the corresponding satellite. The power of the signal received by the DLEO satellite can be expressed as

[0079]

[0080] Where P S3 is the ground station transmission power, is the maximum gain of the ground station transmitting antenna, is the gain of the ground station receiving antenna relative to the satellite direction, c is the speed of light, and f is the center frequency of the frequency band. The antenna gain is related to the off-axis angle of the transmitter or receiver in the beam direction, which can be calculated by the beam direction and the position vector of the satellite and the user. When the satellite moves, the angle θ changes, which will cause a dynamic change in the gain.

[0081] The expression for calculating antenna gain is:

[0082]

[0083] Among them, μ=2.07123sin(θ) / sin(θ 3dB ), J1 and J3 are first-order and third-order Bessel functions respectively. θ is the off-axis angle, θ is the angle corresponding to the 3dB beam width, G0 is the maximum antenna gain when the off-axis angle is 0, and its expression is

[0084]

[0085] Where A represents the antenna area and η represents the antenna efficiency. At the same time, DLEO may receive signals from GEO ground stations. Therefore, the interference of GEO ground stations to DLEO satellites can be expressed as

[0086]

[0087] P E2 As the transmitting power of a geostationary orbit station, As the gain of the transmitting antenna of a geostationary earth station in the direction of a geostationary satellite, The gain of a transmitting antenna in the direction of a geostationary earth station acting as a geostationary receiving antenna.

[0088] From the above formula, we can see that both signal power and interference are related to angle β. Therefore, we can conclude that the received signal-to-noise ratio is also a function of angle β, which can be expressed as follows:

[0089]

[0090] N0=kT n B (16)

[0091] where k is the Boltzmann constant, T n represents the equivalent noise temperature of the receiver, and B represents the transponder bandwidth. GEO receives signals from the GEO earth station and can also receive signals from the DLEO earth station. The power of the received signal at the LEO can be expressed as

[0092]

[0093] P E2 is the transmission power of the GEO ground station, is the maximum gain of the GEO ground station transmitting antenna, is the maximum gain of the GEO receiving antenna. The interference of the low-orbit ground station to the geostationary orbit satellite can be expressed as

[0094]

[0095] P E3 As the transmitting power of the ground station, As the gain of the ground station transmitting antenna in the direction of the geosynchronous orbit, As the gain of the ground station receiving antenna in the direction of the ground station. Therefore, the receiving signal-to-noise ratio of the geostationary orbit is also a function of the angle β, which can be expressed as follows;

[0096]

[0097] ③ Perception satellite analysis: Here, the spectrum perception of SLEO in the first stage is analyzed. When DLEO moves to the interference area, the DLEO ground station sends the request information to the SLEO system through the ground optical fiber system for spectrum perception, and then sends the signal. According to the perception results returned by the SLEO system, the shared spectrum access method is selected. Specifically, the GEO signal received by SLEO can be written as

[0098]

[0099]

[0100] by As the gain of the geostationary ground station in the direction of the satellite, As the maximum gain of the satellite receiving antenna. In addition, H0 represents the assumption that there is no GEO system; H1 represents the assumption that the GEO system is in operation. Therefore, the receiving signal-to-noise ratio of SLEO can be expressed as

[0101]

[0102] Obviously, the received signal-to-noise ratio is a function of the angle α and varies with α. The detection probability and false alarm probability can also be derived as follows

[0103]

[0104]

[0105] Where ε represents the detection threshold, T s is the perceived time, f s is the sampling frequency of SLEO. Obviously, the detection probability and false alarm probability are the product of angle α and detection time T s function.

[0106] ④GEO system activity model

[0107] The state of the geostationary orbit system is modeled as a two-state switching Markov chain. Since the satellite channel can be regarded as an AWGN channel where the channel gain is fixed, the SLEO system can obtain the training sequence by repeatedly visiting the GEO coverage area without any prior knowledge. Since the estimation accuracy of the GEO parameters depends on the length of the training sequence, for simplicity, the following analysis assumes that the estimation error can be ignored. The transfer matrix of the hidden Markov model is

[0108]

[0109] Figure 3 Optimize the spectrum sharing problem between GEO satellites and LEO satellites, such as Figure 3 As shown, including:

[0110] S301, detection interval analysis:

[0111] In practical applications, the time it takes for a DLEO satellite to pass through the interference area is a constant and can be divided into equal time slots τ. Since the future state of the GEO system is predictable to a certain extent, the spectrum sensing interval Θ (abbreviated as interval) consisting of multiple time slots is a key factor in throughput analysis. Each interval is divided into three stages: the sensing duration T of the sensing stage s , Test result reporting stage T t (i.e., the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process) and the DLEO system transmission phase T LEO , T LEO =2τ-T s -T t .

[0112] The activity of a GEO system is difficult to predict accurately, and it may change its state within several consecutive time slots. This problem is solved by studying the average idle / busy time over a period of time. Let the random variable X1 represent the number of busy time slots during Θ consecutive time slots. However, different channel states have different duration probability density functions. Therefore, the average value of X1 is derived independently for two cases: the initial channel state is busy or idle.

[0113] Case 1: The current real channel status is busy, and the expected value of X1 can be rewritten as

[0114]

[0115] Where b is the number of state changes during Θ time slots. Note that if b is an odd number, it means that the last channel state must be busy, and if it is an even number, it means that the last state must be idle. Therefore, Provided by

[0116]

[0117] in and It can be given by the following formula

[0118]

[0119] in

[0120] Case 2: The current real channel status is idle, and the expected value of X1 can be rewritten as:

[0121]

[0122] Note that if b is an even number, it means that the last channel state must be busy, and if it is an odd number, it means that the last state must be idle. Therefore, The expression is

[0123]

[0124] in and It can be given by the following formula

[0125]

[0126] in

[0127] S302, optimization problem establishment:

[0128] In the interference area, DLEO can access the shared spectrum in both overlay mode and underlay mode. Specifically, if the current true channel state is idle for Θ consecutive time slots, DLEO works in overlay mode and the transmit power is set to If the current true channel status is busy, the DLEO works in substrate mode and the transmit power is set to Apparently As shown in Table 1:

[0129]

[0130] In addition, it is worth noting that the active state of the GEO system may not remain for continuous Θ time slots, and the real current state of the GEO system may change. Therefore, when the current sensing result is idle, since the real channel state of the current GEO system has become busy, the use of As the transmission power may cause some interference to the GEO system. In addition, the imperfect characteristics of spectrum sensing may also cause some interference. Therefore, for the four different cases listed in Table 1, the useful throughput of the DLEO system is as follows

[0131]

[0132]

[0133]

[0134]

[0135] Among them, v1, v2, v3 and v4 are defined as

[0136]

[0137]

[0138]

[0139]

[0140] The goal of this step is to maximize the throughput of the DLEO system while satisfying the corresponding constraints. According to Table 1, when the spectrum sensing interval is Θ, the average throughput of the DLEO system per time slot is as follows:

[0141]

[0142] Among them, U 00 , U 01 , U 10 and U 11 Represent the probabilities of the four situations respectively. Since P(H0) and P(H1) are the probabilities of the idle state and busy state of the GEO system, they can be defined as

[0143] U 00 =P(H0)(1-Pf S1 )

[0144] U 01 =P(H0)(Pf S1 )

[0145] U 10 =P(H1)(1-Pd S1 )

[0146] U 11 =P(H1)(Pd S1 ) (38)

[0147] When the spectrum sensing interval is Θ, the average interference to the GEO system is

[0148]

[0149] Among them, G S3 {β} is defined as

[0150]

[0151] In addition, the perceived time T of SLEO s is also incorporated as an optimization variable. Specifically, for a given target false alarm probability Pf S1 , detection probability Pd S1 for

[0152]

[0153] This shows that the higher the Ts Leading to lower Pf S1 and higher Pd S1 , thus improving system performance. However, increasing T s It will also reduce the time used for data transmission and thus reduce the system throughput. Therefore, considering the constraint T from equations 23 and 24 min ,

[0154]

[0155] In addition, the detection interval Θ max The maximum value of is limited. On the one hand, since the activity state of the GEO system cannot remain unchanged for a long time, a larger Θ max It will waste computing resources. On the other hand, DLEO satellites are in high-speed motion. Too large an interval will lead to dynamic changes in the signal-to-noise ratio within the time slot, thus affecting the accuracy of the algorithm. Without losing generality, according to the state transfer matrix of GEO and the high dynamics of DLEO, Θ max Set to a small integer.

[0156] Specifically, the following optimization problem is given:

[0157]

[0158]

[0159]

[0160]

[0161]

[0162] C5:T min ≤T s ≤Θτ-T t

[0163] C6: 1≤Θ≤Θ max (43)

[0165] Constraint (C1) requires that the minimum rate achieved by the DLEO system is greater than the target threshold Constraint (C2) limits the total transmit power of the DLEO ground station to a predetermined value Constraints (C3) and (C4) impose the average interference and instantaneous interference under the substrate model at the GEO system to be less than a predetermined threshold The last constraints (C5) and (C6) limit the perception time and perception interval.

[0166] S303, solving the optimization problem:

[0167] Solve (43) using the two-dimensional line search method to obtain the optimal Θ and T s Therefore, given Θ and T s , (43) can be transformed into the following problem

[0168]

[0169] P2 can be solved using convex optimization techniques, and its Lagrangian is given by

[0170]

[0171] where (μ0, μ1, κ, η) denote the Lagrange multipliers associated with the constraints in (C2), (C3), and (C4). Therefore, the dual function of P2 is given by

[0172]

[0173] Since P2 is a convex optimization problem with strong duality, the Karush-Kuhn-Tucker (KKT) condition is a necessary and sufficient condition for the global optimality of P2, which is given by

[0174]

[0175]

[0176]

[0177] and They represent the optimal primal solution and dual solution of P2 respectively. Then, by solving equation (49), we can obtain (50) and (51). First, Given by the following formula

[0178]

[0179]

[0180] (50)

[0181] Similarly, Given by the following formula

[0182]

[0183]

[0184]

[0185] where [x] +represents max(x, 0). Since there are four equations in (48), 16 cases need to be discussed to get the optimal value. However, 10 cases are either inconsistent with the actual situation or contradict each other, so only 6 cases need to be considered, as shown in Table 2, that is, the optimal solution can be obtained after 6 iterations. Therefore, the smallest L is selected from the set of values ​​that satisfy (47). E3→S3 As the optimal solution, it is expressed as It is worth noting that satisfying (47)(48) and (49) is uniquely determined because the six variables are the solutions to six independent equations. As shown in Table 2:

[0186]

[0187] Figure 4 This is the interference analysis model diagram between satellite and ground networks, such as Figure 4 As shown, the figure shows a frequency sharing model based on perception between the satellite network uplink and the ground network. Among them, the ground network is the main user, and the link from the base station to the ground user is the main user link; the satellite network is the secondary user, and the uplink from the terminal to the satellite is the secondary user link. In this scenario, the satellite terminal has the ability to periodically perceive the working status of the ground network while providing communication guarantee services to users; at the same time, the satellite, as the decision center of the perception network, can make a final decision on the working status of the ground network based on the perception results reported by the terminal, and broadcast the decision results to each terminal. From the perception results of the satellite network, if a missed detection occurs, that is, when the ground network is active but not correctly detected, the satellite network and the ground network use the same frequency at the same time. The satellite can not only receive the communication signal transmitted by its own terminal, but also receive the signal from the ground base station, which will interfere with the reception. Here, it is assumed that the satellite communication uplink and the interference link are both additive Gaussian white noise channels and are independent of each other. This application focuses on the throughput problem of the satellite uplink based on perception, and the free space propagation loss of the transmission link, the gain and directivity of the transceiver antenna, etc. are all normalized at the satellite receiving end.

[0188] Figure 5 The following is a flow chart of spectrum sharing among satellite and ground networks: Figure 5 As shown, the process includes:

[0189] S501, decision data selection; S502, solving false alarm probability and detection probability; S503, solving throughput.

[0190] In order to solve the problem that the perception channel has time-varying characteristics, the present application proposes a spectrum sharing method based on multi-time slot perception, which increases the chances of satellite terminals accessing the channel from the perspective of reducing the false alarm probability, thereby achieving the purpose of improving spectrum utilization.

[0191] The satellite terminal periodically senses the surrounding RF environment, which is essentially a binary hypothesis testing problem. Γ1 is used to represent the active state of the ground network, and Γ0 is used to represent the idle state of the ground network. The duration of each frame is T, and the total duration of perception in each frame is τ, but it is divided into M discrete sub-time slots. ζ is the perception duration of each sub-time slot, so in each frame τ = Mζ, so the number of sample points corresponding to each small perception time slot is recorded as N1 = N / M, assuming that N1 is an integer. Similar to the previous periodic perception detection, assume that the received signal of the kth sub-time slot also has the following two situations

[0192]

[0193] Among them, the channel coefficient h k is a Gaussian random variable with zero mean and unit variance, and for all M sub-time slots, they are independent of each other. Assume that the signal power and noise power of the ground network remain unchanged in a frame, that is, for the kth time slot, there is and And the states in all M sub-time slots will not change, that is, the ground network is in active or idle state.

[0194] Specifically, S501, decision data selection:

[0195] The purpose of multi-slot spectrum sensing is to use the data of M sub-slots in a frame for joint sensing and determine the status of the ground network. In this study scenario, the satellite network uses data fusion to make fusion decisions on multi-slot collected data, that is, the sub-slot data collected by the satellite terminal will be aggregated to the satellite with decision-making capabilities. After the satellite receives all the sensing data, it uses a single-user continuous sensing similar decision method to make the final decision. Assume T k (y) is the data of the kth sub-slot

[0196]

[0197] Using data fusion, the data used for final decision making is

[0198]

[0199] Among them, g k ≥0 is the data weight of the kth sub-time slot, and For the detection probability threshold The best g to achieve the minimum false alarm probability i It can be proved by the Cauchy-Schwarz inequality that

[0200]

[0201] S502, solving the false alarm probability and detection probability:

[0202] When the channel coefficient h k When unknown, it can be simplified At this time, the false alarm probability and detection probability can be obtained respectively

[0203]

[0204]

[0205] S503, solve the throughput:

[0206] in, In a time-varying channel, if the detection probability p of each frame is required d All equal to the threshold Since multi-slot sensing is used, the energy detection threshold ε between each frame will be different, so the false alarm probability p corresponding to each frame is obtained f Here, for a given detection duration τ, the average false alarm probability of all frames is expressed as The normalized average throughput is defined as:

[0207]

[0208] It is easy to notice that this application is designed to solve the problem of spectrum sharing models between star-to-star and star-to-ground networks in related technologies being greatly affected by interference and having small throughput defects. This application is based on a satellite-to-ground fusion multi-layer and multi-dimensional network composed of high-orbit satellites, low-orbit satellites and the ground. It proposes an interference coordination method to solve the co-frequency interference problem between low-orbit satellites and high-orbit satellites and the frequency interference problem between satellite and ground networks. It aims to consider the interference between low-orbit satellites and high-orbit satellites and the ground from the perspective of low-orbit satellites in the multi-layer and multi-dimensional network composed of high, low and ground, and maximize the throughput of low-orbit satellites without interfering with the two nodes of high-orbit satellites and ground. That is, this application comprehensively considers the resource occupation of the three nodes of high, low and ground and designs such an interference coordination method.

[0209] Figure 6 According to an embodiment of the present application, a device for coordinating interference is provided. Figure 6 As shown, the device comprises:

[0210] A detection module 60, configured to detect a real-time trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data;

[0211] The sending module 62 is used to send an assist sensing instruction to the second low earth orbit satellite when it is detected that the first low earth orbit satellite moves into an interference area where interference exists with the geostationary orbit satellite;

[0212] The receiving module 64 is used to receive the sensing result returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy state of the geostationary orbit satellite to generate the sensing result;

[0213] The determination module 66 is used to determine the operating status of the first low earth orbit satellite based on the sensing result, wherein the operating status at least includes: the transmission power of the first low earth orbit satellite.

[0214] In the device, a detection module 60 is used to detect the real-time operation trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; a sending module 62 is used to send an assisting sensing instruction to a second low earth orbit satellite when it is detected that the first low earth orbit satellite is operating in an interference area where interference exists with a geostationary orbit satellite; a receiving module 64 is used to receive a sensing result returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate a sensing result; a determination module 66 is used to determine the operation state of the first low earth orbit satellite based on the sensing result, wherein the operation state at least includes: the transmission power of the first low earth orbit satellite, which realizes the technical effect of coordinating the interference with the high earth orbit satellite and the ground from the perspective of the low earth orbit satellite, and maximizing the throughput of the low earth orbit satellite without interfering with the two nodes of the high earth orbit satellite and the ground, thereby solving the technical problem of poor overall performance due to low frequency resource utilization and throughput of satellites in related technologies, and mutual signal interference between satellites.

[0215] According to another aspect of an embodiment of the present application, a non-volatile storage medium is further provided, the storage medium including a stored program, wherein when the program is running, a device where the storage medium is located is controlled to execute any one of the methods for coordinating interference.

[0216] Specifically, the above storage medium is used to store program instructions for the following functions to implement the following functions:

[0217] Detecting the real-time operating trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; sending an assist sensing instruction to a second low earth orbit satellite when it is detected that the first low earth orbit satellite is operating into an interference area where interference exists with a geostationary orbit satellite; receiving sensing results returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on the spectrum occupancy status of the geostationary orbit satellite to generate sensing results; determining the operating status of the first low earth orbit satellite based on the sensing results, wherein the operating status includes at least: the transmission power of the first low earth orbit satellite.

[0218] According to another aspect of an embodiment of the present application, there is also provided an electronic device, comprising: a processor; and a memory for storing instructions executable by the processor; wherein the processor is configured to execute the instructions to implement any one of the methods for coordinating interference.

[0219] The serial numbers of the above-mentioned embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0220] In the above embodiments of the present application, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0221] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are only schematic. For example, the division of the units can be a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0222] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0223] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0224] If the integrated unit is implemented in the form of 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 application, 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, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, a server or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, disk or optical disk and other media that can store program codes.

[0225] The above is only a preferred embodiment of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A method of coordinating interference, It is characterized in that include: detecting a real-time trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; When it is detected that the first low earth orbit satellite moves into an interference area where interference exists with the geostationary orbit satellite, sending an assist sensing instruction to the second low earth orbit satellite; receiving a sensing result returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is used to perform spectrum sensing on a spectrum occupancy state of the geostationary orbit satellite to generate the sensing result; Determining an operating state of the first low earth orbit satellite based on the sensing result, wherein the operating state at least includes: a transmission power of the first low earth orbit satellite; Determining the operating state of the first low earth orbit satellite based on the perception result includes: detecting whether the channel state of the geostationary orbit satellite remains in an idle state or a busy state in a continuous predetermined number of time slots to obtain a detection result; when the detection result indicates that the channel state remains in an idle state or a busy state in a continuous predetermined number of time slots, determining the operating state of the first low earth orbit satellite based on the perception result; when the detection result indicates that the channel state changes in the continuous predetermined number of time slots, optimizing the data throughput of the first low earth orbit satellite, wherein optimizing the data throughput of the first low earth orbit satellite includes: generating an optimization problem, wherein the first expression P1 of the optimization problem is: C5:T min ≤T s ≤Θτ-T t C6: 1≤Θ≤Θ max ; in, When the objective function is maximized, Perception duration T of the perception stage s And the value of the spectrum sensing interval Θ, represents the average throughput of the first low earth orbit satellite, and constraint (C1) requires that the average throughput of the first low earth orbit satellite is greater than the target threshold Constraint (C2) limits the total transmit power of the first low earth orbit satellite to a predetermined value Constraints (C3) and (C4) are the average interference under the substrate model at the GEO system and transient interference Limit to a predetermined threshold Constraints (C5) and (C6) are used to limit the sensing duration and sensing interval, respectively, where τ represents the time slot, T t represents the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process, S3 represents the first low earth orbit satellite, E3 represents the ground station of the first low earth orbit satellite, represents the first transmission power, represents the second transmission power, β represents the geocentric angle between S2 and S3, S2 represents the second low earth orbit satellite, It represents the gain of the ground station transmitting antenna in the direction of the geosynchronous orbit. represents the gain of the ground station receiving antenna in the direction of the ground station, c represents the beam, f represents the center frequency of the frequency band, σ E2→E3 represents the geocentric angle between E2 and E3, E2 represents the ground station of the second low earth orbit satellite, R represents the radius of the earth, and d S1 d S2 d S3 Respectively represent the distances from S1, S2, and S3 to the center of the earth; Solving the optimization problem The optimization problem is solved, and the specific process of solving the problem includes: subject to(C1)(C2)(C3)(C4); P2 can be solved using convex optimization techniques, and its Lagrangian is given by: Where (μ 0 , μ 1 ,κ,η) denote the Lagrange multipliers associated with the constraints in (C2), (C3), and (C4), and the dual function of P2 is given by Among them, the necessary and sufficient conditions for the global optimality of P2 are given by the following formula and denote the optimal primal solution and dual solution of P2 respectively; Where Θ represents the spectrum sensing interval, τ represents the time slot, and Θ max Indicates the maximum value of the spectrum sensing interval, When the objective function is maximized The value of represents the average throughput of the first low earth orbit satellite, L E3→S3 represents the Lagrangian expression corresponding to P2, The solution of P2 is hour The value of Indicates a predetermined value, It means that the optimal solution of P2 is The average interference of the GEO system under the substrate model is When P2 is the optimal solution, the GEO system is in the instantaneous interference under the substrate model. represents the partial derivative, U 00 Indicates the idle state of the GEO system, the probability that the perception result is idle state, U 01 Indicates the probability that the GEO system is in idle state and the perception result is busy state, U 10 Indicates the busy state of the GEO system, the probability of the perception result being idle state, U 11 Indicates the busy state of the GEO system. The probability of the perception result being busy. v2 indicates v3 means T s Indicates the perception of time, Indicates that when the channel status of the GEO system is busy, X 1 The expected value of Indicates that when the channel status of the GEO system is idle, X 1 expected value.

2. The method according to claim 1, It is characterized in that Determining the operating state of the first low earth orbit satellite based on the sensing result includes: When the sensing result indicates that the channel state of the geostationary orbit satellite is an idle state, determining that the working mode of the first low earth orbit satellite is a coverage mode, and the transmission power is set to a first transmission power 3. The method according to claim 2, It is characterized in that When the sensing result indicates that the channel state of the geostationary orbit satellite is a busy state, determining that the working mode of the first low earth orbit satellite is a substrate mode, and the transmission power is set to a second transmission power in, 4. A system for coordinating interference, It is characterized in that The system comprises: A first low earth orbit satellite for transmitting data, wherein the first low earth orbit satellite is used to detect its own real-time running trajectory, and when it is detected that the first low earth orbit satellite runs into an interference area where interference exists with a geostationary orbit satellite, sends an assist sensing instruction to a second low earth orbit satellite, receives a sensing result returned by the second low earth orbit satellite, and determines an operating state of the first low earth orbit satellite based on the sensing result, wherein the operating state at least includes: a transmission power of the first low earth orbit satellite; The second low earth orbit satellite is used to receive the assisting sensing instruction, perform spectrum sensing on the geostationary orbit satellite to generate a sensing result, and send the sensing result to the first low earth orbit satellite; Determining the operating state of the first low earth orbit satellite based on the perception result includes: detecting whether the channel state of the geostationary orbit satellite remains in an idle state or a busy state in a continuous predetermined number of time slots to obtain a detection result; when the detection result indicates that the channel state remains in an idle state or a busy state in a continuous predetermined number of time slots, determining the operating state of the first low earth orbit satellite based on the perception result; when the detection result indicates that the channel state changes in the continuous predetermined number of time slots, optimizing the data throughput of the first low earth orbit satellite, wherein optimizing the data throughput of the first low earth orbit satellite includes: generating an optimization problem, wherein the first expression P1 of the optimization problem is: C5:T min ≤T s ≤Θτ-T t C6: 1≤Θ≤Θ max ; in, When the objective function is maximized, Perception duration T of the perception stage s And the value of the spectrum sensing interval Θ, represents the average throughput of the first low earth orbit satellite, and constraint (C1) requires that the average throughput of the first low earth orbit satellite is greater than the target threshold Constraint (C2) limits the total transmit power of the first low earth orbit satellite to a predetermined value Constraints (C3) and (C4) are the average interference under the substrate model at the GEO system and transient interference Limit to a predetermined threshold Constraints (C5) and (C6) are used to limit the sensing duration and sensing interval, respectively, where τ represents the time slot, T t represents the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process, S3 represents the first low earth orbit satellite, E3 represents the ground station of the first low earth orbit satellite, represents the first transmission power, represents the second transmission power, β represents the geocentric angle between S2 and S3, S2 represents the second low earth orbit satellite, It represents the gain of the ground station transmitting antenna in the direction of the geosynchronous orbit. represents the gain of the ground station receiving antenna in the direction of the ground station, c represents the beam, f represents the center frequency of the frequency band, σ E2→E3 represents the geocentric angle between E2 and E3, E2 represents the ground station of the second low earth orbit satellite, R represents the radius of the earth, and d S1 d S2 d S3 Respectively represent the distances from S1, S2, and S3 to the center of the earth; Solving the optimization problem The optimization problem is solved, and the specific process of solving the problem includes: subject to(C1)(C2)(C3)(C4); P2 can be solved using convex optimization techniques, and its Lagrangian is given by: Where (μ 0 , μ 1 ,κ,η) denote the Lagrange multipliers associated with the constraints in (C2), (C3), and (C4), and the dual function of P2 is given by Among them, the necessary and sufficient conditions for the global optimality of P2 are given by the following formula and They represent the optimal primal solution and dual solution of P2, respectively. In the formula, Θ represents the spectrum sensing interval, τ represents the time slot, and Θ max Indicates the maximum value of the spectrum sensing interval, When the objective function is maximized The value of represents the average throughput of the first low earth orbit satellite, L E3→S3 represents the Lagrangian expression corresponding to P2, The solution of P2 is hour The value of Indicates a predetermined value, It means that the optimal solution of P2 is The average interference of the GEO system under the substrate model is When P2 is the optimal solution, the GEO system is in the instantaneous interference under the substrate model. represents the partial derivative, U 00 Indicates the idle state of the GEO system, the probability of the perception result being the idle state, U 01 represents the probability that the GEO system is in an idle state and the perception result is a busy state, U 10 Indicates the busy state of the GEO system, the probability of the perception result being idle state, U 11 Indicates the busy state of the GEO system. The probability of the perception result being busy. v2 indicates v3 means T s Indicates the perception of time, Indicates that when the channel status of the GEO system is busy, X 1 The expected value of Indicates that when the channel status of the GEO system is idle, X 1 expected value.

5. A device for coordinating interference, It is characterized in that include: a detection module, configured to detect a real-time running trajectory of a first low earth orbit satellite, wherein the first low earth orbit satellite is used to transmit data; a sending module, configured to send an assist sensing instruction to a second low earth orbit satellite when it is detected that the first low earth orbit satellite moves into an interference area where interference exists with a geostationary orbit satellite; a receiving module, configured to receive a sensing result returned by the second low earth orbit satellite, wherein the second low earth orbit satellite is configured to perform spectrum sensing on a spectrum occupancy state of the geostationary orbit satellite to generate the sensing result; A determination module, configured to determine an operating state of the first low earth orbit satellite based on the sensing result, wherein the operating state at least includes: a transmission power of the first low earth orbit satellite; Determining the operating state of the first low earth orbit satellite based on the perception result includes: detecting whether the channel state of the geostationary orbit satellite remains in an idle state or a busy state in a continuous predetermined number of time slots to obtain a detection result; when the detection result indicates that the channel state remains in an idle state or a busy state in a continuous predetermined number of time slots, determining the operating state of the first low earth orbit satellite based on the perception result; when the detection result indicates that the channel state changes in the continuous predetermined number of time slots, optimizing the data throughput of the first low earth orbit satellite, wherein optimizing the data throughput of the first low earth orbit satellite includes: generating an optimization problem, wherein the first expression P1 of the optimization problem is: C5:T min ≤T s ≤Θτ-T t C6: 1≤Θ≤Θ max ; in, When the objective function is maximized, Perception duration T of the perception stage s And the value of the spectrum sensing interval Θ, represents the average throughput of the first low earth orbit satellite, and constraint (C1) requires that the average throughput of the first low earth orbit satellite is greater than the target threshold Constraint (C2) limits the total transmit power of the first low earth orbit satellite to a predetermined value Constraints (C3) and (C4) are the average interference under the substrate model at the GEO system and transient interference Limit to a predetermined threshold Constraints (C5) and (C6) are used to limit the sensing duration and sensing interval, respectively, where τ represents the time slot, T t represents the time required to feed back the channel status of the geostationary orbit satellite to the first low earth orbit satellite during the throughput analysis process, S3 represents the first low earth orbit satellite, E3 represents the ground station of the first low earth orbit satellite, represents the first transmission power, represents the second transmission power, β represents the geocentric angle between S2 and S3, S2 represents the second low earth orbit satellite, It represents the gain of the ground station transmitting antenna in the direction of the geosynchronous orbit. represents the gain of the ground station receiving antenna in the direction of the ground station, c represents the beam, f represents the center frequency of the frequency band, σ E2→E3 represents the geocentric angle between E2 and E3, E2 represents the ground station of the second low earth orbit satellite, R represents the radius of the earth, d S1 ,d S2 ,d S3 Respectively represent the distances from S1, S2, and S3 to the center of the earth; Solving the optimization problem The optimization problem is solved, and the specific process of solving the problem includes: subject to(C1)(C2)(C3)(C4); P2 can be solved using convex optimization techniques, and its Lagrangian is given by: Where (μ 0 , μ 1 ,κ,η) denote the Lagrange multipliers associated with the constraints in (C2), (C3), and (C4), and the dual function of P2 is given by Among them, the necessary and sufficient conditions for the global optimality of P2 are given by the following formula and They represent the optimal primal solution and dual solution of P2, respectively, where Θ represents the spectrum sensing interval, τ represents the time slot, and Θ max Indicates the maximum value of the spectrum sensing interval, When the objective function is maximized The value of represents the average throughput of the first low earth orbit satellite, L E3→S3 represents the Lagrangian expression corresponding to P2, The solution of P2 is hour The value of Indicates a predetermined value, It means that the optimal solution of P2 is The average interference of the GEO system under the substrate model is When P2 is the optimal solution, the GEO system is in the instantaneous interference under the substrate model. represents the partial derivative, U 00 Indicates the idle state of the GEO system, the probability of the perception result being the idle state, U 01 represents the probability that the GEO system is in an idle state and the perception result is a busy state, U 10 Indicates the busy state of the GEO system, the probability of the perception result being idle state, U 11 Indicates the busy state of the GEO system. The probability of the perception result being busy. v2 indicates v3 means T s Indicates the perception of time, Indicates that when the channel status of the GEO system is busy, X 1 The expected value of Indicates that when the channel status of the GEO system is idle, X 1 expected value.

6. A non-volatile storage medium, It is characterized in that The storage medium includes a stored program, wherein when the program is executed, the device where the storage medium is located is controlled to execute the interference coordination method according to any one of claims 1 to 3.

7. An electronic device, It is characterized in that include: processor; a memory for storing instructions executable by the processor; The processor is configured to execute the instructions to implement the interference coordination method as claimed in any one of claims 1 to 3.

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