Satellite communication methods, systems and electronic devices based on reflectors

Abstract

This disclosure provides a satellite communication method, system, and electronic device based on a reflector. The method includes: a target terminal acquiring its own target received power, comparing the target received power with a preset ideal received power, obtaining a judgment result, and sending it to a reflector; an interfered terminal sending its effective received power and interference signal power to the reflector; in response to the reflector receiving a judgment result that the target received power is greater than or equal to the ideal received power, determining a first signal-to-interference-plus-noise ratio (SNR) for the interfered terminal, constructing an interference avoidance model based on the first SNR, solving the interference avoidance model to obtain first position adjustment data for the reflector, and controlling the reflector; in response to the reflector receiving a judgment result that the target received power is less than the ideal received power, constructing a signal enhancement model based on the target received power, solving the signal enhancement model to obtain second position adjustment data for the reflector, and controlling the reflector.

Description

Technical Field

[0001] This disclosure relates to the field of satellite communication technology, and in particular to a satellite communication method, system and electronic device based on a reflector. Background Technology

[0002] Satellite communication offers advantages such as wide coverage. However, due to its open nature, long-distance transmission characteristics, and the influence of geographical and natural environmental factors, these advantages cannot be fully utilized. In particular, direct communication links from satellite to ground terminals may not always be available due to deep fading (e.g., shadows cast by buildings and mountains). Furthermore, in this field, later-developed satellites cannot interfere with existing satellites that hold advantageous frequency positions.

[0003] In view of this, how to fully leverage the advantages of satellite communication while avoiding interference with existing satellites in orbit has become an urgent problem to be solved. Summary of the Invention

[0004] In view of this, the purpose of this disclosure is to propose a satellite communication method, system and electronic equipment based on a reflective surface to solve or partially solve the above-mentioned technical problems.

[0005] To achieve the above objectives, the first aspect of this disclosure proposes a satellite communication method based on a reflector, applied to a satellite communication system, the satellite communication system comprising: a reflector, a target terminal, and a jammed terminal, the method comprising:

[0006] The target terminal obtains its own target receiving power, compares the target receiving power with the preset ideal receiving power, obtains the judgment result, and sends it to the reflective surface;

[0007] The interfered terminal transmits its own effective receiving power and the interference signal power to the reflective surface;

[0008] In response to the judgment result received by the reflector being that the target received power is greater than or equal to the ideal received power, a first signal-to-interference-plus-noise ratio (SINNR) of the disturbed terminal is determined based on the effective received power and the interference signal power. An interference avoidance model is constructed based on the first SINNR. The interference avoidance model is solved to obtain the first position adjustment data of the reflector. The reflector is controlled according to the first position adjustment data.

[0009] In response to the judgment result received by the reflector indicating that the target received power is less than the ideal received power, a signal enhancement model is constructed based on the target received power, the signal enhancement model is solved to obtain the second position adjustment data of the reflector, and the reflector is controlled according to the second position adjustment data.

[0010] Based on the same inventive concept, a second aspect of this disclosure proposes a satellite communication system based on a reflector, the satellite communication system comprising: a reflector, a target terminal, and a jammed terminal.

[0011] The target terminal is configured to acquire its own target receiving power, compare the target receiving power with a preset ideal receiving power, obtain a judgment result, and send it to the reflective surface;

[0012] The interfered terminal is configured to transmit its effective received power and the interference signal power to the reflective surface;

[0013] The reflector is configured to, in response to the judgment result received by the reflector being that the target received power is greater than or equal to the ideal received power, determine a first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal based on the effective received power and the interference signal power, construct an interference avoidance model based on the first SNR, solve the interference avoidance model to obtain first position adjustment data of the reflector, and control the reflector according to the first position adjustment data;

[0014] The reflector is further configured to respond to the judgment result received by the reflector indicating that the target received power is less than the ideal received power, to construct a signal enhancement model based on the target received power, to solve the signal enhancement model to obtain second position adjustment data of the reflector, and to control the reflector according to the second position adjustment data.

[0015] Based on the same inventive concept, a third aspect of this disclosure proposes an electronic device including a memory, a processor, and a computer program stored in the memory and executable by the processor, wherein the processor implements the method described above when executing the computer program.

[0016] As can be seen from the above, the satellite communication method, system, and electronic equipment based on a reflector provided in this disclosure determine whether the target communication system corresponding to the target terminal can conduct normal communication by comparing the target received power of the target terminal with the preset ideal received power. When the target communication system can conduct normal communication, a first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal is determined, an interference avoidance model is constructed based on the first SNR, and a first position adjustment data of the reflector is determined to control the reflector, so that the reflected signal generated by the reflector cancels the interference signal received by the disturbed terminal, thereby avoiding interference from the target communication system to the disturbed communication system. When the target communication system cannot conduct normal communication, a signal enhancement model is constructed based on the target received power, and a second position adjustment data of the reflector is determined to control the reflector, thereby reducing interference to the disturbed system while ensuring that the target communication system can conduct normal communication. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this disclosure or related technologies, the accompanying drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the accompanying drawings described below are only embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1A This is a flowchart of a satellite communication method based on a reflector according to an embodiment of the present disclosure;

[0019] Figure 1B This is a system structure diagram showing the line-of-sight distance according to an embodiment of the present disclosure;

[0020] Figure 1C This is a non-line-of-sight system structure diagram according to an embodiment of the present disclosure;

[0021] Figure 1D This is a schematic diagram of the reflective surface structure according to an embodiment of the present disclosure;

[0022] Figure 2 This is a flowchart of a method for controlling a reflective surface according to an embodiment of the present disclosure;

[0023] Figure 3 This is a schematic diagram of the structure of a satellite communication system based on a reflective surface according to an embodiment of the present disclosure;

[0024] Figure 4 This is a schematic diagram of the structure of an electronic device according to an embodiment of the present disclosure. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this disclosure clearer, the following detailed description is provided in conjunction with specific embodiments and the accompanying drawings.

[0026] It should be noted that, unless otherwise defined, the technical or scientific terms used in the embodiments of this disclosure should have the ordinary meaning understood by one of ordinary skill in the art to which this disclosure pertains. The terms "first," "second," and similar words used in the embodiments of this disclosure do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0027] As mentioned above, how to overcome deep fading in satellite communications and avoid interference with existing satellites has become an important research problem.

[0028] Based on the above description, such as Figure 1A As shown, the satellite communication method based on a reflector proposed in this embodiment is applied to a satellite communication system, which includes a reflector, a target terminal, and a jammed terminal. The method includes:

[0029] Step 101: The target terminal obtains its own target receiving power, compares the target receiving power with the preset ideal receiving power, obtains the judgment result, and sends it to the reflector.

[0030] In practice, the satellite communication system includes a reflector (i.e., a smart reflector), a target satellite, a target terminal, satellites in the jammed system, and jammed terminals. Communication occurs between the target satellite and the target terminal, and between satellites in the jammed system and jammed terminals. The reflector includes a reflector controller, which controls and adjusts the reflector's position.

[0031] The judgment results include: the target receiving power of the target terminal is greater than or equal to the ideal receiving power, or the target receiving power is less than the ideal receiving power.

[0032] When the target received power is greater than or equal to the ideal received power, the target satellite and the target terminal can communicate normally, that is, the target satellite link is a line-of-sight link; when the target received power is less than the ideal received power, the target satellite and the target terminal cannot communicate normally, that is, the target satellite link is a non-line-of-sight link.

[0033] Step 102: The disturbed terminal sends its effective receiving power and the interference signal power to the reflective surface.

[0034] In practice, the interference signal power is the superposition of the interference signal and the reflected signal. The reflected signal is the signal reflected from the reflective surface to the disturbed terminal, and the interference signal is the signal that interferes with the communication between the target satellite and the target terminal.

[0035] Step 103: In response to the judgment result received by the reflector being that the target received power is greater than or equal to the ideal received power, a first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal is determined based on the effective received power and the interference signal power. An interference avoidance model is constructed based on the first SNR. The interference avoidance model is solved to obtain the first position adjustment data of the reflector. The reflector is controlled according to the first position adjustment data.

[0036] In practice, when the target received power is greater than or equal to the ideal received power, the target satellite and the target terminal can communicate normally.

[0037] like Figure 1B As shown, Figure 1B This is a system architecture diagram for line-of-sight in an embodiment of this disclosure. The target satellite S and the target terminal GT communicate via a target communication system, performing normal communication based on downlink signals from their own system. Satellites in the disrupted system... With the disturbed terminal The communication system in question is disrupted, and communication is based on the downlink signals of the disrupted system. At this time, the disrupted terminal... It will also receive interference signals from the target satellite S, causing interference to the obstructed communication system. In order to eliminate the interference to the obstructed communication system, the reflector is adjusted by adjusting the first position data, and the reflected signal of the intelligent reflector RIS is used to suppress the interference signals from the obstructed system, thereby avoiding the interference of the target satellite S to the obstructed communication system.

[0038] Step 104: In response to the judgment result received by the reflector being that the target received power is less than the ideal received power, a signal enhancement model is constructed based on the target received power, the signal enhancement model is solved to obtain the second position adjustment data of the reflector, and the reflector is controlled according to the second position adjustment data.

[0039] In practice, when the target receiving power is less than the ideal receiving power, normal communication cannot be carried out between the target satellite and the target terminal.

[0040] like Figure 1C As shown, Figure 1CThis is a non-line-of-sight system architecture diagram according to an embodiment of this disclosure. The target satellite S and the target terminal GT communicate via a target communication system, based on downlink signals from the target system. At this time, the direct satellite-to-ground link of the target communication system is blocked. Satellites in the system... With the disturbed terminal The communication system in question is disrupted, and communication is based on the downlink signals of the disrupted system. At this time, the disrupted terminal... It will also receive interference signals from the target satellite S and the reflector, causing interference to the disrupted communication system. In order to reduce the interference to the disrupted communication system while ensuring that the target communication system can communicate normally, the reflector is adjusted by adjusting the second position data. The reflected signal of the intelligent reflector RIS is used to restore the normal communication of the target communication system and reduce the interference signal of the disrupted system.

[0041] Through the above embodiments, by comparing the target received power of the target terminal with the preset ideal received power, it is determined whether the target communication system corresponding to the target terminal can conduct normal communication. When the target communication system can conduct normal communication, the first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal is determined. Based on the first SNR, an interference avoidance model is constructed, and the first position adjustment data of the reflector is determined to control the reflector, so that the reflected signal generated by the reflector cancels the interference signal received by the disturbed terminal, thereby avoiding interference from the target communication system to the disturbed communication system. When the target communication system cannot conduct normal communication, a signal enhancement model is constructed based on the target received power, and the second position adjustment data of the reflector is determined to control the reflector, thereby reducing interference to the disturbed system while ensuring that the target communication system can conduct normal communication.

[0042] In some embodiments, the system further includes a target satellite; step 103 includes:

[0043] Step 1031: Obtain the first target position of the target satellite and the second disturbed position of the disturbed terminal.

[0044] Step 1032: Obtain the effective received power of the disturbed terminal, the power of the interference signal superimposed with the received interference signal and the reflected signal, and the white noise power. Perform calculation processing on the effective received power, the interference signal power, and the white noise power according to the signal-to-interference-plus-noise ratio formula to obtain the first signal-to-interference-plus-noise ratio of the disturbed terminal.

[0045] Step 1033: Construct an interference avoidance model based on the first target location, the second disturbed location, and the first signal-to-interference-plus-noise ratio (SIR); wherein the interference avoidance model is used to optimize the first SIR, and the interference avoidance model includes a first system geometric constraint and a first reflection geometric constraint determined based on the first target location and the second disturbed location.

[0046] Step 1034: Solve the interference avoidance model to obtain the first position adjustment data; wherein, the first position adjustment data includes a first phase shift and a first orientation.

[0047] In specific implementation, when the target communication system is capable of normal communication, the first target position of the target satellite and the second disrupted position of the disrupted terminal are obtained. Based on the first target position and the second disrupted position, first system geometric constraints and first reflection geometric constraints are determined. The first signal-to-interference-plus-noise ratio (SIR / NDR) of the disrupted terminal is determined. Based on the first SIR / NDR and the first constraints, an interference avoidance model is constructed, and first position adjustment data for the reflector is determined to control the reflector. The interference avoidance model is used to determine the first position adjustment data that satisfies the first constraints and maximizes the first SIR / NDR. The first constraints include the first system geometric constraints, the first reflection geometric constraints, and also a unity modulus constraint.

[0048] The above scheme adjusts the data control reflector based on the first position determined by the interference avoidance model, so that the reflected signal generated by the reflector suppresses the interference signal received by the disturbed terminal, thereby avoiding the interference of the target communication system to the disturbed communication system.

[0049] In some embodiments, step 1031 includes:

[0050] Step 10311: Obtain the first distance between the target satellite and the reflector, the first elevation angle from the center position of the reflector to the target satellite, and the first azimuth angle from the center position of the reflector to the target satellite.

[0051] Step 10312: Perform a sine operation on the first elevation angle to obtain the first elevation angle sine, perform a cosine operation on the first elevation angle to obtain the first elevation angle cosine, perform a sine operation on the first azimuth angle to obtain the first azimuth angle sine, and perform a cosine operation on the first azimuth angle to obtain the first azimuth angle cosine.

[0052] Step 10313: The product of the first distance, the first elevation sine, and the first azimuth cosine is taken as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is taken as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is taken as the third directional position of the target satellite.

[0053] Step 10314: Perform vector operations on the first direction position, the second direction position, and the third direction position of the target satellite to obtain the first target position.

[0054] In specific implementation, based on the first distance First elevation angle and first azimuth Determine the location of the first target.

[0055]

[0056] in, This is the first target position of the target satellite.

[0057] Step 10315: Obtain the second distance between the disturbed terminal and the reflective surface, the second elevation angle from the center position of the reflective surface to the disturbed terminal, and the second azimuth angle from the center position of the reflective surface to the disturbed terminal.

[0058] Step 10316: Perform a sine operation on the second elevation angle to obtain the sine of the second elevation angle, perform a cosine operation on the second elevation angle to obtain the cosine of the second elevation angle, perform a sine operation on the second azimuth angle to obtain the sine of the second azimuth angle, and perform a cosine operation on the second azimuth angle to obtain the cosine of the second azimuth angle.

[0059] Step 10317: The product of the second distance, the second elevation angle sine, and the second azimuth angle cosine is taken as the first directional position of the disturbed terminal; the product of the second distance, the second elevation angle sine, and the second azimuth angle sine is taken as the second directional position of the disturbed terminal; and the product of the second distance and the second elevation angle cosine is taken as the third directional position of the disturbed terminal.

[0060] Step 10318: Perform vector operations on the first directional position, the second directional position, and the third directional position of the disturbed terminal to obtain the second disturbed position.

[0061] In specific implementation, based on the second distance Second elevation angle Second azimuth angle Determine the second disturbed location.

[0062]

[0063] in, This is the second disturbed location of the disturbed terminal.

[0064] By using the above scheme, the first target position of the target satellite and the second disturbed position of the disturbed terminal are determined. Based on the target satellite position, the disturbed terminal position and related position parameters, the first system geometric constraint condition and the first reflection geometric constraint condition are determined, so that the constructed interference avoidance model conforms to the actual situation, thereby making the determined first position adjustment data a first phase shift and a first orientation within a reasonable range.

[0065] In some embodiments, the system further includes satellites in the disrupted system; step 1032 includes:

[0066] Step 10321: Obtain the first transmit power of the satellite in the jammed system, the first transmit antenna gain of the satellite in the jammed system, the first receive antenna gain of the jammed terminal, the first signal wavelength of the satellite in the jammed system, and the fourth distance between the satellite in the jammed system and the jammed terminal.

[0067] Step 10322: Calculate the first transmit power, the first transmit antenna gain, the first receive antenna gain, the first signal wavelength, and the fourth distance according to the Fries transmission formula to obtain the effective receive power of the disturbed terminal.

[0068] In practice, the Friis Free Space Formula is an antenna theory formula used to calculate the received power from the transmitting antenna to the receiving antenna. The formula is expressed as: ,in, This refers to the received power of the receiving antenna. This refers to the transmit power of the transmitting antenna. For the transmit antenna gain, For receiving antenna gain, For the operating wavelength, This is the distance between the transmitting antenna and the receiving antenna.

[0069] First transmission power First transmitting antenna gain First receiving antenna gain First signal wavelength and the fourth distance Substituting into the Friesian transmission formula above, we obtain the effective received power of the disturbed terminal.

[0070]

[0071] in, The effective received power of the disturbed terminal.

[0072] Step 10323: Obtain the reflection coefficient of the reflection unit at the target position in the reflecting surface; wherein, the reflection unit at the target position is the reflection unit located at the target row and target column positions in the reflecting surface.

[0073] Step 10324: Determine the power of the interference signal superimposed on the interference signal and the reflected signal received by the disturbed terminal based on the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle, and the second azimuth angle.

[0074] In practical implementation, the reflection coefficient of the reflecting element at the target position in the reflecting surface is: ;in, For the target row of the reflective unit at the target location, The target column of the target position reflection unit.

[0075] According to the reflectance coefficient First elevation angle First azimuth Second elevation angle Second azimuth angle Determine the power of the interference signal resulting from the superposition of the interference signal and the reflected signal received by the disturbed terminal. .

[0076] The interference signal power is also related to the target satellite's transmission power, the target satellite's antenna gain, the antenna gain of the interfered terminal, and the transmission distance from the target satellite to the reflector (i.e., the first distance). The transmission distance from the disturbed terminal to the reflector (i.e., the second distance) This is related to factors such as the transmission distance from the target satellite to the disrupted terminal.

[0077] Step 10325: Calculate the effective received power and the interference signal power according to the signal-to-interference-plus-noise ratio (SINR) formula to obtain the first SINR of the disturbed terminal.

[0078] In practical implementation, the signal-to-interference-plus-noise ratio (SINR) refers to the ratio of the signal to the sum of interference and noise in the system. The formula is expressed as: ,in, For signal-to-interference-to-noise ratio, The effective power of the signal. The effective power of the interference signal, This represents the effective power of the noise.

[0079] The effective received power of the disturbed terminal The power of the interference signal superimposed on the interference signal received by the disturbed terminal and the reflected signal. Additive white Gaussian noise at the disturbed terminal ( Substituting the power of the signal-to-interference-plus-noise ratio (SIR) into the above formula, we obtain the first SIR of the disturbed terminal.

[0080]

[0081] in, The first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal.

[0082] The above scheme calculates the first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal, determines the degree of interference, and constructs an interference avoidance model based on the SIR. This allows the determination of the first position adjustment data of the reflective surface when the degree of interference is minimized, thereby avoiding interference to the disturbed terminal.

[0083] In some embodiments, step 1033 includes:

[0084] Step 10331: Determine the unit modulus constraint condition based on the reflection coefficient.

[0085] Step 10332: Determine the first system geometric constraint condition and the first reflection geometric constraint condition based on the first target position and the second disturbed position.

[0086] Step 10333: Based on the unit modulus constraint, the first system geometric constraint, the first reflection geometric constraint, and the first signal-to-interference-plus-noise ratio, construct the interference avoidance model.

[0087]

[0088] Wherein, P1 is the first position adjustment data. The first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal. The reflection coefficient is the reflection element at the target position in the reflecting surface. The target row of the target position reflection unit. The target column of the target position reflection unit, The total number of rows on the reflective surface. The total number of columns of the reflecting surface. The first elevation angle, This is the first azimuth angle. This is the second elevation angle. This is the second azimuth angle. The unit modulus constraint condition is... These are the geometric constraints of the first system. This is the first reflection geometric constraint condition.

[0089] In practice, the interference avoidance model determines the first position adjustment data of the reflector corresponding to the maximum first signal-to-interference-plus-noise ratio (SNR) under the given constraints. By adjusting the reflector according to this first position adjustment data, the first SNR of the disturbed terminal can be maximized, thereby avoiding interference to the disturbed terminal.

[0090] Among them, the geometric constraints of the first system It is the angle between the reflector, the target satellite, and the disturbed terminal, with the vertex of the angle being the reflector.

[0091] The above scheme constructs an interference avoidance model based on the first signal-to-interference-plus-noise ratio (SINR), determines the first position adjustment data of the reflector to control the reflector, and makes the reflected signal generated by the reflector suppress the interference signal received by the disturbed terminal, thereby avoiding the interference of the target communication system to the disturbed communication system.

[0092] In some embodiments, the system further includes a target satellite; step 104 includes:

[0093] Step 1041: Obtain the first target position of the target satellite and the second target position of the target terminal.

[0094] Step 1042: Construct a signal enhancement model based on the first target position, the second target position, and the target received power; wherein, the signal enhancement model is used to optimize the target received power, and the signal enhancement model includes a second system geometric constraint and a second reflection geometric constraint determined based on the first target position and the second target position.

[0095] Step 1043: Solve the signal enhancement model to obtain the second position adjustment data; wherein, the second position adjustment data includes a second phase shift and a second orientation.

[0096] In specific implementation, when the target communication system cannot communicate normally, the first target position of the target satellite and the second target position of the target terminal are obtained. Based on the first and second target positions, second system geometric constraints and second reflection geometric constraints are determined. A signal enhancement model is constructed based on the target received power and the second constraints to determine the second position adjustment data of the reflector and control the reflector. The signal enhancement model is used to determine the second position adjustment data that satisfies the second constraints and maximizes the target reception. The second constraints include the second system geometric constraints and the second reflection geometric constraints, as well as unity modulus constraints and signal-to-interference-plus-noise ratio constraints.

[0097] The signal-to-interference-plus-noise ratio (SIR) constraint is determined based on the second SIR of the disturbed terminal and a preset SIR threshold, thereby ensuring that the determined second position adjustment data reduces interference to the disturbed terminal while maintaining normal communication between the target satellite and the target terminal.

[0098] The above scheme adjusts the data control reflector based on the second position determined by the signal enhancement model, thereby reducing interference to the disturbed system while ensuring that the target communication system can communicate normally.

[0099] In some embodiments, prior to step 1042, the method further includes:

[0100] Step 1042A: Obtain the first distance between the target satellite and the reflector, the first elevation angle from the center position of the reflector to the target satellite, and the first azimuth angle from the center position of the reflector to the target satellite.

[0101] Step 1042B: Perform a sine operation on the first elevation angle to obtain the first elevation angle sine, perform a cosine operation on the first elevation angle to obtain the first elevation angle cosine, perform a sine operation on the first azimuth angle to obtain the first azimuth angle sine, and perform a cosine operation on the first azimuth angle to obtain the first azimuth angle cosine.

[0102] Step 1042C: The product of the first distance, the first elevation sine, and the first azimuth cosine is taken as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is taken as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is taken as the third directional position of the target satellite.

[0103] Step 1042D: Perform vector operations on the first direction position, the second direction position, and the third direction position of the target satellite to obtain the first target position.

[0104] In specific implementation, based on the first distance First elevation angle and first azimuth Determine the location of the first target.

[0105]

[0106] in, This is the first target position of the target satellite.

[0107] Step 1042E: Obtain the third distance between the target terminal and the reflective surface, the third elevation angle from the center position of the reflective surface to the target terminal, and the third azimuth angle from the center position of the reflective surface to the target terminal.

[0108] Step 1042F: Perform a sine operation on the third elevation angle to obtain the sine of the third elevation angle, perform a cosine operation on the third elevation angle to obtain the cosine of the third elevation angle, perform a sine operation on the third azimuth angle to obtain the sine of the third azimuth angle, and perform a cosine operation on the third azimuth angle to obtain the cosine of the third azimuth angle.

[0109] Step 1042G: The product of the third distance, the third elevation angle sine, and the third azimuth angle cosine is taken as the first directional position of the target terminal; the product of the third distance, the third elevation angle sine, and the third azimuth angle sine is taken as the second directional position of the target terminal; and the product of the third distance and the third elevation angle cosine is taken as the third directional position of the target terminal.

[0110] Step 1042H: Perform vector operations on the first direction position, the second direction position, and the third direction position of the target terminal to obtain the second target position.

[0111] In specific implementation, based on the third distance Third elevation angle and third angle Determine the location of the second target.

[0112]

[0113] in, This is the second target location of the target terminal.

[0114] By using the above scheme, the first target position of the target satellite and the second target position of the target terminal are determined. Based on the target satellite position, the target terminal position and related position parameters, the second system geometric constraints and the second reflection geometric constraints are determined, so that the constructed signal enhancement model conforms to the actual situation, thereby making the determined second position adjustment data a second phase shift and a second orientation within a reasonable range.

[0115] Step 1042I: Obtain the second transmit power of the target satellite, the second transmit antenna gain of the target satellite, the second receive antenna gain of the target terminal, the second signal wavelength of the target satellite, the first power radiation pattern of the target satellite, and the second power radiation pattern of the target position reflection unit, wherein the target position reflection unit is the reflection unit located in the target row and target column positions of the reflection surface.

[0116] Step 1042J: The second transmit power, the second transmit antenna gain, the second receive antenna gain, the second signal wavelength, the first power radiation pattern, and the second power radiation pattern are calculated and processed according to the Fries transmission formula to obtain the target receive power of the target terminal.

[0117] In practice, the Friis Free Space Formula is an antenna theory formula used to calculate the received power from the transmitting antenna to the receiving antenna. The formula is expressed as: ,in, This refers to the received power of the receiving antenna. This refers to the transmit power of the transmitting antenna. For the transmit antenna gain, For receiving antenna gain, For the operating wavelength, This is the distance between the transmitting antenna and the receiving antenna.

[0118] Second transmission power Second transmitting antenna gain Second receiving antenna gain Second signal wavelength and first distance Substituting into the Friesian transmission formula above, we obtain the target received power of the target terminal.

[0119]

[0120] In this model, the target satellite is modeled as the far field of the reflector, and the target terminal is modeled as the near field of the reflector. The target received power of the target terminal. The receiving antenna gain of the reflector is... The area of ​​the reflective unit at the target location is... The first distance between the target satellite and the target terminal. The fifth distance is the distance from the target position reflecting unit in the reflecting surface to the target terminal. This is the first power radiation pattern of the target satellite. This is the second power radiation pattern of the reflective unit at the target location.

[0121] Whether the target satellite or target terminal is located in the near field or far field of the reflector is determined by the Fraunhofer distance, which is expressed by the formula: .

[0122] In antenna theory, the distance between devices is considered the far field when it is greater than the Fraunhofer distance, and the distance between devices is considered the near field when it is less than the Fraunhofer distance. Due to the first distance... Greater than the Fraunhofer distance, the third distance The distance is less than the Fraunhofer distance; therefore, the target satellite is located in the far field of the reflector, and the target terminal is located in the near field of the reflector.

[0123] like Figure 1D As shown, Figure 1D This is a schematic diagram of the structure of the reflective surface according to an embodiment of the present disclosure. For reflective unit The elevation angle to the target satellite, For reflective unit The azimuth angle to the target satellite, For reflective unit The elevation angle to the target terminal, For reflective unit The azimuth angle to the target terminal.

[0124] The first one located on the reflective surface OK The coordinates of the center point of the column's reflective unit are:

[0125]

[0126] in, The total number of rows on the reflective surface. This represents the total number of columns of the reflective surface.

[0127] Step 1042K: Summing the first interference from the target satellite to the disturbed terminal and the second interference from the reflector to the disturbed terminal to obtain the total interference power of the disturbed terminal.

[0128] In practice, based on the first interference from the target satellite to the disturbed terminal and the second interference from the reflector to the disturbed terminal, the total interference power of the disturbed terminal is determined.

[0129]

[0130] in, The receiving antenna gain of the disturbed terminal. The distance between the target satellite and the disturbed terminal is denoted as .

[0131] Step 1042L: The effective received power, the total interference power, and the white noise power are calculated according to the signal-to-interference-plus-noise ratio (SIR) formula to obtain the second SIR of the disturbed terminal.

[0132] In practical implementation, the signal-to-interference-plus-noise ratio (SINR) refers to the ratio of the signal to the sum of interference and noise in the system. The formula is expressed as: ,in, For signal-to-interference-to-noise ratio, The effective power of the signal. The effective power of the interference signal, This represents the effective power of the noise.

[0133] The effective received power of the disturbed terminal Total interference power of the disturbed terminal Additive white Gaussian noise at the disturbed terminal ( Substituting the power of the signal-to-interference-plus-noise ratio (SINR) into the SINR formula, we obtain the second SINR of the disturbed terminal.

[0134]

[0135] in, This is the second signal-to-interference-plus-noise ratio.

[0136] The above scheme calculates the second signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal, and determines the degree of interference based on the second SIR. The SIR constraint condition of the signal enhancement model is set based on the second SIR, thereby ensuring that the determined second position adjustment data reduces interference to the disturbed terminal while maintaining normal communication between the target satellite and the target terminal.

[0137] In some embodiments, step 1042 includes:

[0138] Step 10421: Determine the unit modulus constraint condition based on the reflection coefficient.

[0139] Step 10422: Determine the second system geometric constraints and the second reflection geometric constraints based on the first target position and the second target position.

[0140] Step 10423: Determine the signal-to-interference-plus-noise ratio (SIR) constraint condition based on the second SIR and the preset SIR threshold.

[0141] Step 10424: Based on the unity modulus constraint, the second system geometric constraint, the second reflection geometric constraint, the signal-to-interference-plus-noise ratio constraint, and the target received power, construct the signal enhancement model.

[0142]

[0143] Wherein, P2 is the second position adjustment data. The target received power of the target terminal. The reflection coefficient is the reflection element at the target position in the reflecting surface. The target row of the target position reflection unit. The target column of the target position reflection unit, The total number of rows on the reflective surface. The total number of columns of the reflecting surface. The first elevation angle, This is the first azimuth angle. The third elevation angle, For the third azimuth angle, The unit modulus constraint condition is... These are the geometric constraints of the second system. This is the second reflection geometric constraint condition. This refers to the signal-to-interference-plus-noise ratio (SINR) constraint. This is the preset signal-to-interference-plus-noise ratio (SIN / N) threshold.

[0144] In practical implementation, the signal enhancement model determines the second position adjustment data of the reflector corresponding to the maximum target received power under the condition of satisfying the second reflection geometric constraint. Adjusting the reflector according to the second position adjustment data maximizes the target terminal's received power, thus ensuring normal communication between the target satellite and the target terminal's communication system. Furthermore, by setting signal-to-interference-plus-noise ratio (SIR) constraints, the second SIR of the disturbed terminal can be kept within a reasonable range, thereby reducing interference to the disturbed communication system while ensuring normal communication of the target system.

[0145] Among them, the geometric constraints of the second system It is the angle between the reflector, the target satellite, and the target terminal, with the vertex of the angle being the reflector.

[0146] The above scheme allows for the construction of a signal enhancement model based on the target's received power when the target communication system is unable to communicate normally. This model determines the second position adjustment data of the reflector and controls the reflector, thereby reducing interference to the affected system while ensuring that the target communication system can communicate normally.

[0147] It should be noted that the embodiments of this disclosure can also be further described in the following ways:

[0148] like Figure 2 As shown, Figure 2 This is a flowchart of a method for controlling a reflective surface according to an embodiment of the present disclosure. It includes:

[0149] Step 1: Detect the target received power of the target terminal in the target communication system.

[0150] Step 2.1: The target received power is greater than or equal to the preset ideal received power, and the reflector assists the target satellite in interference avoidance. Step 3.1: Acquire the position information of the target satellite and the interfered terminal, and send it to the reflector's controller. Step 4.1: Based on the acquired position information, the reflector's controller constructs the optimal first phase shift and first orientation of the reflector to maximize the first signal-to-interference-plus-noise ratio of the interfered terminal.

[0151] Step 2.2: If the target received power is less than the preset ideal received power, the reflector assists the target satellite in signal enhancement and interference avoidance. Step 3.2: Acquire the position information of the target satellite and the target terminal, and the second signal-to-interference-plus-noise ratio (SNR) of the interfered terminal, and send this information to the reflector's controller. Step 4.2: Based on the acquired position information and the second SNR, the reflector's controller constructs the optimal second phase shift and second orientation of the reflector to maximize the target received power and ensure that the second SNR of the interfered terminal is higher than the preset SNR threshold.

[0152] Step 5: Perform phase shift and orientation adjustment according to the commands sent by the controller of the reflector.

[0153] Through the above embodiments, during communication between the target satellite and the target terminal, when the communication link is available, the reflector is adjusted according to the first phase shift and the first orientation to avoid interference with the disrupted communication system. When the communication link is unavailable, the reflector can create a virtual line-of-sight link to assist normal communication between the target satellite and the target terminal. Adjusting the reflector according to the second phase shift and the second orientation enhances the target terminal's receiving power while reducing interference with the disrupted terminal, ensuring that the interference experienced by the disrupted terminal is always within a controllable range.

[0154] It should be noted that the method of this disclosure embodiment can be executed by a single device, such as a computer or server. The method of this embodiment can also be applied to a distributed scenario, where multiple devices cooperate to complete the task. In such a distributed scenario, one of these devices may execute only one or more steps of the method of this disclosure embodiment, and the multiple devices will interact with each other to complete the method described.

[0155] It should be noted that the above description describes some embodiments of this disclosure. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in a different order than that shown in the above embodiments and still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require a specific or sequential order to achieve the desired result. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0156] Based on the same inventive concept, corresponding to any of the above embodiments, this disclosure also provides a satellite communication system based on a reflective surface.

[0157] refer to Figure 3 The satellite communication system based on the reflector surface includes: a reflector surface 303, a target terminal 301, and a jammed terminal 302.

[0158] The target terminal 301 is configured to acquire its own target receiving power, compare the target receiving power with a preset ideal receiving power, obtain a judgment result, and send it to the reflector 303.

[0159] The disturbed terminal 302 is configured to transmit its effective receiving power and interference signal power to the reflector 303;

[0160] The reflector 303 is configured to, in response to the judgment result received by the reflector 303 that the target received power is greater than or equal to the ideal received power, determine the first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal 302 based on the effective received power and the interference signal power, construct an interference avoidance model based on the first SNR, solve the interference avoidance model to obtain the first position adjustment data of the reflector 303, and control the reflector 303 according to the first position adjustment data;

[0161] The reflector 303 is further configured to respond to the judgment result received by the reflector 303 indicating that the target received power is less than the ideal received power, to construct a signal enhancement model based on the target received power, to solve the signal enhancement model to obtain second position adjustment data of the reflector 303, and to control the reflector 303 according to the second position adjustment data.

[0162] In some embodiments, the system further includes a target satellite;

[0163] The reflective surface 303 is further configured as follows:

[0164] Obtain the first target position of the target satellite and the second disrupted position of the disrupted terminal 302;

[0165] The effective received power, the power of the interference signal superimposed by the interference signal and the reflected signal, and the white noise power of the disturbed terminal 302 are obtained. The effective received power, the interference signal power, and the white noise power are calculated and processed according to the signal-to-interference-plus-noise ratio formula to obtain the first signal-to-interference-plus-noise ratio of the disturbed terminal 302.

[0166] An interference avoidance model is constructed based on the first target location, the second disturbed location, and the first signal-to-interference-plus-noise ratio (SIR). The interference avoidance model is used to optimize the first SIR, and the interference avoidance model includes a first system geometric constraint and a first reflection geometric constraint determined based on the first target location and the second disturbed location.

[0167] The interference avoidance model is solved to obtain the first position adjustment data; wherein, the first position adjustment data includes a first phase shift and a first orientation.

[0168] In some embodiments, the reflective surface 303 is further configured as follows:

[0169] Obtain the first distance between the target satellite and the reflector 303, the first elevation angle from the center position of the reflector 303 to the target satellite, and the first azimuth angle from the center position of the reflector 303 to the target satellite;

[0170] The first elevation angle is obtained by performing a sine operation on the first elevation angle, and the first elevation angle is obtained by performing a cosine operation on the first elevation angle. The first azimuth angle is obtained by performing a sine operation on the first azimuth angle, and the first azimuth angle is obtained by performing a cosine operation on the first azimuth angle.

[0171] The product of the first distance, the first elevation sine, and the first azimuth cosine is used as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is used as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is used as the third directional position of the target satellite.

[0172] The first target position is obtained by performing vector operations on the first direction position, the second direction position, and the third direction position of the target satellite;

[0173] Obtain the second distance between the disturbed terminal 302 and the reflective surface 303, the second elevation angle from the center position of the reflective surface 303 to the disturbed terminal 302, and the second azimuth angle from the center position of the reflective surface 303 to the disturbed terminal 302;

[0174] The second elevation angle is obtained by performing a sine operation on the second elevation angle, and the second elevation angle is obtained by performing a cosine operation on the second elevation angle. The second azimuth angle is obtained by performing a sine operation on the second azimuth angle, and the second azimuth angle is obtained by performing a cosine operation on the second azimuth angle.

[0175] The product of the second distance, the second elevation angle sine, and the second azimuth angle cosine is used as the first directional position of the disturbed terminal 302; the product of the second distance, the second elevation angle sine, and the second azimuth angle sine is used as the second directional position of the disturbed terminal 302; and the product of the second distance and the second elevation angle cosine is used as the third directional position of the disturbed terminal 302.

[0176] The second disturbed position is obtained by performing vector operations on the first directional position, the second directional position, and the third directional position of the disturbed terminal 302.

[0177] In some embodiments, the system further includes satellites in the disrupted system;

[0178] The reflective surface 303 is further configured as follows:

[0179] The system obtains the first transmit power of the satellite in the jammed system, the first transmit antenna gain of the satellite in the jammed system, the first receive antenna gain of the jammed terminal 302, the first signal wavelength of the satellite in the jammed system, and the fourth distance between the satellite in the jammed system and the jammed terminal 302.

[0180] The effective received power of the disturbed terminal 302 is obtained by performing calculations on the first transmit power, the first transmit antenna gain, the first receive antenna gain, the first signal wavelength, and the fourth distance according to the Fries transmission formula.

[0181] Obtain the reflection coefficient of the reflection unit at the target position in the reflection surface 303; wherein, the reflection unit at the target position is the reflection unit in the reflection surface 303 located at the target row and target column positions;

[0182] Based on the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle, and the second azimuth angle, the power of the interference signal superimposed on the interference signal and the reflected signal received by the disturbed terminal 302 is determined;

[0183] The effective received power and the interference signal power are calculated and processed according to the signal-to-interference-plus-noise ratio (SIR) formula to obtain the first SIR of the disturbed terminal 302.

[0184] In some embodiments, the reflective surface 303 is further configured as follows:

[0185] Determine the unit modulus constraint condition based on the reflection coefficient;

[0186] The first system geometric constraints and the first reflection geometric constraints are determined based on the first target location and the second disturbed location.

[0187] Based on the unit modulus constraint, the first system geometric constraint, the first reflection geometric constraint, and the first signal-to-interference-plus-noise ratio, the interference avoidance model is constructed.

[0188]

[0189] Wherein, P1 is the first position adjustment data. The first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal 302. The reflection coefficient is the reflection coefficient of the reflecting element at the target position in the reflecting surface 303. The target row of the target position reflection unit. The target column of the target position reflection unit, This represents the total number of rows of the reflective surface 303. The total number of columns of the reflecting surface 303. The first elevation angle, This is the first azimuth angle. This is the second elevation angle. This is the second azimuth angle. The unit modulus constraint condition is... These are the geometric constraints of the first system. This is the first reflection geometric constraint condition.

[0190] In some embodiments, the system further includes a target satellite;

[0191] The reflective surface 303 is further configured as follows:

[0192] Obtain the first target position of the target satellite and the second target position of the target terminal 301;

[0193] A signal enhancement model is constructed based on the first target location, the second target location, and the target received power; wherein, the signal enhancement model is used to optimize the target received power, and the signal enhancement model includes a second system geometric constraint and a second reflection geometric constraint determined based on the first target location and the second target location;

[0194] The signal enhancement model is solved to obtain the second position adjustment data; wherein the second position adjustment data includes a second phase shift and a second orientation.

[0195] In some embodiments, the reflective surface 303 is further configured as follows:

[0196] Obtain the first distance between the target satellite and the reflector 303, the first elevation angle from the center position of the reflector 303 to the target satellite, and the first azimuth angle from the center position of the reflector 303 to the target satellite;

[0197] The first elevation angle is obtained by performing a sine operation on the first elevation angle, and the first elevation angle is obtained by performing a cosine operation on the first elevation angle. The first azimuth angle is obtained by performing a sine operation on the first azimuth angle, and the first azimuth angle is obtained by performing a cosine operation on the first azimuth angle.

[0198] The product of the first distance, the first elevation sine, and the first azimuth cosine is used as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is used as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is used as the third directional position of the target satellite.

[0199] The first target position is obtained by performing vector operations on the first direction position, the second direction position, and the third direction position of the target satellite;

[0200] Obtain the third distance between the target terminal 301 and the reflective surface 303, the third elevation angle from the center position of the reflective surface 303 to the target terminal 301, and the third azimuth angle from the center position of the reflective surface 303 to the target terminal 301;

[0201] The third elevation angle is obtained by performing a sine operation on the third elevation angle, and the third elevation angle is obtained by performing a cosine operation on the third elevation angle. The third azimuth angle is obtained by performing a sine operation on the third azimuth angle, and the third azimuth angle is obtained by performing a cosine operation on the third azimuth angle.

[0202] The product of the third distance, the sine of the third elevation angle, and the cosine of the third azimuth angle is used as the first directional position of the target terminal 301; the product of the third distance, the sine of the third elevation angle, and the sine of the third azimuth angle is used as the second directional position of the target terminal 301; and the product of the third distance and the cosine of the third elevation angle is used as the third directional position of the target terminal 301.

[0203] The second target position is obtained by performing vector operations on the first direction position, the second direction position, and the third direction position of the target terminal 301.

[0204] The second transmit power of the target satellite, the second transmit antenna gain of the target satellite, the second receive antenna gain of the target terminal 301, the second signal wavelength of the target satellite, the first power radiation pattern of the target satellite, and the second power radiation pattern of the target position reflection unit are obtained, wherein the target position reflection unit is the reflection unit located in the target row and target column positions of the reflection surface 303;

[0205] The target received power of the target terminal 301 is obtained by performing calculations on the second transmit power, the second transmit antenna gain, the second receive antenna gain, the second signal wavelength, the first power radiation pattern, and the second power radiation pattern according to the Fries transmission formula.

[0206] The total interference power of the disturbed terminal 302 is obtained by summing the first interference of the target satellite to the disturbed terminal 302 and the second interference of the reflector 303 to the disturbed terminal 302.

[0207] The effective received power, the total interference power, and the white noise power are calculated and processed according to the signal-to-interference-plus-noise ratio (SIR) formula to obtain the second SIR of the disturbed terminal 302.

[0208] In some embodiments, the reflective surface 303 is further configured as follows:

[0209] Determine the unit modulus constraint condition based on the reflection coefficient;

[0210] Determine the second system geometric constraints and the second reflection geometric constraints based on the first target position and the second target position;

[0211] The signal-to-interference-plus-noise ratio (SIR) constraint is determined based on the second SIR and the preset SIR threshold.

[0212] Based on the unity modulus constraint, the second system geometric constraint, the second reflection geometric constraint, the signal-to-interference-plus-noise ratio constraint, and the target received power, the signal enhancement model is constructed.

[0213]

[0214] Wherein, P2 is the second position adjustment data. The target received power of the target terminal 301. The reflection coefficient is the reflection coefficient of the reflecting element at the target position in the reflecting surface 303. The target row of the target position reflection unit. The target column of the target position reflection unit, This represents the total number of rows of the reflective surface 303. The total number of columns of the reflecting surface 303. The first elevation angle, This is the first azimuth angle. The third elevation angle, For the third azimuth angle, The unit modulus constraint condition is... These are the geometric constraints of the second system. This is the second reflection geometric constraint condition. This refers to the signal-to-interference-plus-noise ratio (SINR) constraint. This is the preset signal-to-interference-plus-noise ratio (SIN / N) threshold.

[0215] For ease of description, the above apparatus is described in terms of its functions, divided into various modules. Of course, in implementing this disclosure, the functions of each module can be implemented in one or more software and / or hardware.

[0216] The apparatus of the above embodiments is used to implement the corresponding satellite communication method based on the reflector in any of the foregoing embodiments, and has the beneficial effects of the corresponding method embodiments, which will not be repeated here.

[0217] Based on the same inventive concept, corresponding to the methods of any of the above embodiments, this disclosure also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the satellite communication method based on a reflector described in any of the above embodiments.

[0218] Figure 4 This embodiment illustrates a more specific hardware structure of an electronic device. The device may include a processor 1010, a memory 1020, an input / output interface 1030, a communication interface 1040, and a bus 1050. The processor 1010, memory 1020, input / output interface 1030, and communication interface 1040 are interconnected internally via the bus 1050.

[0219] The processor 1010 can be implemented using a general-purpose CPU (Central Processing Unit), microprocessor, application-specific integrated circuit (ASIC), or one or more integrated circuits, and is used to execute relevant programs to implement the technical solutions provided in the embodiments of this specification.

[0220] The memory 1020 can be implemented in the form of ROM (Read Only Memory), RAM (Random Access Memory), static storage device, dynamic storage device, etc. The memory 1020 can store the operating system and other applications. When the technical solutions provided in the embodiments of this specification are implemented by software or firmware, the relevant program code is stored in the memory 1020 and is called and executed by the processor 1010.

[0221] The input / output interface 1030 is used to connect input / output modules to realize information input and output. Input / output modules can be configured as components within the device (not shown in the figure) or externally connected to the device to provide corresponding functions. Input devices may include keyboards, mice, touchscreens, microphones, various sensors, etc., while output devices may include displays, speakers, vibrators, indicator lights, etc.

[0222] The communication interface 1040 is used to connect the communication module (not shown in the figure) to enable communication between this device and other devices. The communication module can communicate via wired means (such as USB (Universal Serial Bus), network cable, etc.) or wireless means (such as mobile network, WIFI (Wireless Fidelity), Bluetooth, etc.).

[0223] Bus 1050 includes a pathway for transmitting information between various components of the device, such as processor 1010, memory 1020, input / output interface 1030, and communication interface 1040.

[0224] It should be noted that although the above-described device only shows the processor 1010, memory 1020, input / output interface 1030, communication interface 1040, and bus 1050, in specific implementations, the device may also include other components necessary for normal operation. Furthermore, those skilled in the art will understand that the above-described device may only include the components necessary for implementing the embodiments of this specification, and not necessarily all the components shown in the figures.

[0225] The electronic devices described above are used to implement the corresponding satellite communication methods based on reflectors in any of the foregoing embodiments, and have the beneficial effects of the corresponding method embodiments, which will not be repeated here.

[0226] Based on the same inventive concept, corresponding to the methods of any of the above embodiments, this disclosure also provides a non-transitory computer-readable storage medium storing computer instructions for causing the computer to execute the satellite communication method based on the reflector as described in any of the above embodiments.

[0227] The computer-readable medium of this embodiment includes permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. Information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic magnetic disk storage or other magnetic storage devices, or any other non-transfer medium that can be used to store information accessible by a computing device.

[0228] The computer instructions stored in the storage medium of the above embodiments are used to cause the computer to execute the satellite communication method based on the reflector as described in any of the above embodiments, and have the beneficial effects of the corresponding method embodiments, which will not be repeated here.

[0229] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of this disclosure (including the claims) is limited to these examples; within the framework of this disclosure, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of different aspects of the embodiments of this disclosure as described above, which are not provided in detail for the sake of brevity.

[0230] Additionally, to simplify the description and discussion, and to avoid obscuring the embodiments of this disclosure, the provided drawings may or may not show well-known power / ground connections to integrated circuit (IC) chips and other components. Furthermore, the apparatus may be shown in block diagram form to avoid obscuring the embodiments of this disclosure, and this also takes into account the fact that the details of implementation of these block diagram apparatuses are highly dependent on the platform on which the embodiments of this disclosure will be implemented (i.e., these details should be fully understood by those skilled in the art). While specific details (e.g., circuits) have been set forth to describe exemplary embodiments of this disclosure, it will be apparent to those skilled in the art that the embodiments of this disclosure can be implemented without these specific details or with variations thereof. Therefore, these descriptions should be considered illustrative rather than restrictive.

[0231] Although this disclosure has been described in conjunction with specific embodiments thereof, many substitutions, modifications, and variations of these embodiments will be apparent to those skilled in the art from the foregoing description. For example, other memory architectures (e.g., dynamic RAM (DRAM)) may be used with the embodiments discussed.

[0232] This disclosure is intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this disclosure should be included within the scope of protection of this disclosure.

Claims

1. A satellite communication method based on a reflector surface, characterized in that, Applied to a satellite communication system, the satellite communication system comprising: a reflector, a target terminal, and a jammed terminal, the method comprising: The target terminal obtains its own target receiving power, compares the target receiving power with the preset ideal receiving power, obtains the judgment result, and sends it to the reflective surface; The interfered terminal transmits its own effective receiving power and the interference signal power to the reflective surface; In response to the judgment result received by the reflector being that the target received power is greater than or equal to the ideal received power, a first signal-to-interference-plus-noise ratio (SINNR) of the disturbed terminal is determined based on the effective received power and the interference signal power. An interference avoidance model is constructed based on the first SINNR. The interference avoidance model is solved to obtain the first position adjustment data of the reflector. The reflector is controlled according to the first position adjustment data. In response to the judgment result received by the reflector indicating that the target received power is less than the ideal received power, a signal enhancement model is constructed based on the target received power, the signal enhancement model is solved to obtain the second position adjustment data of the reflector, and the reflector is controlled according to the second position adjustment data.

2. The method according to claim 1, characterized in that, The system also includes a target satellite; The steps of determining the first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal, constructing an interference avoidance model based on the first SIR, and solving the interference avoidance model to obtain the first position adjustment data of the reflector include: Obtain the first target position of the target satellite and the second disrupted position of the disrupted terminal; The effective received power, the power of the interference signal superimposed with the received interference signal and the reflected signal, and the white noise power of the disturbed terminal are obtained. The effective received power, the interference signal power, and the white noise power are calculated and processed according to the signal-to-interference-plus-noise ratio formula to obtain the first signal-to-interference-plus-noise ratio of the disturbed terminal. An interference avoidance model is constructed based on the first target location, the second disturbed location, and the first signal-to-interference-plus-noise ratio (SIR). The interference avoidance model is used to optimize the first SIR, and the interference avoidance model includes a first system geometric constraint and a first reflection geometric constraint determined based on the first target location and the second disturbed location. The interference avoidance model is solved to obtain the first position adjustment data; wherein, the first position adjustment data includes a first phase shift and a first orientation.

3. The method according to claim 2, characterized in that, The process of obtaining the first target position of the target satellite and the second obstructed position of the obstructed terminal includes: Obtain the first distance between the target satellite and the reflector, the first elevation angle from the center position of the reflector to the target satellite, and the first azimuth angle from the center position of the reflector to the target satellite; The first elevation angle is obtained by performing a sine operation on the first elevation angle, and the first elevation angle is obtained by performing a cosine operation on the first elevation angle. The first azimuth angle is obtained by performing a sine operation on the first azimuth angle, and the first azimuth angle is obtained by performing a cosine operation on the first azimuth angle. The product of the first distance, the first elevation sine, and the first azimuth cosine is used as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is used as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is used as the third directional position of the target satellite. The first target position is obtained by performing vector operations on the first direction position, the second direction position, and the third direction position of the target satellite; Obtain the second distance between the disturbed terminal and the reflective surface, the second elevation angle from the center position of the reflective surface to the disturbed terminal, and the second azimuth angle from the center position of the reflective surface to the disturbed terminal; The second elevation angle is obtained by performing a sine operation on the second elevation angle, and the second elevation angle is obtained by performing a cosine operation on the second elevation angle. The second azimuth angle is obtained by performing a sine operation on the second azimuth angle, and the second azimuth angle is obtained by performing a cosine operation on the second azimuth angle. The product of the second distance, the second elevation sine, and the second azimuth cosine is used as the first directional position of the disturbed terminal; the product of the second distance, the second elevation sine, and the second azimuth sine is used as the second directional position of the disturbed terminal; and the product of the second distance and the second elevation cosine is used as the third directional position of the disturbed terminal. The second disturbed position is obtained by performing vector operations on the first directional position, the second directional position, and the third directional position of the disturbed terminal.

4. The method according to claim 3, characterized in that, The system also includes satellites in the disrupted system; The process of acquiring the effective received power of the disturbed terminal, the power of the superimposed interference signal and the reflected signal, and the white noise power, and then performing calculations on the effective received power, the interference signal power, and the white noise power according to the signal-to-interference-plus-noise ratio (SINR) formula to obtain the first SINR of the disturbed terminal includes: The system obtains the first transmit power of the satellite in the jammed system, the first transmit antenna gain of the satellite in the jammed system, the first receive antenna gain of the jammed terminal, the first signal wavelength of the satellite in the jammed system, and the fourth distance between the satellite in the jammed system and the jammed terminal. The effective received power of the disturbed terminal is obtained by performing calculations on the first transmit power, the first transmit antenna gain, the first receive antenna gain, the first signal wavelength, and the fourth distance according to the Fries transmission formula. Obtain the reflection coefficient of the reflection unit at the target position in the reflecting surface; wherein, the reflection unit at the target position is the reflection unit located at the target row and target column positions in the reflecting surface; Based on the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle, and the second azimuth angle, the power of the interference signal superimposed on the interference signal and the reflected signal is determined for the disturbed terminal. The effective received power and the interference signal power are calculated and processed according to the signal-to-interference-plus-noise ratio (SIR) formula to obtain the first SIR of the disturbed terminal.

5. The method according to claim 4, characterized in that, The interference avoidance model constructed based on the first target location, the second disturbed location, and the first signal-to-interference-plus-noise ratio includes: Determine the unit modulus constraint condition based on the reflection coefficient; The first system geometric constraints and the first reflection geometric constraints are determined based on the first target location and the second disturbed location. Based on the unit modulus constraint, the first system geometric constraint, the first reflection geometric constraint, and the first signal-to-interference-plus-noise ratio, the interference avoidance model is constructed. Wherein, P1 is the first position adjustment data. The first signal-to-interference-plus-noise ratio (SIR) of the disturbed terminal. The reflection coefficient is the reflection coefficient of the reflecting element at the target position in the reflecting surface. The target row of the target position reflection unit. The target column of the target position reflection unit, The total number of rows on the reflective surface. The total number of columns of the reflecting surface. The first elevation angle, This is the first azimuth angle. This is the second elevation angle. This is the second azimuth angle. The unit modulus constraint condition is... These are the geometric constraints of the first system. For the first reflection geometric constraint condition, in the first system geometric constraint condition It is the angle between the reflector, the target satellite, and the disturbed terminal, with the vertex of the angle being the reflector.

6. The method according to claim 5, characterized in that, The system also includes a target satellite; The step of constructing a signal enhancement model based on the target received power and solving the signal enhancement model to obtain the second position adjustment data of the reflector includes: Obtain the first target position of the target satellite and the second target position of the target terminal; A signal enhancement model is constructed based on the first target location, the second target location, and the target received power; wherein, the signal enhancement model is used to optimize the target received power, and the signal enhancement model includes a second system geometric constraint and a second reflection geometric constraint determined based on the first target location and the second target location; The signal enhancement model is solved to obtain the second position adjustment data; wherein the second position adjustment data includes a second phase shift and a second orientation.

7. The method according to claim 6, characterized in that, Before constructing the signal enhancement model based on the first target location, the second target location, and the target received power, the method further includes: Obtain the first distance between the target satellite and the reflector, the first elevation angle from the center position of the reflector to the target satellite, and the first azimuth angle from the center position of the reflector to the target satellite; The first elevation angle is obtained by performing a sine operation on the first elevation angle, and the first elevation angle is obtained by performing a cosine operation on the first elevation angle. The first azimuth angle is obtained by performing a sine operation on the first azimuth angle, and the first azimuth angle is obtained by performing a cosine operation on the first azimuth angle. The product of the first distance, the first elevation sine, and the first azimuth cosine is used as the first directional position of the target satellite; the product of the first distance, the first elevation sine, and the first azimuth sine is used as the second directional position of the target satellite; and the product of the first distance and the first elevation cosine is used as the third directional position of the target satellite. The first target position is obtained by performing vector operations on the first direction position, the second direction position, and the third direction position of the target satellite; Obtain the third distance between the target terminal and the reflective surface, the third elevation angle from the center position of the reflective surface to the target terminal, and the third azimuth angle from the center position of the reflective surface to the target terminal; The third elevation angle is obtained by performing a sine operation on the third elevation angle, and the third elevation angle is obtained by performing a cosine operation on the third elevation angle. The third azimuth angle is obtained by performing a sine operation on the third azimuth angle, and the third azimuth angle is obtained by performing a cosine operation on the third azimuth angle. The product of the third distance, the sine of the third elevation angle, and the cosine of the third azimuth angle is used as the first directional position of the target terminal; the product of the third distance, the sine of the third elevation angle, and the sine of the third azimuth angle is used as the second directional position of the target terminal; and the product of the third distance and the cosine of the third elevation angle is used as the third directional position of the target terminal. The second target position is obtained by performing vector operations on the first directional position, the second directional position, and the third directional position of the target terminal. The second transmit power of the target satellite, the second transmit antenna gain of the target satellite, the second receive antenna gain of the target terminal, the second signal wavelength of the target satellite, the first power radiation pattern of the target satellite, and the second power radiation pattern of the target position reflection unit are obtained, wherein the target position reflection unit is the reflection unit located in the target row and target column positions in the reflection surface; The target received power of the target terminal is obtained by performing calculations on the second transmit power, the second transmit antenna gain, the second receive antenna gain, the second signal wavelength, the first power radiation pattern, and the second power radiation pattern according to the Fries transmission formula. The total interference power of the affected terminal is obtained by summing the first interference from the target satellite to the affected terminal and the second interference from the reflective surface to the affected terminal. The effective received power, the total interference power, and the white noise power are calculated and processed according to the signal-to-interference-plus-noise ratio (SIR) formula to obtain the second SIR of the disturbed terminal.

8. The method according to claim 7, characterized in that, The step of constructing a signal enhancement model based on the first target location, the second target location, and the target received power includes: Determine the unit modulus constraint condition based on the reflection coefficient; Determine the second system geometric constraints and the second reflection geometric constraints based on the first target position and the second target position; The signal-to-interference-plus-noise ratio (SIR) constraint is determined based on the second SIR and the preset SIR threshold. Based on the unity modulus constraint, the second system geometric constraint, the second reflection geometric constraint, the signal-to-interference-plus-noise ratio constraint, and the target received power, the signal enhancement model is constructed. Wherein, P2 is the second position adjustment data. The target received power of the target terminal. The reflection coefficient is the reflection coefficient of the reflecting element at the target position in the reflecting surface. The target row of the target position reflection unit. The target column of the target position reflection unit, The total number of rows on the reflective surface. The total number of columns of the reflecting surface. The first elevation angle, This is the first azimuth angle. The third elevation angle, For the third azimuth angle, The unit modulus constraint condition is... The geometric constraints of the second system are as follows: It is the angle between the reflecting surface, the target satellite, and the target terminal, with the vertex of the angle being the reflecting surface. This is the second reflection geometric constraint condition. This refers to the signal-to-interference-plus-noise ratio (SINR) constraint. This is the second signal-to-interference-plus-noise ratio (SIR). This is the preset signal-to-interference-plus-noise ratio (SIN / N) threshold.

9. A satellite communication system based on a reflector, characterized in that, The satellite communication system includes: a reflector, a target terminal, and a jammed terminal. The target terminal is configured to acquire its own target receiving power, compare the target receiving power with a preset ideal receiving power, obtain a judgment result, and send it to the reflective surface; The interfered terminal is configured to transmit its effective received power and the interference signal power to the reflective surface; The reflector is configured to respond to the judgment result received by the reflector being greater than or equal to the ideal received power, to determine the first signal-to-interference-plus-noise ratio (SNR) of the disturbed terminal based on the effective received power and the interference signal power, to construct an interference avoidance model based on the first SNR, to solve the interference avoidance model to obtain the first position adjustment data of the reflector, and to control the reflector according to the first position adjustment data. The reflector is further configured to respond to the judgment result received by the reflector indicating that the target received power is less than the ideal received power, to construct a signal enhancement model based on the target received power, to solve the signal enhancement model to obtain second position adjustment data of the reflector, and to control the reflector according to the second position adjustment data.

10. An electronic device, characterized in that, It includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the program, implements the method as described in any one of claims 1 to 8.

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