CN116545504A - Satellite communication method and system based on reflecting surface and electronic equipment - Google Patents

Satellite communication method and system based on reflecting surface and electronic equipment Download PDF

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Publication number
CN116545504A
CN116545504A CN202310565175.6A CN202310565175A CN116545504A CN 116545504 A CN116545504 A CN 116545504A CN 202310565175 A CN202310565175 A CN 202310565175A CN 116545504 A CN116545504 A CN 116545504A
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target
interference
signal
terminal
reflecting surface
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景文鹏
曹宁
郑子元
陈亚文
路兆铭
温向明
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Beijing University of Posts and Telecommunications
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Beijing University of Posts and Telecommunications
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Priority to CN202310565175.6A priority Critical patent/CN116545504A/en
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1851—Systems using a satellite or space-based relay
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B15/00—Suppression or limitation of noise or interference
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B17/00—Monitoring; Testing
    • H04B17/30—Monitoring; Testing of propagation channels
    • H04B17/309—Measuring or estimating channel quality parameters
    • H04B17/336—Signal-to-interference ratio [SIR] or carrier-to-interference ratio [CIR]
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B17/00—Monitoring; Testing
    • H04B17/30—Monitoring; Testing of propagation channels
    • H04B17/391—Modelling the propagation channel
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
    • Y02D30/00—Reducing energy consumption in communication networks
    • Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks

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  • Engineering & Computer Science (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Quality & Reliability (AREA)
  • Radio Relay Systems (AREA)

Abstract

The disclosure provides a satellite communication method and system based on a reflecting surface and electronic equipment. The method comprises the following steps: the target terminal obtains the target receiving power of the target terminal, compares and judges the target receiving power with the preset ideal receiving power, obtains a judging result and sends the judging result to the reflecting surface; the disturbed terminal transmits the effective receiving power and the interference signal power to the reflecting surface; responding to the judgment result received by the reflecting surface, wherein the target received power is greater than or equal to the ideal received power, determining a first signal-to-interference-and-noise ratio of the interfered terminal, constructing an interference avoidance model based on the first signal-to-interference-and-noise ratio, solving the interference avoidance model to obtain first position adjustment data of the reflecting surface, and controlling the reflecting surface; and responding to the judgment result received by the reflecting surface as that the target receiving power is smaller than the ideal receiving power, constructing a signal enhancement model based on the target receiving power, solving the signal enhancement model to obtain second position adjustment data of the reflecting surface, and controlling the reflecting surface.

Description

Satellite communication method and system based on reflecting surface and electronic equipment
Technical Field
The disclosure relates to the technical field of satellite communication, in particular to a satellite communication method, system and electronic equipment based on a reflecting surface.
Background
Satellite communication has the advantages of wide coverage range and the like. However, due to the characteristics of the satellite communication such as openness and long-distance transmission characteristics, and the influence of factors such as geography and natural environment, the advantages of the satellite communication cannot be fully utilized. In particular, due to deep fades (e.g., shadows due to buildings and mountains), a direct communication link from the satellite to the ground terminal may not always be available. In addition, in the art, subsequent satellites cannot interfere with satellites that are already in orbit and have dominant frequencies.
In view of this, how to fully exploit the advantages of satellite communication and avoid interference to already in-orbit satellites is a highly desirable problem.
Disclosure of Invention
Accordingly, an objective of the present disclosure is to provide a satellite communication method, system and electronic device based on a reflection surface, which are used for solving or partially solving the above technical problems.
In view of the above object, a first aspect of the present disclosure proposes a satellite communication method based on a reflection surface, applied to a satellite communication system, the satellite communication system comprising: the method comprises the following steps of:
the target terminal obtains the target receiving power of the target terminal, compares and judges the target receiving power with the preset ideal receiving power, obtains a judging result and sends the judging result to the reflecting surface;
The disturbed terminal transmits the effective receiving power and the interference signal power to the reflecting surface;
responding to the judgment result received by the reflecting surface to be that the target received power is greater than or equal to the ideal received power, determining a first signal-to-interference-plus-noise ratio of the interfered terminal based on the effective received power and the interference signal power, constructing an interference avoidance model based on the first signal-to-interference-plus-noise ratio, solving the interference avoidance model to obtain first position adjustment data of the reflecting surface, and controlling the reflecting surface according to the first position adjustment data;
and responding to the judgment result received by the reflecting surface to be that the target receiving power is smaller than the ideal receiving power, constructing a signal enhancement model based on the target receiving power, solving the signal enhancement model to obtain second position adjustment data of the reflecting surface, and controlling the reflecting surface according to the second position adjustment data.
Based on the same inventive concept, a second aspect of the present disclosure proposes a satellite communication system based on a reflection surface, the satellite communication system comprising: the reflecting surface, the target terminal and the disturbed terminal,
The target terminal is configured to acquire own target receiving power, compare and judge the target receiving power with preset ideal receiving power, acquire a judging result and send the judging result to the reflecting surface;
the disturbed terminal is configured to transmit the effective received power and the interference signal power of the disturbed terminal to the reflecting surface;
the reflecting surface is configured to determine a first signal-to-interference-and-noise ratio of the interfered terminal based on the effective receiving power and the interference signal power in response to the determination result received by the reflecting surface being that the target receiving power is greater than or equal to the ideal receiving power, construct an interference avoidance model based on the first signal-to-interference-and-noise ratio, solve the interference avoidance model to obtain first position adjustment data of the reflecting surface, and control the reflecting surface according to the first position adjustment data;
the reflecting surface is further configured to respond to the judgment result received by the reflecting surface that the target received power is smaller than the ideal received power, construct a signal enhancement model based on the target received power, solve the signal enhancement model to obtain second position adjustment data of the reflecting surface, and control the reflecting surface according to the second position adjustment data.
Based on the same inventive concept, a third aspect of the present disclosure proposes an electronic device comprising a memory, a processor and a computer program stored on the memory and executable by the processor, the processor implementing the method as described above when executing the computer program.
As can be seen from the above, the satellite communication method, system and electronic device based on the reflection surface provided by the present disclosure determine whether the target communication system corresponding to the target terminal can perform normal communication by comparing and judging the target received power of the target terminal with the preset ideal received power. When the target communication system can normally communicate, a first signal-to-interference-and-noise ratio of the interfered terminal is determined, an interference avoidance model is constructed based on the first signal-to-interference-and-noise ratio, and the first position adjustment data of the reflecting surface is determined to control the reflecting surface, so that the reflecting signal generated by the reflecting surface counteracts the interference signal received by the interfered terminal, and the interference of the target communication system to the interfered communication system is avoided. When the target communication system cannot perform normal communication, a signal enhancement model is built based on the target received power, the second position adjustment data of the reflecting surface is determined to control the reflecting surface, and interference to a disturbed system is reduced on the basis of ensuring that the target communication system can perform normal communication.
Drawings
In order to more clearly illustrate the technical solutions of the present disclosure or related art, the drawings required for the embodiments or related art description will be briefly described below, and it is apparent that the drawings in the following description are only embodiments of the present disclosure, and other drawings may be obtained according to these drawings without inventive effort to those of ordinary skill in the art.
FIG. 1A is a flow chart of a reflective surface based satellite communication method according to an embodiment of the present disclosure;
FIG. 1B is a system block diagram of a line of sight of an embodiment of the present disclosure;
FIG. 1C is a system block diagram of a non-line-of-sight of an embodiment of the present disclosure;
FIG. 1D is a schematic view of a reflective surface according to an embodiment of the disclosure;
FIG. 2 is a flow chart of a method of controlling a reflective surface according to an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of a configuration of a reflective surface based satellite communication system according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of an electronic device according to an embodiment of the disclosure.
Detailed Description
For the purposes of promoting an understanding of the principles and advantages of the disclosure, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same.
It should be noted that unless otherwise defined, technical or scientific terms used in the embodiments of the present disclosure should be given the ordinary meaning as understood by one of ordinary skill in the art to which the present disclosure pertains. The terms "first," "second," and the like, as used in embodiments of the present disclosure, do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that elements or items preceding the word are included in the element or item listed after the word and equivalents thereof, but does not exclude other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", etc. are used merely to indicate relative positional relationships, which may also be changed when the absolute position of the object to be described is changed.
As described above, how to overcome deep fading in satellite communication and avoid interference to already in-orbit satellites has become an important research problem.
Based on the above description, as shown in fig. 1A, the satellite communication method based on the reflection surface proposed in the present embodiment is applied to a satellite communication system, where the satellite communication system includes: the method comprises the following steps of:
and step 101, the target terminal acquires own target receiving power, compares and judges the target receiving power with preset ideal receiving power, obtains a judging result and sends the judging result to the reflecting surface.
In particular, the satellite communication system includes a reflecting surface (i.e., an intelligent reflecting surface), a target satellite, a target terminal, a satellite in a victim system, and a victim terminal. The satellite in the disturbed system communicates with the disturbed terminal. The reflecting surface comprises a reflecting surface controller, the position of the reflecting surface is controlled and adjusted by the reflecting surface controller,
the judging result comprises the following steps: the target reception power of the target terminal is equal to or greater than the ideal reception power, or the target reception power is less than the ideal reception power.
When the target receiving power is larger than or equal to the ideal receiving power, normal communication can be carried out between the target satellite and the target terminal, namely, the target satellite link is a line-of-sight link; when the target received power is smaller than the ideal received power, normal communication between the target satellite and the target terminal cannot be performed, i.e. the target satellite link is a non-line-of-sight link.
And 102, the interfered terminal transmits the effective received power and the interference signal power to the reflecting surface.
In specific implementation, the interference signal power is the signal power of the superposition of the interference signal and the reflected signal. The reflected signal is a signal reflected by the reflecting surface to the interfered terminal, and the interference signal is a signal which is generated by communication between the target satellite and the target terminal and interferes with the interfered terminal.
And step 103, in response to the result of the judgment received by the reflecting surface being that the target received power is greater than or equal to the ideal received power, determining a first signal-to-interference-and-noise ratio of the interfered terminal based on the effective received power and the interference signal power, constructing an interference avoidance model based on the first signal-to-interference-and-noise ratio, solving the interference avoidance model to obtain first position adjustment data of the reflecting surface, and controlling the reflecting surface according to the first position adjustment data.
In the implementation, when the target received power is greater than or equal to the ideal received power, normal communication can be performed between the target satellite and the target terminal.
As shown in fig. 1B, fig. 1B is a system configuration diagram of a viewing distance according to an embodiment of the present disclosure. The target satellite S and the target terminal GT are a target communication system, and normal communication is performed based on a downlink signal from the system. Satellite S in a disturbed system I With the disturbed terminal GT I The communication is carried out based on downlink signals of the interfered communication system. At this time, the victim terminal GT I And also receives the interference signal of the interfered system sent by the target satellite S, and generates interference to the interfered communication system. In order to eliminate the interference to the disturbed communication system, the reflection surface is adjusted by the first position adjustment data, and the interference signal of the disturbed communication system is restrained by the reflection signal of the intelligent reflection surface RIS, so that the interference of the target satellite S to the disturbed communication system is avoided.
And 104, constructing a signal enhancement model based on the target received power in response to the judgment result received by the reflecting surface being that the target received power is smaller than the ideal received power, solving the signal enhancement model to obtain second position adjustment data of the reflecting surface, and controlling the reflecting surface according to the second position adjustment data.
In particular, when the target received power is smaller than the ideal received power, normal communication between the target satellite and the target terminal cannot be performed.
As shown in fig. 1C, fig. 1C is a system configuration diagram of a non-line-of-sight of an embodiment of the present disclosure. The target satellite S and the target terminal GT are a target communication system, and communication is performed based on a downlink signal from the system, and a satellite-ground direct link of the target communication system is blocked. Satellite S in a system I With the disturbed terminal GT I The communication is carried out based on downlink signals of the interfered communication system. At this time, receivedScrambling terminal GT I And receiving interference signals of the interfered system, which are respectively sent by the target satellite S and the reflecting surface, and generating interference to the interfered communication system. In order to reduce the interference of the disturbed communication system while ensuring that the target communication system can perform normal communication, the reflecting surface is adjusted by the second position adjustment data, and the normal communication of the target communication system is recovered by the reflecting signal of the intelligent reflecting surface RIS while reducing the interference signal of the disturbed communication system.
Through the embodiment, the target receiving power of the target terminal is compared with the preset ideal receiving power, so that whether the target communication system corresponding to the target terminal can perform normal communication or not is determined. When the target communication system can normally communicate, a first signal-to-interference-and-noise ratio of the interfered terminal is determined, an interference avoidance model is constructed based on the first signal-to-interference-and-noise ratio, and the first position adjustment data of the reflecting surface is determined to control the reflecting surface, so that the reflecting signal generated by the reflecting surface counteracts the interference signal received by the interfered terminal, and the interference of the target communication system to the interfered communication system is avoided. When the target communication system cannot perform normal communication, a signal enhancement model is built based on the target received power, the second position adjustment data of the reflecting surface is determined to control the reflecting surface, and interference to a disturbed system is reduced on the basis of ensuring that the target communication system can perform normal communication.
In some embodiments, the system further comprises a target satellite; step 103 comprises:
step 1031, obtaining a first target position of the target satellite and a second disturbed position of the disturbed terminal.
Step 1032, obtaining the effective receiving power of the interfered terminal, the interference signal power obtained by superposition of the interference signal and the reflected signal, and the white noise power, and performing operation processing on the effective receiving power, the interference signal power, and the white noise power according to a signal-to-interference-and-noise ratio formula, so as to obtain the first signal-to-interference-and-noise ratio of the interfered terminal.
Step 1033, constructing an interference avoidance model based on the first target location, the second disturbed location and the first signal to interference plus noise ratio; the interference avoidance model is used for optimizing the first signal-to-interference-and-noise ratio, and comprises a first system geometric constraint condition and a first reflection geometric constraint condition which are determined based on the first target position and the second disturbed position.
Step 1034, solving 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.
When the target communication system can normally communicate, a first target position of the target satellite and a second disturbed position of the disturbed terminal are obtained, and a first system geometric constraint condition and a first reflection geometric constraint condition are determined based on the first target position and the second disturbed position. And determining a first signal-to-interference-and-noise ratio of the disturbed terminal, constructing an interference avoidance model based on the first signal-to-interference-and-noise ratio and a first constraint condition, and determining first position adjustment data of the reflecting surface to control the reflecting surface. The interference avoidance model is used to determine first position adjustment data that satisfies a first constraint condition and when the first signal-to-interference-and-noise ratio is maximum. Wherein the first constraint includes a first system geometry constraint and a first reflection geometry constraint, and further includes a unit modulus constraint.
According to the scheme, the reflection surface is controlled to be adjusted based on the first position adjustment data determined by the interference avoidance model, so that the reflection signal generated by the reflection surface suppresses the interference signal received by the interfered terminal, and the interference of the target communication system on the interfered communication system is avoided.
In some embodiments, step 1031 comprises:
step 10311, obtaining a first distance between the target satellite and the reflecting surface, wherein a central position of the reflecting surface is at a first elevation angle to the target satellite, and a central position of the reflecting surface is at a first azimuth angle to the target satellite.
Step 10312, performing sine operation on the first elevation angle to obtain a first elevation angle sine, performing cosine operation on the first elevation angle to obtain a first elevation angle cosine, performing sine operation on the first azimuth angle to obtain a first azimuth angle sine, and performing cosine operation on the first azimuth angle to obtain a first azimuth angle cosine.
Step 10313, using a product of the first distance, the first elevation sine, and the first azimuth cosine as a target satellite first direction position, using a product of the first distance, the first elevation sine, and the first azimuth sine as a target satellite second direction position, and using a product of the first distance and the first elevation cosine as a target satellite third direction position.
And step 10314, performing vector operation on the first direction position of the target satellite, the second direction position of the target satellite and the third direction position of the target satellite to obtain the first target position.
In practice, according to the first distance d SR First elevation angle theta S And a first azimuth angleA first target location is determined and a second target location is determined,
wherein q S Is a first target position of the target satellite.
Step 10315, obtaining a second distance between the disturbed terminal and the reflection surface, wherein the central position of the reflection surface is at a second elevation angle to the disturbed terminal, and the central position of the reflection surface is at a second azimuth angle to the disturbed terminal.
Step 10316, performing sine operation on the second elevation to obtain a second elevation sine, performing cosine operation on the second elevation to obtain a second elevation cosine, performing sine operation on the second azimuth to obtain a second azimuth sine, and performing cosine operation on the second azimuth to obtain a second azimuth cosine.
Step 10317, taking the product of the second distance, the second elevation sine and the second azimuth cosine as a first direction position of the disturbed terminal, taking the product of the second distance, the second elevation sine and the second azimuth sine as a second direction position of the disturbed terminal, and taking the product of the second distance and the second elevation cosine as a third direction position of the disturbed terminal.
And step 10318, performing vector operation on the first direction position of the interfered terminal, the second direction position of the interfered terminal and the third direction position of the interfered terminal to obtain the second interfered position.
In practice, according to the second distanceSecond elevation +.>And a second azimuth angle->The second disturbed position is determined and,
wherein,,and a second disturbed position of the disturbed terminal.
According to the scheme, the first system geometric constraint condition and the first reflection geometric constraint condition are determined according to the target satellite position, the disturbed terminal position and the relevant position parameters by determining the first target position of the target satellite and the second disturbed position of the disturbed terminal, so that the constructed interference avoidance model accords with the actual situation, and the determined first position adjustment data is the first phase shift and the first orientation in a reasonable range.
In some embodiments, the system further comprises a satellite in the disturbed system; step 1032 includes:
step 10321, obtaining a first transmission power of the satellite in the disturbed system, a first transmission antenna gain of the satellite in the disturbed system, a first reception antenna gain of the disturbed terminal, a first signal wavelength of the satellite in the disturbed system, and a fourth distance between the satellite in the disturbed system and the disturbed terminal.
Step 10322, performing operation processing 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 a fries transmission formula, to obtain an effective receive power of the interfered terminal.
In particular, fries transmission formula (Friis Free Space Formula) is an antenna theory formula for calculating the received power from a transmitting antenna to a receiving antenna. The formula is:wherein P is r For receiving the power of the antenna, P t For transmitting power of transmitting antenna, G t For transmitting antenna gain, G r For the receive antenna gain, λ is the operating wavelength and R is the distance between the transmit and receive antennas.
First transmitting powerFirst transmitting antenna gain->First receiving antenna gain->First signal wavelength>And a fourth distance->Substituting the Fries transmission formula to obtain the effective receiving power of the interfered terminal,
wherein,,and effectively receiving power for the interfered terminal.
Step 10323, obtaining a reflection coefficient of a target position reflection unit in the reflection surface; the target position reflecting unit is a reflecting unit positioned at the target row and the target column in the reflecting surface.
And step 10324, determining interference signal power of the interference signal received by the interfered terminal and the superposition of the reflected signal according to the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle and the second azimuth angle.
In particular, the reflection coefficient of the target position reflection unit in the reflection surface isWherein m is 1 For a target row of target position reflecting units, m 2 Is a target column of target position reflecting units.
According to the reflection coefficientFirst elevation angle theta S First azimuth ∈>Second elevation +.>And a second azimuth angle->Determining the interference signal power of the interference signal and the reflected signal superposition received by the interfered terminal
Wherein the interference signal power is also equal to the transmission power of the target satellite, the antenna gain of the interfered terminal, the transmission distance of the target satellite to the reflecting surface (i.e. the first distance d SR ) Transmission distance of disturbed terminal to reflecting surface (second distance)Separation of) And the transmission distance of the target satellite to the victim terminal, etc.
And step 10325, performing operation processing on the effective received power and the interference signal power according to a signal-to-interference-and-noise ratio formula to obtain a first signal-to-interference-and-noise ratio of the interfered terminal.
In particular, the signal-to-interference-and-noise ratio SINR (Signal to Interference plus Noise Ratio) refers to the ratio of the signal to the sum of interference and noise in the system. The formula is:wherein SINR is signal-to-interference-plus-noise ratio, P S For the effective power of the signal, P I To the effective power of the interference signal, P N Is the effective power of the noise.
Efficient received power of a terminal to be scrambledInterference signal power of interference signal and reflected signal superposition received by interfered terminal>And additive white gaussian noise of the victim terminal +.>) Substituting the power into the signal-to-interference-and-noise ratio formula to obtain a first signal-to-interference-and-noise ratio of the interfered terminal,
wherein,,and the first signal-to-interference-and-noise ratio of the interfered terminal.
According to the scheme, the interference degree of the interfered terminal can be determined according to the first signal-to-interference ratio of the interfered terminal by calculating the first signal-to-interference ratio of the interfered terminal, and the interference avoidance model is constructed based on the first signal-to-interference ratio, so that the first position adjustment data of the reflecting surface when the interference degree of the interfered terminal is the lowest can be determined, and the interference to the interfered terminal is avoided.
In some embodiments, step 1033 includes:
step 10331, determining a unit modulus constraint based on the reflection coefficient.
Step 10332, determining the first system geometry constraint and the first reflection geometry constraint based on the first target location and the second disturbed position.
Step 10333, constructing the disturbance avoidance model based on the unit modulus constraint, the first system geometry constraint, the first reflection geometry constraint, and the first signal-to-interference-and-noise ratio,
wherein P1 is the first position adjustment data,for the first of the disturbed terminalsSignal to interference plus noise ratio,/->For the reflection coefficient, m, of the target position reflection unit in the reflection surface 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 For the total number of lines of the reflecting surface, M 2 For the total number of columns of the reflecting surface, θ S For said first elevation,/a>For the first azimuth angle, θ TI For said second elevation,/->For the second azimuth angle in question,for the unit modulus constraint condition described above,for the first system geometry constraint,for the first reflective geometry constraint.
In the implementation, the interference avoidance model determines first position adjustment data of the reflecting surface corresponding to the maximum signal-to-interference-and-noise ratio under the condition that the constraint condition is met. Therefore, the reflecting surface is adjusted according to the first position adjustment data, so that the first signal-to-interference-and-noise ratio of the interfered terminal can be maximized, and interference of the interfered terminal is avoided.
Wherein, psi is the angle of the contained angle between reflecting surface, target satellite and the terminal that disturbed in the first system geometry constraint condition, and the summit of contained angle is target satellite.
By the scheme, the interference avoidance model is constructed based on the first signal-to-interference-and-noise ratio, and the first position adjustment data of the reflecting surface is determined to control the reflecting surface, so that the reflected signal generated by the reflecting surface suppresses the interference signal received by the interfered terminal, and the interference of the target communication system on the interfered communication system is avoided.
In some embodiments, the system further comprises a target satellite; step 104 comprises:
step 1041, obtaining a first target position of the target satellite and a second target position of the target terminal.
Step 1042, constructing a signal enhancement model based on the first target location, the second target location, and the target received power; the signal enhancement model is used for optimizing the target receiving power, and a second system geometric constraint condition and a second reflection geometric constraint condition which are determined based on the first target position and the second target position are included in the signal enhancement model.
Step 1043, solving 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.
When the target communication system cannot normally communicate, a first target position of the target satellite and a second target position of the target terminal are acquired, and a second system geometric constraint condition and a second reflection geometric constraint condition are determined based on the first target position and the second target position. And constructing a signal enhancement model based on the target received power and the second constraint condition, and determining second position adjustment data of the reflecting surface to control the reflecting surface. The signal enhancement model is used to determine second position adjustment data that satisfies a second constraint and when the target receives maximum. The second constraint condition comprises a second system geometric constraint condition and a second reflection geometric constraint condition, and further comprises a unit modulus constraint condition and a signal-to-interference-and-noise ratio constraint condition.
The signal-to-interference-and-noise ratio constraint condition is determined based on a second signal-to-interference-and-noise ratio of the interfered terminal and a preset signal-to-interference-and-noise ratio threshold value, so that the determined second position adjustment data reduces interference to the interfered terminal on the basis of ensuring normal communication between the target satellite and the target terminal.
By the scheme, the reflection surface is controlled to be adjusted based on the second position adjustment data determined by the signal enhancement model, so that the interference to the interfered system is reduced on the basis of ensuring that the target communication system can perform normal communication.
In some embodiments, prior to step 1042, further comprising:
step 1042A, obtaining a first distance between the target satellite and the reflective surface, the central position of the reflective surface being at a first elevation angle to the target satellite, the central position of the reflective surface being at a first azimuth angle to the target satellite.
Step 1042B, performing sine operation on the first elevation to obtain a first elevation sine, performing cosine operation on the first elevation to obtain a first elevation cosine, performing sine operation on the first azimuth to obtain a first azimuth sine, and performing cosine operation on the first azimuth to obtain a first azimuth cosine.
Step 1042C, using the product of the first distance, the first elevation sine, and the first azimuth cosine as the first direction position of the target satellite, using the product of the first distance, the first elevation sine, and the first azimuth sine as the second direction position of the target satellite, and using the product of the first distance and the first elevation cosine as the third direction position of the target satellite.
Step 1042D, performing vector operation on the first direction position of the target satellite, the second direction position of the target satellite, and the third direction position of the target satellite to obtain the first target position.
In practice, according to the first distance d SR First elevation angle theta S And a first azimuth angleA first target location is determined and a second target location is determined,
wherein q S Is a first target position of the target satellite.
Step 1042E, obtaining a third distance between the target terminal and the reflecting surface, where the center position of the reflecting surface is at a third elevation angle of the target terminal, and the center position of the reflecting surface is at a third azimuth angle of the target terminal.
Step 1042F, performing sine operation on the third elevation to obtain a third elevation sine, performing cosine operation on the third elevation to obtain a third elevation cosine, performing sine operation on the third azimuth to obtain a third azimuth sine, and performing cosine operation on the third azimuth to obtain a third azimuth cosine.
Step 1042G, taking the product of the third distance, the third elevation sine and the third azimuth cosine as the target terminal first direction position, taking the product of the third distance, the third elevation sine and the third azimuth sine as the target terminal second direction position, and taking the product of the third distance and the third elevation cosine as the target terminal third direction position.
And step 1042H, performing vector operation on the first direction position of the target terminal, the second direction position of the target terminal and the third direction position of the target terminal to obtain the second target position.
In practice, according to the third distance d RT Third elevation angle theta T And a third azimuth angleA second target location is determined and a second target location is determined,
wherein q T And a second target position of the target terminal.
According to the scheme, the first target position of the target satellite and the second target position of the target terminal are determined, and the second system geometric constraint condition and the second reflection geometric constraint condition are determined according to the target satellite position, the target terminal position and related position parameters, so that the constructed signal enhancement model accords with the actual situation, and the determined second position adjustment data are the second phase shift and the second orientation within a reasonable range.
Step 1042I, obtaining a second transmitting power of the target satellite, a second transmitting antenna gain of the target satellite, a second receiving antenna gain of the target terminal, a second signal wavelength of the target satellite, a first power radiation pattern of the target satellite, and a second power radiation pattern of the target position reflecting unit, where the target position reflecting unit is a reflecting unit located at a target row and a target column position in the reflecting surface.
And step 1042J, performing operation processing on the second transmitting power, the second transmitting antenna gain, the second receiving antenna gain, the second signal wavelength, the first power radiation pattern and the second power radiation pattern according to a Fries transmission formula to obtain the target receiving power of the target terminal.
In particular, fries transmission formula (Friis Free Space Formula) is an antenna theory formula for calculating the received power from a transmitting antenna to a receiving antenna. The formula is:wherein P is r For receiving the power of the antenna, P t For transmitting power of transmitting antenna, G t For transmitting antenna gain, G r For the receive antenna gain, λ is the operating wavelength and R is the distance between the transmit and receive antennas.
Second transmitting power P S Second transmitting antenna gain G S Second receiving antenna gain G GT Second signal wavelength lambda S And a first distance d SR Substituting the Fries transmission formula to obtain the target receiving power of the target terminal,
wherein the target satellite is modeled as the far field of the reflecting surface and the target terminal is modeled as the near field of the reflecting surface. P (P) GT For the purpose ofTarget reception power of target terminal, G RIS Gain, d, of the receiving antenna for the reflecting surface x ·d y D is the area of the target position reflecting unit SR For a first distance between the target satellite and the target terminal,for a fifth distance of the target position reflecting unit in the reflecting surface to the target terminal +.>For a first power radiation pattern of said target satellite,>a second power radiation pattern for the target position reflecting unit.
Whether the target satellite or target terminal is located in the near field or far field of the reflective surface is determined from the fraunhofer distance (Fraunhofer distance), which is formulated as:
in antenna theory, the distance between devices is far field when the distance is larger than the fraunhofer distance, and near field when the distance is smaller than the fraunhofer distance. Due to the first distance d SR Greater than the French Hough distance, a third distance d RT Less than the fraunhon distance, the target satellite is thus located in the far field of the reflecting surface and the target terminal is located in the near field of the reflecting surface.
As shown in fig. 1D, fig. 1D is a schematic structural diagram of a reflecting surface according to an embodiment of the disclosure.Is a reflecting unit->Elevation angle to target satellite, +_>Is a reflecting unit->Azimuth to target satellite, +_>Is a reflecting unit->Elevation angle to target terminal +. >Is a reflecting unit->Azimuth to the target terminal.
M is located on the reflecting surface 1 Row m 2 The coordinates of the center point of the reflecting element of the column are:
wherein M is 1 For the total number of lines of the reflecting surface, M 2 Is the total number of columns of the reflecting surface.
Step 1042K, summing the first interference of the target satellite to the interfered terminal and the second interference of the reflection surface to the interfered terminal to obtain the total interference power of the interfered terminal.
In particular, determining a total power of interference of the victim terminal based on a first interference of the target satellite to the victim terminal and a second interference of the reflection to the victim terminal,
wherein,,for the receive antenna gain of the victim terminal, and (2)>Is the distance between the target satellite and the victim terminal.
And step 1042L, performing operation processing on the effective received power, the interference total power and the white noise power according to a signal-to-interference-plus-noise ratio formula to obtain a second signal-to-interference-plus-noise ratio of the interfered terminal.
In particular, the signal-to-interference-and-noise ratio SINR (Signal to Interference plus Noise Ratio) refers to the ratio of the signal to the sum of interference and noise in the system. The formula is:wherein SINR is signal-to-interference-plus-noise ratio, P S For the effective power of the signal, P I To the effective power of the interference signal, P N Is the effective power of the noise.
Effective received power P of terminal to be interfered GTI Total interference power P of interfered terminals Interference And additive white gaussian noise of a victim terminalSubstituting the power of the received signal into a signal-to-interference-and-noise ratio formula to obtain a second signal-to-interference-and-noise ratio of the interfered terminal,
wherein,,and (3) the second signal to interference and noise ratio.
According to the scheme, the second signal-to-interference-and-noise ratio of the interfered terminal is calculated, the interference degree of the interfered terminal can be determined according to the second signal-to-interference-and-noise ratio of the interfered terminal, and the signal-to-interference-and-noise ratio constraint condition of the signal enhancement model is set based on the second signal-to-interference-and-noise ratio, so that the determined second position adjustment data can reduce the interference to the interfered terminal on the basis of ensuring normal communication between the target satellite and the target terminal.
In some embodiments, step 1042 comprises:
step 10421, determining a unit modulus constraint based on the reflection coefficient.
Step 10422, determining said second system geometry constraint and said second reflection geometry constraint based on said first target location and said second target location.
And 10423, determining a signal-to-interference-and-noise ratio constraint condition according to the second signal-to-interference-and-noise ratio and a preset signal-to-interference-and-noise ratio threshold.
Step 10424, constructing the signal enhancement model according to the unit modulus constraint, the second system geometry constraint, the second reflection geometry constraint, the signal-to-interference-and-noise ratio constraint, and the target received power,
wherein P2 is the second position adjustment data, P GT For a target received power of the target terminal,for the reflection coefficient, m, of the target position reflection unit in the reflection surface 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 For the total number of lines of the reflecting surface, M 2 For the total number of columns of the reflecting surface, θ S For said first elevation,/a>For the first azimuth angle, θ T For said third elevation,/->For the third azimuth angle to be mentioned,for the unit modulus constraint condition described above,for said second system geometrical constraint, < +.>For said second reflection geometry constraint, < +.>SINR as the SINR constraint 0 Is a preset signal-to-interference-and-noise ratio threshold.
In specific implementation, the signal enhancement model determines second position adjustment data of the reflecting surface corresponding to the maximum target receiving power under the condition that the second reflecting geometric constraint condition is met. Therefore, the reflecting surface is adjusted according to the second position adjustment data, so that the target receiving power of the target terminal can be maximized, and normal communication of a target communication system between the target satellite and the target terminal is ensured. In addition, by setting the constraint condition of the signal-to-interference-and-noise ratio, the second signal-to-interference-and-noise ratio of the interfered terminal can be ensured to be in a reasonable range, so that the interference to the interfered communication system is reduced on the premise of ensuring the normal communication of the target communication system.
Wherein, psi' in the second system geometry constraint condition is the angle of the included angle among the reflecting surface, the target satellite and the target terminal, and the vertex of the included angle is the target satellite.
By the scheme, when the target communication system cannot perform normal communication, a signal enhancement model is built based on the target received power, the second position adjustment data of the reflecting surface is determined to control the reflecting surface, and interference to a disturbed system is reduced on the basis of ensuring that the target communication system can perform normal communication.
It should be noted that the embodiments of the present disclosure may be further described in the following manner:
as shown in fig. 2, fig. 2 is a flowchart of a method for controlling a reflective surface according to an embodiment of the present disclosure. Comprising the following steps:
and step 1, detecting target receiving power of a target terminal in a target communication system.
And 2.1, the target receiving power is larger than or equal to the preset ideal receiving power, and the reflecting surface assists the target satellite in interference avoidance. And 3.1, acquiring the position information of the target satellite and the disturbed terminal, and transmitting the position information to a controller of the reflecting surface. And 4.1, constructing a first phase shift and a first orientation of the optimal reflecting surface by the controller of the reflecting surface according to the obtained position information, and maximizing a first signal-to-interference-and-noise ratio of the interfered terminal.
And 2.2, the target receiving power is smaller than the preset ideal receiving power, and the reflecting surface assists the target satellite to carry out signal enhancement and interference avoidance. And 3.2, acquiring the position information of the target satellite and the target terminal and the second signal-to-interference-and-noise ratio of the interfered terminal, and transmitting the position information and the second signal-to-interference-and-noise ratio to a controller of the reflecting surface. And 4.2, constructing a second phase shift and a second orientation of the optimal reflecting surface according to the obtained position information and the second signal-to-interference-and-noise ratio by the controller of the reflecting surface, maximizing target receiving power, and ensuring that the second signal-to-interference-and-noise ratio of the interfered terminal is higher than a preset signal-to-interference-and-noise ratio threshold.
And 5, performing phase shift and orientation adjustment according to the command sent by the controller of the reflecting surface.
By the above embodiment, during communication between the target satellite and the target terminal, when the communication link is available, the reflection surface is adjusted according to the first phase shift and the first orientation, so that interference to the disturbed communication system is avoided. When the communication link is unavailable, the reflecting surface can create a virtual line-of-sight link to assist normal communication between the target satellite and the target terminal, the reflecting surface is adjusted according to the second phase shift and the second direction, the interference to the interfered terminal is reduced while the target receiving power of the target terminal is enhanced, and the interference to the interfered terminal is ensured to be always within a controllable range.
It should be noted that the method of the embodiments of the present disclosure may be performed by a single device, such as a computer or a server. The method of the embodiment can also be applied to a distributed scene, and is completed by mutually matching a plurality of devices. In the case of such a distributed scenario, one of the devices may perform only one or more steps of the methods of embodiments of the present disclosure, the devices interacting with each other to accomplish the methods.
It should be noted that the foregoing describes some embodiments of the present disclosure. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims may be performed in a different order than in the embodiments described above and still achieve desirable results. In addition, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.
Based on the same inventive concept, the present disclosure also provides a satellite communication system based on a reflection surface, corresponding to the method of any embodiment.
Referring to fig. 3, the reflection-based satellite communication system includes: a reflective surface 303, a target terminal 301 and a victim terminal 302,
the target terminal 301 is configured to obtain a target received power of itself, compare and judge the target received power with a preset ideal received power, obtain a judgment result, and send the judgment result to the reflecting surface 303;
the disturbed terminal 302 is configured to transmit its effective received power and the interference signal power to the reflecting surface 303;
the reflecting surface 303 is configured to determine a first signal-to-interference-and-noise ratio of the interfered terminal 302 based on the effective received power and the interference signal power in response to the determination result received by the reflecting surface 303 being that the target received power is greater than or equal to the ideal received power, construct an interference avoidance model based on the first signal-to-interference-and-noise ratio, solve the interference avoidance model to obtain first position adjustment data of the reflecting surface 303, and control the reflecting surface 303 according to the first position adjustment data;
the reflecting surface 303 is further configured to construct a signal enhancement model based on the target received power in response to the determination result received by the reflecting surface 303 being that the target received power is smaller than the ideal received power, solve the signal enhancement model to obtain second position adjustment data of the reflecting surface 303, and control the reflecting surface 303 according to the second position adjustment data.
In some embodiments, the system further comprises a target satellite;
the reflecting surface 303 is further configured to:
acquiring a first target position of the target satellite and a second disturbed position of the disturbed terminal 302;
acquiring effective receiving power of the interfered terminal 302, interference signal power obtained by superposition of an interference signal and a reflected signal and white noise power, and performing operation processing on the effective receiving power, the interference signal power and the white noise power according to a signal-to-interference-plus-noise ratio formula to obtain the first signal-to-interference-plus-noise ratio of the interfered terminal 302;
constructing an interference avoidance model based on the first target location, the second disturbed location and the first signal to interference plus noise ratio; the interference avoidance model is used for optimizing the first signal-to-interference-and-noise ratio, and comprises a first system geometric constraint condition and a first reflection geometric constraint condition which are determined based on the first target position and the second disturbed position;
solving 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.
In some embodiments, the reflective surface 303 is further configured to:
Acquiring a first distance between the target satellite and the reflecting surface 303, wherein the central position of the reflecting surface 303 is at a first elevation angle to the target satellite, and the central position of the reflecting surface 303 is at a first azimuth angle to the target satellite;
performing sine operation on the first elevation to obtain first elevation sine, performing cosine operation on the first elevation to obtain first elevation cosine, performing sine operation on the first azimuth to obtain first azimuth sine, and performing cosine operation on the first azimuth to obtain first azimuth cosine;
taking the product of the first distance, the first elevation sine and the first azimuth cosine as a first direction position of a target satellite, taking the product of the first distance, the first elevation sine and the first azimuth sine as a second direction position of the target satellite, and taking the product of the first distance and the first elevation cosine as a third direction position of the target satellite;
vector operation is carried out on the first direction position of the target satellite, the second direction position of the target satellite and the third direction position of the target satellite to obtain the first target position;
acquiring a second distance between the disturbed terminal 302 and the reflection surface 303, wherein the center position of the reflection surface 303 is at a second elevation angle to the disturbed terminal 302, and the center position of the reflection surface 303 is at a second azimuth angle to the disturbed terminal 302;
Performing sine operation on the second elevation angle to obtain a second elevation angle sine, performing cosine operation on the second elevation angle to obtain a second elevation angle cosine, performing sine operation on the second azimuth angle to obtain a second azimuth angle sine, and performing cosine operation on the second azimuth angle to obtain a second azimuth angle cosine;
taking the product of the second distance, the second elevation sine and the second azimuth cosine as a first direction position of the disturbed terminal 302, taking the product of the second distance, the second elevation sine and the second azimuth sine as a second direction position of the disturbed terminal 302, and taking the product of the second distance and the second elevation cosine as a third direction position of the disturbed terminal 302;
vector operations are performed on the first direction position of the interfered terminal 302, the second direction position of the interfered terminal 302, and the third direction position of the interfered terminal 302, so as to obtain the second interfered position.
In some embodiments, the system further comprises a satellite in the disturbed system;
the reflecting surface 303 is further configured to:
acquiring a first transmitting power of a satellite in the disturbed system, a first transmitting antenna gain of the satellite in the disturbed system, a first receiving antenna gain of the disturbed terminal 302, a first signal wavelength of the satellite in the disturbed system and a fourth distance between the satellite in the disturbed system and the disturbed terminal 302;
Performing operation processing on the first transmission power, the first transmission antenna gain, the first receiving antenna gain, the first signal wavelength and the fourth distance according to a fries transmission formula to obtain an effective receiving power of the interfered terminal 302;
acquiring a reflection coefficient of a target position reflection unit in the reflection surface 303; wherein the target position reflecting unit is a reflecting unit located at a target row and a target column position in the reflecting surface 303;
determining interference signal power of the interference signal received by the interfered terminal 302 and the superposition of the reflected signal according to the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle and the second azimuth angle;
and calculating the effective receiving power and the interference signal power according to a signal-to-interference-and-noise ratio formula to obtain a first signal-to-interference-and-noise ratio of the interfered terminal 302.
In some embodiments, the reflective surface 303 is further configured to:
determining a unit modulus constraint based on the reflection coefficient;
determining the first system geometry constraint and the first reflection geometry constraint based on the first target location and the second disturbed location;
Constructing the disturbance avoidance model according to the unit modulus constraint, the first system geometry constraint, the first reflection geometry constraint and the first signal-to-interference-and-noise ratio,
/>
wherein P1 is the first position adjustment data,for a first signal-to-interference-and-noise ratio of the victim terminal 302,for the reflection coefficient, m, of the target position reflection unit in the reflection surface 303 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 M is the total number of rows of the reflecting surface 303 2 For the total number of columns, θ, of the reflecting surfaces 303 S For said first elevation,/a>For the first azimuth angle, θ TI For said second elevation,/->For said second azimuth angle->For the unit modulus constraint condition described above,for the first system geometry constraint,for the first reflective geometry constraint.
In some embodiments, the system further comprises a target satellite;
the reflecting surface 303 is further configured to:
acquiring a first target position of the target satellite and a second target position of the target terminal 301;
constructing a signal enhancement model based on the first target location, the second target location, and the target received power; the signal enhancement model is used for optimizing the target receiving power, and comprises a second system geometric constraint condition and a second reflection geometric constraint condition which are determined based on the first target position and the second target position;
Solving 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.
In some embodiments, the reflective surface 303 is further configured to:
acquiring a first distance between the target satellite and the reflecting surface 303, wherein the central position of the reflecting surface 303 is at a first elevation angle to the target satellite, and the central position of the reflecting surface 303 is at a first azimuth angle to the target satellite;
performing sine operation on the first elevation to obtain first elevation sine, performing cosine operation on the first elevation to obtain first elevation cosine, performing sine operation on the first azimuth to obtain first azimuth sine, and performing cosine operation on the first azimuth to obtain first azimuth cosine;
taking the product of the first distance, the first elevation sine and the first azimuth cosine as a first direction position of a target satellite, taking the product of the first distance, the first elevation sine and the first azimuth sine as a second direction position of the target satellite, and taking the product of the first distance and the first elevation cosine as a third direction position of the target satellite;
Vector operation is carried out on the first direction position of the target satellite, the second direction position of the target satellite and the third direction position of the target satellite to obtain the first target position;
acquiring a third distance between the target terminal 301 and the reflecting surface 303, wherein the central position of the reflecting surface 303 is at a third elevation angle to the target terminal 301, and the central position of the reflecting surface 303 is at a third azimuth angle to the target terminal 301;
performing sine operation on the third elevation angle to obtain third elevation angle sine, performing cosine operation on the third elevation angle to obtain third elevation angle cosine, performing sine operation on the third azimuth angle to obtain third azimuth angle sine, and performing cosine operation on the third azimuth angle to obtain third azimuth angle cosine;
taking the product of the third distance, the third elevation angle sine and the third azimuth angle cosine as a first direction position of the target terminal 301, taking the product of the third distance, the third elevation angle sine and the third azimuth angle sine as a second direction position of the target terminal 301, and taking the product of the third distance and the third elevation angle cosine as a third direction position of the target terminal 301;
vector operation is performed on the first direction position of the target terminal 301, the second direction position of the target terminal 301, and the third direction position of the target terminal 301, so as to obtain the second target position;
Acquiring a second transmitting power of the target satellite, a second transmitting antenna gain of the target satellite, a second receiving antenna gain of the target terminal 301, a second signal wavelength of the target satellite, a first power radiation pattern of the target satellite, and a second power radiation pattern of the target position reflecting unit, wherein the target position reflecting unit is a reflecting unit located at a target row and target column position in the reflecting surface 303;
performing operation processing on the second transmitting power, the second transmitting antenna gain, the second receiving antenna gain, the second signal wavelength, the first power radiation pattern and the second power radiation pattern according to a fries transmission formula to obtain a target receiving power of the target terminal 301;
the first interference of the target satellite to the interfered terminal 302 and the second interference of the reflecting surface 303 to the interfered terminal 302 are summed to obtain the total interference power of the interfered terminal 302;
and calculating the effective receiving power, the total interference power and the white noise power according to a signal-to-interference-plus-noise ratio formula to obtain a second signal-to-interference-plus-noise ratio of the interfered terminal 302.
In some embodiments, the reflective surface 303 is further configured to:
determining a unit modulus constraint based on the reflection coefficient;
determining the second system geometric constraint and the second reflection geometric constraint based on the first target location and the second target location;
determining a signal-to-interference-and-noise ratio constraint condition according to the second signal-to-interference-and-noise ratio and a preset signal-to-interference-and-noise ratio threshold;
constructing the signal enhancement model according to the unit modulus constraint, the second system geometry constraint, the second reflection geometry constraint, the signal-to-interference-and-noise ratio constraint and the target received power,
/>
wherein P2 is the second position adjustment data, P GT For a target received power of the target terminal 301,for the reflection coefficient, m, of the target position reflection unit in the reflection surface 303 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 M is the total number of rows of the reflecting surface 303 2 For the total number of columns, θ, of the reflecting surfaces 303 S For said first elevation,/a>For the first azimuth angle, θ T For said third elevation,/->For the third azimuth angle, +. >For the unit modulus constraint condition described above,for the second system geometry constraints,for said second reflection geometry constraint, < +.>SINR as the SINR constraint 0 Is a preset signal-to-interference-and-noise ratio threshold.
For convenience of description, the above devices are described as being functionally divided into various modules, respectively. Of course, the functions of the various modules may be implemented in the same one or more pieces of software and/or hardware when implementing the present disclosure.
The device of the foregoing embodiment is configured to implement the corresponding reflection-surface-based satellite communication method in any of the foregoing embodiments, and has the beneficial effects of the corresponding method embodiment, which is not described herein.
Based on the same inventive concept, the present disclosure also provides an electronic device corresponding to the method of any embodiment, including a memory, a processor, and a computer program stored on the memory and capable of running on the processor, where the processor implements the satellite communication method based on the reflection surface according to any embodiment when executing the program.
Fig. 4 shows a more specific hardware architecture of an electronic device according to this embodiment, where the device may include: a processor 1010, a memory 1020, an input/output interface 1030, a communication interface 1040, and a bus 1050. Wherein processor 1010, memory 1020, input/output interface 1030, and communication interface 1040 implement communication connections therebetween within the device via a bus 1050.
The processor 1010 may be implemented by a general-purpose CPU (Central Processing Unit ), microprocessor, application specific integrated circuit (Application Specific Integrated Circuit, ASIC), or one or more integrated circuits, etc. for executing relevant programs to implement the technical solutions provided in the embodiments of the present disclosure.
The Memory 1020 may be implemented in the form of ROM (Read Only Memory), RAM (Random Access Memory ), static storage device, dynamic storage device, or the like. Memory 1020 may store an operating system and other application programs, and when the embodiments of the present specification are implemented in software or firmware, the associated program code is stored in memory 1020 and executed by processor 1010.
The input/output interface 1030 is used to connect with an input/output module for inputting and outputting information. The input/output module may be configured as a component in a device (not shown) or may be external to the device to provide corresponding functionality. Wherein the input devices may include a keyboard, mouse, touch screen, microphone, various types of sensors, etc., and the output devices may include a display, speaker, vibrator, indicator lights, etc.
Communication interface 1040 is used to connect communication modules (not shown) to enable communication interactions of the present device with other devices. The communication module may implement communication through wired mode (such as USB (Universal Serial Bus, universal serial bus), network cable, etc.), or may implement communication through wireless mode (such as mobile network, WIFI (Wireless Fidelity, wireless network communication technology), bluetooth, etc.).
Bus 1050 includes a path for transferring information between components of the device (e.g., processor 1010, memory 1020, input/output interface 1030, and communication interface 1040).
It should be noted that although the above-described device only shows processor 1010, memory 1020, input/output interface 1030, communication interface 1040, and bus 1050, in an implementation, the device may include other components necessary to achieve proper operation. Furthermore, it will be understood by those skilled in the art that the above-described apparatus may include only the components necessary to implement the embodiments of the present description, and not all the components shown in the drawings.
The electronic device of the foregoing embodiment is configured to implement the corresponding reflection-surface-based satellite communication method in any of the foregoing embodiments, and has the beneficial effects of the corresponding method embodiment, which is not described herein.
Based on the same inventive concept, the present disclosure also provides a non-transitory computer readable storage medium storing computer instructions for causing the computer to perform the reflection-surface-based satellite communication method according to any of the above embodiments, corresponding to any of the above embodiments.
The computer readable media of the present embodiments, including both permanent and non-permanent, removable and non-removable media, may be used to implement information storage by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of storage media for a computer 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 technology, compact disc read only memory (CD-ROM), digital Versatile Discs (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices, or any other non-transmission medium, which can be used to store information that can be accessed by a computing device.
The storage medium of the foregoing embodiments stores computer instructions for causing the computer to perform the satellite communication method based on the reflection surface according to any one of the foregoing embodiments, and has the advantages of the corresponding method embodiments, which are not described herein.
Those of ordinary skill in the art will appreciate that: the discussion of any of the embodiments above is merely exemplary and is not intended to suggest that the scope of the disclosure, including the claims, is limited to these examples; the technical features of the above embodiments or in the different embodiments may also be combined under the idea of the present disclosure, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present disclosure as described above, which are not provided in details for the sake of brevity.
Additionally, well-known power/ground connections to Integrated Circuit (IC) chips and other components may or may not be shown within the provided figures, in order to simplify the illustration and discussion, and so as not to obscure the embodiments of the present disclosure. Furthermore, the devices may be shown in block diagram form in order to avoid obscuring the embodiments of the present disclosure, and this also accounts for the fact that specifics with respect to implementation of such block diagram devices are highly dependent upon the platform on which the embodiments of the present disclosure are to be implemented (i.e., such specifics should be well within purview of one skilled in the art). Where specific details (e.g., circuits) are set forth in order to describe example embodiments of the disclosure, it should be apparent to one skilled in the art that embodiments of the disclosure can be practiced without, or with variation of, these specific details. Accordingly, the description is to be regarded as illustrative in nature and not as restrictive.
While the present disclosure has been described in conjunction with specific embodiments thereof, many alternatives, modifications, and variations of those embodiments will be apparent to those skilled in the art in light of the foregoing description. For example, other memory architectures (e.g., dynamic RAM (DRAM)) may use the embodiments discussed.
The disclosed embodiments are intended to embrace all such alternatives, modifications and variances which fall within the broad scope of the appended claims. Accordingly, any omissions, modifications, equivalents, improvements, and the like, which are within the spirit and principles of the embodiments of the disclosure, are intended to be included within the scope of the disclosure.

Claims (10)

1. A satellite communication method based on a reflection surface, applied to a satellite communication system, the satellite communication system comprising: the method comprises the following steps of:
the target terminal obtains the target receiving power of the target terminal, compares and judges the target receiving power with the preset ideal receiving power, obtains a judging result and sends the judging result to the reflecting surface;
the disturbed terminal transmits the effective receiving power and the interference signal power to the reflecting surface;
Responding to the judgment result received by the reflecting surface to be that the target received power is greater than or equal to the ideal received power, determining a first signal-to-interference-plus-noise ratio of the interfered terminal based on the effective received power and the interference signal power, constructing an interference avoidance model based on the first signal-to-interference-plus-noise ratio, solving the interference avoidance model to obtain first position adjustment data of the reflecting surface, and controlling the reflecting surface according to the first position adjustment data;
and responding to the judgment result received by the reflecting surface to be that the target receiving power is smaller than the ideal receiving power, constructing a signal enhancement model based on the target receiving power, solving the signal enhancement model to obtain second position adjustment data of the reflecting surface, and controlling the reflecting surface according to the second position adjustment data.
2. The method of claim 1, wherein the system further comprises a target satellite;
the determining a first signal-to-interference-and-noise ratio of the interfered terminal, constructing an interference avoidance model based on the first signal-to-interference-and-noise ratio, and solving the interference avoidance model to obtain first position adjustment data of the reflecting surface includes:
Acquiring a first target position of the target satellite and a second disturbed position of the disturbed terminal;
acquiring effective receiving power of the interfered terminal, interference signal power obtained by superposition of an interference signal and a reflected signal and white noise power, and carrying out operation processing on the effective receiving power, the interference signal power and the white noise power according to a signal-to-interference-plus-noise ratio formula to obtain the first signal-to-interference-plus-noise ratio of the interfered terminal;
constructing an interference avoidance model based on the first target location, the second disturbed location and the first signal to interference plus noise ratio; the interference avoidance model is used for optimizing the first signal-to-interference-and-noise ratio, and comprises a first system geometric constraint condition and a first reflection geometric constraint condition which are determined based on the first target position and the second disturbed position;
solving 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.
3. The method of claim 2, wherein the acquiring the first target location of the target satellite and the second victim location of the victim terminal comprises:
Acquiring a first distance between the target satellite and the reflecting surface, wherein the central position of the reflecting surface reaches a first elevation angle of the target satellite, and the central position of the reflecting surface reaches a first azimuth angle of the target satellite;
performing sine operation on the first elevation to obtain first elevation sine, performing cosine operation on the first elevation to obtain first elevation cosine, performing sine operation on the first azimuth to obtain first azimuth sine, and performing cosine operation on the first azimuth to obtain first azimuth cosine;
taking the product of the first distance, the first elevation sine and the first azimuth cosine as a first direction position of a target satellite, taking the product of the first distance, the first elevation sine and the first azimuth sine as a second direction position of the target satellite, and taking the product of the first distance and the first elevation cosine as a third direction position of the target satellite;
vector operation is carried out on the first direction position of the target satellite, the second direction position of the target satellite and the third direction position of the target satellite to obtain the first target position;
acquiring a second distance between the disturbed terminal and the reflecting surface, wherein the central position of the reflecting surface reaches a second elevation angle of the disturbed terminal, and the central position of the reflecting surface reaches a second azimuth angle of the disturbed terminal;
Performing sine operation on the second elevation angle to obtain a second elevation angle sine, performing cosine operation on the second elevation angle to obtain a second elevation angle cosine, performing sine operation on the second azimuth angle to obtain a second azimuth angle sine, and performing cosine operation on the second azimuth angle to obtain a second azimuth angle cosine;
taking the product of the second distance, the second elevation sine and the second azimuth cosine as a first direction position of the disturbed terminal, taking the product of the second distance, the second elevation sine and the second azimuth sine as a second direction position of the disturbed terminal, and taking the product of the second distance and the second elevation cosine as a third direction position of the disturbed terminal;
and vector operation is carried out on the first direction position of the interfered terminal, the second direction position of the interfered terminal and the third direction position of the interfered terminal, so as to obtain the second interfered position.
4. A method according to claim 3, wherein the system further comprises satellites in a disturbed system;
the obtaining the effective receiving power of the interfered terminal, the interference signal power obtained by overlapping the interference signal and the reflected signal, and the white noise power, and performing operation processing on the effective receiving power, the interference signal power, and the white noise power according to a signal-to-interference-and-noise ratio formula to obtain the first signal-to-interference-and-noise ratio of the interfered terminal, including:
Acquiring first transmitting power of satellites in the disturbed system, first transmitting antenna gain of the satellites in the disturbed system, first receiving antenna gain of the disturbed terminal, first signal wavelength of the satellites in the disturbed system and fourth distance between the satellites in the disturbed system and the disturbed terminal;
calculating the first transmitting power, the first transmitting antenna gain, the first receiving antenna gain, the first signal wavelength and the fourth distance according to a Fries transmission formula to obtain the effective receiving power of the disturbed terminal;
obtaining the reflection coefficient of a target position reflection unit in the reflection surface; the target position reflecting unit is a reflecting unit positioned at the position of a target row and a target column in the reflecting surface;
according to the reflection coefficient, the first elevation angle, the first azimuth angle, the second elevation angle and the second azimuth angle, determining interference signal power of the interfered terminal subjected to superposition of interference signals and reflection signals;
and carrying out operation processing on the effective receiving power and the interference signal power according to a signal-to-interference-and-noise ratio formula to obtain a first signal-to-interference-and-noise ratio of the interfered terminal.
5. The method of claim 4, wherein the constructing an interference avoidance model based on the first target location, the second disturbed location, and the first signal-to-interference-and-noise ratio comprises:
determining a unit modulus constraint based on the reflection coefficient;
determining the first system geometry constraint and the first reflection geometry constraint based on the first target location and the second disturbed location;
constructing the disturbance avoidance model according to the unit modulus constraint, the first system geometry constraint, the first reflection geometry constraint and the first signal-to-interference-and-noise ratio,
wherein P1 is the first position adjustment data,for a first signal-to-interference-and-noise ratio of said victim terminal,>for the reflection coefficient, m, of the target position reflection unit in the reflection surface 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 For the total number of lines of the reflecting surface, M 2 For the total number of columns of the reflecting surface, θ S For said first elevation,/a>For the first azimuth angle, θ TI For said second elevation,/->For the second partyThe angle of orientation of the lens,for the unit modulus constraint condition described above, For the first system geometry constraint,for the first reflective geometry constraint.
6. The method of claim 1, wherein the system further comprises 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 second position adjustment data of the reflecting surface includes:
acquiring a first target position of the target satellite and a second target position of the target terminal;
constructing a signal enhancement model based on the first target location, the second target location, and the target received power; the signal enhancement model is used for optimizing the target receiving power, and comprises a second system geometric constraint condition and a second reflection geometric constraint condition which are determined based on the first target position and the second target position;
solving 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.
7. The method of claim 6, further comprising, prior to said building a signal enhancement model based on said first target location, said second target location, and said target received power:
Acquiring a first distance between the target satellite and the reflecting surface, wherein the central position of the reflecting surface reaches a first elevation angle of the target satellite, and the central position of the reflecting surface reaches a first azimuth angle of the target satellite;
performing sine operation on the first elevation to obtain first elevation sine, performing cosine operation on the first elevation to obtain first elevation cosine, performing sine operation on the first azimuth to obtain first azimuth sine, and performing cosine operation on the first azimuth to obtain first azimuth cosine;
taking the product of the first distance, the first elevation sine and the first azimuth cosine as a first direction position of a target satellite, taking the product of the first distance, the first elevation sine and the first azimuth sine as a second direction position of the target satellite, and taking the product of the first distance and the first elevation cosine as a third direction position of the target satellite;
vector operation is carried out on the first direction position of the target satellite, the second direction position of the target satellite and the third direction position of the target satellite to obtain the first target position;
acquiring a third distance between the target terminal and the reflecting surface, wherein the central position of the reflecting surface reaches a third elevation angle of the target terminal, and the central position of the reflecting surface reaches a third azimuth angle of the target terminal;
Performing sine operation on the third elevation angle to obtain third elevation angle sine, performing cosine operation on the third elevation angle to obtain third elevation angle cosine, performing sine operation on the third azimuth angle to obtain third azimuth angle sine, and performing cosine operation on the third azimuth angle to obtain third azimuth angle cosine;
taking the product of the third distance, the third elevation sine and the third azimuth cosine as a first direction position of a target terminal, taking the product of the third distance, the third elevation sine and the third azimuth sine as a second direction position of the target terminal, and taking the product of the third distance and the third elevation cosine as a third direction position of the target terminal;
vector operation is carried out on the first direction position of the target terminal, the second direction position of the target terminal and the third direction position of the target terminal to obtain the second target position;
acquiring a second transmitting power of the target satellite, a second transmitting antenna gain of the target satellite, a second receiving antenna gain of the target terminal, a second signal wavelength of the target satellite, a first power radiation pattern of the target satellite and a second power radiation pattern of the target position reflecting unit, wherein the target position reflecting unit is a reflecting unit positioned at a target row and a target column position in the reflecting surface;
Performing operation processing on the second transmitting power, the second transmitting antenna gain, the second receiving antenna gain, the second signal wavelength, the first power radiation pattern and the second power radiation pattern according to a fries transmission formula to obtain target receiving power of the target terminal;
summing the first interference of the target satellite to the interfered terminal and the second interference of the reflecting surface to the interfered terminal to obtain the total interference power of the interfered terminal;
and calculating the effective receiving power, the interference total power and the white noise power according to a signal-to-interference-plus-noise ratio formula to obtain a second signal-to-interference-plus-noise ratio of the interfered terminal.
8. The method of claim 7, wherein the constructing a signal enhancement model based on the first target location, the second target location, and the target received power comprises:
determining a unit modulus constraint based on the reflection coefficient;
determining the second system geometric constraint and the second reflection geometric constraint based on the first target location and the second target location;
determining a signal-to-interference-and-noise ratio constraint condition according to the second signal-to-interference-and-noise ratio and a preset signal-to-interference-and-noise ratio threshold;
Constructing the signal enhancement model according to the unit modulus constraint, the second system geometry constraint, the second reflection geometry constraint, the signal-to-interference-and-noise ratio constraint and the target received power,
wherein P2 is the second position adjustment data, P GT For a target received power of the target terminal,for the reflection coefficient, m, of the target position reflection unit in the reflection surface 1 For the target row of the target position reflecting unit, m 2 For the target column of the target position reflecting unit, M 1 For the total number of lines of the reflecting surface, M 2 For the total number of columns of the reflecting surface, θ S For said first elevation,/a>For the first azimuth angle, θ T For said third elevation,/->For the third azimuth angle to be mentioned,for the unit modulus constraint condition described above,for the second system geometry constraints,for said second reflection geometry constraint, < +.>SINR as the SINR constraint 0 Is a preset signal-to-interference-and-noise ratio threshold.
9. A reflective surface based satellite communication system, the satellite communication system comprising: the reflecting surface, the target terminal and the disturbed terminal,
the target terminal is configured to acquire own target receiving power, compare and judge the target receiving power with preset ideal receiving power, acquire a judging result and send the judging result to the reflecting surface;
The disturbed terminal is configured to transmit the effective received power and the interference signal power of the disturbed terminal to the reflecting surface;
the reflecting surface is configured to determine a first signal-to-interference-and-noise ratio of the interfered terminal based on the effective receiving power and the interference signal power in response to the determination result received by the reflecting surface being that the target receiving power is greater than or equal to the ideal receiving power, construct an interference avoidance model based on the first signal-to-interference-and-noise ratio, solve the interference avoidance model to obtain first position adjustment data of the reflecting surface, and control the reflecting surface according to the first position adjustment data;
the reflecting surface is further configured to respond to the judgment result received by the reflecting surface that the target received power is smaller than the ideal received power, construct a signal enhancement model based on the target received power, solve the signal enhancement model to obtain second position adjustment data of the reflecting surface, and control the reflecting surface according to the second position adjustment data.
10. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the method of any one of claims 1 to 8 when the program is executed.
CN202310565175.6A 2023-05-18 2023-05-18 Satellite communication method and system based on reflecting surface and electronic equipment Pending CN116545504A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117250646A (en) * 2023-11-17 2023-12-19 毫厘智能科技(江苏)有限公司 Direction finding method and device based on chip, chip module and storage medium

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117250646A (en) * 2023-11-17 2023-12-19 毫厘智能科技(江苏)有限公司 Direction finding method and device based on chip, chip module and storage medium
CN117250646B (en) * 2023-11-17 2024-02-02 毫厘智能科技(江苏)有限公司 Direction finding method and device based on chip, chip module and storage medium

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