CN115801047A - Method for suppressing self-interference of full-duplex satellite communication - Google Patents
Method for suppressing self-interference of full-duplex satellite communication Download PDFInfo
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- CN115801047A CN115801047A CN202211342869.5A CN202211342869A CN115801047A CN 115801047 A CN115801047 A CN 115801047A CN 202211342869 A CN202211342869 A CN 202211342869A CN 115801047 A CN115801047 A CN 115801047A
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- 238000004891 communication Methods 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000001629 suppression Effects 0.000 claims abstract description 6
- 238000002955 isolation Methods 0.000 abstract description 7
- 238000001228 spectrum Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 description 6
- 230000008030 elimination Effects 0.000 description 4
- 238000003379 elimination reaction Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
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- 238000010295 mobile communication Methods 0.000 description 1
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
- H04B1/38—Transceivers, i.e. devices in which transmitter and receiver form a structural unit and in which at least one part is used for functions of transmitting and receiving
- H04B1/40—Circuits
- H04B1/50—Circuits using different frequencies for the two directions of communication
- H04B1/52—Hybrid arrangements, i.e. arrangements for transition from single-path two-direction transmission to single-direction transmission on each of two paths or vice versa
- H04B1/525—Hybrid arrangements, i.e. arrangements for transition from single-path two-direction transmission to single-direction transmission on each of two paths or vice versa with means for reducing leakage of transmitter signal into the receiver
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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
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a method for improving self-interference of full-duplex satellite communication, and belongs to the technical field of satellite communication. According to the invention, under the condition of not using extra software and hardware resources, the microstrip antenna is optimally deployed by using the structural characteristics of the satellite, the isolation between the transmitting antenna and the receiving antenna is increased while the directivity and the portability of the antenna are ensured, the self-interference suppression in a common-frequency simultaneous full-duplex mode is realized in an airspace, and the frequency spectrum efficiency is improved.
Description
Technical Field
The invention relates to the technical field of satellite communication, in particular to a method for improving self-interference of full-duplex communication by combining satellite communication and a same-frequency simultaneous full-duplex technology to improve the utilization rate of frequency band resources and combining the structural characteristics of a satellite, so that the transmission quality is effectively improved.
Background
The convergence of satellite access and traditional terrestrial network is an important direction for the development of future mobile communication technology, and with the increase of traffic, the increasing shortage of frequency band resources will be followed. Meanwhile, the co-frequency full duplex technology is a very effective solution, the spectrum efficiency can be increased by two times theoretically, and the combination of the satellite communication and the full duplex technology becomes an effective means for relieving the spectrum resource problem.
The sharing of the transceiving frequency band necessarily causes a self-interference problem, and a proper cancellation scheme needs to be designed. In a terrestrial cellular network, self-interference cancellation techniques can be divided into spatial, analog and digital domains, depending on where signal cancellation occurs. The purpose of the spatial isolation technique is to block the propagation of electromagnetic waves between the transmit and receive chains, the analog domain refers to suppression of self-interference in the analog receive chain circuitry before the received signal passes through the ADC, and the digital domain is to eliminate the self-interference after passing through the ADC by applying complex DSP techniques to the received signal. However, there is still insufficient research on how to design a self-interference cancellation scheme specifically according to the characteristics of satellite communication.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a method for inhibiting the self-interference of full-duplex satellite communication.
The technical scheme adopted by the invention is as follows:
a method for suppressing self-interference of full-duplex satellite communication is characterized in that receiving and transmitting antennas are respectively arranged at the tail ends of two sides of a solar sailboard of a satellite platform and are respectively connected with the solar sailboard through a rotating shaft, the rotating angles of the receiving and transmitting antennas are calculated according to the satellite attitude, the rotating angles of the solar sailboard are compensated, and self-interference suppression in a same-frequency simultaneous full-duplex mode is realized in an airspace.
The receiving and transmitting antennas are of microstrip antenna structures, and if the solar array panel rotates by an angle delta theta, the microstrip antenna at the tail end of the solar array panel deflects by the same angle. To ensure that the rotation of the solar array does not change the relative angle of the antenna with respect to the nacelle, the antenna should actively rotate by an angle of- Δ θ. On the basis, the directional adjustment of the micro-strip antenna aiming at the satellite attitude can be carried out according to the traditional mode.
The microstrip antenna and the solar sailboard are folded together, the solar sailboard is usually of a long strip-shaped flat plate structure, the microstrip antenna is divided into small sections in length during folding and folded sequentially, the microstrip antenna is also of a flat plate structure, is similar to the solar sailboard and is folded together with the sailboard, and satellite carrying is facilitated.
In the same-frequency simultaneous full-duplex mode, the receiving and transmitting signals share the same time-frequency resource, thereby reducing the cost of frequency or time slot resources in the half-duplex mode and achieving the purpose of improving the frequency spectrum efficiency. The key to the technical realization lies in the elimination of the same-frequency self-interference (SI) generated by the same-node transmitter by the receiver, and if the SI between the receiving and the transmitting can be ideally eliminated, the frequency spectrum efficiency can be theoretically doubled.
For a full-duplex satellite communication node, the size of the full-duplex satellite communication node is usually far larger than that of ground communication equipment, particularly solar sailboards positioned on two sides of a satellite platform, in order to obtain enough energy supply, the surface area of the full-duplex satellite communication node is usually dozens of square meters, and the length of the full-duplex satellite communication node can usually reach several meters to ten meters. In order to obtain a large gain for the satellite antenna, the antenna needs to be pointed in the same direction as the communication target. Therefore, the antenna is connected with the solar panel through the rotating shaft, and the direction adjustability of the solar panel is met. The invention can effectively reduce the residual power of the self-interference signal reaching the receiving antenna.
Compared with the prior art, the method provided by the invention has the advantages that:
1) The space domain self-interference signal elimination is realized by utilizing the structural characteristics of the satellite, the complexity is low, the realization is easy, and the additional resource consumption is almost avoided.
2) The direction of the antenna can be flexibly adjusted, and the consistency with the direction of a communication target is ensured.
3) The microstrip antenna can be folded in the same way as the solar array, and satellite carrying is easy to realize.
Drawings
FIG. 1 is a diagram illustrating a theoretical value of spatial loss of electromagnetic waves in an embodiment of the present invention;
FIG. 2 is a schematic diagram of antenna placement and connection according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a microstrip antenna folding mode.
Detailed Description
The invention will be further described by way of examples, without in any way limiting the scope of the invention, with reference to the accompanying drawings.
In satellite communications, the satellite structure is generally composed of a primary structure (a platform cabin structure, a payload cabin structure), a secondary structure (an unfolded antenna side plate mounting frame, a solar cell array mounting frame). In a conventional half-duplex communication mode, since receiving and transmitting signals respectively occupy orthogonal communication resources and do not interfere with each other, the transceiving antennas are usually deployed on a main structure, and the orientation of the transceiving antennas can be adjusted in real time according to the attitude of a satellite, so that the communication obtains a large gain.
For full duplex communication, the transmitted signal of the satellite node will constitute strong self-interference to the target received signal. The self-interference elimination technology in analog and digital domains inevitably needs the support of a hardware system, and brings extra burden to the whole satellite system. The spatial domain isolation technology does not need transceiving hardware to accurately process signals with a large dynamic range. Considering that the resources of earth orbit satellites, particularly small low-orbit earth satellites widely adopted at present are limited, the self-interference signal suppression method is based on the airspace self-interference elimination theory and achieves self-interference signal suppression through reasonable deployment of the antennas.
Based on the free space loss model, the path loss of the self-interference signal generated by the satellite transmitting to the receiving antenna due to antenna isolation is as follows:
Los＝32.44+20lg d+20lg f
in the above equation, d represents the distance between the two antennas in km, f represents the frequency of the transmission signal in MHz, los represents the path loss in dB. The above equation shows that the magnitude of the path loss is mainly related to the distance between the antennas and the frequency of the signal, as shown in fig. 1. When the signal frequency is constant, the distance between the transmitting and receiving antennas is increased, the generated path loss is increased accordingly, and the attenuation of the self-interference signal is increased.
For the traditional ground communication equipment, due to the limited size, the receiving and transmitting antenna cannot be extended far, so that the isolation degree obtained by the mode is very limited.
The receiving and transmitting antenna adopts a micro-strip antenna structure, the micro-strip antennas are respectively arranged at two ends of a solar array of the satellite platform, the strip structure of the solar array provides natural advantages for the remote extension of the receiving and transmitting antenna, and the receiving and transmitting antenna is connected with the solar array through a rotatable shaft, so that the real-time adjustment of the pointing direction of the antenna is realized, as shown in fig. 2. When the direction of the antenna is adjusted, in addition to considering the track and the attitude of the satellite in the traditional mode, the rotation angle of the sailboard is compensated, the angle is calculated by the solar sail rotation control system according to the vector position of the satellite relative to the sun, the rotation angle is a known quantity for the antenna rotation control system, and the compensation of the angle does not consume extra calculation resources.
The transceiving antenna adopts a microstrip antenna, has a flat-plate-shaped appearance structure similar to that of the solar sailboard, and can be folded together with the solar sailboard in the same way, as shown in figure 3. The volume of the folded satellite is greatly reduced, and the satellite can be conveniently carried. Taking the Starlink system as an example, the unfolding size of the 1.0 version satellite single-wing solar array is 4 multiplied by 15 meters, and a Ku (12 to 18 GHz) frequency band and a Ka (27 to 40 GHz) frequency band are adopted. The width of a central cabin body of the satellite is ignored, only the space isolation caused by the lengths of the two solar sailboards is considered, and for a 40GHz signal, the isolation degree caused by path loss can be achieved
Los＝32.44+20lg 0.03+20lg(4×10 4 )≈94dB
The attenuation of self-interference signals will continue to increase as higher frequency bands are developed and utilized in the future.
It is noted that the disclosed embodiments are intended to aid in further understanding of the invention, but those skilled in the art will appreciate that: various substitutions and modifications are possible without departing from the spirit and scope of the invention and appended claims. Therefore, the invention should not be limited by the disclosure of the embodiments, but should be defined by the scope of the appended claims. Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (3)
1. A method for suppressing self-interference of full-duplex satellite communication is characterized in that receiving and transmitting antennas are respectively placed at the tail ends of two sides of a solar array of a satellite platform and are respectively connected with the solar array through rotating shafts, the rotating angles of the receiving and transmitting antennas are calculated according to the satellite attitude, the rotating angles of the solar array are compensated, and self-interference suppression in a same-frequency simultaneous full-duplex mode is realized in an airspace.
2. The method for suppressing self-interference in full-duplex satellite communication according to claim 1, wherein the transmitting and receiving antennas are microstrip antenna structures.
3. The method for suppressing self-interference in full-duplex satellite communication according to claim 2, wherein the microstrip antenna has a flat structure similar to that of the solar panel, and is folded together with the solar panel to facilitate satellite carrying.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211342869.5A CN115801047A (en) | 2022-10-31 | 2022-10-31 | Method for suppressing self-interference of full-duplex satellite communication |
| PCT/CN2023/093396 WO2024093180A1 (en) | 2022-10-31 | 2023-05-11 | Method for suppressing self-interference during full-duplex satellite communication |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211342869.5A CN115801047A (en) | 2022-10-31 | 2022-10-31 | Method for suppressing self-interference of full-duplex satellite communication |
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| CN115801047A true CN115801047A (en) | 2023-03-14 |
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| WO (1) | WO2024093180A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024093180A1 (en) * | 2022-10-31 | 2024-05-10 | 北京大学 | Method for suppressing self-interference during full-duplex satellite communication |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2969580B1 (en) * | 2010-12-23 | 2013-08-16 | Thales Sa | DEPLOYABLE STRUCTURE FORMING AN ANTENNA EQUIPPED WITH A SOLAR GENERATOR FOR A SATELLITE |
| CN106848558B (en) * | 2017-02-08 | 2020-01-10 | 耿歌 | Solar sailboard conformal antenna of spacecraft |
| AU2020276300A1 (en) * | 2019-05-15 | 2021-12-02 | Ast & Science, Llc | Solar, electronic, RF radiator for a self-contained structure for space application array |
| CN114735238B (en) * | 2022-03-25 | 2023-03-21 | 哈尔滨工业大学 | Satellite assembly composed of solar sailboard and antenna and satellite |
| CN115801047A (en) * | 2022-10-31 | 2023-03-14 | 北京大学 | Method for suppressing self-interference of full-duplex satellite communication |
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2022
- 2022-10-31 CN CN202211342869.5A patent/CN115801047A/en active Pending
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- 2023-05-11 WO PCT/CN2023/093396 patent/WO2024093180A1/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024093180A1 (en) * | 2022-10-31 | 2024-05-10 | 北京大学 | Method for suppressing self-interference during full-duplex satellite communication |
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