CN113873536A - Low-orbit satellite beam design method and system based on interference avoidance - Google Patents
Low-orbit satellite beam design method and system based on interference avoidance Download PDFInfo
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- CN113873536A CN113873536A CN202111143845.2A CN202111143845A CN113873536A CN 113873536 A CN113873536 A CN 113873536A CN 202111143845 A CN202111143845 A CN 202111143845A CN 113873536 A CN113873536 A CN 113873536A
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- 238000013461 design Methods 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000011664 signaling Effects 0.000 claims description 36
- 238000004891 communication Methods 0.000 claims description 7
- 238000010408 sweeping Methods 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000002955 isolation Methods 0.000 description 16
- 238000005516 engineering process Methods 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 3
- 230000004907 flux Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W16/00—Network planning, e.g. coverage or traffic planning tools; Network deployment, e.g. resource partitioning or cells structures
- H04W16/24—Cell structures
- H04W16/28—Cell structures using beam steering
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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
- H04B7/18578—Satellite systems for providing broadband data service to individual earth stations
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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
- H04B7/18578—Satellite systems for providing broadband data service to individual earth stations
- H04B7/18597—Arrangements for system physical machines management, i.e. for construction, operations control, administration, maintenance
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W16/00—Network planning, e.g. coverage or traffic planning tools; Network deployment, e.g. resource partitioning or cells structures
- H04W16/18—Network planning tools
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- 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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Abstract
The invention belongs to the technical field of satellite interference avoidance, and particularly discloses a low-orbit satellite beam design method and system based on interference avoidance. By adopting the technical scheme, the requirement of frequency interference index is met through the design of the wave beam, and meanwhile, the complexity of the ground terminal access design is reduced, thereby being beneficial to saving on-satellite resources.
Description
Technical Field
The invention belongs to the technical field of satellite interference avoidance, and relates to a low-orbit satellite beam design method and system based on interference avoidance.
Background
With the development of space science, the requirement of broadband services of Low Earth Orbit (LEO) satellites is continuously increased, the used frequency band of the LEO satellites is expanded to a high frequency band such as Ka, the use frequency band of the LEO satellites and the high frequency band of Ka inevitably generate same frequency interference with a geostationary orbit (GEO) satellite system, and if no system design or optimization means is adopted, the communication quality of the LEO satellite system and the GEO satellite system is influenced by each other. To address this problem, the International Telecommunications Union (ITU) specifies in radio regulations that LEO satellite systems must not cause interference to GEO satellite systems.
To meet the requirement of the isolation angle between the low-orbit satellite and the high-orbit satellite, the beam of the low-orbit satellite needs to be designed to be narrow enough. The wave beam is formed by the antenna, the Ka frequency band satellite-borne antenna of the low orbit satellite basically adopts a phased array antenna, the existing Ka frequency band transmitting phased array at home and abroad can form 8 wave beams at most, and the wave beam is narrow, so that the single-satellite coverage requirement can be met only by one hundred wave positions or even hundreds of wave positions. According to a communication system adopted by the satellite broadband service, a service beam and a signaling beam are separately designed, so that a phased array antenna needs to be additionally configured for the signaling beam, and a beam hopping technology is matched, so that more satellite resources are occupied.
Disclosure of Invention
The invention aims to provide a low-orbit satellite beam design method and system based on interference avoidance, and the consumption of satellite resources is reduced.
In order to achieve the purpose, the basic scheme of the invention is as follows: a low-orbit satellite beam design method based on interference avoidance comprises the following steps:
the uplink service beam adopts a plurality of beams with first width;
the downlink service beam adopts a plurality of beams with second width;
the uplink signaling wave beam adopts a plurality of wave beams with a third width, and the overlapping coverage of the uplink signaling wave beam meets the requirement of a single-satellite coverage range;
the first width is less than the third width, and the second width is less than the third width;
one or more downlink service beams are selected as downlink signaling beams.
The working principle and the beneficial effects of the basic scheme are as follows: the method limits the beam width of the uplink service beam, the downlink service beam and the downlink signaling beam, can meet the requirement of a space isolation angle threshold between a high orbit satellite system and a low orbit satellite system, can control the EPFD (equivalent power flux density) interference within a specified threshold, and is favorable for saving on-board resources. The uplink signaling beam can enable a user to access at any time, so that the waiting time caused by beam hopping is avoided, the requirement of frequency interference index is met, and the complexity of the access design of the ground terminal can be reduced. The downlink service wave beam is selected as the downlink signaling wave beam, so that the service wave beam phased array can be shared, the consumption of satellite resources is greatly reduced, and meanwhile, the downlink signaling wave beam can be narrow enough to support higher information rate and information quantity.
Further, the first width is equal to or unequal to the second width.
The uplink service beam and the downlink service beam can adopt beams with corresponding widths according to requirements, and the use is facilitated.
Further, the beam width of the first width beam and/or the second width beam is adjustable.
The designed beam width is adjustable, so that the system can adjust the total time of sweeping all beams once according to the user amount, and the flexibility of the system is improved.
Furthermore, the beam widths of the beams with the first width and the beams with the second width are adjusted according to the user quantity, so that the total time of the wave positions required by one-time jump-scanning is smaller than a time threshold T, and the waiting time of users at all positions is shortened.
Further, the beam with the first width and the beam with the second width are beams with an included angle between two half-power points of the beams being smaller than or equal to 7 degrees.
The adoption of the narrow beam can support higher information rate and information quantity, support concurrent access and reduce the antenna gain of the ground terminal.
Further, the beam with the third width is a beam with an included angle between two half-power points of the beam larger than 10 degrees.
The uplink signaling beam adopts a plurality of fixed wide beams, so that a user can access at any time, the waiting time caused by beam hopping is avoided, the requirement of frequency interference index is met, and the complexity of the access design of a ground terminal can be reduced.
Further, the beam with the first width and the beam with the second width can track the gaze of the terminal by adopting a gaze beam technology.
This may satisfy the system requirements for providing continuous service to the target area.
Furthermore, a beam hopping technology is adopted to control the downlink signaling beam to carry out hopping scanning only at the wave position of the user.
The technology of beam hopping is adopted to ensure that the downlink signaling beam is subjected to hopping scanning only at the wave position of a user, and the access waiting time of the user at each position is shortened.
The invention also provides a low-orbit satellite communication system which comprises the ground terminal and the satellite, wherein the ground terminal and the satellite are communicated through the method.
By utilizing the system, the occupation of on-satellite resources is reduced, and the requirement of a space isolation angle threshold value between a high-orbit satellite system and a low-orbit satellite system can be met.
Drawings
Fig. 1 is a schematic diagram of a low earth orbit satellite communication system according to the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
In the description of the present invention, unless otherwise specified and limited, it is to be noted that the terms "mounted," "connected," and "connected" are to be interpreted broadly, and may be, for example, a mechanical connection or an electrical connection, a communication between two elements, a direct connection, or an indirect connection via an intermediate medium, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
The invention discloses a low orbit satellite beam design method based on interference avoidance, which adopts a separated design mode for a service beam and a signaling beam, wherein the service beam is used as a transmission channel of user service data, and the signaling beam is used for transmitting control plane signaling such as connection establishment, bearing establishment, attachment and authentication, mobility control and the like. The uplink service beam, the downlink service beam, the uplink signaling beam and the downlink signaling beam are formed by a satellite-borne antenna, the uplink is used for transmitting signals to a satellite for a ground terminal, and the downlink is used for transmitting signals to the ground terminal by the satellite. The invention designs an uplink service beam, a downlink service beam, an uplink signaling beam and a downlink signaling beam, and specifically comprises the following steps:
according to the formula
It is determined that the GEO (geosychrons earth orbit) system receives the power flux density generated by all the senders of the LEO (Low earth orbit) system. Wherein N is the number of the sending ends, i isNumber, PiFor the transmission power of each transmitting end, diFor each sender-to-receiver distance, Gt(θi) In order to gain the transmit antenna(s),
for receiving antenna gain, thetaiThe angle between the antenna direction of the transmitting antenna and the connecting line from the transmitting end to the receiving end,
is the angle between the antenna direction of the receiving antenna and the line from the transmitting end to the receiving end, GrmaxIs the maximum receive antenna gain.
Respectively selecting downlink isolation angle threshold alphadlAnd an uplink isolation angle threshold alphaulAnd alpha is an included angle between the ground antenna and 2 different orbit satellites, and a downlink isolation angle threshold is determined by calculating the EPFD of the LEO satellite received by the GEO ground receiving antenna (the downlink isolation angle is changed, and when the downlink isolation angle is smaller than a certain value, the EPFD meets the ITU regulation, and the value is the downlink isolation angle threshold). The uplink isolation angle threshold is determined by calculating the EPFD of the LEO ground antenna received by the GEO satellite receiving antenna (the uplink isolation angle is changed, and when the uplink isolation angle is smaller than a certain value, the EPFD meets ITU regulations, and the value is the uplink isolation angle threshold). Enabling a calculation result of the EPFD (Equivalent Power Flux Density) to meet a downlink EPFD limiting condition given by ITU (International Telecommunication Union), and determining a spatial isolation angle of alpha max (alpha max)ul,αdl)。
The uplink service beam adopts a plurality of beams with first width, the downlink service beam adopts a plurality of beams with second width, the first width is equal to or not equal to the second width, and the first width is preferably equal to the second width. The beam width of the first width beam and the second width beam is adjustable. The beam width of the service beam is preferably determined according to the spatial isolation angle, and then the beam widths of the beam with the first width and the beam with the second width are adjusted according to the system index and the user amount, so that the system is favorable for adjusting the total time of sweeping all the beams once according to the user amount, the flexibility of the system is increased, and the total time of sweeping all the beams once is smaller than the time threshold T. In the real-time mode, the beam with the first width and the beam with the second width are preferably beams with an included angle between two half-power points of the beams being less than or equal to 7 °, and such narrow beams can support higher information rate and information quantity, support concurrent access, and reduce antenna gain of the ground terminal. More preferably, the first width beam and the second width beam may track gaze towards the terminal, facilitating beam access.
And the uplink signaling beam adopts a plurality of beams with a third width, the required uplink signaling beam is determined according to the single satellite coverage index and the uplink signaling beam width of the system, the overlapping coverage of the uplink signaling beam meets the single satellite coverage requirement, the third width is larger than the first width and the second width, and the beam with the third width is preferably a beam with an included angle of more than 10 degrees between two half-power points of the beam. The uplink signaling beam is a plurality of fixed wide beams, a small amount of access signaling is transmitted, so that a user can access at any time, the waiting time caused by beam hopping is avoided, the requirement of frequency interference index is met, and the complexity of ground terminal access design can be reduced.
In this embodiment, one or several downlink service beams are selected as downlink signaling beams, but in this embodiment, one or several downlink service beams may be selected as downlink signaling beams according to the number of users, and when the number of users is small, one downlink service beam is used; when the number of users reaches a certain number, the number of downlink signaling beams is increased, which can be determined according to actual conditions. The downlink service wave beam and the downlink signaling wave beam can share the service wave beam phased array, so that the downlink signaling wave beam can be narrow enough, and the consumption of satellite resources is greatly reduced. The embodiment can adopt a beam hopping technology to control the downlink signaling beam to hop and scan only at the wave position of the user, so that the downlink signaling beam hops and scans only at the wave position of the user, and the access waiting time of the user at each position is shortened.
The beam design can meet the requirement of a space isolation angle threshold between a high orbit satellite system and a low orbit satellite system, can control the EPFD interference within a specified threshold, is favorable for saving satellite resources and increases the flexibility of the system.
As shown in fig. 1, the present invention further provides a low earth orbit satellite communication system, which includes a ground terminal and a satellite, wherein the ground terminal and the satellite communicate with each other by the method of the present invention, which is beneficial to saving satellite resources and increasing system flexibility.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (9)
1. A low-orbit satellite beam design method based on interference avoidance is characterized by comprising the following steps:
the uplink service beam adopts a plurality of beams with first width;
the downlink service beam adopts a plurality of beams with second width;
the uplink signaling wave beam adopts a plurality of wave beams with a third width, and the overlapping coverage of the uplink signaling wave beam meets the requirement of a single-satellite coverage range;
the first width is less than the third width, and the second width is less than the third width;
one or more downlink service beams are selected as downlink signaling beams.
2. The interference avoidance based low-earth orbit satellite beam design method of claim 1, wherein the first width is equal to or not equal to the second width.
3. The interference avoidance based low-earth orbit satellite beam design method of claim 1, wherein the beam width of the first width beam and/or the second width beam is adjustable.
4. The interference avoidance-based low-earth-orbit satellite beam design method according to claim 3, wherein the beam widths of the first-width beam and the second-width beam are adjusted according to the user amount so that the total time of sweeping the wave position required for one pass is less than a time threshold T.
5. The method as claimed in claim 1, wherein the first width beam and the second width beam are beams with an angle of 7 ° or less between two half-power points.
6. The method as claimed in claim 1, wherein the third width of the beam is a beam with an angle of more than 10 ° between two half-power points.
7. The interference avoidance based low-orbit satellite beam design method according to claim 1, wherein a gaze beam technique is adopted so that the first width beam and the second width beam can track gaze towards a terminal.
8. The method as claimed in claim 1, wherein the beam hopping technique is used to control downlink signaling beams to hop and scan only at the wave position where there is a user.
9. A low earth satellite communications system comprising a ground terminal and a satellite, said ground terminal and satellite communicating by the method of any one of claims 1 to 8.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114785395A (en) * | 2022-03-08 | 2022-07-22 | 西安电子科技大学 | Wave beam hopping communication method, system and terminal for 5G fusion low-orbit satellite system |
| CN117278105B (en) * | 2023-09-27 | 2024-04-26 | 中国人民解放军31007部队 | Low-orbit satellite-borne communication downlink interference resisting method based on avoidance angle |
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| CN112004235A (en) * | 2019-05-27 | 2020-11-27 | 华为技术有限公司 | Method and device for adjusting received beam |
| CN112910541A (en) * | 2021-01-20 | 2021-06-04 | 华力智芯(成都)集成电路有限公司 | Satellite user side wave beam design method applied to satellite mobile communication system |
| CN113038618A (en) * | 2021-05-20 | 2021-06-25 | 银河航天(北京)网络技术有限公司 | Satellite communication system and method for accessing satellite communication system |
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| CN107949066A (en) * | 2017-11-21 | 2018-04-20 | 西安空间无线电技术研究所 | A kind of ripple position resource flexible scheduling system and dispatching method towards beam-hopping |
| CN112004235A (en) * | 2019-05-27 | 2020-11-27 | 华为技术有限公司 | Method and device for adjusting received beam |
| CN112910541A (en) * | 2021-01-20 | 2021-06-04 | 华力智芯(成都)集成电路有限公司 | Satellite user side wave beam design method applied to satellite mobile communication system |
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| CN117278105B (en) * | 2023-09-27 | 2024-04-26 | 中国人民解放军31007部队 | Low-orbit satellite-borne communication downlink interference resisting method based on avoidance angle |
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