CN111786716A - Low-earth-orbit communication satellite constellation networking structure and inter-satellite communication method - Google Patents
Low-earth-orbit communication satellite constellation networking structure and inter-satellite communication method Download PDFInfo
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Abstract
The invention provides a low-orbit communication satellite constellation networking structure and an inter-satellite communication method. The networking structure comprises at least one track A surface and at least one track B surface which are distributed along the longitude line, wherein the track A surfaces and the track B surfaces are alternately arranged; the A orbit surface is provided with at least two A-type satellites; at least two B-type satellites are arranged on the B orbit surface; all or part of the A/B type satellites can be respectively connected and communicated with the right communication link and the left communication link of the adjacent B/A type satellite in the adjacent orbital planes through the left communication link and the right communication link; the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the transmitting frequency of the left communication link and the right communication link of the B-type satellite are both the second frequency, and the receiving frequency is both the first frequency. The problem of mutual interference of transmitting signals of satellites adjacent to the orbital plane in a polar region and the problem of broken links of phase switching microwave links of satellites in the polar region can be solved, and all-weather reliable transmission of communication links is guaranteed.
Description
Technical Field
The invention relates to an inter-satellite link networking structure, in particular to a low earth orbit communication satellite constellation networking structure and an inter-satellite communication method.
Background
The low earth orbit communication satellite constellation adopts a near-polar orbit, and the quantity of satellites in south and north poles is gathered, because the satellites are too compact, frequency interference is easy to generate, and the condition that inter-satellite links are invalid is caused, particularly the interference occurs between the transmitting signals of the satellites on two adjacent orbital planes. When the satellite is in the north-south two poles, if the connection link between satellites is not changed, the inter-satellite link between adjacent orbital planes can have large-range angle change, however, the satellite-borne antenna mostly adopts a mechanical rotation mode and cannot realize the change of the large-range angle, so that the problem of broken link of the microwave link after the phase switching of the satellites in polar regions is caused.
Disclosure of Invention
In order to overcome the defects in the prior art, the present invention provides a low earth orbit communication satellite constellation networking structure and an inter-satellite communication method.
In order to achieve the above object, according to a first aspect of the present invention, the present invention provides a low earth orbit communication satellite constellation networking structure, comprising at least one a-orbit surface and at least one B-orbit surface distributed along a meridian line, wherein the a-orbit surface and the B-orbit surface are alternately arranged; the A orbit surface is provided with at least two A-type satellites; the B orbit surface is provided with at least two B-type satellites; all or part of the A/B type satellites can be respectively connected and communicated with the right communication link and the left communication link of the adjacent B/A type satellite in the adjacent orbital planes through the left communication link and the right communication link; the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the transmitting frequency of the left communication link and the right communication link of the B-type satellite are both the second frequency, and the receiving frequency is both the first frequency.
The beneficial effects of the above technical scheme are: the constellation networking structure adopts the frequency division duplex networking technology with different frequencies of inter-satellite links, adopts two types of satellites to realize constellation networking, can simultaneously solve the problem that the inter-satellite links fail due to mutual interference of transmitting signals of the satellites on adjacent orbital planes caused by too tight satellites in polar regions and the problem of broken links of satellite phase switching microwave links in the polar regions, establishes reliable inter-satellite links of low-orbit communication satellites, and ensures all-weather reliable transmission of communication links; two communication frequency bands are adopted, so that space frequency resources can be saved; the constellation type spectrum of the low orbit communication satellite is satisfied, the reliability is high, and the batch production is suitable. In a preferred embodiment of the present invention, the left communication link of one type of satellite is in communication with the right communication link of another type of satellite adjacent to the right side or the upper right side or the lower right side, and the right communication link of one type of satellite is in communication with the left communication link of another type of satellite adjacent to the left side or the upper left side or the lower left side.
The beneficial effects of the above technical scheme are: a form of satellite networking on adjacent orbital planes is disclosed, forming left and right communication links.
In a preferred embodiment of the present invention, the number of a-type satellites in the a orbital plane is equal to the number of B-type satellites in the B orbital plane.
The beneficial effects of the above technical scheme are: the communication links among a plurality of adjacent orbital plane satellites are convenient to establish, and the communication of each orbital plane of the constellation is enhanced.
In a preferred embodiment of the present invention, the a-type satellites and the B-type satellites are arranged in a space on the adjacent a-orbit plane and B-orbit plane.
The beneficial effects of the above technical scheme are: the interference immunity is further improved by making the receive antenna direction of the left and right parts of the satellite different from the transmit antenna direction of the interfering signal (the transmit signal antenna of the other satellite not establishing a communication link with the left and right parts of the satellite).
In a preferred embodiment of the present invention, the track comprises a B-track surface and two a-track surfaces, and the two a-track surfaces are respectively located on two sides of the B-track surface.
The beneficial effects of the above technical scheme are: the symmetrical structure is adopted, so that the structure change is small when the constellation crosses a polar region, the inter-satellite link communication can be maintained, and the chain breakage is avoided.
In a preferred embodiment of the present invention, the a-type satellites on the a-orbit plane are sequentially connected for communication in a back-and-forth order; and the B-type satellites on the B orbit surface are sequentially connected and communicated according to the front-back sequence.
The beneficial effects of the above technical scheme are: enhancing inter-satellite communication within the constellation.
In a preferred embodiment of the invention, on the orbital plane of any type of satellite, the upper communication link of the satellite is in communication with the lower communication link of the previous satellite, and the lower communication link of the satellite is in communication with the upper communication link of the next satellite; the receiving frequency of the front communication link of the satellite is a first frequency, the transmitting frequency of the front communication link of the satellite is a second frequency, the receiving frequency of the rear communication link of the satellite is a second frequency, and the transmitting frequency of the rear communication link of the satellite is a first frequency.
The beneficial effects of the above technical scheme are: the upper communication link and the lower communication link of the satellite are in a different-frequency duplex mode, so that the mutual interference of the transmitting signals of the lower communication link of the satellite with the same orbital plane and the upper communication link of the next-to-upper satellite is avoided, and the anti-interference performance is enhanced.
In order to achieve the above object, according to a second aspect of the present invention, there is provided an inter-satellite communication method comprising: establishing a low earth orbit communication satellite constellation networking structure, wherein the transmitting frequencies of a left part communication link and a right part communication link of the A-type satellite are both first frequencies, and the receiving frequencies are both second frequencies; the receiving frequency of the left communication link and the right communication link of the B-type satellite are both first frequencies, and the transmitting frequency is both second frequencies; the receiving frequencies of the front communication links of the A-type satellite and the B-type satellite are both first frequencies, the transmitting frequencies of the front communication links of the A-type satellite and the B-type satellite are both second frequencies, the receiving frequencies of the rear communication links of the A-type satellite and the B-type satellite are both second frequencies, and the transmitting frequencies of the rear communication links of the A-type satellite and the B-type satellite are both first frequencies.
The beneficial effects of the above technical scheme are: the communication method adopts the frequency division duplex networking technology with different frequencies of inter-satellite links, adopts two types of satellites to realize constellation networking, can simultaneously solve the problem that inter-satellite links fail due to mutual interference of satellite transmitting signals on two orbital planes which are too close and adjacent to the satellites in polar regions, the problem that the transmitting signals of a lower communication link of the satellite with the orbital planes and an upper communication link of a next-adjacent satellite behind the satellite interfere with each other, and the problem that the phase of the satellite in the polar regions is switched to a microwave link to break the link, establishes a reliable inter-satellite link of the constellation of the low-orbit communication satellite, and ensures all-weather reliable transmission of the communication link; two communication frequency bands are adopted, so that space frequency resources can be saved; the constellation type spectrum of the low orbit communication satellite is satisfied, the reliability is high, and the batch production is suitable.
In a preferred embodiment of the present invention, the method further includes a step of identifying interference between left and right received signals, including: when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a second frequency, the received signal is considered to be from a B-type satellite adjacent to the left or right B orbit plane and is a useful signal, and when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a first frequency, the received signal is considered to be an interference signal; when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a first frequency, the received signal is considered to be a useful signal from an adjacent A-type satellite on the left or right A-orbit plane, and when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a second frequency, the received signal is considered to be an interference signal.
The beneficial effects of the above technical scheme are: interference signals emitted by other orbital planes on the left communication link and the right communication link of the satellite can be accurately identified, and the anti-interference performance of inter-satellite communication is improved.
In a preferred embodiment of the present invention, the method further comprises a front-back received signal interference identification step, including: when the power of a received signal of a front communication link of the A/B type satellite reaches a power threshold value, the received signal is considered to be from a previous A/B type satellite in the same orbit plane with the A/B type satellite and is a useful signal, and when the power of the received signal at the front part of the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal; when the power of the received signal of the communication link behind the A/B type satellite reaches a power threshold value, the received signal is considered to be from the A/B type satellite behind the A/B type satellite on the same orbital plane and is a useful signal, and when the power of the received signal behind the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal.
The beneficial effects of the above technical scheme are: interference signals transmitted by other satellites on the same orbit plane on the front communication link and the rear communication link of the satellite can be accurately identified, and the anti-interference performance of inter-satellite communication is further improved.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic diagram of a constellation networking structure of a low earth orbit communication satellite in a preferred embodiment of the invention;
fig. 2 is a schematic diagram of broken link of polar region phase switching communication link, wherein fig. 2(a) shows a schematic diagram of constellation networking structure before passing through polar region; fig. 2(b) shows a schematic diagram of a constellation network structure after phase switching of the over-polar region.
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, 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 provides a low-orbit communication satellite constellation networking structure, which comprises at least one A orbit surface and at least one B orbit surface which are distributed along a meridian line in a preferred embodiment as shown in figure 1, wherein the A orbit surface and the B orbit surface are alternately arranged; the A orbit surface is provided with at least two A-type satellites; at least two B-type satellites are arranged on the B orbit surface; all or part of the A/B type satellites can be respectively connected and communicated with the right communication link and the left communication link of the adjacent B/A type satellite in the adjacent orbital planes through the left communication link and the right communication link; the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the transmitting frequency of the left communication link and the right communication link of the B-type satellite are both the second frequency, and the receiving frequency is both the first frequency.
In this embodiment, all or a portion of the a-satellites may be in communication with the right communication link of an adjacent B-satellite in an adjacent orbital plane via the left communication link; all or part of the A-type satellites can be connected and communicated with the left communication link of the adjacent B-type satellite in the adjacent orbital plane through the right communication link; all or part of the B-type satellites can be connected and communicated with the right communication link of the adjacent A-type satellite in the adjacent orbital plane through the left communication link; all or a portion of the type B satellites may be in communication with the left communication link connection of an adjacent type a satellite in an adjacent orbital plane via the right communication link.
In the present embodiment, as shown in fig. 1, for a type a satellite: left communication link, transmit frequency F1, receive frequency F2; right communication link, transmit frequency F1, receive frequency F2. For type B satellites: left communication link, transmit frequency F2, receive frequency F1; the right communication link, transmit frequency F2, receive frequency F1.
In the present embodiment, the a orbital plane and the B orbital plane are both distributed along the meridian line, and the other type of satellite adjacent to the one type of satellite in the adjacent orbital plane may be on the left/right side, or the upper left/right side, or the lower left/right side of the one type of satellite. Preferably, the left communication link of one type of satellite is in communication connection with the right communication link of another type of satellite adjacent to the right side or the upper right side or the lower right side, and the right communication link of one type of satellite is in communication connection with the left communication link of another type of satellite adjacent to the left side or the upper left side or the lower left side.
In the present embodiment, as shown in fig. 2, the B- type 4, 5, and 6 are all on the B-track plane; satellites 1, 2, 3, 7, 8, 9 are type a satellites, with 1, 2, 3 on the adjacent a orbital plane to the right of the B orbital plane and 7, 8, 9 on the adjacent a orbital plane to the left of the B orbital plane. As shown in fig. 2(a), the earth front surface is connected before passing through the polar region in the following manner; 4-1, 4-7; 5-2, 5-8; 6-3 and 6-9. When the polar region is crossed, the phase is switched, after the switching, as shown in fig. 2(b), the satellite 7 is changed from the upper right to the upper left, the connection mode of the front side of the earth on the back side of the earth cannot meet the requirement, if the inter-satellite link is connected with the satellite and is not changed, the inter-satellite link of the adjacent orbital planes can have wide-range angle change, but the inter-satellite antenna adopts a mechanical rotation mode and cannot meet the change of the wide-range angle, so that the link breaking condition is caused, and the inter-satellite link communication cannot be maintained. According to the A, B type satellite, the left communication link and the right communication link adopt different frequency division duplex communication modes, constellation networking is realized by adopting two satellite states, the link connection mode of the satellite can be changed when the satellite crosses polar regions, and quick inter-satellite link building is realized, so that the rotation angle of an antenna is reduced, and continuous link connection is ensured.
In the embodiment, the orbit surfaces a and B adopt near polar orbits, and the number of satellites in the north and south poles is gathered, because the satellites are too close, frequency interference is easy to generate, and the inter-satellite link fails, especially interference occurs between the transmission signals of two adjacent orbit surfaces. In the networking structure of the present invention, as shown in fig. 1, since the states of the A, B type satellites can ensure that the receiving directions of the same frequency are different, and the satellite frequencies received in the same direction can be clearly distinguished, for example, for the a type satellite on the a orbit plane on the right side of the B orbit plane, when the frequency of the received upper left signal is F2, the signal transmitted by the B type satellite on the upper left B orbit plane can be clearly judged, and when the frequency of the received signal by the left communication link is F1, the signal transmitted by the a type satellite on the a orbit plane on the left side of the B orbit plane can be known, so that the problem of frequency interference between adjacent orbits is solved.
In a preferred embodiment, as shown in fig. 1, the number of a-type satellites in the a orbital plane is equal to the number of B-type satellites in the B orbital plane.
In a preferred embodiment, as shown in figure 1, the a-type satellites and the B-type satellites are spaced apart on adjacent a-orbital planes and B-orbital planes.
In a preferred embodiment, as shown in fig. 1, the two-way valve comprises a B-track surface and two a-track surfaces, and the two a-track surfaces are respectively positioned on two sides of the B-track surface.
In a preferred embodiment, as shown in fig. 1, the a-type satellites on the a-orbit plane are sequentially connected for communication in a back-and-forth order; and the B-type satellites on the B orbit surface are sequentially communicated in a front-back order.
In this embodiment, optionally, on the orbital plane of any type of satellite, the upper communication link of the satellite is in communication with the lower communication link of the previous satellite, and the lower communication link of the satellite is in communication with the upper communication link of the next satellite; the receiving frequency of the front communication link of the satellite is a first frequency, the transmitting frequency of the front communication link of the satellite is a second frequency, the receiving frequency of the rear communication link of the satellite is a second frequency, and the transmitting frequency of the rear communication link of the satellite is a first frequency. As shown in fig. 1, a type a satellite: upper communication link, transmit frequency F2, receive frequency F1; lower communication link, transmit frequency F1, receive frequency F2; type B satellite: upper communication link, transmit frequency F2, receive frequency F1; lower communication link, transmit frequency F1, receive frequency F2.
The invention also discloses an inter-satellite communication method, which comprises the following steps: establishing the low-orbit communication satellite constellation networking structure; the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the receiving frequency of the left communication link and the right communication link of the B-type satellite are both first frequencies, and the transmitting frequency is both second frequencies; the receiving frequencies of the front communication links of the A-type satellite and the B-type satellite are both first frequencies, the transmitting frequencies of the front communication links of the A-type satellite and the B-type satellite are both second frequencies, the receiving frequencies of the rear communication links of the A-type satellite and the B-type satellite are both second frequencies, and the transmitting frequencies of the rear communication links of the A-type satellite and the B-type satellite are both first frequencies.
In a preferred embodiment, the method further comprises a step of identifying interference between the left and right received signals, which comprises: when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a second frequency, the received signal is considered to be from a B-type satellite adjacent to the left or right B orbit plane and is a useful signal, and when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a first frequency, the received signal is considered to be an interference signal; when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a first frequency, the received signal is considered to be a useful signal from an adjacent A-type satellite on the left or right A-orbit plane, and when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a second frequency, the received signal is considered to be an interference signal.
In the present embodiment, as shown in fig. 1, for the B-type satellite 5 in the B-orbit plane, when the frequency of the received signal of the left communication link of the B-type satellite 5 is the first frequency F1, the received signal is considered to be a useful signal from the a-type satellite 2, and when the frequency of the received signal of the left communication link of the B-type satellite 5 is the second frequency F2, the received signal is considered to be an interference signal not from the a-type satellite 2; for the B-type satellite 5 in the B-orbital plane, when the frequency of the received signal of the right communication link of the B-type satellite 5 is the first frequency F1, the received signal is considered to be a useful signal from the a-type satellite 9, and when the frequency of the received signal of the right communication link of the B-type satellite 5 is the second frequency F2, the received signal is considered to be an interference signal not from the a-type satellite 9.
In the present embodiment, as shown in fig. 1, when the frequency of the received signal of the left communication link of the a-type satellite 8 is the second frequency F2, the received signal is considered to be from the adjacent B-type satellite 4 on the left B-orbit plane and is a useful signal, and when the frequency of the received signal of the left communication link of the a-type satellite 8 is the first frequency F1, the received signal is considered to be an interference signal, such as possibly from the a-type satellite 1; when the frequency of the received signal of the right communication link of the a-type satellite 8 is the second frequency F2, the received signal is considered to be a useful signal from an adjacent B-type satellite (not shown) on the right B-orbital plane, and when the frequency of the received signal of the right communication link of the a-type satellite 8 is the first frequency F1, the received signal is considered to be an interference signal.
In a preferred embodiment, the method further comprises a front-back received signal interference identification step, including: when the power of a received signal of a communication link at the front part of the A/B type satellite reaches a power threshold value, the received signal is considered to be from a previous A/B type satellite in the same orbit plane with the A/B type satellite and is a useful signal, and when the power of the received signal at the front part of the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal; when the power of the received signal of the communication link behind the A/B type satellite reaches a power threshold value, the received signal is considered to be from the following A/B type satellite on the same orbital plane of the A/B type satellite and is a useful signal, and when the power of the received signal behind the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal. The power threshold may be set empirically.
In the present embodiment, as shown in fig. 1, when the received signal power of the front communication link of the a-type satellite 3 reaches the power threshold, it is considered that the received signal is from the previous a-type satellite 2 in the same orbit plane and is a useful signal, and when the received signal power of the front of the a-type satellite 3 does not reach the power threshold, it is considered that the received signal is an interference signal, such as may come from the a-type satellite 1; when the power of the received signal of the rear communication link of the type a satellite 1 reaches the power threshold, the received signal is considered to be from the next type a satellite 2 in the same orbital plane of the type a satellite 1 and is a useful signal, and when the power of the rear received signal of the type a satellite 1 does not reach the power threshold, the received signal is considered to be an interference signal, such as possibly from the type a satellite 3.
In the present embodiment, as shown in fig. 1, when the received signal power of the forward communication link of the B-type satellite 6 reaches the power threshold, it is considered that the received signal is from the previous B-type satellite 5 on the same orbit plane and is a useful signal, and when the forward received signal power of the B-type satellite 6 does not reach the power threshold, it is considered that the received signal is an interference signal, such as possibly from the B-type satellite 4; when the power of the received signal of the back communication link of the B-type satellite 4 reaches the power threshold, the received signal is considered to be a useful signal from the next B-type satellite 5 in the same orbital plane as the B-type satellite 4, and when the power of the back received signal of the B-type satellite 4 does not reach the power threshold, the received signal is considered to be an interference signal, such as possibly from the B-type satellite 6.
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 (10)
1. A constellation networking structure of a low-orbit communication satellite is characterized by comprising at least one A orbit surface and at least one B orbit surface which are distributed along a meridian line, wherein the A orbit surface and the B orbit surface are alternately arranged;
the A orbit surface is provided with at least two A-type satellites; the B orbit surface is provided with at least two B-type satellites;
all or part of the A/B type satellites can be respectively connected and communicated with the right communication link and the left communication link of the adjacent B/A type satellite in the adjacent orbital planes through the left communication link and the right communication link;
the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the transmitting frequency of the left communication link and the right communication link of the B-type satellite are both the second frequency, and the receiving frequency is both the first frequency.
2. The low earth orbit communication satellite constellation networking architecture of claim 1, wherein the left communication link of one type of satellite is in communication with the right communication link of another type of satellite adjacent to the right side or the upper right side or the lower right side, and the right communication link of one type of satellite is in communication with the left communication link of another type of satellite adjacent to the left side or the upper left side or the lower left side.
3. The low earth orbit communication satellite constellation networking architecture of claim 1, wherein the number of type a satellites in the a orbital plane is equal to the number of type B satellites in the B orbital plane.
4. The low earth orbit communication satellite constellation networking architecture of claim 1, wherein a type a satellite and a type B satellite are in a null arrangement on adjacent a and B orbital planes.
5. The low earth orbit communication satellite constellation networking architecture of claim 1, comprising a B-orbital plane and two a-orbital planes, wherein the two a-orbital planes are respectively located on both sides of the B-orbital plane.
6. The low earth orbit communication satellite constellation networking architecture of one of claims 1 to 5, wherein the type A satellites on the A orbit plane are sequentially connected for communication in a back-and-forth order; and the B-type satellites on the B orbit surface are sequentially connected and communicated according to the front-back sequence.
7. The low earth orbit communication satellite constellation networking architecture of claim 6, wherein on the orbital plane of any type of satellite, the upper communication link of the satellite is in communication with the lower communication link of a previous satellite, and the lower communication link of the satellite is in communication with the upper communication link of a subsequent satellite;
the receiving frequency of the front communication link of the satellite is a first frequency, the transmitting frequency of the front communication link of the satellite is a second frequency, the receiving frequency of the rear communication link of the satellite is a second frequency, and the transmitting frequency of the rear communication link of the satellite is a first frequency.
8. An inter-satellite communication method based on the low earth orbit communication satellite constellation networking architecture of one of claims 1 to 7, comprising:
a low-orbit communication satellite constellation networking structure is established,
the transmitting frequency of the left communication link and the right communication link of the A-type satellite are both first frequencies, and the receiving frequency is both second frequencies; the receiving frequency of the left communication link and the right communication link of the B-type satellite are both first frequencies, and the transmitting frequency is both second frequencies;
the receiving frequencies of the front communication links of the A-type satellite and the B-type satellite are both first frequencies, the transmitting frequencies of the front communication links of the A-type satellite and the B-type satellite are both second frequencies, the receiving frequencies of the rear communication links of the A-type satellite and the B-type satellite are both second frequencies, and the transmitting frequencies of the rear communication links of the A-type satellite and the B-type satellite are both first frequencies.
9. The inter-satellite communication method of claim 8, further comprising a left-right received signal interference identification step comprising:
when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a second frequency, the received signal is considered to be from a B-type satellite adjacent to the left or right B orbit plane and is a useful signal, and when the frequency of the received signal of the left communication link or the right communication link of the A-type satellite is a first frequency, the received signal is considered to be an interference signal;
when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a first frequency, the received signal is considered to be a useful signal from an adjacent A-type satellite on the left or right A-orbit plane, and when the frequency of the received signal of the left communication link or the right communication link of the B-type satellite is a second frequency, the received signal is considered to be an interference signal.
10. The inter-satellite communication method according to claim 8, further comprising a front-to-back received signal interference identification step comprising:
when the power of a received signal of a front communication link of the A/B type satellite reaches a power threshold value, the received signal is considered to be from a previous A/B type satellite in the same orbit plane with the A/B type satellite and is a useful signal, and when the power of the received signal at the front part of the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal;
when the power of the received signal of the communication link behind the A/B type satellite reaches a power threshold value, the received signal is considered to be from the A/B type satellite behind the A/B type satellite on the same orbital plane and is a useful signal, and when the power of the received signal behind the A/B type satellite does not reach the power threshold value, the received signal is considered to be an interference signal.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160269098A1 (en) * | 2015-03-11 | 2016-09-15 | The Aerospace Corporation | Ring constellations for decreased data latency and increased download rates |
| US20170324465A1 (en) * | 2016-05-04 | 2017-11-09 | Thales | Inter-satellite communication device, associated satellite and associated constellation of satellites |
| CN108736955A (en) * | 2018-04-09 | 2018-11-02 | 西安空间无线电技术研究所 | A kind of full duplex inter-satellite link system and method that transmitting-receiving frequency is changeable |
| CN108880665A (en) * | 2018-09-20 | 2018-11-23 | 上海微小卫星工程中心 | A kind of full duplex satellite communication system |
| CN109474324A (en) * | 2018-10-26 | 2019-03-15 | 中国空间技术研究院 | A method for avoiding co-channel interference of polar orbit constellation by using phased array beam reconstruction |
-
2020
- 2020-06-08 CN CN202010514117.7A patent/CN111786716A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160269098A1 (en) * | 2015-03-11 | 2016-09-15 | The Aerospace Corporation | Ring constellations for decreased data latency and increased download rates |
| US20170324465A1 (en) * | 2016-05-04 | 2017-11-09 | Thales | Inter-satellite communication device, associated satellite and associated constellation of satellites |
| CN108736955A (en) * | 2018-04-09 | 2018-11-02 | 西安空间无线电技术研究所 | A kind of full duplex inter-satellite link system and method that transmitting-receiving frequency is changeable |
| CN108880665A (en) * | 2018-09-20 | 2018-11-23 | 上海微小卫星工程中心 | A kind of full duplex satellite communication system |
| CN109474324A (en) * | 2018-10-26 | 2019-03-15 | 中国空间技术研究院 | A method for avoiding co-channel interference of polar orbit constellation by using phased array beam reconstruction |
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