CN115776329A - Inter-satellite link construction method and system - Google Patents
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Abstract
The invention discloses a construction method of an inter-satellite link, which comprises the steps of determining the orbit type of the inter-satellite link to be constructed; carrying out same-orbit connection processing on each star orbit of the same-orbit inter-star link in sequence; performing sequential different-orbit processing on all satellites of all orbits of the different-orbit inter-satellite link; and completing the construction of the inter-satellite link according to the construction process of the inter-satellite link of the same orbit and the inter-satellite link of the different orbit. The invention also discloses a system for constructing the inter-satellite link, which comprises a track confirmation module, an on-track connection module, an off-track connection module and a track construction module.
Description
Technical Field
The invention relates to the technical field of communication, in particular to a method for constructing an inter-satellite link.
Background
In a low-earth-orbit satellite communication system, interconnection communication among satellites is often realized by configuring an inter-satellite link, and cross-regional transmission of user service data is realized. That is, in a satellite constellation, one satellite needs to establish an inter-satellite communication link (referred to as an inter-satellite link) with two satellites in the same orbit and two satellites in east-west adjacent orbits. An inter-satellite link established between satellites running on the same orbit is called as an inter-satellite link of the same orbit; the inter-satellite links established between satellites operating in different orbits are called inter-orbital inter-satellite links.
In order to reduce the power consumption of the antenna and increase the information transmission rate, the inter-satellite link usually uses spot beams to implement point-to-point communication between satellites. Taking microwave communication as an example, because the relative position of the co-orbit operation satellite is fixed, the communication antenna can adopt a fixed installation mode, and the accurate pointing of the wave beam is ensured to establish the inter-satellite link through the satellite attitude control precision. Due to the fact that the azimuth angle (yaw angle and pitch angle) between two satellites of the different-orbit operation satellite is changed greatly, the point beam bidirectional accurate pointing is required to be achieved in the pitching and yawing directions through beam scanning to establish an inter-satellite link, and the beam scanning can be achieved through mechanical scanning and electrical scanning or a combination mode of the mechanical scanning and the electrical scanning.
The conventional method for establishing and maintaining the inter-satellite link of the satellite in the different orbit comprises the following steps: after the satellite establishes the inter-satellite link through ground guidance, the ground injects precise orbit parameters of the satellite and left and right adjacent satellites to the satellite at a fixed time period, the satellite carries out three satellite orbit data recursion through a preset algorithm, thereby calculating the beam pointing angle at intervals, controlling the antenna beam to reach the specified angle position on the satellite, and establishing the inter-satellite link with the adjacent satellite. The method needs the ground to inject accurate orbit parameters periodically in a short period, is used for correcting the deviation generated by orbit recursion on the satellite, and has high dependence on ground measurement and control.
Disclosure of Invention
This section is for the purpose of summarizing some aspects of embodiments of the invention and to briefly introduce some preferred embodiments. In this section, as well as in the abstract and the title of the invention of this application, simplifications or omissions may be made to avoid obscuring the purpose of the section, the abstract and the title, and such simplifications or omissions are not intended to limit the scope of the invention.
The present invention has been made in view of the above and/or other problems occurring in the conventional inter-satellite link construction method.
Therefore, the problem to be solved by the present invention is how to provide a method for constructing inter-satellite links.
In order to solve the technical problems, the invention provides the following technical scheme: the method for constructing the inter-satellite link comprises the following steps,
determining the track type of an inter-satellite link to be constructed;
carrying out sequential on-orbit connection processing on each star orbit of the on-orbit inter-star link;
sequentially carrying out different-orbit processing on all satellites of all orbits of the different-orbit inter-satellite link;
and completing the construction of the inter-satellite link according to the construction process of the inter-satellite link of the same orbit and the inter-satellite link of the different orbit.
As a preferable scheme of the inter-satellite link construction method of the present invention, wherein: the in-sequence on-orbit connection processing is to execute the following steps on all satellites in each on-orbit inter-satellite link for each satellite orbit of the on-orbit inter-satellite link,
starting from the first satellite in orbit, connecting the forward inter-satellite link port of the first satellite with the next satellite until the connection between the last satellite in the current orbit and the forward inter-satellite link port of the last satellite in the current orbit is completed.
As a preferred scheme of the inter-satellite link construction method of the present invention, wherein: the in-sequence off-orbit processing is to connect the right inter-satellite link port of a first satellite to the first satellite of the adjacent second orbit from the first satellite of the first orbit and connect the left inter-satellite link of the second orbit to the first satellite of the first orbit until the connection of all the satellites of the off-orbit orbits is completed.
As a preferred scheme of the inter-satellite link construction method of the present invention, wherein: after the inter-satellite link is constructed, calculating the routing information of the inter-satellite link;
the inter-satellite link calculation mode is
Finding all target satellites capable of communicating with the gateway station from the inter-satellite link;
respectively determining satellites connected with a backward inter-satellite link, a forward inter-satellite link, a right inter-satellite link and a left inter-satellite link of the target satellite, and calculating hop counts between the target satellite and each connected satellite;
determining the exit of each satellite in the inter-satellite link according to the hop count;
and calculating the distance and the time delay of each satellite to the gateway station according to the distance and the time delay from the outlet of the inter-satellite link to the connected satellite.
As a preferable scheme of the inter-satellite link construction method of the present invention, wherein: the step of determining the satellites to which the backward inter-satellite links of the target satellite are connected and calculating the hop count between the target satellite and each connected satellite includes the steps of
And for all satellites connected with the backward inter-satellite link of the target satellite, finding out candidate satellites connected with the backward inter-satellite link of the target satellite, and adding one to the hop count between the target satellite and the candidate satellite when the candidate satellites are not connected with the gateway station until traversal of all satellites is completed to obtain the hop count between the target satellite and all satellites.
As a preferable scheme of the inter-satellite link construction method of the present invention, the calculating, according to the distance and the time delay from the exit of the inter-satellite link to the connected satellite, the distance and the time delay from each satellite to the gateway station includes:
for each target satellite, acquiring the hop count with the minimum hop count value between the target satellite and each connected satellite;
taking the port corresponding to the hop count with the minimum hop count value as an intersatellite link outlet;
calculating the distance and the time delay between the inter-satellite link outlet and the connected satellite according to the inter-satellite link outlet;
and if the hop numbers with the minimum hop number values are all 0, calculating the distance and the time delay from the exit of the inter-satellite link to the gateway station.
As a preferable scheme of the inter-satellite link construction method of the present invention, wherein: the construction method of the inter-star link with different rails comprises the following steps
Starting from a first star of the first track, connecting a right-hand inter-satellite link port of the first star with the same serial number star of the second track, and simultaneously connecting a left-hand inter-satellite link of the second track with the first star of the first track;
repeating the steps for the stars with the same serial number of the second track to be connected with the first star of the next track;
if the longitude difference between the orbits multiplied by the number of orbits m is not equal to 360 when connected to the first star of the last orbit of such orbit, it indicates that there is no interstellar link between them;
if the longitude difference between the orbits, multiplied by the number of orbits m, is equal to 360 when connected to the first star of the last orbit of such orbit, it means that there is an inter-satellite link between them;
if the longitude difference between the orbits multiplied by the number m of orbits is not equal to 360, it indicates that there is no inter-satellite link between them because the moving directions of the satellites in the two orbits are opposite.
The present invention has been made in view of the above and/or other problems occurring in the conventional inter-satellite link construction system.
Therefore, the problem to be solved by the present invention is how to provide an inter-satellite link construction system.
In order to solve the technical problems, the invention provides the following technical scheme: an intersatellite link construction system comprising: the system comprises a track confirmation module, a same-track connection module, an abnormal-track connection module and a track building module;
the orbit confirmation module is used for determining the orbit type of the inter-satellite link to be constructed;
the co-orbit connection module is used for executing the following steps on all satellites in each co-orbit inter-satellite link for each satellite orbit of the co-orbit inter-satellite link: starting from a first satellite in the orbit, connecting a forward inter-satellite link port of the first satellite with a next satellite until the connection between the last satellite in the current orbit and a forward inter-satellite link port of a previous satellite is completed;
the different-orbit connection module is used for connecting a right-direction inter-satellite link port of a first satellite to a first satellite of an adjacent second orbit from the first satellite of the first orbit and connecting a left-direction inter-satellite link of the second orbit to the first satellite of the first orbit until the connection of all the satellites of different-orbit orbits is completed;
as a preferable scheme of the inter-satellite link construction method of the present invention, wherein: the track type in the track confirmation module comprises the same track and the different track.
As a preferable scheme of the inter-satellite link construction method of the present invention, wherein: the track building module can be used for carrying out track building work and track data storage and has a storage medium storage program.
The method has the advantages that the method for establishing and maintaining the inter-satellite link of the satellite in the prior art needs to periodically inject the accurate orbit parameters into the ground in a shorter period to correct the deviation generated by the recursion of the on-satellite orbit, and has high dependence degree on the ground measurement and control.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise. Wherein:
fig. 1 is a flowchart of an inter-satellite link construction method in embodiment 1.
Fig. 2 is a structural diagram of an inter-satellite link construction system in embodiment 2.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described and will be readily apparent to those of ordinary skill in the art without departing from the spirit of the present invention, and therefore the present invention is not limited to the specific embodiments disclosed below.
Furthermore, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one implementation of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
Example 1
Referring to fig. 1 and 2, a first embodiment of the present invention provides an inter-satellite link construction method, which includes
The method of the invention comprises the following steps:
determining the track type of an inter-satellite link to be constructed, wherein the track type comprises the same track and the different track;
for each satellite orbit of the inter-satellite link with the same orbit, executing the following steps on all satellites in each inter-satellite link with the same orbit: starting from a first satellite in orbit, connecting a forward inter-satellite link port of the first satellite with a next satellite until the connection between the last satellite in the current orbit and a forward inter-satellite link port of the last satellite in the previous orbit is completed;
for all the satellites in all the orbits of the inter-satellite links with different orbits, starting from the first satellite in the first orbit, connecting the right inter-satellite link port of the first satellite to the first satellite in the adjacent second orbit, and connecting the left inter-satellite link of the second orbit to the first satellite in the first orbit until the connection of all the satellites in all the different orbits is completed;
and completing the construction of the inter-satellite link according to the construction process of the inter-satellite link of the same orbit and the inter-satellite link of the different orbit.
The method further comprises the following steps:
and after the inter-satellite link is constructed, calculating the routing information of the inter-satellite link.
After the inter-satellite link construction is completed, calculating the routing information of the inter-satellite link, including:
finding all target satellites capable of communicating with the gateway station from the inter-satellite link;
respectively determining satellites connected with a backward inter-satellite link, a forward inter-satellite link, a right inter-satellite link and a left inter-satellite link of the target satellite, and calculating hop counts between the target satellite and each connected satellite;
determining the exit of each satellite in the inter-satellite link according to the hop count;
and calculating the distance and the time delay of each satellite to the gateway station according to the distance and the time delay from the exit of the inter-satellite link to the connected satellite.
For the backward inter-satellite link, the step of determining the satellite connected to the backward inter-satellite link of the target satellite and calculating the hop count between the target satellite and each connected satellite comprises:
and for all satellites connected with the backward inter-satellite link of the target satellite, finding out candidate satellites connected with the backward inter-satellite link of the target satellite, and adding one to the hop count between the target satellite and the candidate satellite when the candidate satellites are not connected with the gateway station until traversal of all satellites is completed to obtain the hop count between the target satellite and all satellites.
The calculating the distance and the time delay of each satellite to the gateway station according to the distance and the time delay from the exit of the inter-satellite link to the connected satellite comprises:
for each target satellite, acquiring the hop count with the minimum hop count value between the target satellite and each connected satellite;
taking the port corresponding to the hop count with the minimum hop count value as an intersatellite link outlet;
according to the inter-satellite link outlet, calculating the distance and time delay between the inter-satellite link outlet and the connected satellite
And if the hop counts with the minimum hop count values are all 0, calculating the distance and the time delay of the inter-satellite link outlet to the gateway station.
Example 2
Referring to FIG. 2, a second embodiment of the present invention, which is different from the first embodiment, is an inter-satellite link construction system comprising
The system comprises a track confirmation module 100, an on-track connection module 200, an off-track connection module 300 and a track building module 400;
the orbit determination module 100 is configured to determine an orbit type of an inter-satellite link to be constructed;
the on-orbit connection module 200 is configured to, for each satellite orbit of the on-orbit inter-satellite link, perform the following steps for all satellites in each on-orbit inter-satellite link: starting from a first satellite in orbit, connecting a forward inter-satellite link port of the first satellite with a next satellite until the connection between the last satellite in the current orbit and a forward inter-satellite link port of the last satellite in the previous orbit is completed;
the different-orbit connection module 300 is configured to connect, starting from a first satellite in a first orbit, a right inter-satellite link port of the first satellite to a first satellite in an adjacent second orbit, and connect a left inter-satellite link in the second orbit to the first satellite in the first orbit, for all satellites in all orbits of different-orbit inter-satellite links, until connection of all satellites in all different-orbit orbits is completed;
the track building module 400 is used for completing inter-satellite link building according to the building process of the inter-satellite link with the same orbit and the inter-satellite link with different orbits, has a storage function, and is used for storing the inter-satellite link.
The track type in the track confirmation module 100 includes the same track and the different track.
The track building module 400 may also store track data and have a storage medium storing a program, in addition to performing track building work.
Example 3
A third embodiment of the invention, which differs from the first two embodiments, is: .
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-only memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk.
The logic and/or steps represented in the flowcharts or otherwise described herein, e.g., an ordered listing of executable instructions that can be considered to implement logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device.
More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or more wires, a portable computer diskette (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). Further, the computer-readable medium could even be paper or another suitable medium upon which the program is printed, as the program can be electronically captured, via for instance optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner if necessary, and then stored in a computer memory.
It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, various steps or methods may be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
It should be noted that the above-mentioned embodiments are only for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the claims of the present invention.
Claims (10)
1. A method for constructing an inter-satellite link is characterized by comprising the following steps:
determining the track type of an inter-satellite link to be constructed;
carrying out same-orbit connection processing on each star orbit of the same-orbit inter-star link in sequence;
sequentially carrying out different-orbit processing on all satellites of all orbits of the different-orbit inter-satellite link;
and completing the construction of the inter-satellite link according to the construction process of the inter-satellite link of the same orbit and the inter-satellite link of the different orbit.
2. The inter-satellite link construction method according to claim 1, characterized in that: the in-sequence on-orbit connection processing is to execute the following steps on all satellites in each on-orbit inter-satellite link for each satellite orbit of the on-orbit inter-satellite link,
starting from the first satellite in orbit, connecting the forward inter-satellite link port of the first satellite with the next satellite until the connection between the last satellite in the current orbit and the forward inter-satellite link port of the last satellite in the current orbit is completed.
3. The inter-satellite link construction method according to claim 2, characterized in that: the in-sequence off-orbit processing is to connect the right inter-satellite link port of a first satellite to the first satellite of the adjacent second orbit from the first satellite of the first orbit and connect the left inter-satellite link of the second orbit to the first satellite of the first orbit until the connection of all the satellites of the off-orbit orbits is completed.
4. The inter-satellite link construction method according to claim 3, characterized in that: after the inter-satellite link is constructed, calculating the routing information of the inter-satellite link;
the inter-satellite link calculation mode is
Finding all target satellites capable of communicating with the gateway station from the inter-satellite link;
respectively determining satellites connected with a backward inter-satellite link, a forward inter-satellite link, a right inter-satellite link and a left inter-satellite link of the target satellite, and calculating hop counts between the target satellite and each connected satellite;
determining the exit of each satellite in the inter-satellite link according to the hop count;
and calculating the distance and the time delay of each satellite to the gateway station according to the distance and the time delay from the outlet of the inter-satellite link to the connected satellite.
5. The inter-satellite link construction method according to any one of claims 1, 2 and 4, characterized by: the step of determining the satellites connected to the backward inter-satellite link of the target satellite and calculating the hop count between the target satellite and each connected satellite includes
And for all satellites connected with the backward inter-satellite link of the target satellite, finding out candidate satellites connected with the backward inter-satellite link of the target satellite, and adding one to the hop count between the target satellite and the candidate satellite when the candidate satellites are not connected with the gateway station until traversal of all satellites is completed to obtain the hop count between the target satellite and all satellites.
6. The method according to claim 5, wherein the calculating of the distance and the time delay from each satellite to the gateway station according to the distance and the time delay from the exit of the inter-satellite link to the connected satellite comprises:
for each target satellite, acquiring the hop count with the minimum hop count value between the target satellite and each connected satellite;
taking the port corresponding to the hop count with the minimum hop count value as an intersatellite link outlet;
calculating the distance and the time delay between the inter-satellite link outlet and the connected satellite according to the inter-satellite link outlet;
and if the hop count with the minimum hop count value is 0, calculating the distance and the time delay of the inter-satellite link outlet to the gateway station.
7. The inter-satellite link construction method according to claim 6, characterized in that: the construction method of the inter-star link with different rails comprises the following steps
Starting from a first star of the first track, connecting a right-hand inter-satellite link port of the first star with the same serial number star of the second track, and simultaneously connecting a left-hand inter-satellite link of the second track with the first star of the first track;
repeating the steps for the stars with the same serial number of the second track, and connecting the stars with the first star of the next track;
if the longitude difference between the tracks multiplied by the number of tracks m is not equal to 360 when connected to the first star of the last track of such a track, it means that there is no inter-satellite link between them;
if the longitude difference between the orbits, multiplied by the number of orbits m, is equal to 360 when connected to the first star of the last orbit of such orbit, it means that there is an inter-satellite link between them;
if the longitude difference between the orbits multiplied by the number m of orbits is not equal to 360, it indicates that there is no inter-satellite link between them because the moving directions of the satellites in the two orbits are opposite.
8. An inter-satellite link construction system, characterized in that: the system comprises a track confirmation module (100), a same-track connection module (200), an abnormal-track connection module (300) and a track building module (400);
the orbit confirmation module (100) is used for determining the orbit type of the inter-satellite link to be constructed;
the co-orbit connection module (200) is used for executing the following steps on all satellites in each co-orbit inter-satellite link for each satellite orbit of the co-orbit inter-satellite link: starting from a first satellite in orbit, connecting a forward inter-satellite link port of the first satellite with a next satellite until the connection between the last satellite in the current orbit and a forward inter-satellite link port of the last satellite in the previous orbit is completed;
the different-orbit connection module (300) is used for connecting the right-direction inter-satellite link port of a first satellite to the adjacent first satellite of a second orbit and connecting the left-direction inter-satellite link of the second orbit to the first satellite of the first orbit from the first satellite of the first orbit for all the satellites of all the orbits of different-orbit inter-satellite links until the connection of all the satellites of all the different-orbit orbits is completed;
the track building module (400) is used for completing inter-satellite link building according to the building process of the inter-same-orbit satellite link and the inter-different-orbit satellite link, has a storage function, and is used for achieving the storage effect of the inter-satellite link.
9. The inter-satellite link construction system according to claim 8, characterized in that: the track type in the track confirmation module (100) comprises same track and different track.
10. The inter-satellite link construction system according to claim 8 or 9, characterized in that: the track building module (400) can also store track data and has a storage medium storage program besides carrying out track building work.
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Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4461260B2 (en) * | 2004-02-27 | 2010-05-12 | 独立行政法人情報通信研究機構 | Manhattan Street Network Configuration Method Using Low Orbit Satellites |
| CN105471493A (en) * | 2015-11-17 | 2016-04-06 | 北京邮电大学 | Multi-measure routing method applicable to double-layer satellite network |
| CN106656302A (en) * | 2016-09-22 | 2017-05-10 | 南京理工大学 | Distributed node self-adaptive routing algorithm for LEO satellite network |
| CN107257261A (en) * | 2017-05-18 | 2017-10-17 | 中国科学院计算技术研究所 | A kind of dynamic link dispatching method for 6TiSCH multi-hop wireless networks |
| CN107634793A (en) * | 2017-09-29 | 2018-01-26 | 北京空间飞行器总体设计部 | A kind of LEO/MEO double layer minipellets low overhead flooding method and satellite node |
| CN110493791A (en) * | 2019-07-26 | 2019-11-22 | 中国电子科技集团公司第三十八研究所 | Empty Incorporate network architecture and design method based near space platform |
| CN111182583A (en) * | 2020-01-05 | 2020-05-19 | 西安电子科技大学 | Task delay constraint-oriented low-orbit satellite data transmission method |
| WO2020119494A1 (en) * | 2018-12-14 | 2020-06-18 | 华为技术有限公司 | Satellite network communication method, related apparatus, and system |
| CN111522037A (en) * | 2020-04-30 | 2020-08-11 | 中国科学院微小卫星创新研究院 | Autonomous navigation method and navigation system for constellation co-orbital plane satellite |
| CN111953512A (en) * | 2020-07-02 | 2020-11-17 | 西安电子科技大学 | Construction method, system and application of Mobius constellation topology configuration facing Walker constellation |
| CN112054852A (en) * | 2020-08-11 | 2020-12-08 | 如般量子科技有限公司 | Sky-ground integrated quantum communication system based on satellite |
| CN112152695A (en) * | 2019-06-27 | 2020-12-29 | 千寻位置网络有限公司 | Low-orbit satellite constellation measuring, operation and control system and method thereof |
| CN113055076A (en) * | 2021-03-09 | 2021-06-29 | 东南大学 | Routing method in LEO/MEO double-layer satellite communication network |
| CN113676242A (en) * | 2021-08-06 | 2021-11-19 | 成都天奥集团有限公司 | Control method for constellation satellite-borne network equipment |
| CN114423058A (en) * | 2021-12-22 | 2022-04-29 | 网络通信与安全紫金山实验室 | Satellite topology separation route forwarding method, device, equipment and storage medium |
| CN114422009A (en) * | 2021-12-15 | 2022-04-29 | 中国人民解放军国防科技大学 | Two-dimensional annular self-organizing inter-satellite link channel access control method |
| CN114640619A (en) * | 2022-05-18 | 2022-06-17 | 鹏城实验室 | Low-earth-orbit satellite network topology planning method based on laser communication and related equipment |
| CN114666865A (en) * | 2022-03-17 | 2022-06-24 | 国网上海市电力公司 | Communication method, device and equipment of low-earth-orbit satellite and readable storage medium |
| CN114710193A (en) * | 2022-03-15 | 2022-07-05 | 中国移动通信有限公司研究院 | Satellite-to-ground link processing method and device and network equipment |
| CN114928869A (en) * | 2022-04-22 | 2022-08-19 | 清华大学 | Satellite-ground cooperative global content distribution routing method, system and electronic equipment |
| CN115225135A (en) * | 2021-04-20 | 2022-10-21 | 大唐移动通信设备有限公司 | Signal transmission method and device and readable storage medium |
| CN115297045A (en) * | 2022-05-10 | 2022-11-04 | 北京邮电大学 | Flooding topology construction method and device for low-earth-orbit satellite network and storage medium |
-
2022
- 2022-11-17 CN CN202211440243.8A patent/CN115776329A/en active Pending
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4461260B2 (en) * | 2004-02-27 | 2010-05-12 | 独立行政法人情報通信研究機構 | Manhattan Street Network Configuration Method Using Low Orbit Satellites |
| CN105471493A (en) * | 2015-11-17 | 2016-04-06 | 北京邮电大学 | Multi-measure routing method applicable to double-layer satellite network |
| CN106656302A (en) * | 2016-09-22 | 2017-05-10 | 南京理工大学 | Distributed node self-adaptive routing algorithm for LEO satellite network |
| CN107257261A (en) * | 2017-05-18 | 2017-10-17 | 中国科学院计算技术研究所 | A kind of dynamic link dispatching method for 6TiSCH multi-hop wireless networks |
| CN107634793A (en) * | 2017-09-29 | 2018-01-26 | 北京空间飞行器总体设计部 | A kind of LEO/MEO double layer minipellets low overhead flooding method and satellite node |
| WO2020119494A1 (en) * | 2018-12-14 | 2020-06-18 | 华为技术有限公司 | Satellite network communication method, related apparatus, and system |
| CN112152695A (en) * | 2019-06-27 | 2020-12-29 | 千寻位置网络有限公司 | Low-orbit satellite constellation measuring, operation and control system and method thereof |
| CN110493791A (en) * | 2019-07-26 | 2019-11-22 | 中国电子科技集团公司第三十八研究所 | Empty Incorporate network architecture and design method based near space platform |
| CN111182583A (en) * | 2020-01-05 | 2020-05-19 | 西安电子科技大学 | Task delay constraint-oriented low-orbit satellite data transmission method |
| CN111522037A (en) * | 2020-04-30 | 2020-08-11 | 中国科学院微小卫星创新研究院 | Autonomous navigation method and navigation system for constellation co-orbital plane satellite |
| CN111953512A (en) * | 2020-07-02 | 2020-11-17 | 西安电子科技大学 | Construction method, system and application of Mobius constellation topology configuration facing Walker constellation |
| CN112054852A (en) * | 2020-08-11 | 2020-12-08 | 如般量子科技有限公司 | Sky-ground integrated quantum communication system based on satellite |
| CN113055076A (en) * | 2021-03-09 | 2021-06-29 | 东南大学 | Routing method in LEO/MEO double-layer satellite communication network |
| CN115225135A (en) * | 2021-04-20 | 2022-10-21 | 大唐移动通信设备有限公司 | Signal transmission method and device and readable storage medium |
| CN113676242A (en) * | 2021-08-06 | 2021-11-19 | 成都天奥集团有限公司 | Control method for constellation satellite-borne network equipment |
| CN114422009A (en) * | 2021-12-15 | 2022-04-29 | 中国人民解放军国防科技大学 | Two-dimensional annular self-organizing inter-satellite link channel access control method |
| CN114423058A (en) * | 2021-12-22 | 2022-04-29 | 网络通信与安全紫金山实验室 | Satellite topology separation route forwarding method, device, equipment and storage medium |
| CN114710193A (en) * | 2022-03-15 | 2022-07-05 | 中国移动通信有限公司研究院 | Satellite-to-ground link processing method and device and network equipment |
| CN114666865A (en) * | 2022-03-17 | 2022-06-24 | 国网上海市电力公司 | Communication method, device and equipment of low-earth-orbit satellite and readable storage medium |
| CN114928869A (en) * | 2022-04-22 | 2022-08-19 | 清华大学 | Satellite-ground cooperative global content distribution routing method, system and electronic equipment |
| CN115297045A (en) * | 2022-05-10 | 2022-11-04 | 北京邮电大学 | Flooding topology construction method and device for low-earth-orbit satellite network and storage medium |
| CN114640619A (en) * | 2022-05-18 | 2022-06-17 | 鹏城实验室 | Low-earth-orbit satellite network topology planning method based on laser communication and related equipment |
Non-Patent Citations (4)
| Title |
|---|
| SHUKUN LI: "Load-Balanced Cooperative Transmission in MEO-LEO Satellite Network", 《2018 IEEE 32ND INTERNATIONAL CONFERENCE ON ADVANCED INFORMATION NETWORKING AND APPLICATIONS (AINA)》, 13 August 2018 (2018-08-13) * |
| 仉陈: "大规模低轨卫星组网方法与性能评估", 《中国优秀硕士学位论文全文数据库-信息科技辑》, 15 May 2022 (2022-05-15) * |
| 刘飞: "一种异轨等高MEO 卫星的建链模式设计方法", 《航天器工程》, 6 May 2022 (2022-05-06) * |
| 郭丽荣: "低轨道卫星星座的拓扑结构设计", 《中国优秀硕士学位论文全文数据库-信息科技辑》, 15 March 2022 (2022-03-15) * |
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