CN116112061A - Space routing method, device and storage medium based on solar avoidance - Google Patents
Space routing method, device and storage medium based on solar avoidance Download PDFInfo
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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
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L45/00—Routing or path finding of packets in data switching networks
- H04L45/02—Topology update or discovery
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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
Abstract
The invention discloses a space routing method, a device and a storage medium based on a solar energy evasion, which are used for solving the technical problem that space routing cannot be effectively and conveniently carried out when solar energy occurs, and comprise the following steps: receiving user data; acquiring an inter-satellite link topology matrix corresponding to a time period at the current moment from a plurality of inter-satellite routing topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in the low-orbit constellation in a corresponding time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar-energy-avoiding angle in the corresponding time period, and the solar-energy-avoiding angle is used for representing a critical angle of solar energy causing inter-satellite link interruption; determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix; the user data is transmitted to the next low-orbit satellite by the route forwarding path.
Description
Technical Field
The present invention relates to the field of satellite communications, and in particular, to a space routing method, apparatus and storage medium based on a solar cell evasion.
Background
With the development of laser communication technology, laser inter-satellite communication is becoming a main means of satellite constellation inter-satellite communication.
The ultra-large capacity communication rate of laser communication has a very strong advantage compared to microwave communication. However, during operation of large satellite constellations, solar interference occurs when the angle between sunlight and the laser communication beam is within a certain range.
In the prior art, when the phenomenon of solar interference occurs, common treatment measures of a laser terminal are as follows: turning off the laser communication terminal or making a pointing evasion, all of which cause interruption of the inter-satellite communication link. Generally, the inter-satellite communication link interruption caused by the solar cell is regular and continuous, which brings continuous dynamic topology change to the space networking, if the topology node table of the space networking is not updated again, the problem of frequent rerouting due to the actual communication link interruption will occur when the routing path selection is performed, otherwise, a great amount of packet loss will occur. If a link monitoring static routing strategy is adopted, the problem of frequently starting backup paths exists; frequent path recalculation problems may also occur if local dynamic routing policies are employed. Since the interference of the solar is concentrated and sustained for a certain period of time, therefore, whether static routing or adopting a locally dynamic and dynamic combined routing strategy, the problem of influence of dynamic change of network topology on the route cannot be effectively and conveniently solved.
In view of this, how to effectively and conveniently perform space routing when the solar cell is in a solar cell is a technical problem to be solved.
Disclosure of Invention
The invention provides a space routing method based on a solar cell evasion, which is used for solving the technical problem that space routing cannot be effectively and conveniently carried out when solar cell evasion occurs in the prior art.
In order to solve the above technical problems, a space routing device based on a solar-based avoidance provided by an embodiment of the present invention is applied to a satellite, and the technical scheme of the space routing method is as follows:
receiving user data;
acquiring an inter-satellite link topology matrix corresponding to a time period at the current moment from a plurality of inter-satellite routing topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in a low-orbit constellation in a corresponding time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar-energy-avoiding angle in the corresponding time period, and the solar-energy-avoiding angle is used for representing a critical angle of solar energy causing the inter-satellite link to break;
determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
and transmitting the user data to the next low-orbit satellite according to the route forwarding path.
An implementation manner, a determining manner of an inter-satellite link topology matrix corresponding to a time period, includes:
determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in the time period to obtain a first included angle matrix;
and establishing an inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar-control evasion angle.
In one implementation, determining a first included angle between sunlight and a laser beam emitted by each low-orbit satellite in the time period to obtain a first included angle matrix, including:
receiving a plurality of first included angle matrixes corresponding to a plurality of continuous time periods including the time period sent by a ground station;
and acquiring a first included angle matrix corresponding to the time period from a plurality of first included angle matrices corresponding to the continuous time periods.
In one implementation, determining a first included angle between sunlight and a laser beam emitted by each low-orbit satellite in the time period to obtain a first included angle matrix, including:
calculating an incident included angle between the sunlight and each low-orbit satellite along the running direction of the corresponding satellite orbit according to the satellite orbit in which each low-orbit satellite is positioned;
and converting the incident included angle corresponding to each satellite into a first included angle between the sunlight and the laser beams emitted by each satellite, and obtaining the first included angle matrix.
In one implementation manner, establishing an inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar control avoidance angle, including:
judging whether each first included angle in the first included angle matrix is larger than the solar control avoidance angle;
if the first included angle in the first included angle matrix is larger than the Rabdosia avoidance angle, setting the corresponding inter-satellite link state as an interruption state;
or if the first included angle in the first included angle matrix is smaller than or equal to the solar energy evasion angle, setting the corresponding inter-satellite link state as a connection state;
and constructing inter-satellite link states corresponding to all the first included angles into the inter-satellite link topology matrix.
An implementation, setting a corresponding inter-satellite link state to a connected state, comprising:
performing weighted calculation on the connection state to obtain a weighted connection state; the weighted value in the weighted calculation is used for representing the load capacity of the corresponding satellite link.
An implementation of transmitting the user data to a next low-orbit satellite according to the route forwarding path, comprising:
acquiring an original route forwarding table corresponding to the user data;
modifying the original route forwarding table according to the route forwarding path to obtain a route forwarding table;
and transmitting the user data to the next low-orbit satellite according to the routing forwarding table.
In one implementation, the time period is the minimum time interval between any inter-satellite link in the low-orbit constellation changing from a state of a solar break to a state of a connection or from the state of the connection to the state of the solar break.
In one implementation, the minimum time interval further includes a guard time interval.
In a second aspect, an embodiment of the present invention provides a space routing device based on a solar-based avoidance, applied to a satellite, where the space routing device includes:
a receiving unit configured to receive user data;
the acquisition unit is used for acquiring an inter-satellite link topology matrix corresponding to the time period of the current moment from a plurality of inter-satellite route topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in a low-orbit constellation in a time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar-energy avoiding angle in a corresponding time period, and the solar-energy avoiding angle is used for representing a critical angle of solar energy causing the inter-satellite link to break;
the determining unit is used for determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
and the transmission unit is used for transmitting the user data to the next low-orbit satellite according to the route forwarding path.
In one implementation, the obtaining unit is further configured to:
determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in a time period, and obtaining a first included angle matrix;
and establishing an inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar-control evasion angle.
In one implementation, the obtaining unit is further configured to:
receiving a plurality of first included angle matrixes corresponding to a plurality of continuous time periods including the time period sent by a ground station;
and acquiring a first included angle matrix corresponding to the time period from a plurality of first included angle matrices corresponding to the continuous time periods.
In one implementation, the obtaining unit is further configured to:
calculating an incident included angle between the sunlight and each low-orbit satellite along the running direction of the corresponding satellite orbit according to the satellite orbit in which each low-orbit satellite is positioned;
and converting the incident included angle corresponding to each satellite into a first included angle between the sunlight and the laser beams emitted by each satellite, and obtaining the first included angle matrix.
In one implementation, the obtaining unit is further configured to:
judging whether each first included angle in the first included angle matrix is larger than the solar control avoidance angle;
if the first included angle in the first included angle matrix is larger than the Rabdosia avoidance angle, setting the corresponding inter-satellite link state as an interruption state;
or if the first included angle in the first included angle matrix is smaller than or equal to the solar energy evasion angle, setting the corresponding inter-satellite link state as a connection state;
and constructing inter-satellite link states corresponding to all the first included angles into the inter-satellite link topology matrix.
In one implementation, the obtaining unit is further configured to:
performing weighted calculation on the connection state to obtain a weighted connection state; the weighted value in the weighted calculation is used for representing the load capacity of the corresponding satellite link.
An implementation, the transmission unit is further configured to include:
acquiring an original route forwarding table corresponding to the user data;
modifying the original route forwarding table according to the route forwarding path to obtain a route forwarding table;
and transmitting the user data to the next low-orbit satellite according to the routing forwarding table.
In one implementation, the time period is the minimum time interval between any inter-satellite link in the low-orbit constellation changing from a state of a solar break to a state of a connection or from the state of the connection to the state of the solar break.
In one implementation, the minimum time interval further includes a guard time interval.
In a third aspect, an embodiment of the present invention further provides a space routing device based on a solar avoidance, including:
at least one processor, and
a memory coupled to the at least one processor;
wherein the memory stores instructions executable by the at least one processor, the at least one processor performing the method of the first aspect described above by executing the instructions stored by the memory.
In a fourth aspect, an embodiment of the present invention further provides a readable storage medium, including:
the memory device is used for storing the data,
the memory is configured to store instructions that, when executed by the processor, cause an apparatus comprising the readable storage medium to perform the method as described in the first aspect above.
Through the technical scheme in the one or more embodiments of the present invention, the embodiments of the present invention have at least the following technical effects:
in the embodiment provided by the invention, after receiving user data, an inter-satellite link topology matrix corresponding to a time period at the current moment is obtained from a plurality of inter-satellite route topology matrices; determining a route forwarding path for transmitting the user data to the target satellite according to the inter-satellite link topology matrix; changing a routing forwarding table according to a routing forwarding path, and transmitting the user data to the next low-orbit satellite; wherein elements in the inter-satellite link topology matrix are used to characterize inter-satellite link states between adjacent pairs of low-orbit satellites in the low-orbit constellation during a corresponding one of the time periods, the inter-satellite link state is related to the included angle between the laser beams of a pair of low-orbit satellites and sunlight and the solar avoidance angle, which is used for representing the critical angle of the solar caused inter-satellite link interruption. The method can effectively avoid frequent switching and repeated calculation of static routes and local dynamic routes which are not specifically designed by the center of the prior art, and improves the working efficiency of space routes when the solar heat occurs.
Drawings
Fig. 1 is a flowchart of a space routing method based on a solar avoidance according to an embodiment of the present invention;
FIG. 2 is a schematic diagram illustrating operation of a low-orbit satellite according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a state of an inter-satellite link according to an embodiment of the present invention;
fig. 4 is a schematic diagram of user data transmission according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a space routing device based on a solar avoidance according to an embodiment of the present invention.
Detailed Description
The embodiment of the invention provides a space routing method based on a solar cell evasion, which is used for solving the technical problem that space routing cannot be effectively and conveniently carried out when solar cell occurs in the prior art.
In order to better understand the above technical solutions, the following detailed description of the technical solutions of the present invention is made by using the accompanying drawings and specific embodiments, and it should be understood that the specific features of the embodiments and the embodiments of the present invention are detailed descriptions of the technical solutions of the present invention, and not limiting the technical solutions of the present invention, and the technical features of the embodiments and the embodiments of the present invention may be combined with each other without conflict.
Referring to fig. 1, an embodiment of the present invention provides a space routing method based on a solar-based avoidance, which is applied to satellites, and the processing procedure of the method is as follows.
Step 101: receiving user data;
in the embodiment provided by the invention, the satellite is a low-orbit satellite currently receiving the user data in the low-orbit constellation, and can be a source satellite or any low-orbit satellite through which the source satellite transmits the user data to a target satellite, and the low-orbit satellite receives the user data. The source satellite is a low-orbit satellite for receiving user application in a low-orbit constellation, and the target satellite is a final low-orbit satellite which needs to be reached by user data.
Step 102: acquiring an inter-satellite link topology matrix corresponding to a time period at the current moment from a plurality of inter-satellite routing topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in the low-orbit constellation in a corresponding time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar avoidance angle in the corresponding time period, and the solar avoidance angle is used for representing a critical angle of solar caused inter-satellite link interruption.
In the embodiment provided by the invention, the determining mode of the inter-satellite link topology matrix corresponding to one time period comprises the following steps:
determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in a time period to obtain a first included angle matrix; and establishing an inter-satellite link topology matrix of the low-orbit constellation in a time period according to the magnitude relation between the first included angle in the first included angle matrix and the Rabdosia avoiding angle.
Determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in a time period to obtain a first included angle matrix, wherein the first included angle matrix can be realized by the following two modes:
firstly, calculating an incident included angle between sunlight and each low-orbit satellite along the running direction of the corresponding satellite orbit according to the satellite orbit in which each low-orbit satellite is positioned; and converting the incident included angle corresponding to each satellite into a first included angle between sunlight and laser beams emitted by each satellite, and obtaining a first included angle matrix.
Fig. 2 is a schematic diagram of a low-orbit satellite according to an embodiment of the invention. The satellite orbit of a low-orbit satellite in an ideal case has the following characteristics: when the running orbit is a circular orbit, a fixed configuration relation exists between the running orbit and the earth equator, and the running orbit is represented by six orbit numbers.
The satellite orbit of the low-orbit satellite in the presence of the influence of the perturbation has the following characteristics: under the influence of the gravitational field of the earth and the space environment perturbation force, the practical running orbit number presents the oscillation drift phenomena of long term, short term, long period and short period. The earth gravitational field distribution function changes along with latitude and longitude, and the satellite orbit surface slowly precesses under the influence of the perturbation force mainly comprising the earth non-spherical gravitational force J2 term and under the earth center inertial coordinate system.
By utilizing the characteristics of the satellite orbit of the low-orbit satellite, the incident angle between the incident direction O 'N of sunlight and the direction of the low-orbit satellite along the orbit running direction (O' M) can be calculated, the first included angle between the laser terminal beam center of the low-orbit satellite and the laser beam (marked as theta) can be determined by converting the earth center inertial coordinate system with the earth fixed coordinate system, the earth fixed coordinate system with the satellite celestial coordinate system and the coordinate system of a laser terminal mounted on the low-orbit satellite, and converting the incident angle between the incident direction O 'N of sunlight and the direction of the low-orbit satellite along the orbit running direction (O' M) into the included angle between the sunlight and the mounting axis of the laser terminal emitted by the low-orbit satellite (marked as alpha), and the included angle between the laser terminal beam center of the low-orbit satellite and the mounting axis of the laser terminal is a fixed angle (marked as beta). In order to simplify the calculation, the coordinate system conversion process can be realized by setting a conversion matrix, so that the calculation amount of satellites can be reduced, and the processing speed can be improved.
Because the low orbit satellites included in the constellation are numerous, the satellite can consume more time to calculate the first included angle matrix by itself, so that the ground station can calculate the first included angle matrix corresponding to each time period and then transmit the calculation result to the satellite, the ground station can transmit the calculated first included angle matrix corresponding to a plurality of continuous time periods to the satellite together, and the satellite only needs to select the needed first included angle matrix for use, thereby the second scheme provided by the invention is recorded.
The second type of the first angle matrixes corresponding to a plurality of continuous time periods including the time period and sent by the ground station are received; and acquiring a first included angle matrix corresponding to the time period from a plurality of first included angle matrixes corresponding to a plurality of continuous time periods.
After the first included angle matrix is obtained, an inter-satellite link topology matrix of the low-orbit constellation in a time period can be established according to the magnitude relation between the first included angle in the first included angle matrix and the solar control avoidance angle, and the inter-satellite link topology matrix can be specifically realized by the following modes:
judging whether each first included angle in the first included angle matrix is larger than a solar-control avoiding angle; if the first included angle in the first included angle matrix is larger than the Rabdosia avoiding angle, setting the corresponding inter-satellite link state as an interruption state; or if the first included angle in the first included angle matrix is smaller than or equal to the solar avoidance angle, setting the corresponding inter-satellite link state as a connection state; and constructing the inter-satellite link states corresponding to all the first included angles into an inter-satellite link topology matrix.
For example, the Rabdosia avoidance angle is noted as beta c The first angle matrix is marked as theta, and the elements in the first angle matrix are marked as theta ij-mn A first included angle between the laser beam and sunlight between the low-orbit satellite ij and the low-orbit satellite mn is represented, and theta is judged ij-mn Whether or not to be less than beta c If theta ij-mn <β c Inter-satellite link state (denoted as T) between low-orbit satellite ij and low-orbit satellite mn ij-mn ) Is set to an interrupt state (if the interrupt state is denoted by 0, T ij-mn ＝0)，θ ij-mn ≥β c Inter-satellite link state (T) between low-orbit satellite ij and low-orbit satellite mn ij-mn ) Is set to a connected state (if the connected state is denoted by 1, T ij-mn ＝1)。
In some embodiments, setting the corresponding inter-satellite link state to the connected state may also be achieved by:
performing weighted calculation on the connection state to obtain a weighted connection state; the weighted value in the weighted calculation is used for representing the load capacity of the corresponding satellite link.
For example, when the inter-satellite links are in a connection state, in order to further distinguish the inter-satellite links with different load amounts, a weight value (denoted by a) can be set for the inter-satellite links, so that the inter-satellite links with the connection state can be denoted by non-zero values, and when the route forwarding paths are determined subsequently, the paths with lower load amounts can be selected as the route forwarding paths in combination with the load conditions of the inter-satellite links, thereby improving the data forwarding efficiency and avoiding congestion.
Fig. 3 is a schematic diagram of a state of an inter-satellite link according to an embodiment of the present invention. FIG. 3 shows a portion of low-orbit satellites (S11-S33) in the constellation, S11 and S21 are adjacent satellites, S11 and S12 are also adjacent satellites, and the inter-satellite link between S11 and S12 is denoted as T 11-12 (representing the inter-satellite link that S11 signals to S12), T 12-11 (indicating the inter-satellite link that S12 signals to S11). If the first angle theta between the laser beam and the sunlight between S11 and S12 11-12 、θ 12-11 <Beta c is T 11-12 、T 12-11 In the interrupted state, if the first angle θ between the laser beam and the sunlight between S11 and S21 11-21 、θ 21-11 >Beta c is T 11-21 、T 21-11 For the connected state, assume that T is now 11-21 The corresponding weight of the load quantity of the (a) is a 1 ，T 21-11 The loading of (a) is corresponding to weight a 2 T is then 11-12 ＝a 1 、T 21-11 ＝a 2 . The state of other inter-satellite links is set in a similar manner and will not be described in detail.
By the method, the inter-satellite link topology matrix corresponding to each time period can be determined.
In some embodiments, the time period is the minimum time interval for any inter-satellite link in the low-rail constellation to change from a Rabdosia-off state to a connected state or from a connected state to a Rabdosia-off state.
In other embodiments, the minimum time interval further comprises a guard time interval.
For example, the time period is Δt, and the time period may be a time interval when any inter-satellite link in the low-orbit constellation changes from a state of a solar break to a state of a connection, or may be a minimum time interval when any inter-satellite link in the low-orbit constellation changes from a state of a connection to a state of a solar break.
For example, in order to prevent packet loss caused by the asynchronization of the state of the inter-satellite link and the network state during the transmission process of the user data, the minimum time interval may include a guard time interval, that is, a time period may be the sum of the guard time interval and the time interval of any inter-satellite link in the low-track constellation from the state of the rabi interrupt to the connection state, or the sum of the guard time interval and the minimum time interval of any inter-satellite link in the low-track constellation from the state of the connection to the state of the rabi interrupt.
When the inter-satellite link state is changed from the connection state to the interrupt state, user data can be started to be transmitted in advance of Deltaρ when data are transmitted; when the inter-satellite link state is changed from the interrupted state to the connected state, the transmission of user data may be started with a delay Δρ when transmitting data. Δρ is the minimum time interval, so that the packet loss of user data due to the inter-satellite link state change can be prevented, and the reliability of data transmission is improved.
Each low-orbit satellite in the low-orbit constellation stores a plurality of inter-satellite routing topology matrices, which are in one-to-one correspondence with a plurality of consecutive time periods, one of which contains the current time.
After the satellite receives the user data, the inter-satellite link topology matrix corresponding to the time period including the current moment is obtained from the plurality of inter-satellite route topology matrices stored locally, and the route forwarding path for transmitting the user data to the target satellite can be determined therefrom, namely, steps 103-104 are executed.
Step 103: determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
step 104: the user data is transmitted to the next low-orbit satellite by the route forwarding path.
In determining the route forwarding path of the user data transmitted from the satellite to the target satellite, the route forwarding path may be determined by a minimum path method (i.e. the shortest path from the satellite to the target satellite), a minimum load method (i.e. the minimum load amount of the path from the satellite to the target satellite) or other algorithm, and the specific algorithm is not limited herein.
Taking fig. 3 as an example, the satellite is S11, the target satellite is S23, and T is in the inter-satellite link topology matrix corresponding to the time period in which the current moment is located 22-32 、T 32-22 、T 31-32 、T 32-31 、T 32-33 、T 33-32 All are in a terminal state, and the rest inter-star links are in a connection state. If the minimum path method is adopted, it can be determined that the route forwarding path can be s11→s12→s13→s23→s33, or s11→s12→s22→s23→s33, or s11→s21→s22→s23→s33, and further, one with the smallest load capacity can be selected from the several route forwarding paths as the route forwarding path for the end use (assumed as s11→s12→s22→s23→s33), the satellite can modify the route forwarding table of the user data according to the route forwarding path which is finally selected, and transmit the user data to the next low orbit satellite (S12). When the low-orbit satellite S12 receives the user data, the low-orbit satellite S12 is regarded as a satellite, and the steps S101 to S104 are repeated.
Fig. 4 is a schematic diagram of user data transmission according to an embodiment of the present invention. The method comprises the steps that inter-satellite link topology matrixes corresponding to time periods from t0 to tn are stored in satellites, the time period is delta t, each inter-satellite link topology matrix is affected by load capacity of the corresponding time period (congestion estimation is carried out according to historical load conditions) and time, for example, the inter-satellite link topology matrix at t0 is affected by the congestion estimation at t0 and the time of day of the time of t0, the time of t congestion estimation is the load capacity estimated according to the historical load conditions of the time period corresponding to the time of t0, corresponding weight can be determined according to the congestion estimation, the time of t0 is affected by day of the time of day, namely whether time of day occurs in the time period corresponding to the time of t0, after user data are received by the satellites, the inter-satellite link topology matrix at the current time is determined from the time of t0 to tn (the time period corresponding to the time of t2 is assumed), route forwarding paths are determined from the inter-satellite link topology matrix at the time of t2, route forwarding paths are modified according to the route forwarding paths, and the user data are published to the next low orbit satellites according to route forwarding.
In some embodiments, transmitting user data to the next low-orbit satellite on a routed forwarding path may be accomplished by:
acquiring an original route forwarding table corresponding to user data; modifying an original route forwarding table according to the route forwarding path to obtain the route forwarding table; and transmitting the user data to the next low-orbit satellite according to the routing forwarding table.
For example, when user data is acquired, an original route forwarding table corresponding to the user data is also acquired, and because the satellite determines a route forwarding path for the satellite to reach the target satellite according to the inter-satellite link topology matrix, the original route forwarding table needs to be modified according to the route forwarding path to obtain a new route forwarding table, and then the user data is transmitted to the next low-orbit satellite according to the new route forwarding table.
In the embodiment provided by the invention, after receiving user data, an inter-satellite link topology matrix corresponding to a time period at the current moment is obtained from a plurality of inter-satellite route topology matrices; determining a route forwarding path for transmitting the user data to the target satellite according to the inter-satellite link topology matrix; changing a routing forwarding table according to a routing forwarding path, and transmitting the user data to the next low-orbit satellite; wherein elements in the inter-satellite link topology matrix are used to characterize inter-satellite link states between adjacent pairs of low-orbit satellites in the low-orbit constellation during a corresponding one of the time periods, the inter-satellite link state is related to the included angle between the laser beams of a pair of low-orbit satellites and sunlight and the solar avoidance angle, which is used for representing the critical angle of the solar caused inter-satellite link interruption. The method can effectively avoid frequent switching and repeated calculation of static routes and local dynamic routes which are not specifically designed by the center of the prior art, and improves the working efficiency of space routes when the solar heat occurs.
Based on the same inventive concept, in an embodiment of the present invention, a space routing device based on a solar energy avoidance is provided, and the space routing device is applied to a satellite, and a specific implementation of a space routing method based on a solar energy avoidance of the space routing device can be referred to the description of the embodiment of the method, and the repetition is omitted, and referring to fig. 5, the space routing device includes:
a receiving unit 501 for receiving user data;
an obtaining unit 502, configured to obtain an inter-star link topology matrix corresponding to a time period in which the current moment is located from a plurality of inter-star route topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in a low-orbit constellation in a time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar-energy avoiding angle in a corresponding time period, and the solar-energy avoiding angle is used for representing an angle range of solar energy causing the inter-satellite link to break;
a determining unit 503, configured to determine a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
a transmission unit 504, configured to transmit the user data to a next low-orbit satellite according to the route forwarding path.
In one implementation, the obtaining unit 502 is further configured to:
determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in a time period, and obtaining a first included angle matrix;
and establishing an inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar-control evasion angle.
In one implementation, the obtaining unit 502 is further configured to:
receiving a plurality of first included angle matrixes corresponding to a plurality of continuous time periods including the time period sent by a ground station;
and acquiring a first included angle matrix corresponding to the time period from a plurality of first included angle matrices corresponding to the continuous time periods.
In one implementation, the obtaining unit 502 is further configured to:
calculating an incident included angle between the sunlight and each low-orbit satellite along the running direction of the corresponding satellite orbit according to the satellite orbit in which each low-orbit satellite is positioned;
and converting the incident included angle corresponding to each satellite into a first included angle between the sunlight and the laser beams emitted by each satellite, and obtaining the first included angle matrix.
In one implementation, the obtaining unit 502 is further configured to:
judging whether each first included angle in the first included angle matrix is larger than the solar control avoidance angle;
if the first included angle in the first included angle matrix is larger than the Rabdosia avoidance angle, setting the corresponding inter-satellite link state as an interruption state;
or if the first included angle in the first included angle matrix is smaller than or equal to the solar energy evasion angle, setting the corresponding inter-satellite link state as a connection state;
and constructing inter-satellite link states corresponding to all the first included angles into the inter-satellite link topology matrix.
In one implementation, the obtaining unit 502 is further configured to:
performing weighted calculation on the connection state to obtain a weighted connection state; the weighted value in the weighted calculation is used for representing the load capacity of the corresponding satellite link.
In one implementation, the time period is the minimum time interval between any inter-satellite link in the low-orbit constellation changing from a state of a solar break to a state of a connection or from the state of the connection to the state of the solar break.
In one implementation, the minimum time interval further includes a guard time interval.
Based on the same inventive concept, the embodiment of the invention provides a space routing device based on a solar-based avoidance, which comprises: at least one processor, and
a memory coupled to the at least one processor;
wherein the memory stores instructions executable by the at least one processor, the at least one processor executing the space routing method based on the slush avoidance as described above by executing the instructions stored by the memory.
Based on the same inventive concept, an embodiment of the present invention also provides a readable storage medium, including:
the memory device is used for storing the data,
the memory is for storing instructions that, when executed by the processor, cause an apparatus comprising the readable storage medium to perform a method of spatial routing based on a slush avoidance as described above.
It will be appreciated by those skilled in the art that embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, embodiments of the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the invention may take the form of a computer program product on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) having computer-usable program code embodied therein.
Embodiments of the present invention are described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (12)
1. A space routing method based on a solar avoidance, applied to a satellite, comprising:
receiving user data;
acquiring an inter-satellite link topology matrix corresponding to a time period at the current moment from a plurality of inter-satellite routing topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in a low-orbit constellation in a corresponding time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar-energy-avoiding angle in the corresponding time period, and the solar-energy-avoiding angle is used for representing a critical angle of solar energy causing the inter-satellite link to break;
determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
and transmitting the user data to the next low-orbit satellite according to the route forwarding path.
2. The spatial routing method of claim 1, wherein the determining the inter-satellite link topology matrix corresponding to a time period comprises:
determining a first included angle between sunlight and laser beams emitted by each low-orbit satellite in the time period to obtain a first included angle matrix;
and establishing an inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar-control evasion angle.
3. The spatial routing method of claim 2, wherein determining a first angle between sunlight and each of the low-orbit satellite-transmitted laser beams over the time period, obtains a first angle matrix, comprising:
receiving a plurality of first included angle matrixes corresponding to a plurality of continuous time periods including the time period sent by a ground station;
and acquiring a first included angle matrix corresponding to the time period from a plurality of first included angle matrices corresponding to the continuous time periods.
4. The spatial routing method of claim 2, wherein determining a first angle between sunlight and each of the low-orbit satellite-transmitted laser beams over the time period, obtains a first angle matrix, comprising:
calculating an incident included angle between the sunlight and each low-orbit satellite along the running direction of the corresponding satellite orbit according to the satellite orbit in which each low-orbit satellite is positioned;
and converting the incident included angle corresponding to each satellite into a first included angle between the sunlight and the laser beams emitted by each satellite, and obtaining the first included angle matrix.
5. The spatial routing method as set forth in claim 2, wherein establishing the inter-satellite link topology matrix of the low-orbit constellation in the time period according to the magnitude relation between the first included angle in the first included angle matrix and the solar-control evasion angle includes:
judging whether each first included angle in the first included angle matrix is larger than the solar control avoidance angle;
if the first included angle in the first included angle matrix is larger than the Rabdosia avoidance angle, setting the corresponding inter-satellite link state as an interruption state;
or if the first included angle in the first included angle matrix is smaller than or equal to the solar energy evasion angle, setting the corresponding inter-satellite link state as a connection state;
and constructing inter-satellite link states corresponding to all the first included angles into the inter-satellite link topology matrix.
6. The spatial routing method of claim 5, wherein setting the corresponding inter-satellite link state to a connected state comprises:
performing weighted calculation on the connection state to obtain a weighted connection state; the weighted value in the weighted calculation is used for representing the load capacity of the corresponding satellite link.
7. The spatial routing method of any of claims 1-6, wherein transmitting the user data to a next low-orbit satellite along the route forwarding path comprises:
acquiring an original route forwarding table corresponding to the user data;
modifying the original route forwarding table according to the route forwarding path to obtain a route forwarding table;
and transmitting the user data to the next low-orbit satellite according to the routing forwarding table.
8. A space routing method according to any of claims 2-6, wherein the time period is the minimum time interval for any inter-satellite link in the low-rail constellation to change from a slush outage state to a connection state or from the connection state to the slush outage state.
9. The spatial routing method of claim 8, wherein the minimum time interval comprises a guard time interval.
10. A space routing device based on a slush avoidance, applied to a satellite, comprising:
a receiving unit configured to receive user data;
the acquisition unit is used for acquiring an inter-satellite link topology matrix corresponding to the time period of the current moment from a plurality of inter-satellite route topology matrices; the elements in the inter-satellite link topology matrix are used for representing inter-satellite link states between a pair of adjacent low-orbit satellites in a low-orbit constellation in a corresponding time period, the inter-satellite link states are related to included angles between laser beams of the pair of low-orbit satellites and sunlight and a solar avoidance angle in the corresponding time period, and the solar avoidance angle is used for representing a critical angle of solar avoidance causing the inter-satellite link to be interrupted;
the determining unit is used for determining a route forwarding path to a target satellite according to the inter-satellite link topology matrix;
and the transmission unit is used for transmitting the user data to the next low-orbit satellite according to the route forwarding path.
11. A space routing device based on a slush avoidance, comprising:
at least one processor, and
a memory coupled to the at least one processor;
wherein the memory stores instructions executable by the at least one processor, the at least one processor performing the method of any of claims 1-9 by executing the instructions stored by the memory.
12. A readable storage medium comprising a memory,
the memory is configured to store instructions that, when executed by a processor, cause an apparatus comprising the readable storage medium to perform the method of any of claims 1-9.
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| CN116633425A (en) * | 2023-07-25 | 2023-08-22 | 北京最终前沿深空科技有限公司 | Satellite communication interference prediction method, communication adjustment method, device and medium |
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| CN116633425A (en) * | 2023-07-25 | 2023-08-22 | 北京最终前沿深空科技有限公司 | Satellite communication interference prediction method, communication adjustment method, device and medium |
| CN116633425B (en) * | 2023-07-25 | 2023-10-03 | 北京最终前沿深空科技有限公司 | Satellite communication interference prediction method, communication adjustment method, device and medium |
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