CN114189276A - Satellite communication method, device, readable medium and electronic equipment - Google Patents
Satellite communication method, device, readable medium and electronic equipment Download PDFInfo
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- CN114189276A CN114189276A CN202111518957.1A CN202111518957A CN114189276A CN 114189276 A CN114189276 A CN 114189276A CN 202111518957 A CN202111518957 A CN 202111518957A CN 114189276 A CN114189276 A CN 114189276A
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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
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1007—Communications satellites
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18578—Satellite systems for providing broadband data service to individual earth stations
- H04B7/18584—Arrangements for data networking, i.e. for data packet routing, for congestion control
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Abstract
The invention discloses a satellite communication method, a satellite communication device, a readable medium and electronic equipment, wherein the satellite communication device comprises the following components: determining a target message of a first satellite; determining a second satellite corresponding to the target ground station at the current moment; according to a preset routing strategy, the target message is sent to the second satellite from the first satellite; to cause the second satellite to forward the target message to the target ground station; the first satellite and the second satellite are in a first satellite orbit; according to the method, the communication of the co-orbit satellites among the satellite groups is realized, the indirect ground-to-ground communication of the first satellite is completed based on the second satellite, the real-time ground-to-ground communication of any first satellite in the satellite groups is realized, the communication efficiency is relatively high, the communication mechanism is relatively stable, and the defect that the large-scale real-time ground-to-ground communication cannot be realized in the prior art is overcome.
Description
Technical Field
The present invention relates to the field of satellite technologies, and in particular, to a satellite communication method, an apparatus, a readable medium, and an electronic device.
Background
As is known, satellites travel in a fixed orbit around the earth after entering space, while ground stations capable of communicating with the satellites are located at fixed positions on the earth's surface. Based on the principle of linear propagation of electromagnetic waves, a satellite can communicate with a ground station only when the satellite passes through a certain range above the ground station. When the satellite falls below the horizon, communication cannot be performed.
That is, during the course of a satellite orbiting a week, only a certain period of time may be in communication with the ground. If the satellite needs real-time ground-to-ground communication at other times, the relay is realized by other satellites or other ground stations.
However, the communication method using other satellites or ground stations as relays is more similar to a temporary communication method, and often has the characteristics of incompleteness and low efficiency, and cannot meet the requirement of large-scale real-time ground communication.
Disclosure of Invention
The invention provides a satellite communication method, a satellite communication device, a readable medium and electronic equipment, which are used for realizing large-scale satellite-to-ground real-time communication.
In a first aspect, the present invention provides a satellite communication method, including:
determining a target message of a first satellite;
determining a second satellite corresponding to the target ground station at the current moment;
according to a preset routing strategy, the target message is sent to the second satellite from the first satellite; to cause the second satellite to forward the target message to the target ground station;
the first satellite and the second satellite are in a first satellite orbit.
Preferably, the method further comprises the following steps:
establishing a satellite group using at least two co-orbiting satellites of the first satellite orbit; two adjacent co-orbiting satellites in the satellite group are in communication connection;
determining a routing strategy of each co-orbiting satellite in the satellite group;
the co-orbiting satellites of the group of satellites include the first satellite and the second satellite.
Preferably, the communication connection between two adjacent co-orbiting satellites in the satellite group includes:
a laser link communication connection, or a microwave signal communication connection.
Preferably, the routing policy includes a routing table, and the routing table includes forwarding addresses corresponding to the co-orbiting satellites; according to a preset routing strategy, the step of sending the target message from the first satellite to the second satellite comprises the following steps:
and sequentially forwarding the target message from the first satellite to the second satellite according to the forwarding address.
Preferably, the routing policy comprises a path algorithm; the sending the target message from the first satellite to the second satellite according to a preset routing policy includes:
calculating a forwarding path from the first satellite to the second satellite according to the path algorithm and based on the relative position relationship of the first satellite and the second satellite in the satellite group;
transmitting the targeted message from the first satellite to the second satellite based on the forwarding path.
Preferably, the method further comprises the following steps:
determining a third satellite corresponding to the high-orbit relay satellite at the current moment;
according to a preset routing strategy, the target message is sent to the third satellite from the first satellite; to cause the third satellite to forward the target message to the high-orbit relay satellite;
and sending the target message to a fourth satellite in the second satellite orbit by utilizing the high-orbit relay satellite.
Preferably, the method further comprises the following steps:
transmitting, with the target ground station, the target message to a fifth satellite in a third satellite orbit.
In a second aspect, the present invention provides a satellite communication device, comprising:
a message determination module for determining a target message of a first satellite;
the second satellite determining module is used for determining a second satellite corresponding to the target ground station at the current moment;
the routing module is used for sending the target message to the second satellite from the first satellite according to a preset routing strategy; to cause the second satellite to forward the target message to the target ground station;
the first satellite and the second satellite are in a first satellite orbit.
In a third aspect, the present invention provides a readable medium comprising executable instructions, which when executed by a processor of an electronic device, cause the electronic device to perform the satellite communication method according to any one of the first aspect.
In a fourth aspect, the present invention provides an electronic device, including a processor and a memory storing execution instructions, wherein when the processor executes the execution instructions stored in the memory, the processor executes the satellite communication method according to any one of the first aspect.
The invention provides a satellite communication method, a satellite communication device, a readable medium and electronic equipment, which are used for realizing real-time ground communication of any first satellite in a satellite group through communication of all co-orbit satellites among the satellite group and indirect ground communication of the first satellite based on a second satellite, have relatively high communication efficiency and relatively stable communication mechanism and overcome the defect that the prior art cannot realize large-scale real-time ground communication.
Further effects of the above-mentioned unconventional preferred modes will be described below in conjunction with specific embodiments.
Drawings
In order to more clearly illustrate the embodiments or the prior art solutions of the present invention, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive labor.
Fig. 1 is a flowchart illustrating a satellite communication method according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a satellite group in a satellite communication method according to an embodiment of the present invention;
fig. 3 is a flowchart illustrating another satellite communication method according to an embodiment of the invention;
fig. 4 is a flowchart illustrating another satellite communication method according to an embodiment of the invention;
fig. 5 is a schematic diagram illustrating a relationship between a high-orbit relay satellite, a first satellite orbit, and a second satellite orbit in another satellite communication method according to an embodiment of the invention;
fig. 6 is a schematic structural diagram of a satellite communication device according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of an electronic device according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail and completely with reference to the following embodiments and accompanying drawings. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
During the course of a satellite orbiting a week, only a certain period of time may be in communication with the ground. If the satellite needs real-time ground-to-ground communication at other times, other satellites or other ground stations are used as relay equipment. However, this communication method using other satellites or ground stations as relays is more similar to a temporary communication method. That is, the relay device is only searched when needed for single use, which is inefficient. And the system is not formed, real-time communication can not be continuously carried out for a long time, and the requirement of large-scale real-time ground communication can not be met.
In view of the above, the present invention provides a satellite communication method. Referring to fig. 1, a specific embodiment of a satellite communication method according to the present invention is shown.
Since the satellites in the same orbit have a relatively stationary characteristic, in this embodiment, a satellite group is constructed in advance based on a plurality of satellites in the same orbit. That is, a satellite group is established by using at least two co-orbiting satellites in a specific first satellite orbit, and the satellite group is generally established based on a plurality of co-orbiting satellites so as to sufficiently cover the whole first satellite orbit. The co-orbiting satellite refers to any satellite operating in a first orbit, and generally belongs to a so-called low orbit satellite in the field of aerospace. In other words, the first satellite orbit generally belongs to a low orbit.
The satellite group is established, which means that two adjacent co-orbiting satellites in the satellite group have communication connection with each other, as shown in fig. 2. The circle shape in fig. 2 represents the first satellite orbit, the white circles represent satellites, the common satellites a to H in the figure represent 8 co-orbiting satellites, and the dotted lines represent the communication connections between adjacent satellites. Where satellite a, satellite B, and satellite C are 3 co-orbiting satellites in orbit with the first satellite. Satellite a and satellite C are both neighbors of satellite B. The satellites B establish communication connections with them, respectively.
The communication connection may be a laser link communication connection. That is, each of the in-orbit satellites may be equipped with a laser transmitter and a laser receiver. One satellite transmits a laser signal for communication by using a laser transmitter, and the adjacent co-orbiting satellite receives the laser signal by using a laser receiver, thereby realizing communication between the satellites. By analogy, since the communication connection between the satellites in the same orbit forms a closed loop, direct or indirect communication can be realized between any two satellites in fig. 2.
Alternatively, the communication connection may be a microwave signal communication connection. Namely, each in-orbit satellite can be provided with a microwave emitter and a microwave receiver. One satellite transmits a microwave signal for communication by using a microwave transmitter, and the adjacent co-orbiting satellite receives the microwave signal by using a microwave receiver
On the basis, the method comprises the following steps:
The first satellite may be any one of the satellites in the first satellite orbit described above. Referring to fig. 2, satellite a may be considered the first satellite. A target message is generated on the first satellite and is communicated to the ground based on the target message, that is, the target message is sent to a specific target ground station. If the first satellite is just above the target ground station at the current time, the two can easily communicate based on the prior art without redundancy.
However, in the scenario of the present embodiment, the first satellite has "fallen below the horizon" with respect to the target ground station at the present time, i.e., is not able to communicate directly with the target ground station. It is necessary to implement real-time ground communication by the method of the present embodiment.
And 102, determining a second satellite corresponding to the target ground station at the current moment.
At this time, the second satellite corresponding to the target ground station at the current moment can be determined according to the real-time position of each co-orbiting satellite in the satellite group. The second satellite is a satellite in the first satellite orbit that is currently within communication range of the target ground station. Referring to fig. 2, satellite C may be considered the second satellite. It is obvious that the targeted messages of the first bit line can be indirectly communicated to ground by means of the second satellite.
103, sending the target message from the first satellite to the second satellite according to a preset routing strategy; such that the second satellite forwards the target message to the target ground station.
In this embodiment, a routing policy is set in advance. The routing policy specifies the forwarding mechanism of the message between groups of satellites. In particular, the routing policy may include a routing table. The routing table has forwarding addresses corresponding to the co-orbiting satellites. That is, each co-orbiting satellite can determine from the routing table which adjacent co-orbiting satellite it is to forward the message to. Thereby forming a mechanism for the streaming of messages between the co-orbiting satellites. This manner of routing may be referred to as static routing, i.e., the routing table is typically kept unchanged. And according to the forwarding address, sequentially forwarding the target message from the first satellite, and finally forwarding the target message to the second satellite. The target message is then forwarded by the second satellite to the target ground station, thereby completing the ground-to-ground communication.
Taking fig. 2 as an example, assume that the forwarding address of satellite a is set in the routing table to be the address of satellite B, meaning that satellite a fixedly forwards the message to satellite B. Similarly, the forwarding address of satellite B is the address of satellite C, meaning that satellite B fixedly forwards the message to satellite C. By analogy, the direction of message flow in the satellite constellation may appear clockwise in fig. 2. In this embodiment, assume that the satellite a is a first satellite and the satellite C is a second satellite. The targeted message from the first satellite may be sent to the second satellite over the path a-B-C to enable the second satellite to complete the communication to earth. In other cases, if satellite D is the first satellite, the message targeted by the first satellite may be routed to the second satellite via D-E-F-G-H-A-B-C. Alternatively, it is also possible to set the forwarding address of satellite a to be the address of satellite H, the forwarding address of satellite B to be the address of satellite a, and so on in the routing table. I.e., the direction of message flow in the satellite constellation may appear counterclockwise in fig. 2. The targeted message for the first satellite (satellite a) may be sent to the second satellite over the path a-H-G-F-E-D-C.
Therefore, the method in the embodiment realizes the communication of each co-orbit satellite among the satellite groups, and realizes the ground communication based on the second satellite. Typically, at any time, at least one satellite in the satellite group is within communication range of the target ground station and can exist as a second satellite. And messages on one satellite in the satellite group can be forwarded to any other co-orbiting satellite through a routing strategy. This is equivalent to that the target message from any first satellite in the satellite group can be finally sent to the second satellite, so that all the satellites in the group can realize real-time ground-to-ground communication.
Moreover, the communication mechanism between satellites in this embodiment is fixed and persistent. The method can ensure communication at any time based on a stable mechanism, and has a non-temporary means and high efficiency.
In addition, in the embodiment, the laser signal or the microwave signal is adopted as a communication means between satellites, so that the power consumption is lower and the communication speed is higher compared with the traditional communication mode.
According to the technical scheme, the beneficial effects of the embodiment are as follows: through the communication of the co-orbit satellites among the satellite groups and the indirect ground-to-ground communication of the first satellite based on the second satellite, the real-time ground-to-ground communication of any first satellite in the satellite groups is realized, the communication efficiency is relatively high, the communication mechanism is relatively stable, and the defect that the large-scale real-time ground-to-ground communication cannot be realized in the prior art is overcome.
Fig. 1 shows only a basic embodiment of the method of the present invention, and based on this, certain optimization and expansion can be performed, and other preferred embodiments of the method can also be obtained.
Fig. 3 shows another embodiment of the satellite communication method according to the present invention. The present embodiment is further described on the basis of the foregoing embodiments. In this embodiment, the method includes the steps of:
And step 302, determining a second satellite corresponding to the target ground station at the current moment.
In this embodiment, steps 301 to 302 are consistent with the related steps in the embodiment shown in fig. 1, and will not be described repeatedly.
In the embodiment shown in fig. 1, a static routing based routing policy is illustrated. I.e. messages are circulated between the satellite groups according to a fixed path through the routing table. The above approach has the advantage of being simple and intuitive, requiring little effort. But has the disadvantage that many times the actual path of message forwarding is not the shortest path, resulting in relatively low efficiency.
For example, in one example described above, the direction of message flow in the constellation may appear clockwise in fig. 2, with satellite D being the first satellite and satellite C being the second satellite. The targeted message for the first satellite may be sent to the second satellite via the path of D-E-F-G-H-a-B-C. In practice, it can be seen that the satellite C and the satellite D are originally adjacent co-orbiting satellites, and the target message of the satellite D can be theoretically sent to the satellite C directly without being required to rotate clockwise for one turn. However, since the forwarding address of satellite D in the routing table is not satellite C, the forwarding of the target message can only pass through a relatively frequent path, thereby affecting the efficiency of communication. A similar problem is unavoidable in static routing, i.e. the closest path cannot be selected in a targeted manner depending on the relative positions of the first satellite and the second satellite.
In order to solve this problem, a routing policy of dynamic routing is adopted in this embodiment. I.e. the routing policy comprises a path algorithm. Through a path algorithm, a forwarding path from the first satellite to the second satellite can be calculated based on the relative position relationship between the first satellite and the second satellite in the satellite group. And the forwarding path would be the most efficient communication path. The forwarding algorithm is not specifically limited in this embodiment, and any algorithm capable of achieving the same or similar functions may be combined in the overall technical solution of this embodiment.
In addition, it should be noted that, in a preferred case, the calculation of the path by the path algorithm may be based not only on the relative position relationship between the first satellite and the second satellite, but also further combining the real-time load conditions of the respective co-orbiting satellites on the path.
For example, in FIG. 2, assume satellite A is a first satellite and satellite F is a second satellite. There are two alternative forwarding paths, one is path a-B-C-D-E-F and the other is path a-H-G-F. Obviously, the paths a-H-G-F are more recent and have fewer forwarding times, and should generally be more efficient forwarding paths. But it is possible that in some cases, the communication load on some satellite or satellites in the path is high, for example, the communication load on the current satellite H is high. The target message may be forwarded to satellite G after a certain time waiting in the queue after arriving at satellite H. Resulting in an overall time delay for this path that is greater than the other path a-B-C-D-E-F. In this case, the path algorithm may combine the factors of the relative position relationship and the load condition to calculate the efficiency and the time delay of each path, so as to determine the forwarding path with the highest efficiency.
By contrast, the static routing in the embodiment shown in fig. 1 is characterized by no need of consuming too much computation power, but low overall communication efficiency. The dynamic routing in this embodiment has a characteristic of high overall communication efficiency, but requires a certain amount of computation power. In practical application, the selection and the selection can be performed according to the actual operation resource situation and the specific requirement, or the two can be combined for use. Each of the above situations is within the scope of the present invention.
After the forwarding path is determined, the target message can be sent to the second satellite according to the forwarding path, so as to realize indirect ground communication.
Fig. 4 shows another embodiment of the satellite communication method according to the present invention. In the embodiments shown in fig. 1-3, inter-satellite communication of the targeted message is limited to only co-orbiting satellites in the first satellite orbit. If non-co-orbiting satellites in different satellite orbits need to communicate, the method in the above embodiment cannot be implemented. The method in the embodiment further solves the communication problem among non-co-orbiting satellites. The method in the embodiment comprises the following steps:
And step 402, determining a third satellite corresponding to the high-orbit relay satellite at the current moment.
The present embodiment is primarily directed to forwarding a target message from a first satellite in a first satellite orbit to a target satellite in another satellite orbit (i.e., a second satellite orbit). Typically, the second satellite orbit is also a so-called low orbit. However, two satellites that transmit and receive the target message are in non-orbit (and low orbit), and the relative position relationship changes rapidly, so that direct communication cannot be performed.
In this embodiment, the target message is forwarded through a high orbit relay satellite in a high orbit. The high orbit relay satellite in the high orbit is similar to the ground station, and is far away from the first satellite orbit and the second satellite orbit, so that the position change of the high orbit relay satellite relative to the satellites in the first satellite orbit and the second satellite orbit is relatively gentle, and the communication can be realized. Similarly to the ground station, the communication range of the high-orbit relay satellite also covers a certain satellite in the first satellite orbit at the current time, and can directly communicate with the certain satellite, which is called as a third satellite in this embodiment.
The communication process between a group of satellites in orbit of a first satellite, i.e., a targeted message from the first satellite may be sent to a second satellite, has been described in the embodiments of fig. 1-3. The third satellite is the same orbiting satellite in the satellite group, and the target message can also be sent to the third satellite according to the same principle, which is not described herein. Meanwhile, since the third satellite can directly communicate with the high-orbit relay satellite, the third satellite can further forward the target message to the high-orbit relay satellite.
Similarly, the communication range of the high-orbit relay satellite covers a certain satellite in the second satellite orbit at the current time, and can directly communicate with the certain satellite, which is referred to as a fourth satellite in this embodiment. And after receiving the target message, the high-orbit relay satellite can forward the target message to a fourth satellite.
If the fourth satellite is the target satellite, the target message is successfully delivered. If the fourth satellite is not the target satellite but the group of satellites is also established with the co-orbiting satellite in the second satellite orbit (and the target satellite is in the group of satellites), the target message can be sent to the target satellite by communicating between the group of satellites in the second satellite orbit arbitrarily based on the same principle. If the fourth satellite is not the target satellite and there is no satellite group in the second satellite orbit (or the target satellite is not in the satellite group), the target satellite can wait for the target satellite to move to reach the communication range of the high-orbit relay satellite (i.e. after the target satellite becomes the fourth satellite), and the high-orbit relay satellite sends the target message to the target satellite, so as to achieve the delivery of the target message.
The relationship between the high orbit relay satellite, the first satellite orbit, and the second satellite orbit is shown in fig. 5, where the solid straight line represents the first satellite orbit, the dashed straight line represents the second satellite orbit, the solid circle represents the in-orbit satellite in the first orbit, the dashed circle represents the in-orbit satellite in the second satellite orbit, the rectangle represents the high orbit relay satellite, the satellite 03 represents the third satellite, and the satellite 04 represents the fourth satellite.
In other cases, the target ground station may be used as a relay device instead of the high-orbit relay satellite, so as to implement communication required by the non-in-orbit satellite. That is, after the target message is transmitted to the target ground station as in the method of fig. 1 to 3, the target message is transmitted to a fifth satellite in the orbit of the third satellite by using the target ground station. The third satellite orbit is also a satellite orbit (usually also low orbit) other than the first satellite orbit, and the fifth satellite is a satellite in the third satellite orbit covered by the communication range of the target ground station at the current time. The process of relaying by using the target ground station is similar to the above-described steps 401 to 404, and the description is not repeated here.
Fig. 6 shows a specific embodiment of the satellite communication device according to the present invention. The apparatus of this embodiment is a physical apparatus for performing the methods described in fig. 1-5. The technical solution is essentially the same as that in the above embodiment, and the corresponding description in the above embodiment is also applicable to this embodiment. The device in this embodiment includes:
a message determining module 601, configured to determine a target message of the first satellite.
And a second satellite determining module 602, configured to determine a second satellite corresponding to the target ground station at the current time.
The first routing module 603 is configured to send a target message from the first satellite to the second satellite according to a preset routing policy; to cause the second satellite to forward the target message to the target ground station; the first satellite and the second satellite are in a first satellite orbit.
In addition, on the basis of the embodiment shown in fig. 6, it is preferable that:
a satellite group determination module 604 for establishing a satellite group using at least two co-orbiting satellites in a first satellite orbit; two adjacent co-orbiting satellites in the satellite group are in communication connection; the co-orbiting satellites in the satellite group include a first satellite and a second satellite.
A routing policy determining module 605, configured to determine a routing policy of each co-orbiting satellite in the satellite group.
The third satellite determining module 606 is configured to determine a third satellite corresponding to the high-orbit relay satellite at the current time;
a second routing module 607, configured to send the target message from the first satellite to the third satellite according to a preset routing policy; such that the third satellite forwards the target message to the high orbit relay satellite; the target message is sent to a fourth satellite in orbit with the second satellite using the high orbit relay satellite.
A third routing module 608 for sending the target message to a fifth satellite in the third satellite orbit using the target ground station.
Fig. 7 is a schematic structural diagram of an electronic device according to an embodiment of the present invention. On the hardware level, the electronic device comprises a processor and optionally an internal bus, a network interface and a memory. The Memory may include a Memory, such as a Random-Access Memory (RAM), and may further include a non-volatile Memory, such as at least 1 disk Memory. Of course, the electronic device may also include hardware required for other services.
The processor, the network interface, and the memory may be connected to each other via an internal bus, which may be an ISA (Industry Standard Architecture) bus, a PCI (Peripheral Component Interconnect) bus, an EISA (Extended Industry Standard Architecture) bus, or the like. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of illustration, only one double-headed arrow is shown in FIG. 7, but this does not indicate only one bus or one type of bus.
And the memory is used for storing the execution instruction. In particular, a computer program that can be executed by executing instructions. The memory may include both memory and non-volatile storage and provides execution instructions and data to the processor.
In a possible implementation manner, the processor reads the corresponding execution instruction from the nonvolatile memory into the memory and then executes the execution instruction, and the corresponding execution instruction can also be obtained from other equipment so as to form the satellite communication device on a logic level. The processor executes the execution instructions stored in the memory to implement the satellite communication method provided by any embodiment of the invention through the executed execution instructions.
The method performed by the satellite communication device according to the embodiment of the invention shown in fig. 6 can be applied to or implemented by a processor. The processor may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software. The Processor may be a general-purpose Processor, including a Central Processing Unit (CPU), a Network Processor (NP), and the like; but also Digital Signal Processors (DSPs), Application Specific Integrated Circuits (ASICs), Field Programmable Gate Arrays (FPGAs) or other Programmable logic devices, discrete Gate or transistor logic devices, discrete hardware components. The various methods, steps and logic blocks disclosed in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The steps of the method disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor.
An embodiment of the present invention further provides a readable storage medium, where the readable storage medium stores an execution instruction, and when the stored execution instruction is executed by a processor of an electronic device, the electronic device can be caused to execute the satellite communication method provided in any embodiment of the present invention, and is specifically configured to execute the method shown in fig. 1 to 5.
The electronic device described in the foregoing embodiments may be a computer.
It will be appreciated by those skilled in the art that embodiments of the present invention may be provided as a method or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects.
The embodiments of the present invention are described in a progressive manner, and the same and similar parts among the embodiments can be referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, as for the apparatus embodiment, since it is substantially similar to the method embodiment, the description is relatively simple, and for the relevant points, reference may be made to the partial description of the method embodiment.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The above description is only an example of the present invention, and is not intended to limit the present invention. Various modifications and alterations to this invention will become apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.
Claims (10)
1. A satellite communication method, comprising:
determining a target message of a first satellite;
determining a second satellite corresponding to the target ground station at the current moment;
according to a preset routing strategy, the target message is sent to the second satellite from the first satellite; to cause the second satellite to forward the target message to the target ground station;
the first satellite and the second satellite are in a first satellite orbit.
2. The method of claim 1, further comprising:
establishing a satellite group using at least two co-orbiting satellites of the first satellite orbit; two adjacent co-orbiting satellites in the satellite group are in communication connection;
determining a routing strategy of each co-orbiting satellite in the satellite group;
the co-orbiting satellites of the group of satellites include the first satellite and the second satellite.
3. The method of claim 2, wherein the communication connection between two adjacent co-orbiting satellites in the group of satellites comprises:
a laser link communication connection, or a microwave signal communication connection.
4. The method of claim 2, wherein the routing policy comprises a routing table, and wherein the routing table comprises forwarding addresses corresponding to the co-orbiting satellites; according to a preset routing strategy, the step of sending the target message from the first satellite to the second satellite comprises the following steps:
and sequentially forwarding the target message from the first satellite to the second satellite according to the forwarding address.
5. The method of claim 2, wherein the routing policy comprises a path algorithm; the sending the target message from the first satellite to the second satellite according to a preset routing policy includes:
calculating a forwarding path from the first satellite to the second satellite according to the path algorithm and based on the relative position relationship of the first satellite and the second satellite in the satellite group;
transmitting the targeted message from the first satellite to the second satellite based on the forwarding path.
6. The method according to any one of claims 1 to 5, further comprising:
determining a third satellite corresponding to the high-orbit relay satellite at the current moment;
according to a preset routing strategy, the target message is sent to the third satellite from the first satellite; to cause the third satellite to forward the target message to the high-orbit relay satellite;
and sending the target message to a fourth satellite in the second satellite orbit by utilizing the high-orbit relay satellite.
7. The method according to any one of claims 1 to 5, further comprising:
transmitting, with the target ground station, the target message to a fifth satellite in a third satellite orbit.
8. A satellite communication device, comprising:
a message determination module for determining a target message of a first satellite;
the second satellite determining module is used for determining a second satellite corresponding to the target ground station at the current moment;
the routing module is used for sending the target message to the second satellite from the first satellite according to a preset routing strategy; to cause the second satellite to forward the target message to the target ground station;
the first satellite and the second satellite are in a first satellite orbit.
9. A computer-readable storage medium storing a computer program for executing the satellite communication method according to any one of claims 1 to 7.
10. An electronic device, the electronic device comprising:
a processor;
a memory for storing the processor-executable instructions;
the processor is configured to read the executable instructions from the memory and execute the instructions to implement the satellite communication method according to any one of claims 1 to 7.
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