CN112152695A - Low-orbit satellite constellation measuring, operation and control system and method thereof - Google Patents
Low-orbit satellite constellation measuring, operation and control system and method thereof Download PDFInfo
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- 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
- H04B7/18519—Operations control, administration or maintenance
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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
- H04B7/18513—Transmission in a satellite or space-based system
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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
Abstract
The application relates to a satellite positioning technology and discloses a low-earth-orbit satellite constellation measurement, operation and control system and a method thereof. This survey fortune control system includes: n same-orbit inter-satellite links corresponding to the N orbital planes, wherein each same-orbit inter-satellite link is used for data transmission between node satellites of one corresponding orbital plane, and N is more than or equal to 2; and the satellite-ground link is used for designating a node satellite which runs to the intersection of the N orbital planes in each inter-orbital-satellite link as a hub satellite, and each inter-orbital-satellite link carries out data transmission with at least one ground station which is arranged near the latitude of the intersection of the N orbital planes through the hub satellite. According to the implementation mode of the application, the low-orbit satellite constellation measuring, operation and control requirements are met, meanwhile, the technical complexity of the satellite is reduced, the satellite and ground station cost is reduced, and the engineering feasibility of low-orbit satellite constellation real-time measuring, operation and control is improved.
Description
Technical Field
The application relates to the field of satellite positioning, in particular to a low-orbit satellite constellation measurement, operation and control technology.
Background
The low earth orbit satellite constellation is generally a global-coverage constellation system, the current main application occasions are global broadband communication, navigation enhancement, voice communication and the like, and the application scenes require real-time interaction between the satellite and a ground operation control system, namely requirements are as follows: no matter where the satellite runs in the space, the ground measurement, operation and control system has the capability of interacting data with any satellite system to complete service control.
Currently, the following two methods are adopted to perform real-time measurement, operation and control of low-orbit satellite constellations: the first is to adopt global station arrangement, and establish a ground station through the global method, ensure that every moment, every satellite in the constellation can be directly connected with the ground station, and establish a link with a ground measurement, operation and control center through the ground station in the global range, so as to realize data interaction; the second method is to adopt inter-satellite links, and to establish four inter-satellite links between each satellite and four satellites in front of and behind (in the same orbital plane) and on the left and right (in the different orbital planes) of the satellite, so as to realize in-orbit networking of low-orbit satellite constellations, and thus, any satellite in the constellations can establish a direct or indirect link with an intra-terrestrial station in a manner of the inter-satellite links, and realize data interaction with a terrestrial operation and control center.
However, the above scheme of global stationing and inter-satellite link has obvious defects. For the global station arrangement scheme, a ground system capable of carrying out measurement, operation and control on a global-coverage low-earth-orbit satellite system needs to be established, not less than 40 ground stations need to be established in the global range, the more the number of the ground stations is, the higher the cost is, overseas ground stations with uplink and downlink need to be established, radio transmission permission needs to be obtained locally overseas, and the difficulty of policy is high; for the scheme of the inter-satellite link, each satellite on the constellation needs to be provided with four antennas in total, namely front, rear, left and right, the positions of the front and rear satellites in the same orbital plane are relatively fixed according to the orbital characteristics, the directions of the antennas are fixed, the engineering is simple to realize, but the positions of the left and right satellites in different orbital planes continuously change, the antennas need to be tracked along with each other, the antennas are difficult to develop, and the cost is high. Therefore, the current scheme for realizing the real-time measurement, operation and control of the low-orbit satellite constellation is complex to realize and has higher cost.
Disclosure of Invention
The application aims to provide a low-orbit satellite constellation measuring, operation and control system and a method thereof, which can meet the low-orbit satellite constellation measuring, operation and control requirements, reduce the technical complexity of the satellite, reduce the cost of the satellite and a ground station, and improve the engineering feasibility of the low-orbit satellite constellation real-time measuring, operation and control.
The application discloses survey fortune control system of low earth orbit satellite constellation includes:
n same-orbit inter-satellite links corresponding to the N orbital planes, wherein each same-orbit inter-satellite link is used for data transmission between node satellites of one corresponding orbital plane, and N is more than or equal to 2;
and the satellite-to-ground link is used for designating a node satellite which runs to the intersection of the N orbital planes in each inter-orbital-satellite link as a hub satellite, and each inter-orbital-satellite link carries out data transmission with one ground station of at least one ground station which is arranged near the latitude of the intersection of the N orbital planes through the hub satellite.
In a preferred embodiment, the antenna pitch angle of each node satellite of one of the N inter-orbiting inter-satellite links is 90 ° - (360 °/2N), where N is the number of node satellites in the inter-orbiting inter-satellite link, and N is greater than or equal to 3.
In a preferred example, the intersection of the N track surfaces is a region with south latitude of 50-90 degrees and/or a region with north latitude of 50-90 degrees.
In a preferred embodiment, the number of the at least one ground station is determined according to the track height of the N track surfaces, the track inclination angle of the N track surfaces and the cutoff elevation angle of each ground station antenna.
In a preferred example, the at least one ground station is 1 ground station, and the ground station is arranged in a region of 80-90 degrees south latitude or 80-90 degrees north latitude.
In a preferred example, the at least one ground station is 2 or 3 ground stations, and the 2 or 3 ground stations are respectively arranged in different longitude regions of 50-80 ° south latitude and/or 50-80 ° north latitude.
In a preferred example, each of the inter-orbiting satellite links is further used for bidirectional data transmission between adjacent nodal satellites of the corresponding one of the orbital planes.
In a preferred embodiment, each of the on-orbit inter-satellite links is further configured to send instruction information to each of the node satellites on the orbit plane where the hub satellite is located through the hub satellite, where the instruction information includes a unique identifier of the hub satellite, and each of the node satellites determines a unique sending direction according to the unique identifier of the hub satellite, and sends data information to the hub satellite according to the determined unique sending direction.
In a preferred embodiment, the N on-orbit inter-satellite links are laser links or microwave links.
The application also discloses a low orbit satellite constellation measuring, operation and control method, wherein the low orbit satellite constellation comprises N same orbit inter-satellite links corresponding to N orbit surfaces; the method comprises the following steps:
appointing a node satellite which runs to the intersection of the N orbital planes in each same-orbit inter-satellite link as a hub satellite;
and the hub satellite receives the data information of all node satellites of the orbital plane where the hub satellite is located through the link between the same orbit satellites and sends the data information to one ground station of at least one ground station near the latitude at the intersection of the N orbital planes.
In a preferred embodiment, before the hub satellite receives the data information of all node satellites on the orbital plane through the inter-orbiting satellite link, the method further includes:
the hub satellite sends instruction information to each node satellite of the orbital plane where the hub satellite is located, wherein the instruction information contains the unique identification of the hub satellite;
the node satellites determine a unique sending direction according to the unique identification of the hub satellite;
and the node satellites transmit the data information to the hub satellite according to the determined unique transmitting direction.
In a preferred example, the intersection of the N track surfaces is a region with south latitude of 50-90 degrees and/or a region with north latitude of 50-90 degrees.
In a preferred embodiment, the antenna pitch angle of each node satellite of one of the N inter-orbiting inter-satellite links is 90 ° - (360 °/2N), where N is the number of node satellites in the inter-orbiting inter-satellite link, and N is greater than or equal to 3.
In a preferred embodiment, the number of the at least one ground station is determined according to the track height of the N track surfaces, the track inclination angle of the N track surfaces and the cutoff elevation angle of each ground station antenna.
In a preferred example, the at least one ground station is 1 ground station, and the ground station is arranged in a region of 80-90 degrees south latitude or 80-90 degrees north latitude.
In a preferred example, the at least one ground station is 2 or 3 ground stations, and the 2 or 3 ground stations are respectively arranged in different longitude regions of 50-80 ° south latitude and/or 50-80 ° north latitude.
In a preferred embodiment, the N on-orbit inter-satellite links are laser links or microwave links.
Compared with the currently adopted method for carrying out real-time measurement, operation and control of low-orbit satellite constellations in a global station arrangement and inter-satellite link mode, the method at least has the following advantages:
firstly, only the same orbit satellite on the same orbit plane is established to establish the inter-satellite link, but the inter-satellite link is not established for the satellite on the different orbit plane, for example, the inter-satellite tracking antenna on the satellite can be cancelled, so that the difficulty of the routing algorithm can be reduced, and the complexity and the cost of the satellite can be reduced.
Because the same-orbit satellites on the same orbit plane are established to establish the inter-satellite link, the antenna direction of each node satellite of each same-orbit inter-satellite link can be fixed, the antenna does not need to be tracked in a follow-up manner, the antenna is simple to develop, the cost is low, the difficulty of a routing algorithm can be further reduced, and the complexity and the cost of the satellite are reduced.
Moreover, since the intersections of all the inter-orbiting satellite links of the low-orbit satellite constellation are usually gathered in the high-altitude areas of south-north poles, at least one ground station is arranged in the high-altitude areas of south-north poles on the basis, so that the data of the whole low-orbit satellite constellation can be transmitted and received by using a very small number (for example, 2 or 3) of ground stations, and the engineering cost is further reduced.
Based on the above contents, in the embodiment of the application, an all-weather real-time high-speed communication link is established between a very small number of ground stations arranged in high-altitude areas such as the south-north pole and the low-orbit satellite constellation, so that not only can the technical complexity of the satellite be reduced, the cost of the satellite or the ground station be reduced, but also the engineering feasibility of the low-orbit satellite constellation real-time measurement, operation and control can be improved.
The present specification describes a number of technical features distributed throughout the various technical aspects, and if all possible combinations of technical features (i.e. technical aspects) of the present specification are listed, the description is made excessively long. In order to avoid this problem, the respective technical features disclosed in the above summary of the invention of the present application, the respective technical features disclosed in the following embodiments and examples, and the respective technical features disclosed in the drawings may be freely combined with each other to constitute various new technical solutions (which are considered to have been described in the present specification) unless such a combination of the technical features is technically infeasible. For example, in one example, the feature a + B + C is disclosed, in another example, the feature a + B + D + E is disclosed, and the features C and D are equivalent technical means for the same purpose, and technically only one feature is used, but not simultaneously employed, and the feature E can be technically combined with the feature C, then the solution of a + B + C + D should not be considered as being described because the technology is not feasible, and the solution of a + B + C + E should be considered as being described.
Drawings
Fig. 1 is a schematic structural diagram of a measurement, operation and control system of a low earth orbit satellite constellation according to a first embodiment of the present application
FIG. 2 is a diagram of a terrestrial up-bound to a nodal satellite S according to an example of a first embodiment of the present applicationi,j+kBusiness data flow diagram
FIG. 3 is a nodal satellite S according to an example of a first embodiment of the present applicationi,j+kSchematic flow chart for downlink of satellite service data to ground measurement, operation and control center
FIG. 4 is a schematic flow chart of a method for operation and control of a low earth orbit satellite constellation according to a second embodiment of the present application
FIG. 5 is a schematic flow chart of an example of transmitting data information to a hub satellite by each node satellite according to a second embodiment of the present application
Detailed Description
In the following description, numerous technical details are set forth in order to provide a better understanding of the present application. However, it will be understood by those skilled in the art that the technical solutions claimed in the present application may be implemented without these technical details and with various changes and modifications based on the following embodiments.
Description of partial concepts:
low orbit satellite system: km (500-2000) from the ground, transmission delay and power consumption are small, but the coverage area of each satellite is small, and a typical system is an iridium satellite system of Motorola. The low-orbit satellite communication system can support multi-hop communication due to low satellite orbit and short signal propagation delay, has low link loss, can reduce the requirements on satellites and user terminals, and can adopt miniature/small satellites and handheld user terminals. But low orbit satellite systems also pay a large price for these advantages: due to low orbit, each satellite can cover a relatively small range, and tens of satellites are needed to form a global system, for example, 66 satellites are needed in an iridium system, 48 satellites are needed in Globalstar, and 288 satellites are needed in Teledisc. Meanwhile, because the low-orbit satellite has a fast movement speed, the time from the rise of the satellite from the horizon to the fall of the satellite below the horizon is short for a single user, and therefore the inter-satellite or inter-carrier switching is frequent. Therefore, the system of the low-rail system is complex in construction and control, high in technical risk and relatively high in construction cost. There are 8 major companies who propose low-orbit satellite solutions, and the most representative low-orbit satellite mobile communication systems include Iridium (Iridium) system, Globalstar (Globalstar) system, Arics (Arics) system, Leo-Set (Leo-Set) system, Coscon (Coscon) system, and satellite communication network (Teledesic) system.
Low earth satellite constellation: a low orbit satellite constellation consists of multiple satellites in multiple orbits. Since the low earth orbit satellite and the earth are not synchronized, the constellation is constantly changing, and the relative position of each satellite between different orbits is also constantly changing. In order to facilitate management and realize real-time communication of a multi-satellite system, satellites are connected with ground terminals and gateway stations, and the satellites are also connected with each other through ground links and inter-satellite links.
Track inclination angle: typically the angle between the reference plane and the direction of another plane or axis. Orbital inclination refers to the angle between the orbital plane of a satellite and the equatorial plane of the earth, which determines the relationship of the orbital plane to the equatorial plane or to the earth's axis.
Satellite signal band: including c-band, Ku-band, Ka-band, S-band, L-band, etc. The c-band is a band with the frequency of 4.0-8.0GHz and is used as the band of downlink transmission signals of the communication satellite. In satellite television broadcasting and various small satellite ground station applications, this frequency band was first adopted and has been widely used. The frequency of the Ku band is protected by international legal regulations, with the Ku band going downstream from 10.7 to 12.75GHz and upstream from 12.75 to 18.1 GHz. The Ka band is a part of a microwave band of an electromagnetic spectrum, and the frequency range of the Ka band is 26.5-40 GHz. Ka represents the upper K-above (K-above), in other words, the band is directly above the K band. The Ka band, also known as the 30/20GHz band, is commonly used for satellite communications. The S band is an electromagnetic wave band with the frequency range of 1.55-3.4 GHz. According to the IEEE 521-2002 standard, the L band refers to a radio wave band with a frequency of 1-2 GHz; the north L-band means 40-60 GHz (7.50-5.00 mm wavelength), which belongs to millimeter wave.
To make the objects, technical solutions and advantages of the present application more clear, embodiments of the present application will be described in further detail below with reference to the accompanying drawings.
A first embodiment of the present application relates to a system for measuring, operating and controlling a low-earth satellite constellation, which has a structure shown in fig. 1, and includes N co-orbital inter-satellite links (L) corresponding to N orbital planes1～LN) And a satellite-to-ground link, wherein N is more than or equal to 2.
Specifically, the method comprises the following steps:
each same-orbit inter-satellite link is used for data transmission between the node satellites of the corresponding orbit plane. All node satellites in the same orbital plane are networked by establishing an inter-satellite link in the same orbital plane, that is, the data of all the node satellites can be gathered to one of the node satellites, and similarly, the data on any one node satellite can be distributed to all other node satellites.
Optionally, each of the on-orbit inter-satellite links is further used for bidirectional data transmission between adjacent nodal satellites of the corresponding one of the orbital planes. Further, each of the on-orbit inter-satellite links may be a laser link, a microwave link, or the like. Satellite S with the ith orbital plane and the jth nodei,j"for example, an existing satellite signal band may be selected for data transmission or other signal bands not developed, where Si,jAdjacent nodal satellite S in the same orbital planei,j-1And Si,j+1Establishing a bi-directional link, and allocating frequencies to avoid mutual interference, as shown in Table 1 below, wherein f1≠f2≠f3≠f4。
TABLE 1
| Link circuit | Frequency of |
| Si,j——>Si,j-1 | f1 |
| Si,j-1——>Si,j | f2 |
| Si,j——>Si,j+1 | f3 |
| Si,j+1——>Si,j | f4 |
In order to implement data transmission between the node satellites in the same orbital plane corresponding to each inter-satellite link, in one embodiment, the data transmission can be implemented by arranging an antenna subsystem on each node satellite in the same orbital plane, and the antenna subsystem is responsible for transceiving electromagnetic wave signals between the node satellites in the inter-satellite links.
Alternatively, the antenna pitch angle of each nodal satellite of each inter-orbiting inter-satellite link may be fixed. In one embodiment, the number of the node satellites in each of the N inter-orbiting links may be set according to the antenna pitch angle of each node satellite of one of the N inter-orbiting links, which may be 90 ° - (360 °/2N), where N is the number of the node satellites in the inter-orbiting link, and N ≧ 3.
Further, since only the same-orbit inter-satellite link is established in the present embodiment, the intersections of the N orbital planes are usually gathered at the same altitude in the north-south poles. Alternatively, the intersection of the N track surfaces can be a region with south latitude of 50 degrees to 90 degrees and/or a region with north latitude of 50 degrees to 90 degrees.
Further, the inter-satellite link is configured to designate a node satellite of each inter-satellite link that runs to the intersection of the N orbital planes as a hub satellite, and the inter-satellite link performs data transmission with one of at least one ground station disposed near the latitude of the intersection of the N orbital planes via the hub satellite. Specifically, the node satellite in each of the inter-orbiting links that travels to the intersection of the N orbital planes is designated as a hub satellite, and when the designated hub satellite travels to a range outside the intersection of the N orbital planes, the identity of the designated hub satellite is converted into a node satellite, where the hub satellite of each orbital plane changes with the orbital movement of the satellite.
Further, in order to realize data transmission between the hub satellite and the ground station, in one embodiment, the data transmission can be realized by arranging a receiver and a transmitter at each node satellite in the same orbital plane; the receiver performs amplification, frequency conversion, detection, demodulation, decoding and the like on received signals, provides an interface between an inter-satellite link and a satellite downlink, and the transmitter is responsible for selecting signals needing to be transmitted on the inter-satellite link from an uplink of the satellite and performs coding, modulation, frequency conversion and amplification.
Optionally, the system for measuring, operating and controlling a low-earth satellite constellation further includes a ground measurement, operation and control center, and each ground station of the at least one ground station establishes a connection with the ground measurement, operation and control center to obtain data information of the entire low-earth satellite constellation.
Further, at the same time, the at least one ground station may enable at least one satellite to be visible with each of all N orbital planes. In one embodiment, there is only one hub star S per orbital planei,jEstablishing satellite-ground link with ground station, and allocating frequencies to avoid mutual interference of frequencies as shown in Table 2 below, wherein f5≠f6(ii) a Satellite S from ground up to nodei,j+kAs shown in fig. 2, the data flow of the satellite service is as follows: the ground testing, transporting and controlling center>Ground station>Pivot star S of ith tracki,j(i＝1，2，……，m)——>Nodal satellite Si,j+1——>Nodal satellite Si,j+2——>… … node satellite Si,j+k(ii) a Nodal satellite Si,j+kThe process of downlink of the satellite service data to the ground measurement, operation and control center is shown in fig. 3: nodal satellite Si,j+k——>… … node satellite Si,j+2——>Nodal satellite Si,j+1——>Pivot star S of ith tracki,j(i＝1，2，……，m)——>Ground station>And a ground measurement, operation and control center.
TABLE 2
Optionally, the designated hub satellite may send data from the ground station to other node satellites on the orbital plane through the co-orbital inter-satellite link where the designated hub satellite is located, and receive data such as status information, service information and grasp local network views sent by other node satellites on the orbital plane. In one embodiment, for an on-orbit inter-satellite link, command information including the unique identification of the hub satellite can be sent to each node satellite of the orbital plane through the designated hub satellite, and each node satellite determines a unique sending direction according to the unique identification of the hub satellite and sends data information to the hub satellite according to the determined unique sending direction.
Optionally, the number of the at least one ground station may be determined according to the track height of the N orbital planes, the track inclination of the N orbital planes, and the elevation angle of each ground station antenna cutoff. Further, each ground station of the at least one ground station may further include an acquisition tracking subsystem for tracking the hub star within the cut-off elevation range of the acquisition antenna and controlling the tracking pointing error within a certain error range.
Furthermore, the latitude of the intersection of the N orbital planes is selected as the setting position of the at least one ground station, so that the number of the ground stations can be reduced. For example, the number of the at least one ground station can be 1, and the ground station is arranged in a south latitude 80-90 degrees region or a north latitude 80-90 degrees region; or the number of the at least one ground station can be 2, and the ground stations are respectively arranged in different longitude areas with south latitude of 50-80 degrees and/or north latitude of 50-80 degrees; or the number of the at least one ground station can be 3, and the ground stations are respectively arranged in different longitude areas with south latitude of 50-80 degrees and/or north latitude of 50-80 degrees; but is not limited thereto. In this embodiment, the data transmission and reception of the entire low-orbit constellation can be completed by a very small number of ground stations. For a better understanding, the following examples are given by way of illustration only, and the details listed in the examples are to be considered by way of illustration only and not as limitations on the scope of the present application.
In this example, it is first assumed that the constellation consists of 96 satellites, has an orbital height of 800km, and is divided into 8 orbital planes, each orbital plane contains 12 satellites, the inclination angle of each satellite is 80 °, and the satellites and the orbital planes are linked by inter-satellite links. Aiming at the low-orbit satellite constellation, in order to realize real-time measurement and control of all satellites on the ground, the following scheme (i) or scheme (ii) can be arranged:
the method comprises the following steps that firstly, a Steval station (15 degrees E, 78 degrees N) in a north pole area and a Telel station (2 degrees E, 72 degrees S) in a south pole area are arranged, 2 ground stations are counted, the antenna elevation angle of each ground station is 10 degrees, and the two stations are combined to realize real-time measurement and control of all satellites through simulation analysis;
in view of the fact that the station building cost of the south-north polar region is high, a high-latitude region which is as close as possible to the south-north polar region can be selected, for example, a Heilongjiang station (123 degrees E and 50 degrees N), a Lusenberg station (3 degrees E and 50 degrees N) and a Canadian south station (-117 degrees E and 50 degrees N), 3 ground stations are counted, the elevation angle of an antenna of each ground station is 10 degrees, and real-time measurement and control of all satellites can be achieved through combination of the three stations through simulation analysis.
The second embodiment of the present application relates to a method for measuring, operating and controlling a low earth orbit satellite constellation, where the low earth orbit satellite constellation includes N inter-earth orbit links corresponding to N orbital planes, where each inter-earth orbit link is used for data transmission between each node satellite of one orbital plane corresponding to the inter-earth orbit link, and N is greater than or equal to 2. All node satellites in the same orbital plane are networked by establishing an inter-satellite link in the same orbital plane, that is, the data of all the node satellites can be gathered to one of the node satellites, and similarly, the data on any one node satellite can be distributed to all other node satellites.
The flow of the method for detecting, operating and controlling the low earth orbit satellite constellation is shown in fig. 2, and the method comprises the following steps 101 to 102, and specifically comprises the following steps:
beginning with step 101, a node satellite in each inter-orbiting satellite link that runs to the intersection of the N orbital planes is designated as a hub satellite. Specifically, the node satellite in each of the inter-orbiting links that travels to the intersection of the N orbital planes is designated as a hub satellite, and when the designated hub satellite travels to a range outside the intersection of the N orbital planes, the identity of the designated hub satellite is converted into a node satellite, where the hub satellite of each orbital plane changes with the orbital movement of the satellite.
Optionally, the designated hub satellite may send data from the ground station to other node satellites on the orbital plane through the co-orbital inter-satellite link where the designated hub satellite is located, and receive data information such as status information, service information and grasp local network views sent by other node satellites on the orbital plane.
Then, step 102 is entered, the hub satellite receives the data information of all the node satellites of the orbital plane where the hub satellite is located through the link between the co-orbital satellites, and sends the data information to one of at least one ground station arranged near the latitude at the intersection of the N orbital planes.
Optionally, before the step 102, the following steps 501 to 503 may be further included, as shown in fig. 5: starting step 501, the hub satellite sends instruction information to each node satellite on the orbit plane where the hub satellite is located, wherein the instruction information includes a unique identifier of the hub satellite; then step 502 is entered, and the node satellites determine a unique sending direction according to the unique identification of the hub satellite; then, step 503 is entered, and the respective nodal satellite transmits the data message to the hub satellite according to the determined unique transmission direction.
It should be noted that the embodiment shown in fig. 5 is only one aspect of realizing that each node satellite transmits data information to the hub satellite, and is not limited thereto.
Optionally, after the step 102, the following steps may be further included:
each of the at least one ground station transmits the received data information to a ground test, operation and control center.
Optionally, each of the on-orbit inter-satellite links may also be used for bidirectional data transmission between adjacent nodal satellites of its corresponding one of the orbital planes. Further, each of the on-orbit inter-satellite links may be a laser link, a microwave link, or the like. With the ith orbital plane, the jth node satellite Si,jFor example, a nodal satellite Si,jAdjacent nodal satellite S in the same orbital planei,j-1And Si,j+1Establishing a bi-directional link, and in order to avoid mutual interference of frequencies, allocating frequencies as in table 1 above, wherein f1≠f2≠f3≠f4。
Alternatively, the antenna pitch angle of each node satellite of each inter-orbiting inter-satellite link in this embodiment may be fixed. In one embodiment, the number of the node satellites in each of the N inter-orbiting links may be set according to the antenna pitch angle of each node satellite of one of the N inter-orbiting links, which may be 90 ° - (360 °/2N), where N is the number of the node satellites in the inter-orbiting link, and N ≧ 3.
Further, since only the same-orbit inter-satellite link is established in the present embodiment, the intersections of the N orbital planes are usually gathered at the same altitude in the north-south poles. Alternatively, the intersection of the N track surfaces can be a region with south latitude of 50 degrees to 90 degrees and/or a region with north latitude of 50 degrees to 90 degrees.
Further, the at least one ground station may enable at least one satellite to be visible with each of all N orbital planes. In one embodiment, there is only one hub star S per orbital planei,jEstablishing a satellite-to-ground link with a ground station, and assigning frequencies to avoid interference between frequencies as in Table 2 above, wherein f5≠f6. Satellite S from ground up to nodei,j+kAs shown in fig. 2, the data flow of the satellite service is as follows: the ground testing, transporting and controlling center>Ground station>Pivot star S of ith tracki,j(i＝1，2，……，m)——>Nodal satellite Si,j+1——>Nodal satellite Si,j+2——>… … node satellite Si,j+k(ii) a Nodal satellite Si,j+kThe process of downlink of the satellite service data to the ground measurement, operation and control center is shown in fig. 3: nodal satellite Si,j+k——>… … node satellite Si,j+2——>Nodal satellite Si,j+1——>Pivot star S of ith tracki,j(i＝1，2，……，m)——>Ground station>And a ground measurement, operation and control center.
Optionally, the number of the at least one ground station in this embodiment may be determined according to the track height of the N track surfaces, the track inclination angle of the N track surfaces, and the cut-off elevation angle of each ground station antenna. Further, each ground station of the at least one ground station may further include an acquisition tracking subsystem for tracking the hub star within the cut-off elevation range of the acquisition antenna and controlling the tracking pointing error within a certain error range.
Further, in the present embodiment, the number of ground stations can be reduced by selecting the vicinity of the latitude of the intersection of the N orbital planes as the installation position of the at least one ground station. For example, the number of the at least one ground station can be 1, and the ground station is arranged in a south latitude 80-90 degrees region or a north latitude 80-90 degrees region; or the number of the at least one ground station can be 2, and the ground stations are respectively arranged in different longitude areas with south latitude of 50-80 degrees and/or north latitude of 50-80 degrees; or the number of the at least one ground station can be 3, and the ground stations are respectively arranged in different longitude areas with south latitude of 50-80 degrees and/or north latitude of 50-80 degrees; but is not limited thereto. Therefore, in the embodiment of the present application, data transmission and reception of the entire low-orbit constellation can be completed by a very small number of ground stations. For a better understanding, the following examples are given by way of illustration only, and the details listed in the examples are to be considered by way of illustration only and not as limitations on the scope of the present application.
In this example, it is first assumed that the constellation consists of 96 satellites, has an orbital height of 800km, and is divided into 8 orbital planes, each orbital plane contains 12 satellites, the inclination angle of each satellite is 80 °, and the satellites and the orbital planes are linked by inter-satellite links. Aiming at the low-orbit satellite constellation, in order to realize real-time measurement and control of all satellites on the ground, the following scheme (i) or scheme (ii) can be arranged:
the method comprises the following steps that firstly, a Steval station (15 degrees E, 78 degrees N) in a north pole area and a Telel station (2 degrees E, 72 degrees S) in a south pole area are arranged, 2 ground stations are counted, the antenna elevation angle of each ground station is 10 degrees, and the two stations are combined to realize real-time measurement and control of all satellites through simulation analysis;
in view of the fact that the station building cost of the south-north polar region is high, a high-latitude region which is as close as possible to the south-north polar region can be selected, for example, a Heilongjiang station (123 degrees E and 50 degrees N), a Lusenberg station (3 degrees E and 50 degrees N) and a Canadian south station (-117 degrees E and 50 degrees N), 3 ground stations are counted, the elevation angle of an antenna of each ground station is 10 degrees, and real-time measurement and control of all satellites can be achieved through combination of the three stations through simulation analysis.
Further, in this embodiment, in order to implement the data transmission between the node satellites in the same orbital plane of each inter-orbiting satellite link and the data transmission between the hub satellite and at least one ground station, in one embodiment, the data transmission can be implemented by arranging an antenna subsystem, a receiver and a transmitter at each node satellite in the same orbital plane. The antenna subsystem is responsible for receiving and transmitting electromagnetic wave signals on the same-orbit inter-satellite link, the receiver completes amplification, frequency conversion, detection, demodulation, decoding and the like of the received signals, an interface between the inter-satellite link and a satellite downlink is provided, and the transmitter is responsible for selecting signals needing to be transmitted on the inter-satellite link from an uplink of the satellite to complete coding, modulation, frequency conversion and amplification.
This embodiment is a method embodiment corresponding to the first embodiment, and the technical details in the first embodiment may be applied to this embodiment, and the technical details in this embodiment may also be applied to the first embodiment.
It is noted that, in the present patent application, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, 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, the use of the verb "comprise a" to define an element does not exclude the presence of another, same element in a process, method, article, or apparatus that comprises the element. In the present patent application, if it is mentioned that a certain action is executed according to a certain element, it means that the action is executed according to at least the element, and two cases are included: performing the action based only on the element, and performing the action based on the element and other elements. The expression of a plurality of, a plurality of and the like includes 2, 2 and more than 2, more than 2 and more than 2.
All documents mentioned in this application are to be considered as being incorporated in their entirety into the disclosure of this application so as to be subject to modification as necessary. It should be understood that the above description is only a preferred embodiment of the present disclosure, and is not intended to limit the scope of the present disclosure. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of one or more embodiments of the present disclosure should be included in the scope of protection of one or more embodiments of the present disclosure.
Claims (17)
1. A system for controlling the operation of a low earth orbit satellite constellation, comprising:
n same-orbit inter-satellite links corresponding to the N orbital planes, wherein each same-orbit inter-satellite link is used for data transmission between node satellites of one corresponding orbital plane, and N is more than or equal to 2;
and the satellite-to-ground link is used for designating a node satellite which runs to the intersection of the N orbital planes in each inter-orbital-satellite link as a hub satellite, and each inter-orbital-satellite link carries out data transmission with one ground station of at least one ground station which is arranged near the latitude of the intersection of the N orbital planes through the hub satellite.
2. The system according to claim 1, wherein the antenna pitch angle of each node satellite of one of the N inter-orbiting satellite links is 90 ° - (360 °/2N), where N is the number of node satellites in the inter-orbiting satellite link, and N ≧ 3.
3. The system for detecting, operating and controlling a constellation of low earth orbit satellites as claimed in claim 1, wherein the intersection of the N orbital planes is a region of 50 ° to 90 ° south latitude and/or a region of 50 ° to 90 ° north latitude.
4. The system of claim 1, wherein the number of the at least one ground station is determined according to the orbital height of the N orbital planes, the orbital inclination of the N orbital planes, and the elevation of each ground station antenna cutoff.
5. The system for detecting, operating and controlling a constellation of low earth orbit satellites as claimed in claim 1, wherein the at least one ground station is 1 ground station, and the ground station is located in 80-90 ° south latitude area or 80-90 ° north latitude area.
6. The system for detecting, operating and controlling a constellation of low earth orbit satellites as claimed in claim 1, wherein the at least one ground station is 2 or 3 ground stations, and the 2 or 3 ground stations are respectively disposed in different longitude regions of 50 ° to 80 ° in south latitude and/or 50 ° to 80 ° in north latitude.
7. The system for detecting, operating and controlling a constellation of low-orbit satellites as claimed in claim 1, wherein each of the inter-orbiting satellite links is further configured for bi-directional data transmission between adjacent nodal satellites of the corresponding one of the orbital planes.
8. The system according to claim 7, wherein each of the in-orbit inter-satellite links is further configured to send command information to each of the node satellites on the orbit plane via the hub satellite, wherein the command information includes a unique identifier of the hub satellite, and each of the node satellites determines a unique sending direction according to the unique identifier of the hub satellite and sends data information to the hub satellite according to the determined unique sending direction.
9. The system according to any of claims 1-8, wherein the N inter-orbiting satellite links are laser links or microwave links.
10. A low orbit satellite constellation measuring, operation and control method is characterized in that the low orbit satellite constellation comprises N same orbit inter-satellite links corresponding to N orbit surfaces; the method comprises the following steps:
appointing a node satellite which runs to the intersection of the N orbital planes in each same-orbit inter-satellite link as a hub satellite;
and the hub satellite receives the data information of all node satellites of the orbital plane where the hub satellite is located through the link between the same orbit satellites and sends the data information to one ground station of at least one ground station near the latitude at the intersection of the N orbital planes.
11. The method for detecting, operating and controlling a low earth orbit satellite constellation according to claim 10, wherein before the hub satellite receives the data information of all node satellites on the orbit plane through the link between the same earth orbit satellites, the method further comprises:
the hub satellite sends instruction information to each node satellite of the orbital plane where the hub satellite is located, wherein the instruction information contains the unique identification of the hub satellite;
the node satellites determine a unique sending direction according to the unique identification of the hub satellite;
and the node satellites transmit the data information to the hub satellite according to the determined unique transmitting direction.
12. The method for detecting, operating and controlling a low earth orbit satellite constellation according to claim 10, wherein the intersection of the N orbital planes is a region with 50 ° to 90 ° south latitude and/or a region with 50 ° to 90 ° north latitude.
13. The method according to claim 10, wherein the pitch angle of each node satellite of one of the N inter-orbiting satellite links is 90 ° - (360 °/2N), where N is the number of node satellites in the inter-orbiting satellite link, and N ≧ 3.
14. The method of claim 10, wherein the number of the at least one ground station is determined according to the orbital height of the N orbital planes, the orbital inclination of the N orbital planes, and the elevation of the antenna cutoff of each ground station.
15. The method of claim 10, wherein the at least one ground station is 1 ground station, and the ground station is located in 80-90 ° south latitude area or 80-90 ° north latitude area.
16. The method for detecting, operating and controlling a low earth satellite constellation according to claim 10, wherein the at least one ground station is 2 or 3 ground stations, and the 2 or 3 ground stations are respectively disposed in different longitude regions with 50 ° to 80 ° south latitude and/or 50 ° to 80 ° north latitude.
17. The method according to any of claims 10-16, wherein the N inter-orbiting satellite links are laser links or microwave links.
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