CN112118040A - Method for connecting different-rail inter-satellite links - Google Patents
Method for connecting different-rail inter-satellite links Download PDFInfo
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- CN112118040A CN112118040A CN202010783024.4A CN202010783024A CN112118040A CN 112118040 A CN112118040 A CN 112118040A CN 202010783024 A CN202010783024 A CN 202010783024A CN 112118040 A CN112118040 A CN 112118040A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Abstract
The embodiment of the invention discloses a method for connecting different-rail inter-satellite links, which comprises the following steps: s10, the ground measurement and control station guides the satellite A and the adjacent orbit satellite B to establish a bidirectional inter-satellite communication link at an initial time T0; s30, mutually transmitting orbit parameters at the time of T0+ N.DELTA T by the satellite A and the satellite B with the period of DELTA T, and autonomously calculating the azimuth angle of the opposite satellite at the time of T0+ N.DELTA T through the orbit parameters; s50, the satellite A and the satellite B control respective antenna beams to point to the azimuth angle of the opposite satellite at the time T0+ N.DELTA T, and the inter-satellite communication link at the time T0+ N.DELTA T is continuously connected; wherein N is an integer greater than 0.
Description
Technical Field
The invention relates to the field of satellite communication, in particular to a method for connecting different-orbit inter-satellite links.
Background
In a low-earth-orbit satellite communication system, interconnection communication among satellites is often realized by configuring an inter-satellite link, and cross-regional transmission of user service data is realized. That is, in a satellite constellation, one satellite needs to establish an inter-satellite communication link (referred to as an inter-satellite link) with two satellites in the same orbit and two satellites in east-west adjacent orbits. An inter-satellite link established between satellites running on the same orbit is called as an inter-satellite link of the same orbit; the inter-satellite links established between satellites operating in different orbits are called inter-orbital inter-satellite links.
In order to reduce the power consumption of the antenna and increase the information transmission rate, the inter-satellite link usually adopts spot beams to realize point-to-point communication between satellites. Taking microwave communication as an example, because the relative position of the co-orbit operation satellite is fixed, the communication antenna can adopt a fixed installation mode, and the accurate pointing of the wave beam is ensured to establish an inter-satellite link through the satellite attitude control precision. Due to the fact that the azimuth angle (yaw angle and pitch angle) between two satellites of the different-orbit operation satellite is changed greatly, the point beam bidirectional accurate pointing is required to be achieved in the pitching and yawing directions through beam scanning to establish an inter-satellite link, and the beam scanning can be achieved through mechanical scanning and electrical scanning or a combination mode of the mechanical scanning and the electrical scanning.
The conventional method for establishing and maintaining the inter-satellite link of the satellite in the different orbits is as follows: after the satellite establishes an inter-satellite link through ground guidance, the ground injects precise orbit parameters of the satellite and left and right adjacent satellites to the satellite at a fixed time period, the satellite carries out three satellite orbit data recursion through a preset algorithm so as to calculate the beam pointing angle at intervals of t time, the satellite controls an antenna beam to reach a specified angle position, and the inter-satellite link is established with the adjacent satellites. The method needs the ground to inject accurate orbit parameters periodically in a short period, is used for correcting the deviation generated by orbit recursion on the satellite, and has high dependence on ground measurement and control.
Disclosure of Invention
To solve one of the above problems, an embodiment of the present invention provides an inter-star link connection method, including:
s10, the ground measurement and control station guides the satellite A and the adjacent orbit satellite B to establish a bidirectional inter-satellite communication link at an initial time T0;
s30, mutually transmitting orbit parameters at the time of T0+ N.DELTA T by the satellite A and the satellite B with a period of DELTA T, and autonomously calculating the azimuth angle of the opposite satellite at the time of T0+ N.DELTA T by the satellite A and the satellite B according to the orbit parameters at the time of T0+ N.DELTA T;
s50, the satellite A and the satellite B control respective antenna beams to point to the azimuth angle of the opposite satellite at the time T0+ N.DELTA T, and the inter-satellite communication link at the time T0+ N.DELTA T is continuously connected;
wherein N is an integer greater than 0. In a particular embodiment, S10 includes:
s101, the ground measurement and control station injects initial orbit parameters of the satellite and an adjacent orbit satellite B to the satellite A;
s103, the satellite A calculates an initial azimuth angle of the satellite B according to the orbit parameters of the two satellites;
s105, the satellite A controls the antenna beam of the satellite A to point to the position of the initial azimuth angle, so that the antenna beam of the satellite A is aligned with the satellite B;
s107, the satellite B obtains initial orbit parameters in the same way as the way of S101-S105, calculates the initial azimuth of the satellite A, controls the antenna beam of the satellite B to point to the initial azimuth and leads the antenna beam of the satellite B to be aligned with the satellite A;
s109, the satellite A and the satellite B respectively capture the opposite satellite beam, and a bidirectional inter-satellite communication link of an initial time T0 is established.
In a specific embodiment, the satellite a and the satellite B obtain the current orbit parameters at the time T0+ N · Δ T through on-satellite autonomous navigation positioning.
In a particular embodiment, the azimuth angle comprises a yaw angle and a pitch angle.
In a specific embodiment, the S50 further includes: the satellite A and the satellite B control the antenna beam to point to the azimuth position through beam scanning.
The invention has the following beneficial effects:
according to the method for connecting the inter-different-orbit satellite links, the inter-different-orbit satellite links can be continuously connected by autonomously interacting orbit information and autonomously calculating the antenna beam pointing angle, the dependence of satellite operation on ground measurement and control resources can be effectively reduced, and a solution is provided for efficient autonomous operation of low-orbit constellations.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 shows a flowchart of an inter-star link connection method according to an embodiment of the present invention.
Fig. 2 shows a schematic diagram of the relationship between the positions of two adjacent satellites and the inter-satellite link according to an embodiment of the invention.
Figure 3 illustrates an azimuth definition diagram according to one embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and is not to be taken as limiting the scope of the invention.
Example 1
As shown in fig. 1, a method for connecting inter-star links includes:
and S10, the ground measurement and control station guides the satellite A and the adjacent orbit satellite B to establish a bidirectional inter-satellite communication link at the initial time T0.
Fig. 2 is a schematic diagram showing a position relationship between a satellite a and an adjacent orbit satellite B and a link between two satellites, and it should be noted that the position relationship between the satellites in this embodiment is only for illustration, and the specific position relationship between the two satellites is not limited in the present invention.
S10 specifically includes the following steps:
s101, the ground measurement and control station injects orbit parameters of the satellite and an adjacent orbit satellite B to the satellite A;
s103, calculating the azimuth angle of the satellite B by the satellite A through two satellite orbit parameters;
as shown in fig. 3, the azimuth angle includes a yaw angle and a pitch angle, a spatial rectangular coordinate system is established with the centroid of the satellite a as the origin of coordinates, the X axis points to the flight speed direction of the satellite a, the Y axis points to the negative normal direction of the orbital plane of the satellite a, the Z axis points to the earth center direction, and the pitch angle is the included angle between the antenna beam vector and the projection thereof on the XOY platform; yaw is the angle between the projection of the antenna beam vector on the XOY platform and the OX axis.
S105, the satellite A controls the antenna beam of the satellite A to point to the position of the azimuth angle, so that the antenna beam of the satellite A is aligned with the satellite B;
s107, the satellite B obtains orbit parameters in the same way as the way of S101-S105, calculates the azimuth angle of the satellite A, controls the antenna beam of the satellite B to point to the azimuth angle, and leads the antenna beam of the satellite B to be aligned to the satellite A;
s109, the satellite A and the satellite B respectively capture the opposite satellite beam to realize communication, and a bidirectional inter-satellite communication link of the initial time T0 is established.
The azimuth angle (yaw angle and pitch angle) between two satellites has a large change, a point beam bidirectional accurate pointing is realized by beam scanning in the pitch and yaw directions to establish an inter-satellite link, and the beam scanning can be realized by mechanical scanning, electrical scanning or a combination mode of the two.
S30, the satellite A and the satellite B mutually transmit orbit parameters at the time of T0+ N.DELTA T by taking the DELTA T as a cycle, and the satellite A and the satellite B independently calculate the azimuth angle of the opposite satellite at the time of T0+ N.DELTA T according to the orbit parameters at the time of T0+ N.DELTA T.
The satellite A and the satellite B obtain respective current orbit parameters at the time T0+ N.DELTA T through on-satellite autonomous navigation positioning, orbit data are transmitted to the opposite satellite through an established inter-satellite communication link, and the satellite A calculates the azimuth angle (the yaw angle beta N and the pitch angle alpha N) of the satellite B through the orbit parameters of the two satellites at the time T0+ N.DELTA T (N is 1, 2 and 3 …). Satellite B calculates the azimuth of satellite a in the same manner.
The delta t represents the refresh rate of orbit data of the satellite of the other side, the influence of satellite attitude control precision, beam pointing deviation, satellite orbit determination precision, inter-satellite orbit information transmission delay, on-satellite data processing delay and the like on the beam pointing deviation needs to be comprehensively considered, and the beam pointing is ensured to meet the requirement of communication link allowance. When delta t selection enables link loss caused by beam pointing deviation not to exceed the margin of a link, the satellite can ensure stable, reliable and continuous connection of the inter-satellite communication link through beam scanning.
And S50, the satellite A and the satellite B control respective antenna beams to point to the azimuth angle of the opposite satellite at the time T0+ N.DELTA T, and the inter-satellite communication link at the time T0+ N.DELTA T is continuously connected.
The satellite A and the satellite B control the antenna beam to point to the azimuth position through beam scanning.
In one example, satellite a controls the antenna beam to point at the calculated azimuth position through beam scanning, so that the antenna beam is aligned with satellite B at time T0+ N · Δ T, and satellite B controls the antenna beam to be aligned with satellite a in the same manner, so that the inter-satellite communication link is continuously connected at time T0+ N · Δ T.
According to the method for connecting the inter-different-orbit satellite links, the inter-different-orbit satellite links can be continuously connected by autonomously interacting orbit information and autonomously calculating the antenna beam pointing angle, the dependence of satellite operation on ground measurement and control resources can be effectively reduced, and a solution is provided for efficient autonomous operation of low-orbit constellations.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (5)
1. A method for connecting inter-heterotactic star links, comprising:
s10, the ground measurement and control station guides the satellite A and the adjacent orbit satellite B to establish a bidirectional inter-satellite communication link at an initial time T0;
s30, mutually transmitting orbit parameters at the time of T0+ N.DELTA T by the satellite A and the satellite B with a period of DELTA T, and autonomously calculating the azimuth angle of the opposite satellite at the time of T0+ N.DELTA T by the satellite A and the satellite B according to the orbit parameters at the time of T0+ N.DELTA T;
s50, the satellite A and the satellite B control respective antenna beams to point to the azimuth angle of the opposite satellite at the time T0+ N.DELTA T, and the inter-satellite communication link at the time T0+ N.DELTA T is continuously connected;
wherein N is an integer greater than 0.
2. The method of claim 1, wherein S10 includes:
s101, the ground measurement and control station injects initial orbit parameters of the satellite and an adjacent orbit satellite B to the satellite A;
s103, the satellite A calculates an initial azimuth angle of the satellite B according to the orbit parameters of the two satellites;
s105, the satellite A controls the antenna beam of the satellite A to point to the position of the initial azimuth angle, so that the antenna beam of the satellite A is aligned with the satellite B;
s107, the satellite B obtains initial orbit parameters in the same way as the way of S101-S105, calculates the initial azimuth of the satellite A, controls the antenna beam of the satellite B to point to the initial azimuth and leads the antenna beam of the satellite B to be aligned with the satellite A;
s109, the satellite A and the satellite B respectively capture the opposite satellite beam, and a bidirectional inter-satellite communication link of an initial time T0 is established.
3. The method of claim 1, wherein the satellite a and the satellite B obtain orbit parameters of respective current time T0+ N · Δ T through on-board autonomous navigation positioning.
4. The method of claim 1, wherein the azimuth angle comprises a yaw angle and a pitch angle.
5. The method according to claim 1, wherein the S50 further comprises: the satellite A and the satellite B control the antenna beam to point to the azimuth position through beam scanning.
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