CN113872678B - Method for managing mobility of terminal in satellite - Google Patents
Method for managing mobility of terminal in satellite Download PDFInfo
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- CN113872678B CN113872678B CN202111213966.XA CN202111213966A CN113872678B CN 113872678 B CN113872678 B CN 113872678B CN 202111213966 A CN202111213966 A CN 202111213966A CN 113872678 B CN113872678 B CN 113872678B
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- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000007726 management method Methods 0.000 claims abstract description 7
- 238000012216 screening Methods 0.000 claims description 6
- 230000001174 ascending effect Effects 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 238000010586 diagram Methods 0.000 claims description 4
- 230000009466 transformation Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 238000004891 communication Methods 0.000 abstract description 9
- 230000004075 alteration Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- H04B7/18519—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
- H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
- H04B7/18539—Arrangements for managing radio, resources, i.e. for establishing or releasing a connection
- H04B7/18541—Arrangements for managing radio, resources, i.e. for establishing or releasing a connection for handover of resources
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- Engineering & Computer Science (AREA)
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- Astronomy & Astrophysics (AREA)
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- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention belongs to the technical field of low-orbit satellite communication, and particularly relates to a method for managing the mobility of an intra-satellite terminal, which comprises the following steps: the terminal acquires satellite orbit parameters and position parameters of the terminal, and transmits the acquired parameters to the satellite; the satellite predicts the state information of each wave beam of the satellite access terminal in a period of time according to the terminal position parameter and the satellite orbit parameter; when the terminal is in a state to be switched, the satellite sends a beam access request to an access network manager; after receiving the request, the access network manager sends an access reply to the satellite; after receiving the reply, the satellite sends a beam switching instruction to the terminal, and after receiving the beam switching instruction, the terminal confirms switching information to an access network manager; if the switching information is correct, carrying out beam switching, otherwise, not carrying out beam switching; the invention provides an intra-satellite terminal mobility management method, which is used for explaining intra-satellite beam switching of a low-orbit satellite coverage terminal for a period of time, and greatly improving the intra-satellite beam switching efficiency.
Description
Technical Field
The invention belongs to the technical field of low-orbit satellite communication, and particularly relates to an intra-satellite terminal mobility management method.
Background
Currently, low orbit satellite communication systems are an important research field for numerous scientific institutions, enterprises and universities. Compared with high-orbit satellite communication, the low-orbit satellite communication technology has great advantages in remote mountain areas, ocean-going remote areas or disaster areas, south-north poles and other areas where land communication is difficult to cover, and can better cover the world globally, so that the world-wide interconnection and intercommunication are realized.
The satellite and the user have movement conditions while the low orbit satellite constellation is running at high speed relative to the ground, so that the situation of switching between beam coverage areas occurs in the process of establishing connection by the user is caused. Therefore, in order to ensure the continuity of communication, a handover is required to ensure the continuation of the call. At present, most of the existing low-orbit satellite communication switching methods adopt hard switching or soft switching, and cannot realize rapid and uninterrupted soft-hard seamless switching. Therefore, a new low-orbit satellite communication switching method is urgently needed.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an intra-satellite terminal mobility management method, which comprises the following steps: acquiring satellite orbit parameters and position parameters of the terminal, and transmitting the acquired parameters to a satellite; the satellite predicts the state information of each wave beam of the satellite access terminal in a period of time according to the terminal position parameter and the satellite orbit parameter; when the terminal is in a state to be switched, the satellite sends a beam access request to an access network manager; after receiving the request, the access network manager sends an access reply to the satellite; after receiving the reply, the satellite sends a beam switching instruction to the terminal, and after receiving the beam switching instruction, the terminal confirms switching information to an access network manager and judges whether the current beam can provide time-frequency resources for the terminal to access; if the switching information is correct, beam switching is performed, otherwise, beam switching is not performed.
Preferably, the acquired satellite orbit parameters are six satellite orbit parameters (i, Ω, e, ω, M, a), wherein i represents the orbit inclination angle, Ω represents the right ascent and descent of the intersection point, e represents the orbit eccentricity, ω represents the near-point amplitude angle, M represents the plane-near point angle, and a represents the orbit semi-long axis; the position parameter of the terminal is geographic longitude and latitude high information (B, L, H) of the terminal, wherein B represents the latitude of the terminal, L represents the precision of the terminal, and H represents the altitude of the terminal.
Preferably, the satellite predicts the state information of each beam of the satellite in a period of time, and comprises: the satellite screens the received parameters; converting the position information of the terminal after screening and the position information of the satellite into coordinates under the same coordinate system; according to the directional diagram of the antenna and the relative position of the antenna and satellite installation, carrying out coordinate transformation to obtain the position coordinate of the phased array antenna under a satellite coordinate system; calculating the position of the current terminal relative to the phased array antenna according to the position coordinates of the terminal and the phased array antenna position coordinates; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the current position of the terminal relative to the phased array antenna, and calculating the information of each wave beam of the satellite access terminal in a period of time according to the coverage condition.
Further, the satellite screening the received parameters includes: the satellite deletes the repeated data in the received parameters and complements the incomplete data.
Further, the process of converting the position information of the terminal and the position information of the satellite into coordinates in the same coordinate system includes: converting the position parameters of the terminal into coordinates under a geocentric fixed coordinate system; converting the position parameters of the satellites into coordinates under a geocentric relation coordinate system; and converting the coordinates of the satellite under the geocentric relation coordinate system into coordinates of the satellite under the geocentric fixed coordinate system, and completing unification of the terminal coordinates and the satellite coordinates.
Further, the formula for converting the position parameter of the terminal into the coordinates in the geocentric fixed coordinate system is as follows:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e 2 )+H]sinB
wherein N represents a radius of a mortise circle, e represents a radius of a meridian circle, B represents a latitude of a terminal, L represents an accuracy of the terminal, and H represents an altitude of the terminal.
Further, the process of converting the position parameters of the satellites into coordinates in the geocentric fixed coordinate system includes: converting six parameters of the track into coordinates in a geocentric inertial coordinate system through a geocentric inertial coordinate system conversion formula; and rotating the coordinate under the geocentric inertial coordinate system clockwise around the Z axis by an omega angle to lead the X axis to point to the ascending intersection point, rotating the coordinate clockwise around the X axis by an i angle to lead the Z axis to be perpendicular to the equatorial plane, and finally rotating the coordinate clockwise around the Z axis by the omega angle to obtain the coordinate under the geocentric fixed coordinate system.
Further, the geocentric inertial coordinate system conversion formula is:
E＝M+esinE
X＝acosE-ae
Z＝0
preferably, the process of calculating the information of each beam access terminal of the satellite in a period of time according to the coverage condition comprises the following steps:
the invention provides an intra-satellite terminal mobility management method, which is used for explaining intra-satellite beam switching of a low-orbit satellite coverage terminal for a period of time, and greatly improving the intra-satellite beam switching efficiency.
Drawings
Fig. 1 is a schematic diagram of a switching method according to the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings, and the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by a person skilled in the art without any inventive effort, are intended to be within the scope of the present invention based on the embodiments of the present invention.
As shown in fig. 1, the method for managing mobility of an intra-satellite terminal includes: the terminal acquires satellite orbit parameters and position parameters of the terminal, and transmits the acquired parameters to the satellite; the satellite predicts the state information of each wave beam of the satellite access terminal in a period of time according to the terminal position parameter and the satellite orbit parameter; when the terminal is in a state to be switched, the satellite sends a beam access request to an access network manager; after receiving the request, the access network manager sends an access reply to the satellite; after receiving the reply, the satellite sends a beam switching instruction to the terminal, and after receiving the beam switching instruction, the terminal confirms switching information to an access network manager; and if the switching information is correct, carrying out beam switching, otherwise, not carrying out beam switching.
The satellite orbit parameters are six satellite orbit numbers (i, omega, e, omega, M and a), wherein i represents an orbit inclination angle, omega represents an ascending intersection point, an ascent and descent, e represents an orbit eccentricity, omega represents a near-site amplitude angle, M represents a plane near-point angle, and a represents an orbit semi-long axis; the position parameter of the terminal is geographic longitude and latitude high information (B, L, H) of the terminal, wherein B represents the latitude of the terminal, L represents the precision of the terminal, and H represents the altitude of the terminal.
The process of satellite predicting the state information of each wave beam access terminal of the satellite in a period of time comprises the following steps: the satellite screens the received parameters; converting the position information of the terminal after screening and the position information of the satellite into coordinates under the same coordinate system; acquiring phased array antenna port data carried by a satellite, and calculating an antenna pattern according to the phased array antenna port data; obtaining the position coordinates of the phased array antenna according to the antenna pattern; calculating the position of the current terminal relative to the phased array antenna according to the position coordinates of the terminal and the phased array antenna position coordinates; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the current position of the terminal relative to the phased array antenna, and calculating the information of each wave beam of the satellite access terminal in a period of time according to the coverage condition.
The satellite screening the received parameters includes: the satellite deletes the repeated data in the received parameters and complements the incomplete data.
Preferentially, the terminal coordinates (B, L, H) are converted into geocentric fixed coordinate system (ECF) coordinates (x, y, z) core formulas:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e 2 )+H]sinB
wherein N is the radius of the mortise circle, and e is the radius of the noon.
Six numbers (i, omega, e, omega, M, a) of the track are used for obtaining the geocentric inertial coordinate system (ECI) coordinateThe process comprises the steps of firstly calculating coordinates (X, Y, Z) of a satellite in an orbit coordinate system according to six numbers:
E＝M+esinE
X＝acosE-ae
Z＝0
then, rotating the angle omega clockwise around the Z axis to lead the X axis to point to the ascending intersection point, rotating the angle i clockwise around the X axis to lead the Z axis to be perpendicular to the equatorial plane, finally rotating the angle omega clockwise around the Z axis to obtain the ECI coordinate system, and setting the corresponding rotation matrix as R in sequence 1 ,R 2 ,R 3 Then the ECI coordinates are:
then converting the coordinates of the satellite under the ECI coordinate system into the coordinates under the ECF coordinate system, wherein the origin of the coordinates of the two coordinate systems is overlapped with the Z axis, the conversion can be realized only by rotating the coordinates of the ECI coordinate system around the Z axis by the Greenner angle, and the ECF coordinate is as follows:
and then a new coordinate system is established by taking the satellite as a center, and the (rho, theta, phi) coordinates of the terminal under the new coordinate system are calculated.
And calculating the directional diagram (phi, theta, gain) of the antenna according to the phased array antenna port data, and simultaneously calculating the coordinates of the phased antenna in a coordinate system centering on the satellite according to the position information of the antenna relative to the satellite, and calculating the position of the current terminal relative to the phased array antenna.
Preferably, the phased array antenna mounted on the low-orbit satellite is fixed in mounting position on the satellite.
The fixed mounting phased array antenna can generate beams in multiple directions, and the beam power can be matched to divide the beam coverage into 1km 3 Kilometer cells, each cell using (ρ, θ, ψ, beam Id [ N ]]，P BeamId [N]) The representation is cell-to-satellite distance, plane angle, pitch angle, beam normalized power, respectively, and there may be multiple beam coverage per cell.
Preferably, when the terminal accesses the satellite, the terminal only accesses one single beam at each time, and the terminal accesses a new beam immediately when the last beam is deleted.
Preferably, when a terminal accesses a beam, the terminal accesses the beam according to a signal quality priority principle.
Preferably, when the terminal accesses each wave beam, the switching condition among the accessed wave beams can be preset according to the satellite motion direction, and the switching process is combined with the wave beam signal quality and the access network controller according to the position state of the terminal to send a switching instruction so as to realize the intra-satellite wave beam switching.
The process of calculating the information of each wave beam access terminal of the satellite in a period of time according to the coverage condition comprises the following steps: projecting the pattern to the ground according to six satellite orbits, and calculating the coverage area of each beam of the satellite on the ground at each moment by combining the satellite motion direction and speed information; and according to the moving direction of each beam coverage area and the beam arrangement sequence, calculating the access and switching information of each beam in the satellite in the access process of the terminal by combining time.
While the foregoing is directed to embodiments, aspects and advantages of the present invention, other and further details of the invention may be had by the foregoing description, it will be understood that the foregoing embodiments are merely exemplary of the invention, and that any changes, substitutions, alterations, etc. which may be made herein without departing from the spirit and principles of the invention.
Claims (8)
1. An intra-satellite terminal mobility management method is characterized by comprising the following steps: acquiring satellite orbit parameters and position parameters of the terminal, and transmitting the acquired parameters to a satellite; the satellite predicts the state information of each wave beam of the satellite access terminal in a period of time according to the terminal position parameter and the satellite orbit parameter; when the terminal is in a state to be switched, the satellite sends a beam access request to an access network manager; after receiving the request, the access network manager sends an access reply to the satellite; after receiving the reply, the satellite sends a beam switching instruction to the terminal, and after receiving the beam switching instruction, the terminal confirms switching information to an access network manager; if the switching information is correct, carrying out beam switching, otherwise, not carrying out beam switching; the process of satellite predicting the state information of each wave beam access terminal of the satellite in a period of time comprises the following steps: the satellite screens the received parameters; converting the position information of the terminal after screening and the position information of the satellite into coordinates under the same coordinate system; according to the directional diagram of the antenna and the relative position of the antenna and satellite installation, carrying out coordinate transformation to obtain the position coordinate of the phased array antenna under a satellite coordinate system; calculating the position of the current terminal relative to the phased array antenna according to the position coordinates of the terminal and the phased array antenna position coordinates; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the current position of the terminal relative to the phased array antenna, and calculating the information of each wave beam of the satellite access terminal in a period of time according to the coverage condition.
2. The method for managing the mobility of an intra-satellite terminal according to claim 1, wherein the acquired satellite orbit parameters are six satellite orbits (i, Ω, e, ω, M, a), where i represents an orbit inclination angle, Ω represents an ascending intersection point right ascent, e represents an orbit eccentricity, ω represents a near-to-earth amplitude angle, M represents a near-to-earth angle, and a represents an orbit semi-major axis; the position parameter of the terminal is geographic longitude and latitude high information (B, L, H) of the terminal, wherein B represents the latitude of the terminal, L represents the precision of the terminal, and H represents the altitude of the terminal.
3. The method for mobility management of an intra-satellite terminal according to claim 1, wherein the satellite screening the received parameters comprises: the satellite deletes the repeated data in the received parameters and complements the incomplete data.
4. The method for managing mobility of an intra-satellite terminal according to claim 1, wherein the process of converting the position information of the terminal and the position information of the satellite into coordinates in the same coordinate system comprises: converting the position parameters of the terminal into coordinates under a geocentric fixed coordinate system; converting the position parameters of the satellites into coordinates under a geocentric relation coordinate system; and converting the coordinates of the satellite under the geocentric relation coordinate system into coordinates of the satellite under the geocentric fixed coordinate system, and completing unification of the terminal coordinates and the satellite coordinates.
5. The method for managing mobility of an intra-satellite terminal according to claim 4, wherein the formula for converting the location parameter of the terminal into coordinates in a geocentric fixed coordinate system is:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e 2 )+H]sinB
wherein N represents a radius of a mortise circle, e represents a radius of a meridian circle, B represents a latitude of a terminal, L represents an accuracy of the terminal, and H represents an altitude of the terminal.
6. The method for mobility management of an intra-satellite terminal according to claim 4, wherein the process of converting the position parameters of the satellite into coordinates in a geocentric fixed coordinate system comprises: converting six parameters of the track into coordinates in a geocentric inertial coordinate system through a geocentric inertial coordinate system conversion formula; and rotating the coordinate under the geocentric inertial coordinate system clockwise around the Z axis by an omega angle to lead the X axis to point to the ascending intersection point, rotating the coordinate clockwise around the X axis by an i angle to lead the Z axis to be perpendicular to the equatorial plane, and finally rotating the coordinate clockwise around the Z axis by the omega angle to obtain the coordinate under the geocentric fixed coordinate system.
7. The method for managing mobility of an intra-satellite terminal according to claim 6, wherein the geocentric inertial coordinate system transformation formula is:
E＝M+esinE
X＝acosE-ae
Z＝0
wherein E represents a near-spot angle, M represents a near-spot angle, E represents an eccentricity, and a represents a semi-long axis of the track.
8. The method for managing mobility of an intra-satellite terminal according to claim 1, wherein the step of calculating the information of each beam access terminal of the satellite for a period of time according to the coverage condition comprises: projecting the pattern to the ground according to six satellite orbits, and calculating the coverage area of each beam of the satellite on the ground at each moment by combining the satellite motion direction and speed information; and according to the moving direction of each beam coverage area and the beam arrangement sequence, calculating the access and switching information of each beam in the satellite in the access process of the terminal by combining time.
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| CN112929104A (en) * | 2021-01-02 | 2021-06-08 | 军事科学院系统工程研究院网络信息研究所 | Collinear interference estimation method for high-low orbit co-frequency coexisting satellite communication system |
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| CN109495156A (en) * | 2018-11-02 | 2019-03-19 | 航天科工空间工程发展有限公司 | A kind of low rail wideband satellite communication terminal antenna direction acquisition methods based on ephemeris |
| CN110940310A (en) * | 2019-11-15 | 2020-03-31 | 北京遥测技术研究所 | Calculation method for phased array antenna beam pointing angle of missile-borne relay measurement and control terminal |
| CN112054823A (en) * | 2020-09-10 | 2020-12-08 | 重庆邮电大学 | Low-earth-orbit satellite communication switching method |
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