CN113872678A - Intra-satellite terminal mobility management method - Google Patents
Intra-satellite terminal mobility management method Download PDFInfo
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- CN113872678A CN113872678A CN202111213966.XA CN202111213966A CN113872678A CN 113872678 A CN113872678 A CN 113872678A CN 202111213966 A CN202111213966 A CN 202111213966A CN 113872678 A CN113872678 A CN 113872678A
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- 238000000034 method Methods 0.000 claims abstract description 23
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- 230000001174 ascending effect Effects 0.000 claims description 3
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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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Abstract
The invention belongs to the technical field of low-orbit satellite communication, and particularly relates to an intra-satellite terminal mobility management method, which comprises the following steps: the method comprises the steps that a terminal obtains satellite orbit parameters and position parameters of the terminal and sends the obtained parameters to a satellite; the satellite predicts the state information of each wave beam access terminal of the satellite in the next 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; the network manager of the access network sends an access reply to the satellite after receiving the request; the satellite sends a beam switching instruction to the terminal after receiving the reply, and the beam switching instruction received by the terminal confirms switching information to the network management of the access network; if the switching information is correct, the beam switching is carried out, otherwise, the beam switching is not carried out; the invention provides an intra-satellite terminal mobility management method, which explains intra-satellite beam switching of a low-orbit satellite covering a terminal for a period of time, and greatly improves 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, the low earth orbit satellite communication system is a field of intensive research in many scientific research institutes, enterprises and colleges and universities. Compared with high-orbit satellite communication, the low-orbit satellite communication technology has great advantages in remote mountainous areas, remote areas such as ocean, disaster areas, south and north poles and other areas which are not easy to be covered by land communication, and can better cover the whole world and realize interconnection and intercommunication all over the world.
When the low earth orbit satellite constellation runs at a high speed relative to the ground, the satellite and the user both move, so that the situation of switching between beam coverage areas occurs in the process of establishing connection by the user. Therefore, to ensure the continuity of the communication, a handover is required to ensure the continuation of the call. At present, hard handover or soft handover is mostly adopted in the existing low-earth-orbit satellite communication handover method, and fast and uninterrupted soft-hard seamless handover cannot be realized. Therefore, a new method for switching low-earth-orbit satellite communication 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 the position parameters of a terminal, and sending the acquired parameters to a satellite; the satellite predicts the state information of each wave beam access terminal of the satellite in the next 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; the network manager of the access network sends an access reply to the satellite after receiving the request; the satellite sends a beam switching instruction to the terminal after receiving the reply, and the terminal confirms switching information to an access network manager after receiving the beam switching instruction and judges whether the current beam can provide time-frequency resources for the terminal to access; and if the switching information is correct, performing beam switching, otherwise, not performing beam switching.
Preferably, the acquired satellite orbit parameters are six satellite orbit numbers (i, Ω, e, ω, M, a), where i represents an orbit inclination angle, Ω represents a ascension of a rising intersection point, e represents an orbit eccentricity, ω represents an amplitude angle of a near point, M represents an average near point angle, and a represents an orbit semi-major axis; the position parameter of the terminal is geographical latitude and longitude height 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 process of the satellite predicting the state information of each beam access terminal of the satellite in the next period of time includes: the satellite screens the received parameters; converting the position information of the screened terminal and the position information of the satellite into coordinates in the same coordinate system; according to the directional diagram of the antenna and the relative position of the antenna and the satellite, performing coordinate conversion 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 coordinate of the terminal and the position coordinate of the phased array antenna; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the position of the current terminal relative to the phased array antenna, and calculating the information of each wave beam access terminal of the satellite in a period of time according to the coverage condition.
Further, the satellite screening the received parameters includes: the satellite deletes repeated data in the received parameters and completes 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 satellite into coordinates in a geocentric relationship coordinate system; and converting the coordinates under the earth-center relation coordinate system of the satellite into coordinates under the earth-center fixed coordinate system, and completing the unification of the terminal coordinates and the satellite coordinates.
Further, a formula for converting the position parameter of the terminal into a coordinate under a geocentric fixed coordinate system is as follows:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e2)+H]sinB
wherein, N represents the radius of the prime circle, e represents the radius of the prime circle, B represents the latitude of the terminal, L represents the precision of the terminal, and H represents the altitude of the terminal.
Further, the process of converting the position parameters of the satellite into coordinates in the geocentric fixed coordinate system includes: converting the six-number-of-track parameter into a coordinate under a geocentric inertial coordinate system through a geocentric inertial coordinate system conversion formula; and rotating the coordinates under the geocentric inertial coordinate system clockwise by an angle omega around the Z axis to enable the X axis to point to the ascending point, rotating the coordinates by an angle i around the X axis clockwise to enable the Z axis to be vertical to the equatorial plane, and finally rotating the coordinates by an angle omega around the Z axis clockwise to obtain the coordinates under the geocentric fixed coordinate system.
Further, the geocentric inertial coordinate system is converted into the following formula:
E＝M+esinE
X＝acosE-ae
Z＝0
preferably, the process of calculating the information of each beam access terminal of the satellite in the next period of time according to the coverage condition includes:
the invention provides an intra-satellite terminal mobility management method, which explains intra-satellite beam switching of a low-orbit satellite covering a terminal for a period of time, and greatly improves intra-satellite beam switching efficiency.
Drawings
Fig. 1 is a schematic diagram of a handover 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 a part of the embodiments of the present invention, but not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
An intra-satellite terminal mobility management method, as shown in fig. 1, includes: the method comprises the steps that a terminal obtains satellite orbit parameters and position parameters of the terminal and sends the obtained parameters to a satellite; the satellite predicts the state information of each wave beam access terminal of the satellite in the next 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; the network manager of the access network sends an access reply to the satellite after receiving the request; the satellite sends a beam switching instruction to the terminal after receiving the reply, and the beam switching instruction received by the terminal confirms switching information to the network management of the access network; and if the switching information is correct, performing beam switching, otherwise, not performing beam switching.
The satellite orbit parameters are six satellite orbit numbers (i, omega, e, omega, M, a), wherein i represents an orbit inclination angle, omega represents a ascension of a rising intersection point, e represents an orbit eccentricity, omega represents an amplitude angle of a near place, M represents an average near point angle, and a represents an orbit semi-major axis; the position parameter of the terminal is geographical latitude and longitude height 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 the satellite for predicting the state information of each beam access terminal of the satellite in the next period of time comprises the following steps: the satellite screens the received parameters; converting the position information of the screened terminal and the position information of the satellite into coordinates in the same coordinate system; acquiring satellite-carried phased array antenna port data, and calculating a directional diagram of an antenna according to the phased array antenna port data; obtaining the position coordinates of the phased array antenna according to the directional diagram of the antenna; calculating the position of the current terminal relative to the phased array antenna according to the position coordinate of the terminal and the position coordinate of the phased array antenna; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the position of the current terminal relative to the phased array antenna, and calculating the information of each wave beam access terminal of the satellite in a period of time according to the coverage condition.
The satellite screening the received parameters comprises: the satellite deletes repeated data in the received parameters and completes incomplete data.
Preferably, the terminal coordinates (B, L, H) are converted into the centroid fixed coordinate system (ECF) coordinates (x, y, z) core formula:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e2)+H]sinB
wherein, N is the radius of the unitary mortise and e is the radius of the meridian.
Six orbit numbers (i, omega, e, omega, M, a) obtain the coordinates of the earth center inertial coordinate system (ECI)
Firstly, calculating the coordinates (X, Y, Z) of the satellite in the orbital coordinate system according to six numbers:
E＝M+esinE
X＝acosE-ae
Z＝0
rotating clockwise the angle omega around the Z axis to make the X axis point to the ascending point, rotating clockwise the angle i around the X axis to make the Z axis perpendicular to the equatorial plane, and finally rotating clockwise the angle omega around the Z axis to obtain the ECI coordinate system, and setting the corresponding rotation matrixes as R in sequence1,R2,R3Then the ECI coordinates are:
then, the coordinates of the satellite in the ECI coordinate system are converted into coordinates in the ECF coordinate system, the coordinate origin and the Z axis of the two coordinate systems are superposed, the conversion can be realized only by rotating the coordinates of the ECI coordinate system around the Z axis by a Greenwich mean time angle, and if the rotation matrix is R, the ECF coordinates are as follows:
and then establishing a new coordinate system by taking the satellite as a center, and calculating the (rho, theta, psi) coordinates of the terminal under the new coordinate system.
And calculating a directional diagram (phi, theta, gain) of the antenna according to the port data of the phased array antenna, calculating the coordinate of the phased antenna under a coordinate system with the satellite as the center 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 earth orbit satellite is fixed in position on the satellite.
The fixed phase array antenna can generate wave beams along a plurality of directions, the wave beam power can be matched, and the wave beam coverage is divided into 1km3Kilometer cells, each cell using (rho, theta, psi, BeamId [ N ]]，PBeamId[N]) Indicating cell-to-satellite distance, plane angle, pitch angle, normalized power of the beam, respectively, and there may be multiple beam coverage for each cell.
Preferably, when the terminal accesses the satellite, the terminal accesses only one single beam at a time, and the terminal accesses a new beam immediately upon deleting the last beam.
Preferably, when the terminal accesses the beam, the terminal accesses the beam according to the signal quality priority principle.
Preferably, when the terminal accesses each beam, the switching situation between each accessed beam can be preset according to the satellite motion direction, and the switching is performed according to the terminal position state, the beam signal quality and the access network controller to send a switching instruction in the switching process, so as to implement the intra-satellite beam switching.
The process of calculating the information of each beam access terminal of the satellite in a next period of time according to the coverage condition comprises the following steps: projecting the directional diagram to the ground according to six satellite orbits, and calculating the coverage area of each wave beam of the satellite on the ground at each moment by combining the satellite movement direction and the speed information; and calculating the access and switching information of each beam in the satellite in the access process of the terminal by combining time according to the moving direction and the beam arrangement sequence of each beam coverage area.
The above-mentioned embodiments, which further illustrate the objects, technical solutions and advantages of the present invention, should be understood that the above-mentioned embodiments are only preferred embodiments of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalents, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An intra-satellite terminal mobility management method is characterized by comprising the following steps: acquiring satellite orbit parameters and the position parameters of a terminal, and sending the acquired parameters to a satellite; the satellite predicts the state information of each wave beam access terminal of the satellite in the next 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; the network manager of the access network sends an access reply to the satellite after receiving the request; the satellite sends a beam switching instruction to the terminal after receiving the reply, and the terminal confirms switching information to an access network manager after receiving the beam switching instruction; and if the switching information is correct, performing beam switching, otherwise, not performing beam switching.
2. The method of claim 1, wherein the acquired satellite orbit parameters are six satellite orbit parameters (i, Ω, e, ω, M, a), where i represents an orbit inclination angle, Ω represents a ascension point, e represents an orbit eccentricity, ω represents an argument of a near place, M represents an angle of a mean near point, and a represents a semi-major axis of an orbit; the position parameter of the terminal is geographical latitude and longitude height 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 of claim 1, wherein the step of predicting the state information of each beam access terminal of the satellite in the next period of time comprises: the satellite screens the received parameters; converting the position information of the screened terminal and the position information of the satellite into coordinates in the same coordinate system; according to the directional diagram of the antenna and the relative position of the antenna and the satellite, performing coordinate conversion 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 coordinate of the terminal and the position coordinate of the phased array antenna; and obtaining the coverage condition of each wave beam of the low-orbit satellite to the terminal according to the position of the current terminal relative to the phased array antenna, and calculating the information of each wave beam access terminal of the satellite in a period of time according to the coverage condition.
4. The method of claim 3, wherein the satellite screening the received parameters comprises: the satellite deletes repeated data in the received parameters and completes incomplete data.
5. The method for managing mobility of the terminal in the satellite according to claim 3, wherein the step 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 satellite into coordinates in a geocentric relationship coordinate system; and converting the coordinates under the earth-center relation coordinate system of the satellite into coordinates under the earth-center fixed coordinate system, and completing the unification of the terminal coordinates and the satellite coordinates.
6. The method for managing mobility of the intra-satellite terminal according to claim 5, wherein the formula for converting the location parameter of the terminal into the coordinate of the geocentric fixed coordinate system is as follows:
x＝(N+H)cosBcosL
y＝(N+H)cosBsinL
z＝[N(1-e2)+H]sinB
wherein, N represents the radius of the prime circle, e represents the radius of the prime circle, B represents the latitude of the terminal, L represents the precision of the terminal, and H represents the altitude of the terminal.
7. The method for managing mobility of the intra-satellite terminal according to claim 5, wherein the step of converting the position parameters of the satellite into coordinates in the geocentric fixed coordinate system comprises: converting the six-number-of-track parameter into a coordinate under a geocentric inertial coordinate system through a geocentric inertial coordinate system conversion formula; and rotating the coordinates under the geocentric inertial coordinate system clockwise by an angle omega around the Z axis to enable the X axis to point to the ascending point, rotating the coordinates by an angle i around the X axis clockwise to enable the Z axis to be vertical to the equatorial plane, and finally rotating the coordinates by an angle omega around the Z axis clockwise to obtain the coordinates under the geocentric fixed coordinate system.
8. The method for managing mobility of the intra-satellite terminal according to claim 7, wherein the geocentric inertial coordinate system is transformed into a formula:
E＝M+esinE
X＝acosE-ae
Z＝0
wherein E represents the off-center point angle, M represents the mean-near point angle, E represents the eccentricity, and a represents the semi-major axis of the orbit.
9. The method of claim 3, wherein the step of calculating the access terminal information of each beam of the satellite for the next period of time according to the coverage condition comprises: projecting the directional diagram to the ground according to six satellite orbits, and calculating the coverage area of each wave beam of the satellite on the ground at each moment by combining the satellite movement direction and the speed information; and calculating the access and switching information of each beam in the satellite in the access process of the terminal by combining time according to the moving direction and the beam arrangement sequence of each beam coverage area.
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| CN115314102A (en) * | 2022-09-29 | 2022-11-08 | 中国电子科技集团公司第五十四研究所 | Mobile switching management method suitable for multi-satellite networking |
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