CN115941032B - Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion - Google Patents
Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion Download PDFInfo
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- CN115941032B CN115941032B CN202310021606.2A CN202310021606A CN115941032B CN 115941032 B CN115941032 B CN 115941032B CN 202310021606 A CN202310021606 A CN 202310021606A CN 115941032 B CN115941032 B CN 115941032B
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Abstract
The invention belongs to the technical field of wireless communication, and particularly relates to a Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion.
Description
Technical Field
The invention belongs to the technical field of wireless communication, and particularly relates to a Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion.
Background
In low orbit satellite communication, because of the rapid movement of the satellite, the satellite position and the beam position are rapidly changed, and the wireless transmission between the satellite and the terminal generates larger Doppler frequency offset; for satellite communication investigation systems, frequency correction is required for multiple satellites, multiple beams and multiple terminals.
At present, the Doppler correction of the low orbit satellite is mainly calculated and corrected by using ephemeris:
calculating basic information of the service satellite in the current area according to the ephemeris information and the star operation information of the satellite;
doppler calculation is carried out according to the position information between the satellite and the receiver, so as to obtain frequency offset information;
and carrying out frequency offset correction on communication between the terminal and the satellite by using the frequency offset information between the satellite and the receiver.
Then, the satellite orbit information is required to be continuously updated depending on Doppler correction of the ephemeris, so that the time-dependent correction method has higher time-dependent requirements on the ephemeris and time precision.
The Doppler deviation correction is carried out by depending on the ephemeris, satellite orbit information is required to be updated at the moment (the moment is required to be connected with the Internet, and the ephemeris data is updated), and meanwhile, the clock synchronization requirement on a receiver is high (the clock requirement and the satellite synchronization) and is seriously dependent on external input, and most receiver equipment cannot meet the requirement of the moment connection with the Internet and the clock synchronization.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion, which aims to solve the problem that the prior art is seriously dependent on external input.
In order to solve the technical problems, the invention adopts the following technical scheme:
a Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion comprises the following steps:
step 1: acquiring unidirectional channel information of a satellite;
step 2: analyzing the unidirectional channel information to obtain GPS information of satellites and beam centers;
step 3: analyzing the unidirectional channel information to obtain the wireless signal spectrum information of the unidirectional channel, and calculating the frequency offset information between the current satellite and the receiver based on the satellite GPS information analyzed in the step 2;
step 4: acquiring broadcast information, carrying out frequency offset correction according to the frequency spectrum characteristics of the broadcast information, and carrying out small-range adjustment on the frequency offset information in the step 3 by using the frequency offset information of the broadcast information;
step 5: acquiring an uplink signal of a terminal, estimating a wave speed service area where the terminal is positioned based on the acquired uplink signal, and further calculating the distance between the terminal and a receiver;
step 6: based on the distance between the terminal and the receiver obtained in the step 5, the preliminary frequency offset of the beam service area where the terminal is located is calculated discretely according to a Doppler formula;
step 7: and carrying out fitting smooth calculation based on the initial frequency offset of the terminal and the newly received satellite signals to obtain accurate frequency offset information between the satellite and the terminal.
The invention analyzes satellite GPS information based on a unidirectional channel, corrects the frequency offset according to broadcast information, estimates the terminal area based on uplink signaling of the terminal, and finally obtains accurate frequency offset information between the satellite and the terminal, so that the invention does not depend on external ephemeris for calculation, ensures the independence of a system, calculates the frequency offset between the terminal and the satellite, not only between a receiver and the satellite, and has high accuracy of the frequency offset information obtained by calculation.
Specifically, the calculation formula of the frequency offset information in the step 3 is as follows:
F d = F rx -F tx ；
wherein: f (F) d Frequency offset information between the current satellite and the receiver; f (F) rx The frequency of the satellite burst signal received by the receiver; f (F) tx Is the theoretical frequency of the burst signal transmitted by the satellite.
Preferably, the step 4 includes the steps of:
step 4.1: acquiring broadcast information, and performing preliminary correction on the broadcast according to the frequency offset information acquired in the step 3 to acquire a preliminary correction result;
step 4.2: and carrying out micro deviation correction on the deviation correction result according to the broadcast frequency spectrum characteristics.
Preferably, the step 5 includes the steps of:
step 5.1: acquiring an uplink signal of a terminal, and analyzing the uplink signal to obtain position area code information in the uplink signal of the terminal;
step 5.2: calculating the grating of the terminal on the beam according to the grating information covered by the beam based on the GPS information of the beam center obtained in the step 2 and the position area code information obtained in the step 5.1;
step 5.3: and (5) calculating the distance between the terminal and the receiver according to the grating of the beam where the terminal is obtained in the step 5.2.
Preferably, the step 6 includes the steps of:
step 6.1: calculating preliminary GPS information of the terminal according to the distance between the terminal and the receiver obtained in the step 5 and the GPS information of the beam center obtained in the step 2;
step 6.2: based on the preliminary GPS information of the terminal, the GPS information of the satellite and the running direction of the satellite, the preliminary frequency offset of the terminal is obtained according to a Doppler formula.
Specifically, the doppler formula is as follows:
F d = F*V*cos(a)/C；
wherein: f (F) d The initial frequency offset of the terminal; f is the signal center frequency; v is the satellite speed, a is the included angle between the satellite motion direction and the terminal, and C is the light speed.
Preferably, the fitting smoothing calculation performs mean smoothing according to a change curve of the terminal frequency offset and a frequency offset curve of the unidirectional channel.
The beneficial effects of the invention include:
the invention analyzes satellite GPS information based on a unidirectional channel, corrects the frequency offset according to broadcast information, estimates the terminal area based on uplink signaling of the terminal, and finally obtains accurate frequency offset information between the satellite and the terminal, so that the invention does not depend on external ephemeris for calculation, ensures the independence of a system, calculates the frequency offset between the terminal and the satellite, not only between a receiver and the satellite, and has high accuracy of the frequency offset information obtained by calculation.
Drawings
Fig. 1 is a diagram of a signal acquisition link of the present invention.
Detailed Description
For the purposes of making the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, which are generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, as provided in the accompanying drawings, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, are intended to be within the scope of the present application.
The invention is described in further detail below with reference to fig. 1:
a Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion comprises the following steps:
step 1: acquiring unidirectional channel information of a satellite;
step 2: analyzing the unidirectional channel information to obtain GPS information of satellites and beam centers;
step 3: analyzing the unidirectional channel information to obtain the wireless signal spectrum information of the unidirectional channel, and calculating the frequency offset information between the current satellite and the receiver based on the satellite GPS information analyzed in the step 2;
certain types of data of unidirectional channels are fixed, assumed to be F tx When the signal reaches the receiver, the frequency of the burst signal of the data type received by the receiver is F rx The calculation formula of the frequency offset information in the step 3 is as follows:
F d = F rx -F tx ；
wherein: f (F) d Frequency offset information between the current satellite and the receiver; f (F) rx The frequency of the satellite burst signal received by the receiver; f (F) tx Is the theoretical frequency of the burst signal transmitted by the satellite.
Step 4: acquiring broadcast information, carrying out frequency offset correction according to the frequency spectrum characteristics of the broadcast information, and carrying out small-range adjustment on the frequency offset information in the step 3 by using the frequency offset information of the broadcast information;
the step 4 comprises the following steps:
step 4.1: acquiring broadcast information, and performing preliminary correction on the broadcast according to the frequency offset information acquired in the step 3 to acquire a preliminary correction result;
step 4.2: and carrying out micro deviation correction on the deviation correction result according to the broadcast frequency spectrum characteristics.
The broadcast information is located at a certain relative offset position in a certain frequency range, for example, in the frequency range of [ 1000-2000 ], the frequency is divided into 10 frequency points, and the broadcast information is fixedly located on the 8 th frequency point; and after receiving the broadcast, performing preliminary correction on the broadcast according to the frequency offset information calculated in the third step, and performing micro correction according to the frequency spectrum characteristics of the broadcast.
Step 5: acquiring an uplink signal of a terminal, estimating a wave speed service area where the terminal is positioned based on the acquired uplink signal, and further calculating the distance between the terminal and a receiver;
said step 5 comprises the steps of:
step 5.1: acquiring an uplink signal of a terminal, and analyzing the uplink signal to obtain position area code information in the uplink signal of the terminal;
step 5.2: calculating the grating of the terminal on the beam according to the grating information covered by the beam based on the GPS information of the beam center obtained in the step 2 and the position area code information obtained in the step 5.1;
step 5.3: and (5) calculating the distance between the terminal and the receiver according to the grating of the beam where the terminal is obtained in the step 5.2.
Step 6: based on the distance between the terminal and the receiver obtained in the step 5, the preliminary frequency offset of the beam service area where the terminal is located is calculated discretely according to a Doppler formula;
the step 6 comprises the following steps:
step 6.1: calculating preliminary GPS information of the terminal according to the distance between the terminal and the receiver obtained in the step 5 and the GPS information of the beam center obtained in the step 2;
step 6.2: based on the preliminary GPS information of the terminal, the GPS information of the satellite and the running direction of the satellite, the preliminary frequency offset of the terminal is obtained according to a Doppler formula.
The Doppler formula is as follows:
F d = F*V*cos(a)/C；
wherein: f (F) d The initial frequency offset of the terminal; f is the signal center frequency; v is the satellite speed, a is the included angle between the satellite motion direction and the terminal, and C is the light speed.
Step 7: and carrying out fitting smooth calculation based on the initial frequency offset of the terminal and the newly received satellite signals to obtain accurate frequency offset information between the satellite and the terminal.
And performing mean smoothing according to the change curve of the terminal frequency offset and the frequency offset curve of the unidirectional channel by fitting smoothing calculation.
The invention analyzes satellite GPS information based on a unidirectional channel, corrects the frequency offset according to broadcast information, estimates the terminal area based on uplink signaling of the terminal, and finally obtains accurate frequency offset information between the satellite and the terminal, so that the invention does not depend on external ephemeris for calculation, ensures the independence of a system, calculates the frequency offset between the terminal and the satellite, not only between a receiver and the satellite, and has high accuracy of the frequency offset information obtained by calculation.
The foregoing examples merely represent specific embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the present application. It should be noted that, for those skilled in the art, several variations and modifications can be made without departing from the technical solution of the present application, which fall within the protection scope of the present application.
Claims (6)
1. The Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion is characterized by comprising the following steps:
step 1: acquiring unidirectional channel information of a satellite;
step 2: analyzing the unidirectional channel information to obtain GPS information of satellites and beam centers;
step 3: analyzing the unidirectional channel information to obtain the wireless signal spectrum information of the unidirectional channel, and calculating the frequency offset information between the current satellite and the receiver based on the satellite GPS information analyzed in the step 2;
step 4: acquiring broadcast information, wherein the broadcast information is positioned at a certain relative offset position in a certain frequency range, carrying out frequency offset correction on the broadcast frequency offset information according to the frequency spectrum characteristics of the broadcast information, and adjusting the frequency offset information in the step 3 by using the frequency offset information of the broadcast information;
step 5: acquiring an uplink signal of a terminal, estimating a beam service area where the terminal is positioned based on the acquired uplink signal, and further calculating the distance between the terminal and a receiver;
step 6: based on the distance between the terminal and the receiver obtained in the step 5, the preliminary frequency offset of the beam service area where the terminal is located is calculated discretely according to a Doppler formula;
step 7: and performing fitting smooth calculation based on the preliminary frequency offset of the terminal and the adjusted frequency offset information to obtain accurate frequency offset information between the satellite and the terminal.
2. The doppler correction method based on multi-carrier space-time trajectory multi-feature fusion according to claim 1, wherein the calculation formula of the frequency offset information in the step 3 is as follows:
F d1 = F rx -F tx ；
wherein: f (F) d1 Frequency offset information between the current satellite and the receiver; f (F) rx The frequency of the satellite burst signal received by the receiver; f (F) tx Is the theoretical frequency of the burst signal transmitted by the satellite.
3. The doppler correction method based on multi-carrier space-time trajectory multi-feature fusion according to claim 1, wherein the step 5 comprises the steps of:
step 5.1: acquiring an uplink signal of a terminal, and analyzing the uplink signal to obtain position area code information in the uplink signal of the terminal;
step 5.2: calculating the grating of the terminal on the beam according to the grating information covered by the beam based on the GPS information of the beam center obtained in the step 2 and the position area code information obtained in the step 5.1;
step 5.3: and (5) calculating the distance between the terminal and the receiver according to the grating of the beam where the terminal is obtained in the step 5.2.
4. The doppler correction method based on multi-carrier space-time trajectory multi-feature fusion according to claim 1, wherein the step 6 comprises the steps of:
step 6.1: calculating preliminary GPS information of the terminal according to the distance between the terminal and the receiver obtained in the step 5 and the GPS information of the beam center obtained in the step 2;
step 6.2: based on the preliminary GPS information of the terminal, the GPS information of the satellite and the running direction of the satellite, the preliminary frequency offset of the terminal is obtained according to a Doppler formula.
5. The method for doppler correction based on multi-carrier space-time trajectory multi-feature fusion according to claim 4, wherein the doppler formula is as follows:
F d2 = F*V*cos(a)/C；
wherein: f (F) d2 The initial frequency offset of the terminal; f is the signal center frequency; v is the satellite speed, a is the included angle between the satellite motion direction and the terminal, and C is the light speed.
6. The Doppler deviation rectifying method based on multi-carrier space-time track multi-feature fusion according to claim 1, wherein the fitting smoothing calculation is used for carrying out mean smoothing according to a change curve of terminal frequency offset and a frequency offset curve of a unidirectional channel.
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| CN109525330A (en) * | 2018-09-27 | 2019-03-26 | 南京凯瑞得信息科技有限公司 | Calibrating frequency method based on satellite motion and position frequency deviation |
| CN114244418A (en) * | 2021-11-12 | 2022-03-25 | 华为技术有限公司 | Frequency offset compensation method and device |
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| GB2332111A (en) * | 1997-09-06 | 1999-06-09 | Ico Services Ltd | Compensating for motion in satellite telephone handset |
| US6058306A (en) * | 1998-11-02 | 2000-05-02 | Hughes Electronics Corporation | Compensation of dynamic doppler frequency of large range in satellite communication systems |
| GB2352347A (en) * | 1999-07-22 | 2001-01-24 | Ico Services Ltd | Location of a user terminal in a satellite and earth station network |
| CN101753492A (en) * | 2008-12-03 | 2010-06-23 | 中兴通讯股份有限公司 | Method and system for correcting frequency offset of mobile communication terminal |
| WO2020089471A1 (en) * | 2018-11-02 | 2020-05-07 | Telefonaktiebolaget Lm Ericsson (Publ) | Frequency offset in non-terrestrial networks |
| CN110545247B (en) * | 2019-07-31 | 2021-09-21 | 成都天奥集团有限公司 | Low earth orbit satellite multi-carrier communication system downlink carrier frequency offset estimation and compensation method |
| CN114337769A (en) * | 2020-09-28 | 2022-04-12 | 华为技术有限公司 | Frequency compensation method and frequency compensation device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109525330A (en) * | 2018-09-27 | 2019-03-26 | 南京凯瑞得信息科技有限公司 | Calibrating frequency method based on satellite motion and position frequency deviation |
| CN114244418A (en) * | 2021-11-12 | 2022-03-25 | 华为技术有限公司 | Frequency offset compensation method and device |
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