CN115189754A - Antenna alignment supplement method based on terahertz communication between co-orbiting satellites - Google Patents
Antenna alignment supplement method based on terahertz communication between co-orbiting satellites 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
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/90—Non-optical transmission systems, e.g. transmission systems employing non-photonic corpuscular radiation
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Abstract
The invention discloses an antenna alignment supplementing method based on terahertz communication between co-orbiting satellites, and belongs to the technical field of satellite communication. Under the condition that a servo system is not provided, the terahertz satellite communication system utilizes the fine adjustment of the satellite attitude and takes software as supplement to determine the optimal alignment state of the antenna. The fine tuning attitude of the satellite adopts a cross scanning mode, a transmitting terminal transmits a single carrier signal, and two satellites successively carry out cross scanning. The test data is subjected to a series of operations (such as filtering, FFT, down-sampling detection and the like) on the satellite and on the ground, the receiving satellite processes the data, loads time information, frames and downloads the data, the time information is matched with remote control and remote measurement information downloaded to the ground, the corresponding two-satellite attitude of the strongest point of the signal, namely the antenna alignment state is found out, the attitude information is transmitted to a satellite measurement and control center, the satellite measurement and control center is adjusted to the optimal attitude of the satellite, then the terahertz load is switched to the normal communication state, and the unidirectional information transmission of the terahertz load between the two satellites is completed.
Description
Technical Field
The invention relates to the technical field of satellite communication, in particular to an antenna alignment supplementing method based on terahertz communication between co-orbit satellites.
Background
Terahertz generally refers to frequencies in the electromagnetic spectrum of 0.1 ～ Electromagnetic band in the range of 10 THz. The terahertz wave is between microwave millimeter wave and infrared, is in a transition region from a macroscopic theory to a microscopic quantum theory, and is in a crossing region of electronics and photonics, and special properties different from those of other wave bands are determined by special positions.
Compared with microwave communication, terahertz communication has the following advantages: 1) The bandwidth resource is rich, and the communication capacity is larger; 2) The terahertz waves are completely absorbed by the atmosphere and cannot reach the earth surface, so that the terahertz waves have better confidentiality and anti-interference capability; 3) The terahertz wave wavelength is relatively shorter, the size of the antenna can be smaller under the condition of finishing the same function, the transceiving component can also be simpler, the weight and the size of a communication system can be reduced, and the terahertz wave antenna is suitable for being carried by an aircraft.
For laser communication, the advantages of terahertz communication are: 1) The terahertz wave with photon energy about 1/40 of that of visible light is used as an information carrier, so that the energy efficiency is higher, and the terahertz wave is suitable for a space platform with limited energy; 2) The wave beam of the terahertz signal is relatively wide and can reach several milliradians, and the design difficulty of an acquisition and tracking system (APT) is simplified.
Disclosure of Invention
The invention relates to a method for aligning antennas by utilizing satellite attitude fine tuning and communication software under the condition of no antenna servo tracking system aiming at terahertz communication between co-orbit satellites.
The technical scheme adopted by the invention is as follows:
an antenna alignment supplementing method based on terahertz communication between co-orbiting satellites comprises the following steps:
(1) The satellite measurement and control center fixes the receiving satellite, controls the transmitting satellite to transmit a single carrier signal, and simultaneously controls the transmitting satellite to scan along the direction of the X axis I and scan along the direction of the Y axis I;
(2) Receiving satellite receiving signals, carrying out down-conversion and demodulation on the received signals, transmitting the demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain the track of the signal-to-noise ratio of the transmitting satellite along with the change of time and attitude;
(3) The ground station analyzes and processes the track to obtain the optimal attitude information of the launching satellite;
(4) The satellite measurement and control center fixes the transmitting satellite, controls the receiving satellite to transmit a single carrier signal, and controls the receiving satellite to scan along the direction of the X axis I and scan along the direction of the Y axis I;
(5) Transmitting satellite receiving signals, carrying out down-conversion and demodulation on the received signals, transmitting the demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain the track of the signal-to-noise ratio of the receiving satellite along with the change of time and attitude;
(6) The ground station analyzes and processes the track to obtain the optimal attitude information of the receiving satellite, and transmits the optimal attitude information of the transmitting satellite and the optimal attitude information of the receiving satellite to a satellite measurement and control center;
(7) The satellite measurement and control center carries out two-satellite attitude adjustment according to information transmitted by the ground station, and adjusts the transmitting satellite and the receiving satellite to the optimal attitude.
Further, the received signals are down-converted and demodulated in the step (2) and the step (5), the demodulated data are transmitted to the ground station through a satellite-to-ground link, the ground station processes the received data, and a track of the signal-to-noise ratio changing along with time and attitude is calculated, wherein the specific process comprises the following steps:
(101) Carrying out A/D sampling on a received signal, and carrying out polyphase filtering, synthesis and CIC down-sampling;
(102) Adding time information to the real-time data subjected to down-sampling and framing;
(103) Performing channel coding modulation on the framed data, sending the data to an on-satellite feed link, and transmitting the data to a ground station through the on-satellite feed link in real time;
(104) After demodulating and receiving the received data, the ground station carries out FFT, average down-sampling, single carrier power detection, logarithmic signal-to-noise ratio calculation and noise power calculation processing together with satellite attitude information, then extracts time information and corresponding satellite attitude information, and carries out real-time graphic display.
Further, the trajectory is analyzed and processed in the step (3) and the step (6), and the specific process is as follows:
when a track with rising signal-to-noise ratio appears, the ground station controls the satellite to continuously scan along the original direction until the maximum value in the track appears, and records the position of the maximum value and the time and attitude parameters corresponding to the maximum value; if the signal-to-noise ratio firstly appears in a descending track, the ground station controls the satellite to scan in the opposite direction until the ascending track and the descending track appear, and the position of the maximum value and the time and the attitude parameter corresponding to the maximum value are recorded.
Compared with the prior art, the invention has the following advantages:
(1) The invention utilizes the mode to align the antenna, thereby saving a complex antenna servo system and reducing the weight of the whole satellite.
(2) The invention provides an operable alignment scheme for the existing terahertz intersatellite communication.
Drawings
Fig. 1 is a communication scenario diagram of the present invention.
Fig. 2 is a flow chart of the actual operation of the present invention.
Fig. 3 is a plot of the snr trace received by the ground station of the present invention.
FIG. 4 is a block diagram of software data processing according to the present invention.
Detailed Description
The invention is further explained below with reference to the drawings.
The terahertz communication task scene is composed of a graph 1, a terahertz load is composed of a transmitting part and a receiving part and is respectively installed on two satellites, and engineering measurement and control instructions and service instructions of the two satellites are sent out by a satellite measurement and control center and a ground station.
The specific implementation mode is as follows:
before normal communication operation, a radio frequency loopback test is firstly carried out to verify whether channel equipment works normally and whether the setting of various parameters is correct. After two stars are launched into the rail, when the distance between the two stars is a certain distance and before the distance is over the top for 20 minutes, the terahertz system is started according to a preset instruction, and the power supply of each single machine is started. The terahertz load radio frequency single machine is started 20 minutes ahead of two stars, and the traveling wave tube amplifier is started 3-5 minutes before the terahertz load radio frequency single machine is pushed to the top. Theoretically, the terahertz transceiver antennas in two satellites are in an aligned state because the satellite precision is as follows:
a satellite own position precision: 0.02km
b, satellite attitude error: 0.05 degree
c, antenna installation error: 0.05-0.1 °
The beam width of the antenna is far greater than the satellite attitude error and the antenna installation error, the antenna servo system can be used for communication without the antenna servo system, and when the level received by the receiving load is not high enough, the satellite attitude is only required to be finely adjusted to align the receiving load.
When the satellite passes the top, the satellite sends remote control and remote measurement information, and the terahertz traveling wave tube amplifier, the radio frequency transceiver unit and the like are judged to be in normal working states through the information.
When the top is passed, the communication transmission test is directly carried out. As shown in the left half of fig. 2, after the terahertz system is started, the ground station can normally receive the signal transmitted by the terahertz terminal, and the rate, the signal-to-noise ratio, the bit error rate and the like sent by the receiving satellite feeder link meet the requirements, which indicates that the terahertz intersatellite transmission system is successfully tested without starting the attitude adjusting program. And after the traveling wave tube passes the top, closing the single traveling wave tube.
And when the ground station cannot normally receive the information, starting the process of adjusting the attitude of the satellite.
The specific gesture adjusting process comprises the following steps: and when the two stars cross the top for the second time, starting the posture adjusting mode, wherein the terahertz load is always started or is started 20 minutes before the two stars cross the top.
1) The terahertz load is started 20 minutes ahead of two stars, the transmitting satellite transmits a single carrier, cross scanning perpendicular to the orbital plane is carried out, and the posture of the receiving satellite is fixed. There are three situations for the received signal level prediction of the ground station, and the ground station records parameters such as time scale, attitude and received signal-to-noise ratio of the transmitting satellite position after the maximum value is found. The time for completing one cross scanning by a single star is about 80s, and the time for completing the whole cross scanning by two stars is about 3 minutes.
2) The method comprises the following specific operation steps:
(1) The satellite measurement and control center fixes a receiving satellite, controls the transmitting satellite to transmit a single carrier signal, and simultaneously controls the transmitting satellite to scan along the direction of the X axis I and scan along the direction of the Y axis I;
(2) Receiving satellite receiving signals, carrying out down-conversion and demodulation on the received signals, transmitting the demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain the track of the signal-to-noise ratio of the transmitting satellite along with the change of time and attitude;
(3) The ground station analyzes and processes the track to obtain the optimal attitude information of the launching satellite;
(4) A satellite measurement and control center fixes a transmitting satellite, controls the receiving satellite to transmit a single carrier signal, controls the receiving satellite to scan along the direction of X axis I at the same time, scans along the direction of Y axis I at the scanning angle of +/-0.5 degrees (generally, the angle can meet the requirement according to the satellite attitude and orbit control precision), scans at the scanning speed of 0.05 degrees/s, scans along the direction of Y axis I at the scanning angle of +/-0.5 degrees and the scanning speed of 0.05 degrees/s, and at the moment, scans in the same time needs 20 s;
(5) Transmitting satellite receiving signals, performing down-conversion and demodulation, transmitting demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain the track of the change of the signal-to-noise ratio of the receiving satellite along with time and attitude;
(6) The ground station analyzes and processes the track to obtain the optimal attitude information of the receiving satellite, and transmits the optimal attitude information of the transmitting satellite and the optimal attitude information of the receiving satellite to a satellite measurement and control center;
(7) The satellite measurement and control center carries out two-satellite attitude adjustment according to information transmitted by the ground station, and adjusts the transmitting satellite and the receiving satellite to the optimal attitude.
As shown in fig. 4, the on-satellite single carrier step tracking receiver comprises a THz antenna, a radio frequency down converter, an intermediate frequency AGC, an AD, a polyphase filtering down-sampling module, a CIC down-sampling module, a feeder link modulation, and the like, and the synthesis, CIC down-sampling filtering and modem on the satellite share the same FPGA-V7.
The single carrier stepping tracking receiver is realized and displayed in a ground microcomputer and consists of an FFT module, an average down-sampling module, a single carrier power detection module, a logarithmic signal-to-noise ratio module, a noise power calculation module, a display module and the like.
The ground processing in the figure is realized by a microcomputer, and the frequency spectrum display and the graphic display of the signal-to-noise ratio with the time stamp are completed on a local screen.
And (5) down-converting and demodulating the received signals in the steps (2) and (5), transmitting the demodulated data to a ground station through a satellite-to-ground link, processing the received data by the ground station, and calculating to obtain a track of the signal-to-noise ratio changing along with time and attitude, wherein the specific process is as follows:
(101) Carrying out A/D sampling on a received signal, and carrying out polyphase filtering, synthesis and CIC down-sampling;
(102) Adding time information to the real-time data subjected to down-sampling and framing;
(103) Performing channel coding modulation on the framed data, sending the data to an on-satellite feed link, and transmitting the data to a ground station through the on-satellite feed link in real time;
(104) After demodulating and receiving the received data, the ground station carries out FFT, average down-sampling, single carrier power detection, logarithmic signal-to-noise ratio calculation and noise power calculation processing together with satellite attitude information, then extracts time information and corresponding satellite attitude information, and carries out real-time graphic display.
Wherein, the track is analyzed and processed in the step (3) and the step (6), and the specific process is as follows:
when a track that the signal-to-noise ratio is increased all the time appears as in fig. 3 (a), the ground station controls the satellite to continuously scan along the original direction until the maximum value in the track of fig. 3 (c) appears, and the position of the maximum value and the time and the attitude parameter corresponding to the maximum value are recorded; if the signal-to-noise ratio firstly appears in the descending track of the figure 3 (b), the ground station controls the satellite to scan in the opposite direction until the ascending track of the figure 3 (c) is appeared, and the position of the maximum value and the time and the attitude parameter corresponding to the maximum value are recorded.
Claims (3)
1. An antenna alignment supplementing method based on terahertz communication between co-orbiting satellites is characterized by comprising the following steps:
(1) The satellite measurement and control center fixes the receiving satellite, controls the transmitting satellite to transmit a single carrier signal, and simultaneously controls the transmitting satellite to scan along the direction of the X axis I and scan along the direction of the Y axis I;
(2) Receiving satellite receiving signals, carrying out down-conversion and demodulation on the received signals, transmitting the demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain the track of the signal-to-noise ratio of the transmitting satellite along with the change of time and attitude;
(3) The ground station analyzes and processes the track to obtain the optimal attitude information of the launching satellite;
(4) The satellite measurement and control center fixes the transmitting satellite, controls the receiving satellite to transmit a single carrier signal, and controls the receiving satellite to scan along the direction of the X axis I and scan along the direction of the Y axis I;
(5) Transmitting satellite receiving signals, carrying out down-conversion and demodulation on the received signals, transmitting the demodulated data to a ground station through a satellite-ground link, processing the received data by the ground station, and calculating to obtain a track of the signal-to-noise ratio of the received satellite along with the change of time and attitude;
(6) The ground station analyzes and processes the track to obtain the optimal attitude information of the receiving satellite, and transmits the optimal attitude information of the transmitting satellite and the optimal attitude information of the receiving satellite to a satellite measurement and control center;
(7) The satellite measurement and control center carries out two-satellite attitude adjustment according to information transmitted by the ground station, and adjusts the transmitting satellite and the receiving satellite to the optimal attitude.
2. The method for supplementing antenna alignment based on terahertz communication between in-orbit satellites as claimed in claim 1, wherein the received signals are down-converted and demodulated in steps (2) and (5), the demodulated data are transmitted to the ground station through a satellite-to-ground link, the ground station processes the received data, and the trajectory of the signal-to-noise ratio changing with time and attitude is calculated, and the specific process is as follows:
(101) Carrying out A/D sampling on a received signal, and carrying out polyphase filtering, synthesis and CIC down-sampling;
(102) Adding time information to the real-time data subjected to down-sampling and framing;
(103) Performing channel coding modulation on the framed data, sending the data to an on-satellite feed link, and transmitting the data to a ground station through the on-satellite feed link in real time;
(104) After demodulating and receiving the received data, the ground station carries out FFT, average down sampling, single carrier power detection, logarithmic signal-to-noise ratio calculation and noise power calculation processing together with satellite attitude information, then extracts time information and corresponding satellite attitude information, and carries out real-time graphic display.
3. The antenna alignment supplementing method based on the terahertz communication between co-orbiting satellites as claimed in claim 1, wherein the track is analyzed and processed in the steps (3) and (6), and the specific process is as follows:
when a track with rising signal-to-noise ratio appears, the ground station controls the satellite to continuously scan along the original direction until the maximum value in the track appears, and records the position of the maximum value and the time and attitude parameters corresponding to the maximum value; if the signal-to-noise ratio firstly appears in a descending track, the ground station controls the satellite to scan along the reverse direction, and the position of the maximum value and the time and the attitude parameter corresponding to the maximum value are recorded until the ascending-before-descending track appears.
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Cited By (1)
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| CN116232423A (en) * | 2022-12-29 | 2023-06-06 | 西安空间无线电技术研究所 | Time division duplex inter-satellite link communication method based on master-slave synchronization |
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