Low earth orbit satellite signal tracking deviation correction method and system

Abstract

The invention discloses a low-orbit satellite signal tracking deviation correction method. The method comprises the following steps: step 1, initializing a system; 2, selecting a tracking satellite; step 3, analyzing and calculating the attitude of the antenna to the satellite; 4, determining an antenna angle correction deviation range; 5, inquiring a deviation correction preset value; step 6, detecting a received signal level value in real time; and 7, judging an angle threshold value. According to the correction method disclosed by the invention, the satellite following error of the antenna is reduced by automatically correcting the antenna deviation and the preset stepping angle and dynamically adjusting the attitude of the antenna. Meanwhile, a unique fine tuning scheme is generated for each satellite, so that a flexible and accurate satellite following effect is realized.

Description

Technical Field

[0001] The present invention belongs to the field of electromagnetic monitoring, and in particular relates to a method and system for correcting low-orbit satellite signal tracking deviation in this field. Background Art

[0002] With the rapid deployment of in-orbit constellation systems around the world, the capture and analysis of satellite signals has become a research hotspot in the field of electromagnetic monitoring. Since the posture and position of satellites are constantly changing during their movement, existing satellite signal tracking solutions inevitably have the problem of inaccurate antenna alignment, making it difficult to capture the optimal signal. Existing satellite signal tracking deviation correction methods have the following main drawbacks: 1) Affected by factors such as data, environment, and antenna hardware, existing satellite tracking solutions are prone to antenna deviation from the satellite, affecting the tracking effect. On the one hand, the satellite ephemeris is not obtained in a timely manner, and the calculated azimuth and elevation angles of the antenna to the satellite are deviated, resulting in substandard satellite tracking accuracy and unsatisfactory tracking effects; on the other hand, due to the deviations caused by the installation and deployment of the antenna itself, such as deviations in heading, horizontal deviations, deviations in its own latitude and longitude, and deviations in altitude, these fine-tuning factors are difficult to correct through simple calibration.

[0003] 2) The existing antenna tracking solution obtains the optimal satellite tracking strategy by constantly fine-tuning the antenna attitude, but it has the disadvantages of slow effect and difficulty in operation. On the other hand, for different satellite monitoring tasks, the angle deviation correction strategy needs to be readjusted, or the antenna deviation correction setting will be applied to all tasks, making it difficult to form a unique fine-tuning effect for different satellites. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a method and system for correcting low-orbit satellite signal tracking deviation.

[0005] The present invention adopts the following technical solution: A method for correcting low-orbit satellite signal tracking deviation, the improvement of which is that it comprises the following steps: Step 1, system initialization: Set up antennas in the field, update the location data of the monitoring site through the Beidou location information of the antenna, and complete the initialization of the entire system status; Step 2, Tracking Satellite Selection: Determine the monitoring target, select the satellite ID to be tracked, and update the satellite's ephemeris through the satellite ID; Step 3: Analysis and calculation of antenna-to-satellite attitude: By using the satellite ephemeris, the corresponding azimuth and elevation angles within the time period that the antenna can monitor when the satellite passes overhead are calculated; Step 4: Determine the antenna angle correction deviation range: According to the minimum step angle of the antenna azimuth and elevation angle, determine the deviation correction range of the elevation and azimuth angles of the antenna observing the satellite; Step 5: Query the preset value of deviation correction: If the satellite's azimuth and elevation deviation values ​​exist in the database, the deviation values ​​are added to set the antenna's initial azimuth and elevation angles; if the deviation values ​​do not exist, the calculated antenna azimuth and elevation angles are used as the antenna monitoring initial angle values; Step 6: Real-time detection of the received signal level: Obtain the maximum level value of the received signal at the current moment and record it as the maximum level value of the observation task; Step 7, angle threshold determination: Adjust the azimuth and elevation angles of the antenna according to the angle correction deviation range determined in step 4, continuously update the maximum level value of the monitoring task, and determine the antenna angle adjustment strategy based on the current level change state and whether the difference between the current level and the initial level meets the threshold requirement: If the current maximum level value is greater than or equal to the maximum level value of the previous state, save the current adjustment strategy; if the current maximum level value is less than the maximum level value of the previous state, return to the antenna adjustment strategy of the previous state; if the difference between the maximum level value of the current state and the maximum level value of the initial state is greater than or equal to the threshold, stop the deviation correction and save the current adjustment strategy to the database; if after adjustment, the difference is always less than the threshold, correct the deviation according to the optimal adjustment strategy.

[0006] Furthermore, in step 1, the antenna is adjusted using a horizontal calibration instrument; the location data of the monitoring site includes longitude, latitude and altitude.

[0007] Furthermore, in step 7, if the current signal level value is greater than or equal to the previous state, the antenna azimuth angle and elevation angle are fine-tuned according to the minimum angle step based on the preset angle of the state, and the current angle deviation correction scheme is saved.

[0008] Furthermore, in step 7, if the current signal level value is less than the previous state, the antenna is adjusted to return to the previous state, and the elevation angle and azimuth angle adjustment directions are changed respectively.

[0009] Furthermore, in step 7, if the difference is always smaller than the threshold after adjustment, the antenna posture is adjusted by the adjustment scheme for obtaining the maximum signal level value in the monitoring task, and the correction strategy is saved in the database.

[0010] A low-orbit satellite signal tracking deviation correction system, the improvement of which lies in: comprising a signal receiving unit, a deviation correction unit and a servo control unit, the signal receiving unit comprising an antenna, an LNB, a power divider and a detector electrically connected in sequence, the deviation correction unit being electrically connected to the detector and the servo control unit respectively, and the servo control unit adjusting the azimuth angle and the pitch angle of the antenna through its azimuth motor and the pitch motor according to the information input by the deviation correction unit.

[0011] The beneficial effects of the present invention are: The correction method disclosed in the present invention can reduce the error of antenna tracking by automatically correcting antenna deviation and preset step angle, dynamically adjusting the antenna attitude, and generating a unique fine-tuning scheme for each satellite to achieve flexible and accurate satellite tracking effect.

[0012] The correction method disclosed in the present invention is universal for low satellite tracking accuracy caused by different reasons. The correction of the antenna to the satellite attitude is achieved through automatic adjustment, and the antenna tracking deviation can be corrected for all monitorable satellites without the need to manually check the cause of the deviation and manually adjust the correction strategy.

[0013] The correction method disclosed in the present invention significantly reduces the time required for satellite signal monitoring and adjustment. According to the preset information in the system database, the antenna attitude is adjusted to generate unique deviation correction schemes for different satellite signal monitoring tasks. In multiple monitoring tasks for the same satellite, the deviation correction scheme will be continuously optimized and saved to achieve rapid deviation correction, significantly reducing the time required for the antenna to accurately align with the satellite.

[0014] The correction system disclosed in the present invention can realize automatic satellite tracking and stable tracking. In the satellite tracking mission, the system automatically and dynamically adjusts the antenna's pitch angle and azimuth angle to reduce the signal attenuation caused by the antenna's satellite tracking error, improve the quality of signal reception, and form a unique deviation correction strategy for different satellite tracking missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic flow chart of the correction method disclosed in the present invention; Figure 2 It is a block diagram of the composition of the correction system disclosed in the present invention. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0017] Embodiment 1, this embodiment discloses a low-cost, high-precision low-orbit satellite signal tracking deviation correction method, which reduces the antenna-to-satellite error by dynamically adjusting the antenna attitude, configures a set of deviation correction settings for each satellite, and shortens the deviation correction time by storing and calling the database. With the increase of the tracking period, the accuracy of the deviation correction will be significantly improved. Figure 1 As shown, the specific steps include: Step 1: Set up the experimental antenna in the field and use the horizontal correction instrument to adjust the antenna; Step 2: After the system is powered on, the location data of the monitoring site, such as longitude, latitude, altitude, etc., is updated through the Beidou location information of the antenna; Step 3, determine the monitoring mission for this time, the monitoring satellite is the "Starlink-1366" satellite, and obtain the latest ephemeris data of the satellite from the ephemeris website; Step 4, using the ephemeris, calculate the azimuth and elevation angles of the antenna for all the monitoring times during the satellite's overhead period; Step 5: In this embodiment, the minimum step size of the azimuth and elevation angles that the antenna can reach is 0.01°, and the correction deviation range is set to [-0.5°, 0.5°], that is, the maximum correction angle of the azimuth and elevation angles is 0.5°; Step 6: Query the preset correction value of the "Starlink-1366" mission from the previous monitoring mission database. If the database contains the correction angle of the previous monitoring mission, add the angle correction for this monitoring mission as the initial angle value of the monitoring; if the database does not contain the correction angle of the previous monitoring mission, use the calculated value as the initial angle value of the monitoring; Step 7: Obtain the maximum level value of the current received signal through the signal receiving unit, and determine the next antenna adjustment strategy based on the comparison between the current level value and the previous state level value: If the current signal level value is greater than or equal to the previous state, the antenna azimuth and elevation angles are fine-tuned according to the minimum angle step based on the preset angle of the state, and the current angle deviation correction scheme is saved; If the current signal level value is less than the previous state, adjust the antenna back to the previous state, and change the pitch angle and azimuth adjustment direction respectively; If the current signal level value is higher than the initial state level value and exceeds the threshold value, the angle deviation correction is stopped and the current correction strategy is saved in the database; If the signal strength cannot be improved after adjustment, the antenna posture is adjusted through the adjustment scheme that obtains the maximum signal level value in the monitoring task, and the correction strategy is saved in the database.

[0018] Step 8: Continue to monitor the satellite signal during the satellite overhead period.

[0019] This embodiment also discloses a low-orbit satellite signal tracking deviation correction system, such as Figure 2 As shown, it includes a signal receiving unit for receiving signals, a deviation correction unit for calculating and issuing correction strategies, and a servo control unit for servo control. The signal receiving unit includes an antenna, an LNB (Low Noise Block, also called a high-frequency head), a power divider and a detector electrically connected in sequence. The deviation correction unit is electrically connected to the detector and the servo control unit respectively. The servo control unit adjusts the azimuth and pitch angles of the antenna through its azimuth motor and pitch motor according to the information input by the deviation correction unit.

Claims

1. A method for correcting low-orbit satellite signal tracking deviation, characterized in that: The steps include: Step 1, system initialization: Set up antennas in the field, update the location data of the monitoring site through the Beidou location information of the antenna, and complete the initialization of the entire system status; Step 2, Tracking Satellite Selection: Determine the monitoring target, select the satellite ID to be tracked, and update the satellite's ephemeris through the satellite ID; Step 3: Analysis and calculation of antenna-to-satellite attitude: By using the satellite ephemeris, the corresponding azimuth and elevation angles within the time period that the antenna can monitor when the satellite passes overhead are calculated; Step 4: Determine the antenna angle correction deviation range: According to the minimum step angle of the antenna azimuth and elevation angle, determine the deviation correction range of the elevation and azimuth angles of the antenna observing the satellite; Step 5: Query the preset value of deviation correction: If the satellite's azimuth and elevation deviation values ​​exist in the database, the deviation values ​​are added to set the antenna's initial azimuth and elevation angles; If there is no deviation value, the calculated antenna azimuth and elevation angles are used as the initial angle values ​​for antenna monitoring; Step 6: Real-time detection of the received signal level: Obtain the maximum level value of the received signal at the current moment and record it as the maximum level value of the observation task; Step 7, angle threshold determination: Adjust the azimuth and elevation angles of the antenna according to the angle correction deviation range determined in step 4, continuously update the maximum level value of the monitoring task, and determine the antenna angle adjustment strategy based on the current level change state and whether the difference between the current level and the initial level meets the threshold requirement: If the current maximum level value is greater than or equal to the maximum level value of the previous state, save the current adjustment strategy; If the current maximum level value is less than the maximum level value of the previous state, the antenna adjustment strategy of the previous state is returned; If the difference between the current state maximum level value and the initial state maximum level value is greater than or equal to the threshold, the deviation correction is stopped and the current adjustment strategy is saved in the database; if the difference is always less than the threshold after adjustment, the deviation is corrected according to the optimal adjustment strategy.

2. The method for correcting low-orbit satellite signal tracking deviation according to claim 1, characterized in that: In step 1, the antenna is adjusted using a horizontal calibration instrument; the location data of the monitoring site includes longitude, latitude and altitude.

3. The method for correcting low-orbit satellite signal tracking deviation according to claim 1, characterized in that: In step 7, if the current signal level value is greater than or equal to the previous state, the antenna azimuth angle and elevation angle are fine-tuned according to the minimum angle step based on the preset angle of the state, and the current angle deviation correction scheme is saved.

4. The method for correcting low-orbit satellite signal tracking deviation according to claim 1, characterized in that: In step 7, if the current signal level value is less than the previous state, the antenna is adjusted to return to the previous state, and the elevation angle and azimuth angle adjustment directions are changed respectively.

5. The method for correcting low-orbit satellite signal tracking deviation according to claim 1, characterized in that: In step 7, if the difference is always smaller than the threshold after adjustment, the antenna posture is adjusted by the adjustment scheme for obtaining the maximum signal level value in the monitoring task, and the correction strategy is saved in the database.

6. A low-orbit satellite signal tracking deviation correction system, characterized in that: The invention comprises a signal receiving unit, a deviation correction unit and a servo control unit. The signal receiving unit comprises an antenna, an LNB, a power divider and a detector which are electrically connected in sequence. The deviation correction unit is electrically connected to the detector and the servo control unit respectively. The servo control unit adjusts the azimuth angle and the pitch angle of the antenna through its azimuth motor and the pitch motor according to the information input by the deviation correction unit.

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