A method and system for correcting tracking deviations of low-Earth orbit satellite signals

Abstract

This invention discloses a method for correcting tracking deviations of low-Earth orbit satellite signals, comprising the following steps: Step 1, system initialization; Step 2, satellite selection; Step 3, analysis and calculation of antenna attitude towards the satellite; Step 4, determination of antenna angle correction deviation range; Step 5, querying of preset deviation correction values; Step 6, real-time detection of received signal level; Step 7, angle threshold judgment. The correction method disclosed in this invention reduces the antenna tracking error by automatically correcting antenna deviations and preset step angles, and dynamically adjusting the antenna attitude. Simultaneously, a unique fine-tuning scheme is generated for each satellite to achieve flexible and precise tracking.

Description

Technical Field

[0001] This invention belongs to the field of electromagnetic monitoring, and specifically relates to a method and system for correcting tracking deviations of low-orbit satellite signals. Background Technology

[0002] With the rapid deployment of global on-orbit constellation systems, the acquisition and analysis of satellite signals has become a research hotspot in the field of electromagnetic monitoring. Because satellites constantly change their attitude and position during motion, existing satellite signal tracking schemes inevitably suffer from inaccurate antenna alignment, making it difficult to capture optimal signals. Existing satellite signal tracking deviation correction methods mainly have the following drawbacks:

[0003] 1) Due to factors such as data, environment, and antenna hardware, existing satellite tracking solutions are prone to antenna deviation from the satellite, affecting tracking performance. On the one hand, untimely acquisition of satellite ephemeris leads to deviations in the calculated azimuth and elevation angles of the antenna relative to the satellite, resulting in substandard satellite tracking accuracy and unsatisfactory tracking performance. On the other hand, deviations caused by the antenna's own installation and deployment, such as deviations in heading, level, latitude and longitude, and altitude, are difficult to correct through simple calibration.

[0004] 2) Existing antenna-based satellite tracking solutions rely on continuous fine-tuning of the antenna attitude to obtain the optimal tracking strategy. However, this approach suffers from drawbacks such as slow results and difficulty in operation. Furthermore, for different satellite monitoring tasks, the angle deviation correction strategy needs to be readjusted, or the antenna deviation correction settings are applied to all tasks, making it difficult to achieve unique fine-tuning effects for different satellites. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method and system for correcting tracking deviations of low-orbit satellite signals.

[0006] The present invention adopts the following technical solution:

[0007] An improved method for correcting tracking deviations of low-Earth orbit satellite signals includes the following steps:

[0008] Step 1, System Initialization:

[0009] An antenna is set up in the field, and the location data of the monitoring site is updated through the BeiDou location information of the antenna to complete the initialization of the entire system status;

[0010] Step 2, Select the tracking satellite:

[0011] Identify the monitoring target, select the satellite ID to be tracked, and update the ephemeris of the satellite using the satellite ID;

[0012] Step 3, Analysis and calculation of antenna attitude towards the star:

[0013] By using satellite ephemeris, the azimuth and elevation angles corresponding to the time period during which the antenna can monitor the satellite over the top can be calculated.

[0014] Step 4, Determine the antenna angle correction deviation range:

[0015] The range of elevation and azimuth angle deviation correction for the antenna observation satellite is determined based on the minimum step angle of the antenna azimuth and elevation angles.

[0016] Step 5, Deviation Correction Preset Value Query:

[0017] If the azimuth and elevation deviation values ​​for the satellite exist in the database, add the deviation values ​​and set the initial azimuth and elevation angles of the antenna; if no deviation values ​​exist, use the calculated antenna azimuth and elevation angles as the initial angle values ​​for antenna monitoring.

[0018] Step 6: Real-time detection of received signal level:

[0019] Obtain the maximum level value of the received signal at the current moment and record it as the maximum level value of this observation task;

[0020] Step 7, Angle threshold determination:

[0021] 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 by checking whether the current level change status and the difference between the current level and the initial level meet the threshold requirements.

[0022] If the current maximum voltage level is greater than or equal to the maximum voltage level of the previous state, the current adjustment strategy is saved; if the current maximum voltage level is less than the maximum voltage level of the previous state, the antenna adjustment strategy of the previous state is returned; if the difference between the current maximum voltage level and the initial maximum voltage level is greater than or equal to the threshold, the deviation correction is stopped and the current adjustment strategy is saved to the database; if the difference is always less than the threshold after adjustment, the deviation is corrected according to the optimal adjustment strategy.

[0023] Furthermore, in step 1, the antenna is adjusted using a leveling instrument; the location data of the monitored location includes longitude, latitude, and altitude.

[0024] Furthermore, in step 7, if the current signal level is greater than or equal to the previous state, the antenna azimuth and elevation angles are finely adjusted in minimum angle steps based on the preset angle of that state, and the current angle deviation correction scheme is saved.

[0025] Furthermore, in step 7, if the current signal level is lower than the previous state, the antenna is adjusted back to the previous state, and the elevation angle and azimuth angle are changed to adjust the direction respectively.

[0026] Furthermore, in step 7, if the difference is always less than the threshold after adjustment, the antenna attitude is adjusted according to the adjustment scheme that obtains the maximum signal level value in the monitoring task, and the correction strategy is saved to the database.

[0027] An improvement of a low-orbit satellite signal tracking deviation correction system is that it includes a signal receiving unit, a deviation correction unit, and a servo control unit. The signal receiving unit includes an antenna, an LNB, a power divider, and a detector 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 elevation angles of the antenna through its azimuth motor and elevation motor according to the information input from the deviation correction unit.

[0028] The beneficial effects of this invention are:

[0029] The correction method disclosed in this invention reduces the antenna tracking error by automatically correcting antenna deviation and preset step angles, and dynamically adjusting the antenna attitude. Simultaneously, it generates a unique fine-tuning scheme for each satellite to achieve flexible and precise tracking.

[0030] The correction method disclosed in this invention is universally applicable to low satellite tracking accuracy caused by various reasons. It automatically adjusts the antenna's attitude towards the satellite, eliminating the need for manual investigation of deviations and adjustments to the correction strategy, and can correct antenna tracking deviations for all monitorable satellites.

[0031] The correction method disclosed in this invention significantly reduces the time required for satellite signal monitoring and adjustment. Based on preset information in the system database, the antenna attitude is adjusted, and unique deviation correction schemes are generated for different satellite signal monitoring tasks. In multiple monitoring tasks targeting the same satellite, the deviation correction schemes are continuously optimized and saved, enabling rapid deviation correction and significantly reducing the time required for precise antenna alignment.

[0032] The correction system disclosed in this invention can achieve automatic satellite alignment and stable tracking. During satellite tracking missions, the system automatically and dynamically adjusts the antenna's elevation and azimuth angles to reduce signal attenuation caused by antenna alignment errors, improve signal reception quality, and formulate unique deviation correction strategies for tracking different satellites. Attached Figure Description

[0033] Figure 1 This is a flowchart illustrating the modification method disclosed in this invention;

[0034] Figure 2This is a block diagram of the correction system disclosed in this invention. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0036] Example 1 discloses a low-cost, high-precision method for correcting tracking deviations in low-Earth orbit satellite signals. This method reduces antenna alignment errors by dynamically adjusting antenna attitude. A separate deviation correction setting is configured for each satellite, and the method uses a database for storage and retrieval, shortening the deviation correction time. As the tracking cycle increases, the accuracy of the deviation correction significantly improves. Figure 1 As shown, the specific steps include the following:

[0037] Step 1: Set up the experimental antenna in the field and use a leveling instrument to adjust the antenna.

[0038] Step 2: After the system is powered on, the location data of the monitored area, such as longitude, latitude, and altitude, is updated using the BeiDou location information from the antenna.

[0039] Step 3: Determine the monitoring task for this mission. The monitoring satellite is "Starlink-1366". Obtain the latest ephemeris data for this satellite from the ephemeris website.

[0040] Step 4: Calculate the azimuth and elevation angles of the antenna for all monitorable times during the satellite's overhead transit period using ephemeris data.

[0041] Step 5: In this embodiment, the minimum step size for the azimuth and elevation angles that the antenna can achieve is 0.01°, and the correction deviation range is set to [-0.5°, 0.5°], that is, the maximum correction angle for the azimuth and elevation angles is 0.5°.

[0042] Step 6: Query the database of previous monitoring tasks for the corrected preset value of the "Starlink-1366" task. If the database contains the corrected angle from a previous monitoring task, add the angle correction for this monitoring task as the initial angle value for monitoring; if the database does not contain the corrected angle from a previous monitoring task, use the calculated value as the initial angle value for monitoring.

[0043] Step 7: Obtain the maximum level of the currently received signal through the signal receiving unit. Based on the comparison between the current level and the previous state level, determine the next antenna adjustment strategy.

[0044] If the current signal level is greater than or equal to the previous state, the antenna azimuth and elevation angles are finely adjusted in minimum angle steps based on the preset angle of that state, and the current angle deviation correction scheme is saved.

[0045] If the current signal level is lower than the previous state, adjust the antenna to return to the previous state, and change the elevation angle and azimuth angle to adjust the direction respectively;

[0046] If the current signal level has increased beyond the threshold compared to the initial state level, then stop the angle deviation correction and save the current correction strategy to the database.

[0047] If the signal strength cannot be improved after adjustment, the antenna attitude is adjusted according to the adjustment scheme that obtains the maximum signal level value in the monitoring task, and the correction strategy is saved to the database.

[0048] Step 8: Continuously monitor the satellite signal during the satellite's overhead transit period.

[0049] This embodiment also discloses a low-orbit satellite signal tracking deviation correction system, such as Figure 2 As shown, the system 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), a power divider, and a detector, which are electrically connected together in sequence. The deviation correction unit is electrically connected to the detector and the servo control unit. The servo control unit adjusts the azimuth and elevation angles of the antenna through its azimuth motor and elevation motor according to the information input from the deviation correction unit.

Claims

1. A method for correcting tracking deviations of low-Earth orbit satellite signals, characterized in that, Includes the following steps: Step 1, System Initialization: An antenna is set up in the field, and the location data of the monitoring site is updated through the BeiDou location information of the antenna to complete the initialization of the entire system status; Step 2, Select the tracking satellite: Identify the monitoring target, select the satellite ID to be tracked, and update the ephemeris of the satellite using the satellite ID; Step 3, Analysis and calculation of antenna attitude towards the star: By using satellite ephemeris, the azimuth and elevation angles corresponding to the time period during which the antenna can monitor the satellite over the top can be calculated. Step 4, Determine the antenna angle correction deviation range: The range of correction for elevation and azimuth deviations of the antenna observation satellite is determined based on the minimum step angle of the antenna azimuth and elevation angles. Step 5, Deviation Correction Preset Value Query: If the azimuth and elevation deviation values ​​for the satellite exist in the database, add the deviation values ​​and set the initial azimuth and elevation angles of the antenna. If there is no deviation value, the calculated antenna azimuth and elevation angles will be used as the initial angle values ​​for antenna monitoring. Step 6, Real-time detection of 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 this 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 by checking whether the current level change status and the difference between the current level and the initial level meet the threshold requirements. If the current maximum level value is greater than or equal to the maximum level value in the previous state, then save the current adjustment strategy; If the current maximum voltage level is less than the maximum voltage level in the previous state, then return to the antenna adjustment strategy of the previous state; If the difference between the current maximum level and the initial maximum level is greater than or equal to the threshold, then the deviation correction stops and the current adjustment strategy is saved to the database; if the difference is always less than the threshold after adjustment, then the deviation is corrected according to the optimal adjustment strategy.

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

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

4. The low-orbit satellite signal tracking deviation correction method according to claim 1, characterized in that: In step 7, if the current signal level is lower than the previous state, the antenna is adjusted back to the previous state, and the elevation angle and azimuth angle are changed to adjust the direction.

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

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