A two-channel tracking system self-tracking method, system, device and medium

Abstract

The application discloses a double-channel tracking system free-calibration phase self-tracking method, system, equipment and medium, and relates to the field of spaceflight measurement and control. In view of the problem that the existing star calibration is time-consuming and is prone to failure due to weather and high in-station elevation angle, in the star calibration of each target, the historical environment temperature of the tracking and the differential link of the antenna center body in the temperature change environment is obtained, and the calibration phase parameters are stored in a database; the temperature-phase difference curve is fitted according to the same working frequency and the same parameters such as the rotation direction; the real-time environment temperature of the antenna center body is obtained before the task, the real-time phase difference is calculated by calling the curve, and is placed in the tracking receiver, and the free-calibration phase self-tracking is directly entered. The application skips the star calibration link, avoids the interference of bad weather and the error of high-elevation secant compensation, significantly increases the time length of the low-orbit target high-speed data delivery, realizes the full automation operation and greatly reduces the pressure of the on-duty personnel.

Description

Technical Field

[0001] This invention relates to the field of aerospace telemetry and control, specifically to a method, system, equipment, and medium for phase-acceleration-free self-tracking of a dual-channel tracking system. Background Technology

[0002] The statements in this section are provided only as background information in connection with this disclosure and may not constitute prior art.

[0003] With the rapid development of the aerospace field, the scale of spacecraft operating in low Earth orbit is growing rapidly, and the number of daily missions at aerospace ground stations is increasing exponentially, with increasingly shorter mission intervals. Aerospace ground stations often employ a dual-channel single-pulse tracking system for higher tracking accuracy. However, due to the different paths taken by passive and active devices (low-noise amplifiers, down-converters, etc.) in the multi-band feed network for the tracking and difference signals, the phase difference between the tracking and difference signals is constantly changing due to ambient temperature. The higher the operating frequency, the greater the phase change (generally, the change is relatively gradual in the S-band of telemetry and control, but extremely large in the X or Ka bands of data transmission). If the phase difference of the tracking link is not accurately corrected before the mission, it will cause deterioration in the cross-coupling between the system's azimuth and elevation, leading to a decrease in tracking performance or even loss of target tracking.

[0004] The traditional solution was to build a calibration tower near the ground station, but the calibration tower needed to meet far-field conditions (i.e., the distance between the antenna and the tower). D is the antenna aperture. (for the operating wavelength) and minimum phase correction elevation angle requirements ( This method can only meet the phase correction requirements of the S-band and cannot meet the requirements of high-frequency bands such as X and Ka. In recent years, the "satellite-to-satellite phase correction" technique has been more commonly used. In this technique, the antenna directly performs phase correction on low-Earth orbit targets with large dynamic ranges using a programmable method. After phase correction, it switches to self-tracking to perform the task.

[0005] However, existing satellite phase calibration technologies have several drawbacks: First, the combined phase calibration of conventional telemetry, tracking, and data transmission bands takes about one minute, which significantly reduces the valuable time for transmitting high-speed data for low-Earth orbit targets. Second, they are greatly affected by adverse weather conditions; windy conditions can cause parabolic antennas to vibrate, leading to decreased phase calibration accuracy, while rain can cause signal attenuation and fluctuations, easily resulting in phase calibration failure. Third, when the target's approach elevation angle is too high, antenna misalignment during target acquisition can cause severe azimuth and elevation secant compensation problems, resulting in increased cross-coupling and a higher likelihood of phase calibration failure. Finally, intensive missions require manual intervention from personnel based on weather, elevation angle, and other factors, leading to high mission pressure and a high risk of errors. Summary of the Invention

[0006] The purpose of this invention is to address the technical problems of current dual-channel monopulse aerospace ground antenna systems performing low-orbit, high-dynamic-range target missions. These problems include the long time required for satellite phase calibration, which severely compresses data transmission time, and the susceptibility to adverse weather conditions and high target approach elevation angles, leading to frequent phase calibration failures. This invention provides a phase-calibration-free self-tracking method, system, equipment, and medium for dual-channel tracking systems. Based on constructing a historical phase difference database and specifically fitting a temperature-phase difference curve, the invention automatically calculates and digitally compensates for the current tracking and differential link phase difference by acquiring the real-time ambient temperature of the antenna center. This allows for skipping the satellite phase calibration stage and directly transitioning to stable self-tracking, avoiding weather interference and approach elevation angle limitations, and significantly improving the effective transmission time of high-speed data and the reliability of the fully automated system operation.

[0007] The technical solution of the present invention is as follows: A phase-calibration-free self-tracking method for a dual-channel tracking system includes: Step S1: During the phase alignment process of the aerospace ground antenna with respect to the target, the historical ambient temperature of the tracking and differential link in the temperature-changing environment is obtained by a temperature acquisition device installed in the center of the antenna. Step S2: Store the historical ambient temperature and the corresponding phase correction parameters into the phase difference history database. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, and historical phase difference of the tracking and differential link obtained by satellite phase correction. Step S3: Based on the data accumulated in the historical phase difference database, for the same operating frequency, rotation direction and equipment combination, fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference; Step S4: Before performing the self-tracking task of the target, obtain the current real-time ambient temperature of the antenna center body; Step S5: Based on the current task's operating frequency, rotation direction, and device combination, call the corresponding temperature-phase difference curve, and calculate the real-time phase difference of the current tracking and differential link in conjunction with the real-time ambient temperature; Step S6: Input the real-time phase difference into the tracking receiver, and control the aerospace ground antenna to skip the star phase correction process and directly switch to phase correction-free self-tracking of the target.

[0008] Furthermore, in step S1, the passive and active devices through which the tracking and difference links pass are distributed in the antenna center body, the antenna tower base, and the control room; The antenna tower base and the control room are equipped with temperature-controlled environmental control equipment. The antenna center body and the antenna tower base are connected by a phase-stabilized cable for intermediate frequency signal transmission, and the antenna tower base and the control room are connected by an optical fiber for digital signal transmission. To obtain the historical ambient temperature of the tracking and differential link in a temperature-varying environment, specifically: the temperature inside the antenna center body is obtained solely by the temperature acquisition device installed next to the tracking and differential link within the antenna center body, in order to monitor the phase difference fluctuations caused by temperature changes in devices including the multi-band feed network, low-noise amplifier, and downconverter in a temperature-varying environment.

[0009] Furthermore, in step S2, before storing the historical ambient temperature and the corresponding phase correction parameters into the phase difference history database, a data validity determination step for the historical data is also included: After each phase alignment and target tracking is completed, the tracking accuracy and angular error voltage reported by the antenna control unit are used to automatically determine whether the historical phase difference of the tracking and differential link obtained from this phase alignment is valid data. If the data is deemed valid, it is formally stored in the phase difference history database; if the data is deemed invalid or abnormal, it is identified and removed.

[0010] Furthermore, between step S3 and step S4, an automatic switching step for the working mode based on the amount of accumulated data is also included: Determine whether the data accumulated in the phase difference history database for the same target has covered the entire year's temperature range or a preset temperature range; If so, the tracking method of the target will be automatically configured from the phase-calibration tracking method to the phase-free self-tracking method in the target management interface of the control terminal; when the target task is executed subsequently, steps S4 to S6 will be triggered.

[0011] Furthermore, in step S2, the phase calibration parameters also include: task code, operating frequency band, and operating mode; In step S3, fitting a temperature-phase difference curve reflecting the mapping relationship between ambient temperature and tracking / differential link phase difference based on the data accumulated in the historical phase difference database specifically includes: In the historical phase difference database, data is filtered by using the same operating frequency, rotation direction, and device combination as joint query conditions. Extract all valid historical phase differences distributed across different historical ambient temperatures that satisfy the joint query conditions; The temperature-phase difference curve is generated by fitting the extracted discrete temperature and phase difference data points.

[0012] Furthermore, in step S5, for application scenarios where target measurement and control and data transmission work simultaneously, the operating frequency includes the operating frequency of the measurement and control frequency band and the operating frequency of the data transmission frequency band. When calculating the real-time phase difference of the current tracking and difference links, the pre-fitted temperature-phase difference curves of the measurement and control frequency band and the data transmission frequency band are extracted respectively. Combined with the same real-time ambient temperature obtained at the moment, the independent real-time phase difference of the measurement and control frequency band and the real-time phase difference of the data transmission frequency band are calculated in parallel.

[0013] Furthermore, in step S6, skipping the phase correction step and directly transitioning to phase-correction-free self-tracking of the target specifically includes: When the target enters the station, skip the antenna deflection search for the target and perform satellite phase correction operation to avoid azimuth and elevation secant compensation during satellite phase correction. The calculated real-time phase difference is directly input into the tracking receiver. The tracking receiver performs digital phase shifting on the input differential signal based on the input real-time phase difference, so that it is in phase with the input sum signal to eliminate cross-coupling between azimuth and elevation, thereby realizing the self-tracking of the target signal by the aerospace ground antenna.

[0014] This invention also proposes a dual-channel tracking system with phase-correction-free self-tracking capability to implement the above method, comprising: The historical data acquisition module is used to acquire the historical ambient temperature of the tracking and differential link in a temperature-changing environment during the phase alignment process of the aerospace ground antenna with respect to each target. The data entry module is used to store the historical ambient temperature and the corresponding phase correction parameters into the historical phase difference database. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, and historical phase difference of the tracking and differential link obtained by satellite phase correction. The curve fitting module is used to fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference, based on the data accumulated in the phase difference historical database, for the same operating frequency, rotation direction and equipment combination. The real-time temperature acquisition module is used to acquire the current real-time ambient temperature of the antenna center body before performing the self-tracking task of the target. The phase difference calculation module is used to calculate the real-time phase difference of the current tracking and differential link by calling the corresponding temperature-phase difference curve based on the current task's operating frequency, rotation direction, and device combination, combined with the real-time ambient temperature. The phase-correction-free tracking execution module is used to input the real-time phase difference into the tracking receiver and control the aerospace ground antenna to skip the satellite phase correction process and directly switch to phase-correction-free self-tracking of the target.

[0015] The present invention also proposes an electronic device, comprising: At least one processor; and a memory communicatively connected to said at least one processor; The memory stores instructions that can be executed by the at least one processor, and the at least one processor executes the instructions stored in the memory to perform the method described above.

[0016] The present invention also proposes a computer-readable storage medium for storing instructions that, when executed, cause the method described above to be implemented.

[0017] Compared with existing technologies, the advantages of this invention are: 1. Significantly improves the effective transmission time of high-speed data for low-Earth orbit targets. This invention uses the temperature-phase difference curve to calculate the true phase difference for phase-correction-free self-tracking, completely eliminating the approximately one-minute phase correction step. Given the extreme scarcity of low-Earth orbit target transit arcs, this avoids the risk of losing track due to secondary phase correction, and greatly increases the amount of high-speed data transmitted per orbit.

[0018] 2. Completely avoids the secant compensation problem caused by high elevation angle approach. Existing satellite phase correction methods are prone to failure when facing high elevation angle targets because the azimuth error is amplified sharply with the secant function of the elevation angle due to antenna deflection. This invention skips the phase correction operation of antenna deflection to find the target, and directly puts the calculated phase difference into the tracking receiver for digital phase shifting, perfectly solving the problem of stable self-tracking of high elevation angle approach targets.

[0019] 3. Exceptionally strong all-weather resistance to severe weather. Traditional real-time phase calibration relies heavily on the stability of the target's transmitted signal, making it highly susceptible to antenna jitter caused by gusts and signal attenuation caused by rain. This invention extracts inherent environmental temperature mapping patterns to replace real-time signal measurement, is unaffected by external wind and rain, and can ensure mission success under various harsh weather conditions.

[0020] 4. Fully automated operation, significantly reducing the workload of on-duty personnel. This invention introduces a database accumulation determination mechanism. When the conditions are met, the system can automatically configure the target to a calibration-free tracking mode, eliminating the reliance on manual observation of weather and elevation angles and decision-making by on-duty personnel in the traditional process. This avoids the risk of human decision-making errors and greatly alleviates the on-duty pressure under high-density tasks.

[0021] 5. Extremely wide adaptability and extremely low hardware modification cost. This invention cleverly utilizes the physical characteristic that optical cable transmission based on antenna towers is unaffected by temperature, simplifying the temperature measurement node (monitoring only within the central area) and eliminating the need for large-scale hardware modifications. The solution is compatible with all frequency bands including S, C, X, Ku, and Ka, and supports high / low orbit targets as well as various combined working modes such as single telemetry and control, single data transmission, and telemetry and control + data transmission. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments recorded in the embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0023] Figure 1 The experimental verification results are shown in the figure for tracking the phase difference variation characteristics of the sum and difference links; Figure 2 A block diagram of ground station tracking link and data detection and acquisition; Figure 3 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0024] It should be noted that relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0025] The features and performance of the present invention will be further described in detail below with reference to embodiments.

[0026] Example 1 Traditional calibration towers require meeting far-field conditions (i.e., the distance between the antenna and the tower). D is the antenna aperture. (for the operating wavelength) and elevation angle The limitations of this method mean that while it can meet the requirements of the S-band, it cannot meet the phase correction requirements of higher frequency bands such as X and Ka. Existing technologies such as UAV phase correction, radio star calibration, and offset-feed phase correction also have many limitations and drawbacks. Therefore, satellite-based phase correction is currently the most common method for low-Earth orbit targets with large dynamic ranges.

[0027] To address the technical problems of existing dual-channel monopulse aerospace ground antenna systems performing low-Earth orbit high-dynamic target missions, where the phase difference of the tracking and differential links is affected by temperature changes, requiring phase calibration before each mission, leading to long calibration times (approximately 1 minute, affecting high-speed data transmission), and susceptibility to calibration failures due to severe weather (gusts, rain attenuation) and high target elevation angles (secant compensation error), this embodiment provides a phase calibration-free self-tracking method for dual-channel tracking systems.

[0028] like Figure 2 The diagram shown illustrates the ground station tracking link and data detection and acquisition block diagram of this invention. The aerospace ground antenna system in this embodiment specifically includes: a large-aperture antenna supplied with the aerospace ground antenna, a multi-band feed network and tracking and differential links located within the antenna's central body, an antenna control unit and tracking receiver located in the control room, and an antenna drive unit and signal acquisition equipment located at the antenna tower base. The method provided in this embodiment is applied to this system and specifically includes the following steps: Step S1: During the phase alignment process of the aerospace ground antenna with respect to the target, the historical ambient temperature of the tracking and differential link in the temperature-changing environment is obtained by a temperature acquisition device installed in the center of the antenna. In the specific implementation of this step, it is important to note that: the passive and active devices traversed by the tracking and differential link are distributed in the antenna center body, antenna tower base, and control room; wherein, the antenna tower base and the control room are equipped with temperature-controlled environmental control equipment, the antenna center body and the antenna tower base transmit intermediate frequency signals via a phase-stabilized cable, and the antenna tower base and the control room transmit digital signals via an optical fiber; the historical ambient temperature of the tracking and differential link in a temperature-changing environment is obtained, specifically: the internal temperature of the antenna center body is obtained solely through the temperature acquisition device installed next to the tracking and differential link within the antenna center body, in order to monitor the phase difference fluctuations caused by temperature changes in devices including the multi-band feed network, low-noise amplifier, and downconverter in a temperature-changing environment.

[0029] In this embodiment, it should be noted that the researchers previously installed data acquisition devices for temperature, humidity, and pressure simultaneously along the dual-channel tracking and differential link for long-term observation and verification. Through long-term experiments and tests, they discovered (e.g.) Figure 1 The experimental verification results of the tracking and difference link phase difference variation characteristics shown are as follows: The tracking and difference link phase difference of the dual-channel tracking system is mainly affected by temperature and is basically independent of factors such as time, ambient humidity, and pressure, as well as antenna movement. Under conditions where the ambient temperature is the same or similar, even in different time periods or seasons, the phase difference of the tracking and difference link remains essentially consistent.

[0030] The tracking link of the entire aerospace ground station is distributed across three physical spaces: the antenna center, the antenna tower base, and the control room. The antenna tower base and the control room are equipped with environmental control equipment year-round, maintaining a constant temperature environment. Furthermore, two RF phase-stabilized cables, each approximately 35 meters long, are used to transmit the tracking and difference intermediate frequency (IF) signals between the antenna center and the antenna tower base. The phase difference between the phase-stabilized cables is fixed and unaffected by temperature changes. The signal acquisition equipment at the antenna tower base performs analog-to-digital conversion on the IF signals and then transmits them to the tracking receiver in the control room via a long-distance digital optical cable. The digital signal transmission also does not affect the phase of the tracking and difference links.

[0031] Therefore, only the antenna center is in a "temperature-varying environment" within the entire link. The phase of passive and active components within the antenna center, such as the multi-band feed network, low-noise amplifier (LNA), and downconverter, is affected by temperature changes. Based on this physical finding, this embodiment creatively simplifies the temperature measurement nodes, installing only one temperature acquisition device next to the multi-band feed network and tracking / differential link within the center. This device is connected to the system monitoring in the control room via a switch, accurately monitoring the only source of temperature variation causing phase fluctuations.

[0032] Step S2: Store the historical ambient temperature and the corresponding phase correction parameters into the phase difference history database. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, and historical phase difference of the tracking and differential link obtained by satellite phase correction. In this step, the phase correction parameters also include: mission code, operating frequency band, operating mode, and sensitivity coefficient. To ensure the absolute reliability of the data stored and to avoid contamination of the database by occasional phase correction errors caused by extremely severe weather, a data validity determination step is included before storing the historical ambient temperature and corresponding phase correction parameters into the phase difference history database: After each satellite phase correction and target tracking is completed, based on the tracking accuracy of the target reported by the antenna control unit and the angular error voltage during the tracking process, it is automatically determined whether the historical phase difference of the tracking and difference link obtained from this satellite phase correction is valid data; if it is determined to be valid data, it is officially stored in the phase difference history database; if it is determined to be invalid abnormal data, it is identified and removed.

[0033] In this embodiment, it should be noted that during the initial data accumulation phase, the system still performs routine phase calibration for low-Earth orbit targets. Specifically, the antenna directly performs phase calibration on the low-Earth orbit target with large dynamic range using a programmable method, sequentially checking the telemetry and control (TT&C) and data transmission bands. After each calibration, the system monitors and reads the ambient temperature of the target body at that time, and stores the calibration results along with key parameters. Only after a complete tracking cycle is completed, and the angular error voltage (a core indicator reflecting the degree of deviation between the antenna's electrical axis and the target; a more stable voltage indicates less cross-coupling and more stable tracking) is reviewed during the tracking process, confirming stable tracking and meeting accuracy standards, is the data officially entered into the database. This ensures that each phase difference data point in the database accurately reflects the inherent phase deviation of the link at a specific temperature. Furthermore, this historical phase difference database not only supports automatic data entry and anomaly removal but also supports manual operations such as querying, filtering, sorting, deleting, adding, modifying, exporting, and importing according to various rules, facilitating low-level data management for maintenance personnel.

[0034] Step S3: Based on the data accumulated in the historical phase difference database, for the same operating frequency, rotation direction and equipment combination, fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference; In this step, the specific process of curve fitting is as follows: In the historical phase difference database, the same operating frequency, rotation direction and equipment combination are used as joint query conditions for data filtering; all valid historical phase differences that meet the joint query conditions and are distributed at different historical ambient temperatures are extracted; based on the extracted discrete temperature and phase difference data points, the temperature-phase difference curve is fitted and generated.

[0035] In this embodiment, it should be noted that the above-mentioned patterns were derived from long-term statistical analysis of satellite phase correction data across various frequency bands over a period of more than one year. Combined with... Figure 1 The experimental data shows that the system's tolerance for phase difference fluctuations varies across different frequency bands. Under normal circumstances, the system requires that the phase difference error of the tracking link for stable self-tracking be controlled within [-20º, 20º]. ​​Within the yearly temperature range of -10℃ to +40℃: 1) For the telemetry and control band (S-band), a total of 1,109 phase correction tasks were performed on a certain target during the test. The phase difference showed a slow decreasing trend with temperature. The vast majority of the phase correction results were concentrated within the median value of ±15º, which can basically meet the requirements for stable self-tracking. 2) For data transmission frequency bands (X or Ka band), the higher the frequency, the greater the phase change. During the experiment, 788 phase alignment tasks were performed on a specific target in the X band, and 114 in the Ka band. The average phase difference between the lowest and highest temperatures was approximately 55º in the X band and approximately 85º in the Ka band. However, if a fixed temperature point was maintained, the phase alignment results from multiple adjustments converged within ±12º of the median value.

[0036] Therefore, the fitted temperature-phase difference curve essentially reveals the deterministic law of temperature drift in different frequency bands.

[0037] Furthermore, in order to achieve a high degree of system automation and reduce the intervention pressure on staff during busy days (such as dozens of rounds of tasks), an automatic switching step based on the amount of accumulated data is included between step S3 and step S4: determining whether the data accumulated in the phase difference historical database for the same target has covered the entire year's temperature range or a preset temperature range; if so, the tracking method of the target is automatically configured from the phase calibration tracking method to the phase calibration-free self-tracking method in the target management interface of the control terminal; when the target task is executed subsequently, steps S4 to S6 are triggered.

[0038] Not limited to accumulating data for the whole year, as long as the system determines that the forecast temperature of the current task falls within a "preset temperature range" of the accumulated data, it can also trigger the self-tracking logic without calibration.

[0039] Step S4: Before performing the self-tracking task of the target, obtain the current real-time ambient temperature of the antenna center body; Step S5: Based on the current task's operating frequency, rotation direction, and device combination, call the corresponding temperature-phase difference curve, and calculate the real-time phase difference of the current tracking and differential link in conjunction with the real-time ambient temperature; In this step, for the application scenario where target measurement and control and data transmission work simultaneously, the working frequency points include the working frequency points of the measurement and control frequency band and the working frequency points of the data transmission frequency band; when calculating the real-time phase difference of the current tracking and difference links, the pre-fitted temperature-phase difference curves of the measurement and control frequency band and the temperature-phase difference curves of the data transmission frequency band are extracted respectively, and combined with the same real-time ambient temperature currently obtained, the independent real-time phase difference of the measurement and control frequency band and the real-time phase difference of the data transmission frequency band are calculated in parallel.

[0040] In this embodiment, it should be noted that in actual aerospace telemetry, tracking, and command (TT&C) missions, a dual-band simultaneous operation mode (such as simultaneous S+X or S+Ka) is often adopted. The different frequency band signals transmitted from the target are separated into sum signals (Σ) and difference signals (Δ) of different frequency bands after passing through a multi-band feed network. The separated sum and difference signals are then sent to low-noise amplifiers and down-converters for their respective frequency bands to track the sum and difference signals for processing. At this point, only one real-time ambient temperature within the central area needs to be collected. Different frequency band fitting curves can be used to calculate the real-time phase difference of the S-band and the real-time phase difference of the X / Ka bands in parallel, resulting in extremely high efficiency.

[0041] Step S6: Input the real-time phase difference into the tracking receiver, and control the aerospace ground antenna to skip the star phase correction process and directly switch to phase correction-free self-tracking of the target.

[0042] In this step, skipping the satellite phase correction process and directly transitioning to phase-correction-free self-tracking of the target specifically includes: when the target enters the station, skipping the satellite phase correction operation of antenna deflection to find the target, so as to avoid azimuth and elevation secant compensation during satellite phase correction; directly inputting the calculated real-time phase difference into the tracking receiver; the tracking receiver digitally phase-shifting the input differential signal according to the input real-time phase difference, so that it is consistent with the phase of the input sum signal to eliminate cross-coupling between azimuth and elevation, thereby realizing the self-tracking of the target signal by the aerospace ground antenna.

[0043] In this embodiment, specifically, the method of calculating and directly incorporating the phase difference described above has extremely important engineering significance: 1. Avoiding the High-Elevation-Angle Secant Compensation Challenge: In traditional satellite phase alignment processes, the antenna needs to be deflected at a certain angle to locate the target signal. When a low-Earth orbit target approaches the station at a high elevation angle, due to the physical phenomenon that "azimuth error amplifies sharply with the secant function of elevation angle" during coordinate system transformation, even slight inaccuracies in compensation can lead to severe deterioration in azimuth and elevation cross-coupling, resulting in phase alignment failure. This invention directly skips the deflection-to-target-locate step and directly compensates for the differential signal using digital phase shifting based on the calculated phase difference parameters. This completely avoids the industry-wide challenge of high-elevation-angle secant compensation and significantly improves the mission success rate for high-elevation-angle approaching targets.

[0044] 2. Extremely strong resistance to severe weather: In traditional phase calibration, strong winds can cause the parabolic antenna to vibrate, resulting in significant fluctuations in the received signal; rain can cause signal attenuation, leading to time-varying signal loss and making phase calibration impossible. The method in this embodiment does not rely on real-time signals upon arrival at the site to measure the phase difference, but instead uses a weather-independent "temperature mapping relationship" for compensation, thus enabling all-weather, phase-calibration-free self-tracking.

[0045] 3. Securing the crucial data transmission time to avoid losing track: Low Earth orbit (LEO) target transit arcs are extremely scarce. Traditional telemetry, tracking, and data transmission (TT&C) combined phase calibration takes at least one minute, significantly reducing the time for high-speed data transmission. If a second phase calibration is initiated after the first fails, the target has often already begun transmitting large amounts of data, leading not only to interrupted data reception but also the potentially fatal risk of losing track of the target altogether. This invention, by eliminating one minute of phase calibration time, significantly increases the effective transmission time for LEO target data, substantially increasing the amount of high-speed data transmitted per orbit.

[0046] 4. Achieve full automation and significantly reduce personnel workload: Faced with the high-density missions of dozens of orbits per day at aerospace ground stations, which increase exponentially, existing satellite phase alignment processes require manual intervention and decision-making by on-duty personnel based on weather conditions, target elevation angle, and data transmission time. This results in high workload and a high risk of decision-making errors. The method of this invention can automatically configure and switch to phase alignment-free self-tracking after the system identification conditions are met. The entire process requires no manual intervention, significantly reducing the workload of on-duty personnel and ensuring extremely high system reliability.

[0047] In addition, the method of the present invention has a wide range of applications, not only applicable to the above-mentioned S, X, and Ka frequency bands, but also extendable to commonly used aerospace telemetry and control frequency bands such as C and Ku; it supports a wide variety of target types, not limited to low-orbit high dynamic targets, but also applicable to high-orbit targets; it supports a variety of working modes, and conventional telemetry and control systems and data transmission signals can be applied, including single telemetry and control, single data transmission, and telemetry and control + data transmission targets.

[0048] Example 2 Based on the phase-adjustment-free self-tracking method for a dual-channel tracking system provided in Embodiment 1 above, this embodiment provides a corresponding phase-adjustment-free self-tracking system for a dual-channel tracking system. Since the system in this embodiment is designed to implement the method in Embodiment 1, the technical principles and effects of the two are highly consistent. For technical details not described in detail in this embodiment, please refer to the relevant descriptions in Embodiment 1.

[0049] Specifically, this embodiment provides a dual-channel tracking system with phase-calibration-free self-tracking capability, which is mainly deployed in systems such as... Figure 2 The aerospace ground antenna system architecture shown includes an antenna center, antenna tower base, and control room. The system comprises the following virtual functional modules: 1. Historical Data Acquisition Module This module is used to obtain the historical ambient temperature of the tracking and differential link in a temperature-changing environment during the phase alignment process of the aerospace ground antenna with respect to each target.

[0050] This module communicates with a temperature acquisition device installed inside the antenna's central body via an interface. Since the antenna tower base and control room are equipped with temperature-controlled environmental control equipment, and the intermediate frequency signal and digital signal are transmitted through stable phase cables and optical cables, which are minimally affected by temperature, respectively, this module only needs to extract the real-time temperature monitored by the temperature acquisition device inside the antenna's central body to accurately capture the environmental parameters of components such as the multi-band feed network, low-noise amplifier, and downconverter that are affected by temperature variations.

[0051] 2. Data import module This module is used to store the historical ambient temperature and the corresponding phase correction parameters into the system monitoring and phase difference history database located in the main computer room. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, mission code, operating frequency band, operating mode, sensitivity coefficient, and the historical phase difference of the tracking and differential link obtained by satellite phase correction.

[0052] To ensure the purity and reliability of the data stored in the database, this module includes a data validity judgment subunit. After each satellite phase correction and target tracking is completed, this subunit reads the tracking accuracy and angular error voltage reported by the antenna control unit, and automatically determines whether the historical phase difference obtained from this phase correction is valid data. If valid, it is officially stored in the database; if it is abnormal data caused by gusts of wind or severe rain attenuation, it is identified and automatically removed. Simultaneously, this module supports manual operations such as querying, filtering, sorting, and modifying the database by maintenance personnel.

[0053] 3. Curve Fitting Module This module is used to fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference, based on the data accumulated in the phase difference historical database, for the same operating frequency, rotation direction and equipment combination.

[0054] This module uses the same operating frequency, rotation direction, and device combination as joint query conditions to extract all valid historical phase difference discrete data points corresponding to different historical ambient temperatures from the database and perform curve fitting.

[0055] In addition, this module is linked to an automatic working mode switching subunit, which determines whether the data accumulated in the database for the same target has covered the entire year's temperature range or a preset temperature range. If the judgment condition is met, the tracking method of the target in the target management interface of the control terminal is automatically configured from phase-calibration tracking to phase-calibration-free self-tracking mode, thereby achieving fully automatic skipping of the phase calibration step in subsequent tasks.

[0056] 4. Real-time temperature acquisition module This module is used to wake up and obtain the current real-time ambient temperature of the antenna center body before performing the phase-tracking task of the target without calibration.

[0057] 5. Phase Difference Calculation Module This module is used to call the corresponding temperature-phase difference curve based on the current task's operating frequency, rotation direction, and device combination, and to calculate the real-time phase difference of the current tracking and differential links by combining the obtained real-time ambient temperature.

[0058] In dual-band joint mission scenarios such as simultaneous operation of S+X or S+Ka, the module can extract the temperature-phase difference curves of the measurement and control band and the temperature-phase difference curves of the data transmission band in parallel based on the real-time ambient temperature of the same central body, thereby rapidly and independently calculating the real-time phase difference of the S band and the real-time phase difference of the X / Ka band.

[0059] 6. Phase-tracking execution module without calibration This module is used to input the calculated real-time phase difference into the tracking receiver in the control room, and control the aerospace ground antenna to skip the satellite phase correction process and directly switch to phase-correction-free self-tracking of the target.

[0060] When the target approaches the station, this module controls the antenna system to skip the traditional satellite phase correction operation of antenna deflection to find the target, completely avoiding the azimuth and elevation secant compensation problem. After receiving the real-time phase difference from this module, the tracking receiver digitally phase-shifts the input difference signal to make it consistent with the input sum signal, thereby eliminating the cross-coupling between azimuth and elevation and directly achieving stable self-tracking. This saves valuable time for the transmission of high-speed data.

[0061] Example 3 Based on the same inventive concept, embodiments of the present invention also provide an electronic device that can implement the phase-calibration-free self-tracking method flow of a dual-channel tracking system provided in the above embodiments of the present invention. In one embodiment, the electronic device can be a server, a terminal device, or other electronic devices. Figure 3 As shown, the electronic device may include: At least one processor and a memory connected to the at least one processor. In this embodiment of the invention, the specific connection medium between the processor and the memory is not limited. Figure 3 The example used is the connection between the processor and memory via a bus. The bus... Figure 3 The connections between other components are indicated by thick lines and are for illustrative purposes only, not as limiting information. Buses can be divided into address buses, data buses, control buses, etc., but for ease of representation, [the specific bus type is not shown here]. Figure 3The processor is represented by a single thick line, but this does not imply that there is only one bus or one type of bus. Alternatively, a processor can also be called a controller; there are no restrictions on the name.

[0062] In this embodiment of the invention, the memory stores instructions executable by at least one processor. By executing the instructions stored in the memory, the at least one processor can perform the phase-correction-free self-tracking method for a dual-channel tracking system described above. The processor can implement... Figure 3 The functions of each module in the device shown.

[0063] The processor is the control center of the device. It can connect to various parts of the control device through various interfaces and lines. By running or executing instructions stored in memory and calling data stored in memory, it can monitor the device's various functions and process data, thereby enabling overall monitoring of the device.

[0064] In an alternative design, the processor may include one or more processing units. The processor may integrate an application processor and a modem processor, wherein the application processor primarily handles the operating system, user interface, and applications, while the modem processor primarily handles wireless communication. It is understood that the modem processor may also not be integrated into the processor. In some embodiments, the processor and memory may be implemented on the same chip; in some embodiments, they may also be implemented separately on separate chips.

[0065] The processor can be a general-purpose processor, such as a CPU, digital signal processor, application-specific integrated circuit, field-programmable gate array or other programmable logic device, discrete gate or transistor logic device, or discrete hardware component, capable of implementing or executing the methods, steps, and logic block diagrams disclosed in the embodiments of this invention. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the dual-channel tracking system phase-correction-free self-tracking method disclosed in the embodiments of this invention can be directly manifested as execution by a hardware processor, or execution by a combination of hardware and software modules within the processor.

[0066] Memory, as a non-volatile computer-readable storage medium, can be used to store non-volatile software programs, non-volatile computer-executable programs, and modules. Memory can include at least one type of storage medium, such as flash memory, hard disk, multimedia cards, card-type memory, random access memory (RAM), static random access memory (SRAM), programmable read-only memory (PROM), read-only memory (ROM), and electrically erasable programmable read-only memory (EPROM). Only memory (EEPROM), magnetic storage, magnetic disks, optical disks, etc. A memory is any other medium capable of carrying or storing desired program code in the form of instructions or data structures, and accessible by a computer, but is not limited thereto. The memory in embodiments of this invention can also be a circuit or any other device capable of performing storage functions for storing program instructions and / or data.

[0067] By designing and programming the processor, the code corresponding to the phase-tracking self-tracking method of the dual-channel tracking system described in the foregoing embodiments can be embedded into the chip, enabling the chip to execute the steps of the method described in the foregoing embodiments during operation. How to design and program the processor is a technique well-known to those skilled in the art and will not be elaborated upon here.

[0068] Based on the same inventive concept, embodiments of the present invention also provide a storage medium storing computer instructions that, when executed on a computer, cause the computer to perform a dual-channel tracking system phase-free self-tracking method described above.

[0069] In some alternative embodiments, the present invention also provides a method for phase-tracking self-tracking of a dual-channel tracking system without phase calibration, which can also be implemented in the form of a program product including program code. When the program product is run on a device, the program code is used to cause the control device to perform the steps in the method for phase-tracking self-tracking of a dual-channel tracking system without phase calibration described above according to various exemplary embodiments of the present invention.

[0070] It should be noted that although several units or sub-units of the apparatus have been mentioned in the detailed description above, this division is merely exemplary and not mandatory. In fact, according to embodiments of the invention, the features and functions of two or more units described above can be embodied in one unit. Conversely, the features and functions of one unit described above can be further divided and embodied by multiple units. Furthermore, although the operation of the method of the invention is described in a specific order in the drawings, this does not require or imply that these operations must be performed in that specific order, or that all the operations shown must be performed to achieve the desired result. Additionally or alternatively, certain steps may be omitted, multiple steps may be combined into one step, and / or one step may be broken down into multiple steps.

[0071] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can be implemented in one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROMs) containing computer-usable program code. The form of a computer program product implemented on ROM, optical memory, etc.

[0072] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a server, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0073] Program code for performing the operations of this invention can be written using any combination of one or more programming languages, including object-oriented programming languages ​​such as Java and C++, as well as conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on the user's computing device, partially on the user's device, as a standalone software package, partially on the user's computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0074] In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0075] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0076] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0077] The embodiments described above merely illustrate specific implementation methods of this application, and while the descriptions are detailed and specific, they should not be construed as limiting the scope of protection of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the technical solution of this application, and these modifications and improvements all fall within the scope of protection of this application.

[0078] This background section is provided to generally present the context of the invention. The work of the currently named inventors, the work to the extent described in this background section, and aspects of this section that did not constitute prior art at the time of application are neither expressly nor impliedly acknowledged as prior art to the invention.

Claims

1. A phase-calibration-free self-tracking method for a dual-channel tracking system, characterized in that, include: Step S1: During the phase alignment process of the aerospace ground antenna with respect to the target, the historical ambient temperature of the tracking and differential link in the temperature-changing environment is obtained by a temperature acquisition device installed in the center of the antenna. Step S2: Store the historical ambient temperature and the corresponding phase correction parameters into the phase difference history database. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, and historical phase difference of the tracking and differential link obtained by satellite phase correction. Step S3: Based on the data accumulated in the historical phase difference database, for the same operating frequency, rotation direction and equipment combination, fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference; Step S4: Before performing the self-tracking task of the target, obtain the current real-time ambient temperature of the antenna center body; Step S5: Based on the current task's operating frequency, rotation direction, and device combination, call the corresponding temperature-phase difference curve, and calculate the real-time phase difference of the current tracking and differential link in conjunction with the real-time ambient temperature; Step S6: Input the real-time phase difference into the tracking receiver, and control the aerospace ground antenna to skip the star phase correction process and directly switch to phase correction-free self-tracking of the target.

2. The phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1, characterized in that, In step S1, the passive and active devices that the tracking and difference links pass through are distributed in the antenna center body, the antenna tower base, and the control room. The antenna tower base and the control room are equipped with temperature-controlled environmental control equipment. The antenna center body and the antenna tower base are connected by a phase-stabilized cable for intermediate frequency signal transmission, and the antenna tower base and the control room are connected by an optical fiber for digital signal transmission. To obtain the historical ambient temperature of the tracking and differential link in a temperature-varying environment, specifically: the temperature inside the antenna center body is obtained solely by the temperature acquisition device installed next to the tracking and differential link within the antenna center body, in order to monitor the phase difference fluctuations caused by temperature changes in devices including the multi-band feed network, low-noise amplifier, and downconverter in a temperature-varying environment.

3. The phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1, characterized in that, In step S2, before storing the historical ambient temperature and the corresponding phase correction parameters into the phase difference history database, a data validity determination step for the historical data is also included: After each phase alignment and target tracking is completed, the tracking accuracy and angular error voltage reported by the antenna control unit are used to automatically determine whether the historical phase difference of the tracking and differential link obtained from this phase alignment is valid data. If the data is deemed valid, it is formally stored in the phase difference history database; if the data is deemed invalid or abnormal, it is identified and removed.

4. The phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1, characterized in that, Between step S3 and step S4, there is also an automatic switching step for working modes based on the amount of accumulated data: Determine whether the data accumulated in the phase difference history database for the same target has covered the entire year's temperature range or a preset temperature range; If so, the tracking method of the target will be automatically configured from the phase-calibration tracking method to the phase-free self-tracking method in the target management interface of the control terminal; when the target task is executed subsequently, steps S4 to S6 will be triggered.

5. The phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1, characterized in that, In step S2, the phase calibration parameters further include: task code, operating frequency band, and operating mode; In step S3, fitting a temperature-phase difference curve reflecting the mapping relationship between ambient temperature and tracking / differential link phase difference based on the data accumulated in the historical phase difference database specifically includes: In the historical phase difference database, data is filtered by using the same operating frequency, rotation direction, and device combination as joint query conditions. Extract all valid historical phase differences distributed across different historical ambient temperatures that satisfy the joint query conditions; The temperature-phase difference curve is generated by fitting the extracted discrete temperature and phase difference data points.

6. The phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1, characterized in that, In step S5, for the application scenario where target measurement and control and data transmission work simultaneously, the working frequency points include the working frequency points of the measurement and control frequency band and the working frequency points of the data transmission frequency band. When calculating the real-time phase difference of the current tracking and difference links, the pre-fitted temperature-phase difference curves of the measurement and control frequency band and the data transmission frequency band are extracted respectively. Combined with the same real-time ambient temperature obtained at the moment, the independent real-time phase difference of the measurement and control frequency band and the real-time phase difference of the data transmission frequency band are calculated in parallel.

7. A phase-calibration-free self-tracking method for a dual-channel tracking system according to claim 1 or 6, characterized in that, In step S6, skipping the phase correction step and directly transitioning to phase-correction-free self-tracking of the target specifically includes: When the target enters the station, skip the antenna deflection search for the target and perform satellite phase correction operation to avoid azimuth and elevation secant compensation during satellite phase correction. The calculated real-time phase difference is directly input into the tracking receiver. The tracking receiver performs digital phase shifting on the input differential signal based on the input real-time phase difference, so that it is in phase with the input sum signal to eliminate cross-coupling between azimuth and elevation, thereby realizing the self-tracking of the target signal by the aerospace ground antenna.

8. A dual-channel tracking system with phase-calibration-free self-tracking capability, characterized in that, To implement the method according to any one of claims 1-7, comprising: The historical data acquisition module is used to acquire the historical ambient temperature of the tracking and differential link in a temperature-changing environment during the phase alignment process of the aerospace ground antenna with respect to each target. The data entry module is used to store the historical ambient temperature and the corresponding phase correction parameters into the historical phase difference database. The phase correction parameters include at least: operating frequency, rotation direction, equipment combination, and historical phase difference of the tracking and differential link obtained by satellite phase correction. The curve fitting module is used to fit a temperature-phase difference curve that reflects the mapping relationship between ambient temperature and tracking and differential link phase difference, based on the data accumulated in the phase difference historical database, for the same operating frequency, rotation direction and equipment combination. The real-time temperature acquisition module is used to acquire the current real-time ambient temperature of the antenna center body before performing the self-tracking task of the target. The phase difference calculation module is used to calculate the real-time phase difference of the current tracking and differential link by calling the corresponding temperature-phase difference curve based on the current task's operating frequency, rotation direction, and device combination, combined with the real-time ambient temperature. The phase-correction-free tracking execution module is used to input the real-time phase difference into the tracking receiver and control the aerospace ground antenna to skip the satellite phase correction process and directly switch to phase-correction-free self-tracking of the target.

9. An electronic device, characterized in that, include: At least one processor; and a memory communicatively connected to the at least one processor; The memory stores instructions executable by the at least one processor, which executes the instructions stored in the memory to perform the method as described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium is used to store instructions that, when executed, cause the method as described in any one of claims 1-7 to be implemented.

Images