A system and method for predicting the angle of receiving antenna of Fengyun synchronous orbit satellite

Abstract

The present invention discloses a method and system for predicting the receiving antenna angle of a Fengyun synchronous orbit satellite, wherein the method comprises the following steps: establishing a dynamic database for antenna tracking angles; generating a queue by one-to-one correspondence of all antenna angles and moments in each space-relative revolution period of the satellite according to the dynamic database; calculating the antenna tracking angle change difference of the satellite at each moment in adjacent revolution periods according to the queue; calculating the antenna angle in the next period according to the antenna tracking angle change difference. Thus, the present invention can calculate the antenna pointing angle position of the receiving antenna when the satellite signal is lost, and predict the angle that the antenna should point to in the next 24 hours, so that once the satellite signal is restored, the receiving antenna can quickly lock the satellite.

Description

Technical Field

[0001] The invention relates to the technical field of satellite navigation, and in particular to a method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite. Background Art

[0002] After being fixed, the position of a geosynchronous orbit satellite in space is not completely stationary, but rather it performs periodic reciprocating regular motion over the equator, and the position of the satellite in space also forms a certain pattern to follow every day. The Fengyun series of synchronous orbit satellites also follow a certain pattern to operate in space every day. The Fengyun synchronous orbit satellite receiving antenna tracks satellite signals at all times, and the pointing angle of the receiving antenna changes regularly every day as the spatial position of the satellite changes. When the satellite signal is lost due to an unexpected situation, the existing tracking method is to directly use the antenna pointing angle 24 hours ago as a reference to find the satellite signal. Due to the 24-hour time difference, the actual position of the satellite will drift a certain amount compared to 24 hours ago, and the pointing angle of the antenna will also have a certain error, which is not conducive to locking the satellite signal. Summary of the invention

[0003] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a method and system for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna, which can calculate the antenna pointing angle position of the receiving antenna when the satellite signal is lost, and predict the angle that the antenna should point to within the next 24 hours, so that once the satellite signal is restored, the receiving antenna can quickly lock onto the satellite.

[0004] In the first aspect, in order to solve the above technical problems, the basic concept of the technical solution adopted by the present invention is:

[0005] A method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite, the method comprising the following steps:

[0006] Establish a dynamic database for antenna tracking angles;

[0007] According to the dynamic database, all antenna angles and time in each space relative revolution period of the satellite are matched one by one to generate a queue;

[0008] According to the queue, the difference of the satellite's antenna tracking angle change at each moment in adjacent revolution periods is calculated;

[0009] The antenna angle in the next cycle is calculated based on the difference in antenna tracking angle change.

[0010] In a preferred embodiment of any of the above schemes, the dynamic database includes the time stamp of the antenna tracking angle, the azimuth and pitch tracking angle of the antenna, the dynamic database stores the antenna angle data of at least two tracking cycles, and the dynamic database is a first-in-first-out timely updated queue, and can set the number of dates and time intervals of the stored antenna tracking angles according to needs and storage medium capacity.

[0011] In a preferred embodiment of any of the above schemes, the calculation formula for calculating the difference in antenna tracking angle change of the satellite at each moment in adjacent revolution periods according to the queue is:

[0012] Δθ=θ n -θ n-1

[0013] Among them, θ n is the antenna angle at this moment in the previous tracking cycle, θ n-1 is the antenna angle at that moment in the previous tracking cycle, and Δθ is the change in the angle difference between the last two tracking cycles at that moment.

[0014] In a preferred embodiment of any of the above schemes, the calculation formula for calculating the antenna angle in the next cycle according to the antenna tracking angle change difference is:

[0015] θ n+1 =θ n +Δθ

[0016] Among them, θ n+1 is the antenna angle in the next cycle.

[0017] In a preferred embodiment of any of the above schemes, after the dynamic database for antenna tracking angles is established, it also includes: acquiring satellite signals; tracking the satellite signals in real time based on the satellite signals, and entering intelligent prediction tracking mode when the tracked satellite signals are abnormally unlocked.

[0018] In a preferred embodiment of any of the above schemes, after entering the intelligent prediction tracking mode, it also includes: receiving an error signal from a tracking receiver; digitally processing the error signal to obtain a digital signal; amplifying the digital signal to obtain an amplified signal; and feeding back the amplified signal to an actuator to achieve correction and tracking of the target.

[0019] In a second aspect, the present invention provides a system for predicting the receiving antenna angle of a Fengyun synchronous orbit satellite, comprising: an establishment module, a generation module, a first calculation module and a second calculation module. The establishment module is used to establish a dynamic database for antenna tracking angles. The generation module is used to generate a queue according to the dynamic database, one-to-one corresponding to all antenna angles and moments in each space-relative revolution period of the satellite. The first calculation module is used to calculate the difference in antenna tracking angle changes of the satellite at each moment in adjacent revolution periods according to the queue. And the second calculation module is used to calculate the antenna angle in the next period according to the difference in antenna tracking angle changes.

[0020] In a preferred embodiment of any of the above schemes, the dynamic database includes the time stamp of the antenna tracking angle, the azimuth and pitch tracking angle of the antenna, and the dynamic database stores the antenna angle data of at least two tracking cycles, and the dynamic database is a first-in-first-out timely updated queue, and can set the number of dates and time intervals of the stored antenna tracking angles according to needs and the capacity of the storage medium.

[0021] In a third aspect, the present invention provides a computing device for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna, comprising: one or more processors; a storage device for storing one or more programs, and when the one or more programs are executed by one or more processors, the one or more processors implement the method for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna as described above.

[0022] In a fourth aspect, the present invention provides a computer-readable storage medium, in which a program is stored, and when the program is executed by a processor, the method for predicting the angle of a FY geosynchronous orbit satellite receiving antenna as described above is implemented.

[0023] Compared with the prior art, the method and system for predicting the angle of the FY geosynchronous orbit satellite receiving antenna in the embodiments of the present application can calculate the antenna pointing angle position of the receiving antenna when the satellite signal is lost, and predict the angle that the antenna should point to within the next 24 hours, so that once the satellite signal is restored, the receiving antenna can quickly lock onto the satellite.

[0024] The specific implementation modes of the present invention are further described in detail below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. Some specific embodiments of the present application will be described in detail in an illustrative and non-restrictive manner with reference to the drawings. The same reference numerals in the drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the drawings:

[0026] Figure 1 is a flow chart of a method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite according to an embodiment of the present invention;

[0027] Figure 2 is a detailed flow chart of a method for predicting the angle of a receiving antenna of a FY-GEO satellite according to an embodiment of the present invention;

[0028] Figure 3 is a schematic diagram of an azimuth angle tracking curve of an embodiment of a method for predicting the angle of a receiving antenna of a FY-GEO satellite according to an embodiment of the present invention;

[0029] Figure 4 is a schematic diagram of a pitch angle tracking curve of an embodiment of a method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite according to an embodiment of the present invention;

[0030] Figure 5 is a schematic diagram of an azimuth tracking degree curve of another embodiment of a method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite according to an embodiment of the present invention;

[0031] Figure 6 is a schematic diagram of comparing the predicted azimuth angle and the actual angle of another embodiment of the method for predicting the angle of a receiving antenna of a FY-GEO satellite according to an embodiment of the present invention;

[0032] Figure 7 is a schematic diagram of a pitch tracking angle curve of another embodiment of a method for predicting a receiving antenna angle of a FY-GEO satellite according to an embodiment of the present invention;

[0033] Figure 8 is a schematic diagram showing a comparison between a predicted pitch angle and an actual angle in another embodiment of a method for predicting a receiving antenna angle of a FY-GEO satellite according to an embodiment of the present invention;

[0034] Fig. 9 is a schematic diagram of a wireframe structure of a servo system of a method for predicting the angle of a receiving antenna of a Fengyun synchronous orbit satellite according to an embodiment of the present invention;

[0035] Fig.10is a schematic diagram of the main interface of an antenna control unit of a method for predicting the angle of a FY-GEO satellite receiving antenna according to an embodiment of the present invention;

[0036] Fig.11 It is a schematic diagram of a memory tracking data interface of a method for predicting the angle of a FY geostationary orbit satellite receiving antenna according to an embodiment of the present invention.

[0037] Fig.12 It is a schematic diagram of a work log storage interval interface of a method for predicting a FY-GEO satellite receiving antenna angle according to an embodiment of the present invention.

[0038] Fig.13 2 is a schematic diagram of an angle data record queue of a method for predicting the angle of a FY geostationary orbit satellite receiving antenna according to an embodiment of the present invention.

[0039] Fig.14 2 is a schematic diagram of another angle data record queue of the method for predicting the angle of a FY geostationary orbit satellite receiving antenna according to an embodiment of the present invention.

[0040] Fig.15 It is a schematic diagram of the structure of a computing device for predicting the angle of a receiving antenna of a FY geosynchronous orbit satellite according to an embodiment of the present invention.

[0041] It should be noted that these drawings and textual descriptions are not intended to limit the conceptual scope of the present invention in any way, but are intended to illustrate the concept of the present invention for those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0042] The specific implementation modes of the present invention are described in detail below in conjunction with the accompanying drawings, but it should be understood that the protection scope of the present invention is not limited by the specific implementation modes.

[0043] Unless explicitly stated otherwise, throughout the specification and claims, the term “comprise” or variations such as “include” or “comprising”, etc., will be understood to include the stated elements or components but not to exclude other elements or components.

[0044] In order to make the technical personnel in the technical field better understand the scheme of the present application, the technical scheme in the embodiment of the present application will be clearly and completely described below in combination with the drawings in the embodiment of the present application. Obviously, the described embodiment is only a part of the embodiment of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work should fall within the scope of protection of the present application.

[0045] It should be noted that the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0046] The following embodiment of the present application takes the 3D passive source pseudo-shot gather calculation method as an example to explain the solution of the present application in detail, but this embodiment cannot limit the protection scope of the present application.

[0047] Example

[0048] like Figure 1 As shown, the present invention provides a 3D passive source pseudo-shot gather calculation method, the method comprising the following steps:

[0049] Step 1: Establish a dynamic database for antenna tracking angles;

[0050] Step 2: Generate a queue by mapping all antenna angles and time in each relative orbital period of the satellite according to the dynamic database;

[0051] Step 3: Based on the queue, calculate the difference in the satellite's antenna tracking angle change at each moment in adjacent revolution periods;

[0052] Step 4: Calculate the antenna angle in the next cycle based on the difference in antenna tracking angle change.

[0053] In a preferred embodiment of any of the above schemes, the dynamic database includes the time stamp of the antenna tracking angle, the azimuth and pitch tracking angle of the antenna, the dynamic database stores the antenna angle data of at least two tracking cycles, and the dynamic database is a first-in-first-out timely updated queue, and can set the number of dates and time intervals of the stored antenna tracking angles according to needs and storage medium capacity.

[0054] In a preferred embodiment of any of the above schemes, the calculation formula for calculating the difference in antenna tracking angle change of the satellite at each moment in adjacent revolution periods according to the queue is:

[0055] Δθ=θ n -θ n-1

[0056] Among them, θ n is the antenna angle at this moment in the previous tracking cycle, θ n-1 is the antenna angle at that moment in the previous tracking cycle, and Δθ is the change in the angle difference between the last two tracking cycles at that moment.

[0057] In a preferred embodiment of any of the above schemes, the calculation formula for calculating the antenna angle in the next cycle according to the antenna tracking angle change difference is:

[0058] θ n+1 =θ n +Δθ

[0059] Among them, θ n+1 is the antenna angle in the next cycle.

[0060] In a preferred embodiment of any of the above schemes, after completing the above calculations, it is necessary to consider the tracking accuracy issue to verify whether the operation requirements can be met, and the variance calculation of the tracking accuracy needs to consider the azimuth variance and the pitch variance, and the azimuth pitch prediction angle combined overall variance calculation formula is:

[0061]

[0062] Where σ is the joint standard deviation of azimuth and elevation tracking accuracy, σ A is the standard deviation of the orientation, σ E is the pitch standard deviation.

[0063] In a preferred embodiment of any of the above schemes, the method for predicting the angle of the FY geosynchronous orbit satellite receiving antenna also includes entering an intelligent prediction tracking mode when the antenna control subsystem tracks the satellite signal and loses lock abnormally, and the antenna control subsystem includes an antenna control unit and an antenna driving unit, and the antenna control subsystem is used to control and drive the antenna.

[0064] In a preferred embodiment of any of the above schemes, the antenna control subsystem receives the error signal from the tracking receiver, and feeds it back to the actuator servo motor after digital processing and amplification, driving the antenna to move in the direction of reducing the error, thereby completing the functions of pointing, capturing, tracking and measuring the angle of the target.

[0065] In a second aspect, the present invention provides a system for predicting the receiving antenna angle of a Fengyun synchronous orbit satellite, comprising: a system monitoring station, an antenna control unit, an antenna driving unit, an azimuth combination mechanism, a pitch combination mechanism, and an antenna protection device. The antenna control unit is respectively connected to the system monitoring station and the tracking receiver. The antenna driving unit is connected to the antenna control unit. The azimuth combination mechanism is respectively connected to the antenna driving unit and the antenna. The pitch combination mechanism is respectively connected to the antenna driving unit and the antenna. The antenna protection device is respectively connected to the antenna driving unit and the antenna, and the antenna is used to track the satellite in real time. Among them, the antenna control unit controls the system monitoring station to establish a dynamic database for antenna tracking angles, and generates a queue according to the dynamic database for all antenna angles and moments in each space relative revolution period of the satellite, and calculates the difference in antenna tracking angle changes of the satellite at each moment in adjacent revolution periods according to the queue, so as to calculate the antenna angle in the next period according to the difference in antenna tracking angle changes.

[0066] In a third aspect, the present invention provides a computing device for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna, comprising: one or more processors; a storage device for storing one or more programs, and when the one or more programs are executed by one or more processors, the one or more processors implement the method for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna as described above.

[0067] In a fourth aspect, the present invention provides a computer-readable storage medium, in which a program is stored, and when the program is executed by a processor, the method for predicting the angle of a FY geosynchronous orbit satellite receiving antenna as described above is implemented.

[0068] In practical applications, the method of predicting the receiving antenna angle of a FY-SSO satellite of the present invention specifically includes: creating a dynamic database of antenna tracking angles. If the antenna control subsystem tracks the satellite signal and loses lock abnormally, it enters the intelligent prediction and tracking mode. The antenna azimuth angle is intelligently predicted and tracked, calling the azimuth angle information in the dynamic database of the antenna tracking angle at the current moment of the previous two tracking cycles, and calculating the azimuth prediction angle, and the antenna control subsystem drives the pointing direction to the azimuth prediction angle. The antenna pitch angle is intelligently predicted and tracked, calling the pitch angle information in the dynamic database of the antenna tracking angle at the current moment of the previous two tracking cycles, and calculating the pitch prediction angle, and the antenna control subsystem drives the pointing direction to the pitch prediction angle. Antenna 1 maintains the azimuth prediction angle and pitch prediction angle at this moment, and the antenna signal drops to the tracking threshold, and enters the prediction tracking of the next time. Among them, the antenna tracking angle dynamic database includes the time mark of the antenna tracking angle, the azimuth and pitch tracking angle of antenna 1, and the antenna tracking angle dynamic database stores the antenna angle data of at least two tracking cycles. Among them, the antenna tracking angle dynamic database is a first-in-first-out timely update queue, and the number of dates and time intervals of the stored antenna tracking angles can be set according to needs and the capacity of the storage medium. Among them, all antenna angles and time in at least two spatial relative revolution periods of the satellite are stored in a dynamic database of antenna tracking angles in a one-to-one correspondence, and then the antenna prediction angle is calculated.

[0069] The satellite receiving antenna 1 is a key link in realizing satellite-to-ground link communication. The main function of the receiving antenna 1 is to accurately and quickly point to the satellite and continuously and stably track the satellite. The purpose of the present invention is to solve the error problem of using the antenna tracking pointing angle 24 hours ago after the Fengyun synchronous satellite signal is lost. The Fengyun synchronous satellites currently in orbit include the Fengyun-2 and Fengyun-4 series. Taking the pointing angle of the antenna 1 during the actual operation of the Fengyun-4 satellite as an example, the specific content and purpose of the present invention are explained.

[0070] On December 11, 2016, the FY-4A satellite was successfully launched from the Xichang Satellite Launch Center on a Long March 3B rocket, and was positioned at an altitude of 36,000 kilometers above the Earth's equator at 104.5° east longitude. The slightest deviation of the ground antenna pointing to the satellite can mean a difference of tens or even hundreds of kilometers relative to space. Therefore, it is very important for the actual system to ensure that Antenna 1 can point to the satellite quickly and accurately. Taking the actual tracking data of the FY-4A satellite receiving antenna as an example, from August 10 to August 12, 2019, the azimuth and pitch angle data of Antenna 1 tracking the satellite for three consecutive days are shown in the figure below: Figure 3 and Figure 4 As shown:

[0071] By analyzing the tracking data, the following conclusions can be drawn:

[0072] 1. The daily tracking operation of antenna 1 follows a certain rule, and the antenna tracking angle is periodic;

[0073] 2. The change rules of the azimuth and elevation angles of the antenna tracking angle in each tracking cycle are similar;

[0074] 3. The changing trend of the antenna angle at the same time in this tracking cycle and the previous cycle is similar, and the difference in the angle change is small.

[0075] According to the antenna tracking operation rules analyzed above, we can design a prediction tracking model for antenna 1. First, we need to establish a dynamic database of antenna tracking angles, which includes the time stamp of antenna tracking angles, the azimuth and elevation tracking angles of antenna 1. According to actual needs, the antenna angle data of the most recent tracking cycle (no less than two tracking cycles) can be stored, and the data can be stored in the folder where the antenna tracking software is located so that it can be called at any time. This is a "first in, first out" timely update queue. According to actual needs and storage medium capacity, the number of dates and time intervals of the stored tracking angles can be set (can be set to seconds, minutes or hours). All antenna angles and moments within at least two spatial relative revolution periods of the satellite are stored in the antenna angle database in a one-to-one correspondence, and then the difference in the change of the antenna tracking angle of the satellite at each moment in the previous revolution period and the previous revolution period is calculated. Finally, the angle of the previous tracking period plus the change in the angle difference of the adjacent period can be used to predict the antenna angle in the next period.

[0076] The calculation method of the antenna prediction angle is:

[0077] θ n+1 =θ n +Δθ

[0078] Δθ=θ n -θ n-1

[0079] Among them, θ n+1 is the antenna angle at the time to be predicted, θ n is the antenna angle at this moment in the previous tracking cycle, θ n-1 is the antenna angle at that moment in the previous tracking cycle, and Δθ is the change in the angle difference between the last two tracking cycles at that moment.

[0080] For example, take the prediction of the antenna tracking angle at 00:07 on August 12, 2019 as an example. First, trace back the angle data of the previous two tracking cycles, that is, the antenna azimuth and elevation angle at 00:07 on August 10, 2019 and 00:07 on August 11, 2019, as shown in Table 1:

[0081] Table 1 Example of prediction angle calculation method

[0082]

[0083] Calculations show that the absolute value of the difference between the actual antenna azimuth angle and the predicted angle at this moment is 0.001 degrees, which is smaller than the absolute value of the angle difference of 0.0022 degrees when directly using the 11th day. The absolute value of the difference between the actual antenna pitch angle and the predicted angle is 0.005 degrees, which is smaller than the absolute value of the angle difference of 0.008 degrees when directly using the 11th day.

[0084] Without loss of generality, the actual tracking data of the FY-4 receiving antenna is used as an example to illustrate the relationship between the predicted angle and the actual angle within a tracking cycle. The data on August 10, 2019 is used as the first cycle position data, and the data on August 11, 2019 is used as the second cycle position data. The angle difference at the same time in the first cycle and the second cycle is the predicted angle increment. The predicted angle data on August 12, 2019 is calculated according to the predicted angle formula and compared with the actual angle of that day, as shown in the figure below: Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown:

[0085] The files recorded in the antenna database record the azimuth and elevation angle of the antenna in units of ten minutes, 6 times per hour, and 144 sets of data per day. Based on the angles recorded on August 10, 2019, August 11, 2019, and August 12, 2019, the angle change differences of the antenna azimuth angle and elevation angle at the corresponding moments of the cycle are calculated respectively. The comparison results of the predicted tracking accuracy test results and the actual angles are shown in Table 2 below:

[0086] Table 2 Comparison of relevant parameters of prediction and tracking results

[0087]

[0088] The existing memory tracking method directly uses the angle of the previous tracking cycle, that is, after the antenna signal loses lock on August 12, 2019, the antenna angle of the corresponding cycle time on August 11, 2019 is directly called. Since the satellite has a daily fixed drift, there will be a constant error a when the tracking angle of the previous day is directly used. Now, after the intelligent prediction tracking method is used, the tracking angle of the previous day plus a correction angle c is used as the predicted angle after the antenna loses lock. The predicted angle obtained in this way is better than the angle of the previous day directly used, that is, the absolute value of the difference b between the predicted angle and the actual angle is smaller than the absolute value of the difference a between the angle of the previous day directly used and the actual angle.

[0089] The actual pointing angle of the antenna consists of two parts, the azimuth angle and the elevation angle. The maximum signal reception can be achieved only when the azimuth and elevation are accurately pointed at the satellite at the same time. Therefore, the variance calculation of tracking accuracy needs to comprehensively consider the azimuth variance and the elevation variance. The formula for calculating the combined overall variance of the azimuth and elevation prediction angles is:

[0090]

[0091] Where σ is the joint standard deviation of azimuth and elevation tracking accuracy, σ A is the standard deviation of the orientation, σ E is the pitch standard deviation.

[0092] The following conclusions can be drawn from the analysis and comparison of tracking results:

[0093] 1. The absolute value b of the difference between the predicted angle and the actual angle of the average azimuth difference and the average pitch difference is smaller than the absolute value a of the difference between the angle of the previous tracking cycle and the actual angle. The absolute value a of the azimuth average is 0.02424, and the absolute value b of the azimuth average is 0.00544.

[0094] 2. Azimuth standard deviation σ of the difference between the predicted angle and the actual angle A is 0.00275, and the pitch standard deviation σ between the predicted angle and the actual angle E The predicted tracking result variance is 0.005115, and the overall variance is 0.007742, which is about one twentieth of the beam width of 0.16°. It can meet the operational requirements. The business operation requires that the azimuth and elevation joint overall variance is less than one tenth of the beam width.

[0095] Conclusion: Tracking satellites using predicted angles is better than directly using the angles from the previous cycle.

[0096] Since antenna 1 tracks satellites all the time, when heavy rain or snow occurs in the signal link transmission space, the tracking signal of antenna 1 will be greatly attenuated, resulting in signal loss, so that the original tracking method cannot be used to point to the satellite, or the antenna signal tracking receiver 9 fails, resulting in the inability of antenna 1 to identify and resolve the tracking signal. In this case, the tracking mode fails. The original solution directly uses yesterday's tracking angle data to ensure that antenna 1 points to the satellite. The defect is that there is a deviation between yesterday's pointing angle of antenna 1 and today's pointing angle. The intelligent memory tracking method of the present invention is now used to add a correction value calculated by intelligent comparison to yesterday's angle to offset the error between yesterday's angle and today's angle, which can ensure that the antenna tracking pointing is more accurate.

[0097] The present invention proposes a method for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna based on the conventional tracking operation mode of the original Fengyun synchronous satellite receiving antenna. A receiving antenna prediction tracking model can be established, and the predicted tracking angle data and the actual angle data are compared to meet the antenna tracking angle index. According to this method, the pointing position of the antenna 1 when the satellite tracking path signal is lost can be predicted and calculated according to the periodic law of the antenna's daily operation. This method has certain reference significance for improving antenna tracking efficiency, predicting satellite orbital positions, and stably receiving high-frequency satellite signals that are more susceptible to environmental influences.

[0098] The method for predicting the angle of the receiving antenna of a Fengyun synchronous orbit satellite of the present invention can be achieved by writing a software program that records the antenna tracking angle at all times and a program that calculates the angle difference of the antenna tracking cycle in the tracking software of the satellite receiving antenna. The method can be achieved by writing a software program that causes the receiving antenna to enter an intelligent memory tracking program after the satellite signal is lost.

[0099] Fig. 9 FIG. 1 is a schematic diagram of a wireframe structure of a servo system for predicting the angle of a FY-GEO satellite receiving antenna according to an embodiment of the present invention. Fig. 9 As shown, the antenna control subsystem is mainly composed of an antenna control unit 2 (ACU) and an antenna drive unit 3 (ADU). It is an important part of the antenna servo feed system and mainly drives and controls the antenna 1. It receives the error signal from the receiver, digitally processes and amplifies it, and finally feeds it back to the actuator servo motor (azimuth motor combination 4, azimuth transmission combination 5, pitch motor combination 6 and pitch transmission combination 7), driving the antenna 1 to move in the direction of reducing the error, thereby completing the functions of pointing, capturing, tracking and measuring the angle of the target. The antenna control subsystem also includes a time system 8, a tracking receiver 9, a system monitoring station 10, an encoding time code unit 11, an azimuth / pitch rotary mechanism 12 and an antenna protection device 13.

[0100] The antenna control unit 2 is configured with an operating system (MS Windows 7 Ultimate Edition) and application software (Delphi 5.0). The startup process of the antenna control unit 2 is as follows:

[0101] 1. The antenna control unit 2 (ACU) is powered on and the Windows 7 system displays normally;

[0102] 2. Double-click the ACU shortcut icon on the desktop, or run the ACU.exe file in the D:\ACU\bin folder to enter the main interface of the ACU software.

[0103] Fig.10 1 is a schematic diagram of the main interface of the antenna control unit 2 of the method for predicting the angle of the FY geostationary orbit satellite receiving antenna according to an embodiment of the present invention. Fig.11Schematic diagram of the memory tracking data interface of the method for predicting the angle of the FY geostationary orbit satellite receiving antenna according to one embodiment of the present invention. Figure 10 to Figure 11 As shown, a memory tracking data interface and a predictive tracking data calculation module are added. The module stores at least two days and 48 hours of effective tracking data. In the self-tracking or step tracking mode, after tracking is in place, a group of data is recorded every 10 minutes, and a total of 24*6=144 groups are recorded every day. When the antenna signal is unlocked and self-tracking and step tracking cannot be performed, the tracking data calculated intelligently according to the algorithm of the present invention is used for predictive tracking.

[0104] like Fig.12 As shown in the figure, the construction process of the dynamic database is as follows: select an appropriate storage tracking data time interval in the work log storage interval interface, such as Figure 1 As shown in the figure, the available gears are 1 second, 1 minute, 10 minutes, 30 minutes, 40 minutes, and 60 minutes. Generate an ACU data record file database under the WorkData file, such as Figure 2 The data log file content includes date, time, antenna working mode, azimuth and elevation angle, tracking signal level and online receiver status and other parameters.

[0105] The antenna angle and time are generated into a queue: if you choose to record a set of data every 10 minutes, then 6 sets of data will be recorded every hour. The tracking revolution period of the Fengyun synchronous orbit satellite is one day, so 144 sets of data are recorded in 24 hours a day. The data sets form a daily record of 144 sets of data queues arranged in time in the memory tracking data and are numbered in a one-to-one correspondence between the sequence number, time, azimuth and pitch angle, such as Fig.13 and Fig.14 According to actual needs, at least the data within the last two tracking cycles should be saved and recorded. The stored data queue should be dynamically updated according to the tracking cycle, and the called data queue should always be the data of the last two tracking cycles.

[0106] The difference of the antenna tracking angle change of the satellite at each moment in the adjacent revolution period is calculated. For example, how to get the predicted antenna angle at a certain moment on January 3, 2022? Predict the angle at 0:45 on January 3, 2022 (recorded as ∠C), select the angle of the record with the closest time to 0:45 on January 2, 2022 at 0:43 and serial number 5 (recorded as ∠A) and the angle of the record with the closest time to 0:45 on January 1, 2022 at 0:43 and serial number 5 (recorded as ∠B), and predict the angle calculation formula for January 3, 2022: ∠C=∠A+∠A-∠B.

[0107] Fig.15A schematic diagram of the structure of a computing device for predicting the angle of a FY geosynchronous orbit satellite receiving antenna provided in an embodiment of the present invention. Fig.15 A block diagram of an exemplary computing device for predicting the angle of a FY-GEO satellite receiving antenna suitable for implementing an embodiment of the present invention is shown. Fig.15 The calculation device for predicting the angle of the FY geostationary orbit satellite receiving antenna shown is only an example and should not bring any limitation to the function and scope of use of the embodiments of the present invention.

[0108] like Fig.15 As shown, the computing device for predicting the angle of the FY geostationary orbit satellite receiving antenna is presented in the form of a general computing device. The components of the computing device for predicting the angle of the FY geostationary orbit satellite receiving antenna may include, but are not limited to: one or more processors or processing units, memory, and a bus connecting different system components (including memory and processing units).

[0109] The term "bus" refers to one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processor or a local bus using any of a variety of bus architectures. For example, these architectures include, but are not limited to, the Industry Standard Architecture (ISA) bus, the Micro Channel Architecture (MAC) bus, the Enhanced ISA bus, the Video Electronics Standards Association (VESA) local bus, and the Peripheral Component Interconnect (PCI) bus.

[0110] The computing device for predicting the angle of the FY geostationary orbit satellite receiving antenna typically includes a variety of computer system readable media. These media can be any available media that can be accessed by the computing device for predicting the angle of the FY geostationary orbit satellite receiving antenna, including volatile and non-volatile media, removable and non-removable media.

[0111] The memory may include computer system readable media in the form of volatile memory, such as random access memory (RAM) 30 and / or cache memory. The computing device for predicting the FY-SSO satellite receiving antenna angle may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, the storage system may be used to read and write non-removable, non-volatile magnetic media ( Fig.15 not shown, usually called a "hard drive"). Although Fig.15Not shown, a disk drive for reading and writing to a removable non-volatile disk (e.g., a "floppy disk"), and an optical disk drive for reading and writing to a removable non-volatile optical disk (e.g., a CD-ROM, DVD-ROM, or other optical medium) may be provided. In these cases, each drive may be connected to the bus via one or more data medium interfaces. The memory may include at least one program product having a set (e.g., at least one) of program modules that are configured to perform the functions of the embodiments of the present invention.

[0112] A program / utility having a set (at least one) of program modules may be stored, for example, in a memory, such program modules including but not limited to an operating system, one or more application programs, other program modules, and program data, each of which or some combination may include an implementation of a network environment. The program modules generally perform the functions and / or methods of the embodiments described herein.

[0113] The computing device for predicting the angle of the FY-GSO satellite receiving antenna can also communicate with one or more external devices (e.g., keyboard, pointing device, display, etc.), and can also communicate with one or more devices that enable users to interact with the computing device for predicting the angle of the FY-GSO satellite receiving antenna, and / or communicate with any device (e.g., network card, modem, etc.) that enables the computing device for predicting the angle of the FY-GSO satellite receiving antenna to communicate with one or more other computing devices. Such communication can be performed through an input / output (I / O) interface. In addition, the computing device for predicting the angle of the FY-GSO satellite receiving antenna can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN) and / or public network, such as the Internet) through a network adapter. As shown in the figure, the network adapter communicates with other modules of the computing device for predicting the angle of the FY-GSO satellite receiving antenna through a bus. It should be understood that, although not shown in the figure, other hardware and / or software modules can be used in conjunction with the computing device for predicting the angle of the FY-GSO satellite receiving antenna, including but not limited to: microcode, device driver, redundant processing unit, external disk drive array, RAID system, tape drive, and data backup storage system, etc.

[0114] The processing unit executes various functional applications and data processing by running the program stored in the memory, for example, implementing the stack splitting processing method provided by any embodiment of the present invention. That is: establishing a dynamic database for antenna tracking angles; generating a queue by one-to-one correspondence of all antenna angles and moments in each space-relative revolution period of the satellite according to the dynamic database; calculating the difference in antenna tracking angle changes of the satellite at each moment in adjacent revolution periods according to the queue; calculating the antenna angle in the next period according to the difference in antenna tracking angle changes.

[0115] An embodiment of the present invention also provides a computer-readable storage medium, in which a program is stored. When the program is executed by a processor, the method for processing stack splitting as described in any embodiment of the present invention is implemented, and the method includes: establishing a dynamic database for antenna tracking angles; generating a queue according to the dynamic database, one-to-one correspondingly matching all antenna angles and moments in each spatial relative revolution period of the satellite; calculating the difference in antenna tracking angle changes of the satellite at each moment in adjacent revolution periods according to the queue; and calculating the antenna angle in the next period according to the difference in antenna tracking angle changes.

[0116] In summary, the method and system for predicting the angle of the receiving antenna of the Fengyun synchronous orbit satellite of the present invention can calculate the antenna pointing angle position of the receiving antenna when the satellite signal is lost, and predict the angle that the antenna should point to in the next 24 hours, so that once the satellite signal is restored, the receiving antenna can quickly lock the satellite. The computer storage medium of the embodiment of the present invention can adopt any combination of one or more computer-readable media. The computer-readable medium can be a computer-readable signal medium or a computer-readable storage medium. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media (non-exhaustive list) include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In this document, a computer-readable storage medium can be any tangible medium containing or storing a program, which can be used by an instruction execution system, device or device or used in combination with it.

[0117] Computer-readable signal media may include data signals propagated in baseband or as part of a carrier wave, which carry computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Computer-readable signal media may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0118] The program code embodied on the computer readable medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing.

[0119] Computer program code for performing the operations of the present invention may be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., through the Internet using an Internet service provider).

[0120] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for predicting the angle of a FY geostationary orbit satellite receiving antenna, characterized in that: include: Establish a dynamic database for antenna tracking angles; According to the dynamic database, all antenna angles and time in each space relative revolution period of the satellite are matched one by one to generate a queue; According to the queue, the difference of the antenna tracking angle change of the satellite at each moment in adjacent revolution periods is calculated; The antenna angle in the next cycle is calculated according to the antenna tracking angle change difference.

2. The method for predicting the angle of a FY-SSO satellite receiving antenna according to claim 1, characterized in that: The dynamic database includes the time stamp of the antenna tracking angle, the azimuth and pitch tracking angle of the antenna. The dynamic database stores the antenna angle data of at least two tracking cycles, and the dynamic database is a first-in-first-out timely updated queue, and can set the number of dates and time intervals of the stored antenna tracking angles according to needs and storage medium capacity.

3. The method for predicting the angle of a FY-GSO satellite receiving antenna as claimed in claim 1, characterized in that: The calculation formula for calculating the difference in the antenna tracking angle change of the satellite at each moment in adjacent revolution periods is: Δθ=θ n -θ n-1 Among them, θ n is the antenna angle at this moment in the previous tracking cycle, θ n-1 is the antenna angle at that moment in the previous tracking cycle, and Δθ is the change in the angle difference between the last two tracking cycles at that moment.

4. The method for predicting the angle of a FY-SSO satellite receiving antenna as claimed in claim 3, characterized in that: The calculation formula for calculating the antenna angle in the next cycle according to the antenna tracking angle change difference is: i n+1 =θ n +Δθ Among them, θ n+1 is the antenna angle in the next cycle.

5. The method for predicting the angle of a FY-GSO satellite receiving antenna as claimed in claim 1, characterized in that: After the dynamic database for antenna tracking angle is established, the method further includes: Acquire satellite signals; According to the satellite signal, the satellite signal is tracked in real time, and when the tracked satellite signal is abnormally lost, the intelligent prediction tracking mode is entered.

6. The method for predicting the angle of a FY-GSO satellite receiving antenna as claimed in claim 5, characterized in that: When entering the intelligent prediction tracking mode, it also includes: receiving an error signal from a tracking receiver; Digitally processing the error signal to obtain a digital signal; Amplifying the digital signal to obtain an amplified signal; The amplified signal is fed back to the actuator to achieve correction and tracking of the target.

7. A system for predicting the angle of a FY geostationary satellite receiving antenna, characterized in that: include: A module is established for establishing a dynamic database for antenna tracking angles; A generation module, used for generating a queue by one-to-one correspondence between all antenna angles and time in each space relative revolution period of the satellite according to the dynamic database; A first calculation module is used to calculate the difference of the antenna tracking angle change of the satellite at each moment in adjacent revolution periods according to the queue; as well as The second calculation module is used to calculate the antenna angle in the next cycle according to the antenna tracking angle change difference.

8. The system for predicting the angle of a FY-GSO satellite receiving antenna as claimed in claim 7, characterized in that: The dynamic database includes the time stamp of the antenna tracking angle, the azimuth and pitch tracking angle of the antenna. The dynamic database stores the antenna angle data of at least two tracking cycles, and the dynamic database is a first-in-first-out timely updated queue, and can set the number of dates and time intervals of the stored antenna tracking angles according to needs and storage medium capacity.

9. A computing device for predicting the angle of a FY geostationary orbit satellite receiving antenna, characterized in that: include: one or more processors; A storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the method for predicting the angle of a Fengyun synchronous orbit satellite receiving antenna as described in any one of claims 1-6.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a program, which, when executed by a processor, implements the method for predicting the angle of a FY-GEO satellite receiving antenna as described in any one of claims 1 to 6.

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