A method and system for searching for geosynchronous orbit satellites

Abstract

The application discloses a method and system for searching geosynchronous orbit satellite, wherein the method comprises the following steps: calculating the theoretical position of antenna pointing based on the nominal position of the launched satellite, wherein the launched satellite is a geosynchronous orbit satellite; setting the step distance and the step number in advance, and scanning and searching according to the equidistance spiral involute expansion, wherein the first sidelobe signal of the launched satellite is identified in one scanning, and the main lobe satellite signal is identified by performing secondary scanning based on the first sidelobe position, so as to locate the launched satellite. The method for searching geosynchronous orbit satellite provided by the application has high searching efficiency, and the main lobe can be quickly found by performing secondary scanning based on the position of the first sidelobe in scanning, without performing large range searching, so that the searching time is saved and the searching efficiency is improved.

Description

Technical Field

[0001] This invention belongs to the field of satellite navigation technology and relates to a method and system for searching for geostationary orbit satellites. Background Technology

[0002] Currently, Fengyun geostationary meteorological satellites are mostly large remote sensing platforms, and are geostationary orbit satellites carrying multiple observation instruments, positioned at an altitude of approximately 36,000 kilometers above the Earth's equator. After launch, geostationary orbit satellites utilize a slight deviation from their nominal position due to orbital drift to conserve propellant. During their operational period, they also periodically drift back and forth around their nadir position at the equator. The primary task of the ground receiving antenna for Fengyun geostationary meteorological satellites is to ensure rapid acquisition and precise, stable tracking of the satellite, providing high-quality radio frequency channels for the uplink and downlink of the receiving system. Ensuring that the ground receiving antenna can quickly and accurately acquire signals from high-orbit geostationary satellites is fundamental to receiving satellite cloud images.

[0003] The existing search method is the "azimuth (elevation) single scan" method. This involves randomly selecting a starting elevation (or azimuth) position, allowing the antenna to perform a straight-line scan of the spatial area at that elevation (or azimuth), observing changes in the received signal level (AGC) value, and then manually changing the elevation (or azimuth) value. This azimuth (or elevation) straight-line scan is repeated until the maximum signal value is found, indicating the location pointing to the satellite. This search method requires a large scanning range, is time-consuming with manual operation (search time is typically measured in hours), and has almost a 50% chance of incorrect search direction. For example, if the satellite is located in the lower half of the Y-axis, but the initial search direction is set to the upper half, and no signal is found, the search must return from the upper half of the Y-axis and start searching the lower half again, ultimately doubling the search time. The azimuth (elevation) single scan search method relies heavily on the experience of the search personnel, and the search time varies considerably depending on the individual.

[0004] Therefore, overcoming the shortcomings of the existing technology is an urgent problem to be solved in this technical field. Summary of the Invention

[0005] The purpose of this invention is to provide a method and system for searching for geostationary orbit satellites, which solves the technical problems of long search times and low efficiency in the prior art.

[0006] The present invention achieves the above objectives through the following technical solutions:

[0007] In a first aspect, the present invention provides a method for searching for geostationary orbit satellites, the method comprising:

[0008] The theoretical position to which the antenna points is calculated based on the nominal position of the launched satellite, wherein the launched satellite is a geostationary orbit satellite;

[0009] Starting from the theoretical position of the antenna, the step size and number of steps are preset, and the scanning search is carried out according to the equal step size spiral involute.

[0010] During the first scan, the first sidelobe signal of the launched satellite is identified. Then, a second scan is performed based on the position of the first sidelobe to identify the main lobe satellite signal, thereby locating the launched satellite.

[0011] Preferably, the method for calculating the theoretical position of the antenna pointing based on the nominal position of the launched satellite includes:

[0012] The theoretical position is the nominal position of the orbital insertion point of the launched satellite;

[0013] The theoretical position that the antenna points to includes the azimuth angle θ. A and pitch angle θ E The algorithm formulas are as follows:

[0014]

[0015]

[0016] Wherein: the geographical longitude of the ground station is denoted as α1; the satellite longitude is α2; the station latitude is denoted as β; the Earth's radius is R; and the satellite altitude is H.

[0017] Preferably, the method for presetting the step distance and number of steps includes:

[0018] When performing a scan, starting from the theoretical position of the antenna, the first step distance is set to be no greater than half of the antenna beamwidth;

[0019] When performing a second scan, the second step distance is set to no more than one-quarter of the antenna beamwidth, starting from the position of the first sidelobe.

[0020] Preferably, the method of pre-setting the step distance and number of steps, starting from the theoretical position of the antenna, includes:

[0021] The step distance and the number of steps are inversely proportional.

[0022] Preferably, the expected search time t for the scanning search following the equal-step spiral involute unfolding is:

[0023]

[0024] Wherein: the step distance of each antenna scan is q, the antenna running speed is v, the adjustment time for each scan is s, the search count is i, and the total number of search steps is N.

[0025] Preferably, the method for identifying the first sidelobe of the launched satellite during a single scan includes:

[0026] The scanning and search program is initiated, and the antenna performs azimuth, elevation, and pointing scans according to the preset step distance and number of steps.

[0027] Starting from the theoretical position of the antenna, within the equidistant spiral involute scanning space, if the signal level exceeds the first sidelobe threshold, the first sidelobe signal of the transmitting satellite is identified.

[0028] Preferably, the method for locating the launched satellite by performing a secondary scan based on the first sidelobe position to identify the main lobe satellite signal includes:

[0029] Starting from the position of the first side lobe, within the scanning space of the equidistant spiral involute, if the sum of the signal levels exceeds the threshold of the main lobe, the main lobe satellite signal is identified, thereby locating the launched satellite.

[0030] In a second aspect, the present invention provides a system for searching for geostationary orbit satellites, the system comprising:

[0031] The calculation module is used to calculate the theoretical position to which the antenna should point, based on the nominal position of the launched satellite;

[0032] The search module is used to perform a scanning search according to a spiral involute with equal step spacing, based on a preset step spacing and number of steps.

[0033] The identification module is used to identify the positions of the first side lobe and the main lobe based on the preset first side lobe threshold value and the main lobe threshold value.

[0034] Thirdly, the present invention provides a computing device for searching geostationary orbit satellites, comprising:

[0035] One or more processors;

[0036] A storage device for storing one or more programs that, when executed by one or more processors, cause the one or more processors to perform the method of searching for geosynchronous orbit satellites as described in the first aspect.

[0037] Fourthly, the present invention provides a computer-readable storage medium storing a program that, when executed by a processor, implements the method for searching for geosynchronous orbit satellites as described in the first aspect.

[0038] The beneficial effects of this invention are:

[0039] The method for searching geosynchronous orbit satellites provided by this invention has high search efficiency and adjustable search step size. It is a constant velocity spiral extrapolation step operation, with the same extrapolation step size for each point in the search space. During the search process, each quadrant is scanned at least once, so satellite positions will not be missed. Once the antenna received signal level exceeds the threshold value of the first sidelobe or main lobe, it indicates that the antenna has entered the first sidelobe or main lobe signal. After finding the main lobe signal, the antenna switches to automatic tracking mode to lock onto the geosynchronous orbit satellite signal. Attached Figure Description

[0040] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments of the present invention will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without any creative effort.

[0041] Figure 1 This is a flowchart of the method for searching for geostationary orbit satellites in this embodiment 1;

[0042] Figure 2 This is the flowchart of the medium step pitch spiral involute scanning engineering algorithm in this embodiment.

[0043] Figure 3 This is a schematic diagram of a medium-speed spiral scan in Embodiment 1;

[0044] Figure 4 This is a schematic diagram comparing the main lobe and side lobes of the antenna in this embodiment.

[0045] Figure 5 This is a schematic diagram of the computing device structure for searching geosynchronous orbit satellites provided in Embodiment 3. Detailed Implementation

[0046] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0047] Furthermore, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0048] Example 1:

[0049] This embodiment provides a method for searching for geostationary orbit satellites, such as... Figure 1 As shown, the method includes:

[0050] S101: Calculate the theoretical position to which the antenna is pointing based on the nominal position of the launched satellite, wherein the launched satellite is a geostationary orbit satellite.

[0051] In this first embodiment, the theoretical position that the antenna should point to is calculated based on the nominal position of the launched satellite. The theoretical position is the nominal position of the orbital insertion point of the launched satellite.

[0052] The theoretical position that the antenna points to includes the azimuth angle θ. A and pitch angle θ E The algorithm formulas are as follows:

[0053]

[0054]

[0055] Wherein: the geographical longitude of the ground station is denoted as α1; the satellite longitude is α2; the station latitude is denoted as β; R is the Earth's radius; and H is the satellite altitude.

[0056] S102: Starting from the theoretical position of the antenna, the step size and number of steps are preset, and the scanning search is carried out according to the equal step size spiral involute.

[0057] In this first embodiment, when setting the search step size and number of search steps, the step size is related to the first and second scans. During the first scan, starting from the theoretical position of the antenna, the first step size is set to no more than half the antenna beamwidth; during the second scan, starting from the position of the first sidelobe, the second step size is set to no more than one-quarter of the antenna beamwidth. This ensures both the speed of signal search and prevents missing actual satellite signals.

[0058] In this first embodiment, the step distance and the number of steps are inversely proportional. The number of search steps is determined by the beamwidth characteristics of the satellite signal and the search step distance. The larger the search step distance, the fewer the number of search steps can be, and the smaller the search step distance, the more the number of search steps can be.

[0059] If the step size and number of steps are not manually set, and the default values ​​are used, the default step size is 0.001°, the minimum step size achievable by antenna rotation, and the default number of steps is 4096. The antenna then performs a constant-step spiral involute scan with azimuth and elevation step sizes of 0.001°, covering a range of 4096 × 0.001 = 4.096 degrees. The search space is approximately azimuth [-1°, 1°] and elevation [-1°, 1°]. The search time is 4.096 degrees ÷ 0.001 degrees / second = 4096 seconds. Taking Fengyun-2 as an example, with a beamwidth of 0.6 degrees, if the step size for both the first and second scans is set to one-quarter of the beamwidth (0.15 degrees), searching the same space takes 4.096 degrees ÷ 0.15 degrees / second = 27.3 seconds. This demonstrates that the constant-step spiral involute scan method significantly improves search efficiency.

[0060] In this first embodiment, a combined azimuth and elevation spiral involute search method with equal step intervals is adopted. By setting the search step size and number of steps, the goal of quickly and automatically finding the satellite is achieved. The antenna is centered on the calculated reference angle and scans the spatial range with equal step interval spiral involutes. Through two spiral scans, the antenna angle that meets the threshold value for the antenna to automatically track the satellite signal is found, and the antenna can then instantly switch to automatically track and lock onto the satellite signal.

[0061] S103: During the first scan, the first sidelobe signal of the launched satellite is identified, and then a second scan is performed based on the position of the first sidelobe to identify the main lobe satellite signal, thereby locating the launched satellite.

[0062] The main lobe of an antenna is the direction in which the antenna radiates the most concentrated energy; the other directions are called side lobes. The first side lobe is the outermost side lobe with the highest energy. It is closest to the main lobe and its radiated energy is second only to the main lobe. Theoretical calculations show that the first side lobe of a Fengyun geostationary meteorological satellite receiving antenna is generally about 15 dB lower than the main lobe. 1 dB corresponds to a 0.2V attenuation in the receiver's voltage level when tracking the antenna. Taking Fengyun-2 as an example, the receiver's voltage level is about 7V when tracking the main lobe. The theoretically calculated voltage level of the first side lobe is 7 - 0.2 × 15 = 4V, which is consistent with the actual receiver voltage level when tracking the first side lobe. Therefore, it can be seen that the equal-step spiral involute scanning method greatly improves search efficiency. The threshold value for the first side lobe is 3V, and the threshold value for the main lobe is 5V.

[0063] The relative positions of the main lobe and the first side lobe in space are determined by the antenna structure. These are relatively fixed and objective positions that are not affected by external factors. The side lobes of the antenna are outside the main lobe. During the search, the side lobes of the antenna must be found first. Therefore, if the first side lobe is found, the relative position of the main lobe must be near the side lobe. During the scan, the main lobe can be found quickly by performing a second scan based on the position of the first side lobe, without the need for a large-scale search. This saves search time and improves search efficiency.

[0064] In this first embodiment, the expected search time t for the scanning search performed by unfolding the spiral involute with equal step intervals is:

[0065]

[0066] Wherein: the step distance of each antenna scan is q, the antenna running speed is v, the adjustment time for each scan is s, the search count is i, and the total number of search steps is N.

[0067] In this first embodiment, the flowchart of the equal-step spiral involute scanning engineering algorithm is as follows: Figure 2 As shown, starting from the initial position, it is determined whether the antenna received signal level (AGC) is greater than the first sidelobe threshold. If yes, a second scan is performed; if no, a first scan is performed until it is determined that the antenna received signal level (AGC) is greater than the first sidelobe threshold. Then, a second scan is performed to determine whether the antenna received signal level (AGC) is greater than the main lobe threshold. If yes, the scan ends, indicating that the satellite has been found, and the automatic tracking program is entered; if no, a second scan is performed until it is determined that the antenna received signal level (AGC) is greater than the main lobe threshold.

[0068] In this first embodiment, a constant velocity spiral refers to the trajectory of a moving point that moves away from a fixed point at a constant speed while rotating around the fixed point at a fixed angular velocity.

[0069] The polar equation of a constant velocity spiral is:

[0070] R = v * t θ = w * t

[0071] Where R represents the polar radius, θ represents the polar angle, v represents the radial velocity, and w represents the angular velocity.

[0072] The formula for calculating the transformation of a constant-velocity spiral from polar coordinates to Cartesian plane coordinates is as follows:

[0073] θ=tan -1 (Y / X)

[0074] Among them: X=R*sinθ, Y=R*cosθ.

[0075] The equation for a constant velocity spiral can also be expressed using the pitch parameter r, radial velocity v, and angular velocity w, as shown in the formula:

[0076] The antenna search speed V is the arithmetic square root of the search linear velocity and angular velocity. The azimuth angle is denoted as X, the elevation angle is denoted as Y, and the actual search space is azimuth [-X,+X] and elevation [-Y,+Y].

[0077] The characteristics of a constant-velocity spiral determine its use as the algorithm basis for antenna searching of satellite spatial positions. Since a fixed point can serve as the starting point of the search, and the moving point represents the spatial position being searched, the equal pitch of each spiral rotation, when set with an appropriate search step size, ensures the completeness of the search space and prevents the actual position of the satellite from being missed.

[0078] A Cartesian coordinate system is established with the line connecting the antenna and the star as the normal. Without loss of generality, assuming the satellite angle is in the second quadrant, the schematic diagram of two constant-velocity spiral scan searches is shown below. Figure 3 As shown. A single scan is performed in all four quadrants, while a second scan is performed only in the second quadrant.

[0079] In this first embodiment, the method for identifying the first sidelobe of the launched satellite during a single scan includes:

[0080] The scanning and search program is initiated, and the antenna performs azimuth, elevation, and pointing scans according to the preset step distance and number of steps.

[0081] Starting from the theoretical position of the antenna, within the equidistant spiral involute scanning space, if the signal level exceeds the first sidelobe threshold, the first sidelobe signal of the transmitting satellite is identified.

[0082] In this first embodiment, the method of identifying the main lobe satellite signal by performing a secondary scan based on the first sidelobe position, thereby locating the launched satellite, includes:

[0083] Starting from the position of the first side lobe, within the scanning space of the equidistant spiral involute, if the sum of the signal levels exceeds the threshold of the main lobe, the main lobe satellite signal is identified, thereby locating the launched satellite.

[0084] like Figure 4As shown, the first sidelobe of the Fengyun geostationary meteorological satellite receiving antenna is generally about 15dB lower than the main lobe. 1dB corresponds to a 0.2V attenuation in the receiver's voltage level when the antenna tracks the main lobe. Taking Fengyun-2 as an example, the receiver's voltage level is about 7V when the antenna tracks the main lobe. The theoretically calculated voltage level of the first sidelobe is 7 - 0.2 × 15 = 4 (V), which is consistent with the actual receiver voltage level when tracking the first sidelobe. Therefore, a threshold of 3V is set for entering the first sidelobe, and a threshold of 5V is set for entering the main lobe, in order to quickly identify the position of geostationary orbit satellites.

[0085] Example 2:

[0086] This second embodiment provides a system for searching for geostationary orbit satellites, including:

[0087] The calculation module is used to calculate the theoretical position to which the antenna should point, based on the nominal position of the launched satellite.

[0088] In this second embodiment, the theoretical position that the antenna should point to is calculated based on the nominal position of the launched satellite. The theoretical position is the nominal position of the orbital insertion point of the launched satellite.

[0089] The theoretical position that the antenna points to includes the azimuth angle θ. A and pitch angle θ E The algorithm formulas are as follows:

[0090]

[0091]

[0092] Wherein: the geographical longitude of the ground station is denoted as α1; the satellite longitude is α2; the station latitude is denoted as β; R is the Earth's radius; and H is the satellite altitude.

[0093] The search module is used to perform a scanning search according to a spiral involute with equal step spacing, based on a preset step spacing and number of steps.

[0094] When setting the search step size and number of search steps, the step size is related to the first and second scans. During the first scan, starting from the theoretical position of the antenna, the first step size is set to no more than half the antenna beamwidth. During the second scan, starting from the position of the first sidelobe, the second step size is set to no more than one-quarter of the antenna beamwidth. This ensures both rapid signal search and avoids missing actual satellite signals.

[0095] The step distance and the number of steps are inversely proportional. The number of search steps is determined by the beamwidth characteristics of the satellite signal and the search step distance. The larger the search step distance, the fewer the search steps can be, and the smaller the search step distance, the more the search steps can be.

[0096] If the step size and number of steps are not manually set, and the default values ​​are used, the default step size is 0.001°, the minimum step size achievable by antenna rotation, and the default number of steps is 4096. The antenna then performs a constant-step spiral involute scan with azimuth and elevation step sizes of 0.001°, covering a range of 4096 × 0.001 = 4.096 degrees. The search space is approximately azimuth [-1°, 1°] and elevation [-1°, 1°]. The search time is 4.096 degrees ÷ 0.001 degrees / second = 4096 seconds. Taking Fengyun-2 as an example, with a beamwidth of 0.6 degrees, if the step size for both the first and second scans is set to one-quarter of the beamwidth (0.15 degrees), searching the same space takes 4.096 degrees ÷ 0.15 degrees / second = 27.3 seconds. This demonstrates that the constant-step spiral involute scan method significantly improves search efficiency.

[0097] In this first embodiment, a combined azimuth and elevation search method with equal-step intervals is adopted. By setting the search step size and number of steps, the goal of quickly and automatically finding the satellite is achieved. The antenna is centered on the calculated reference angle and scans the spatial range with equal-step interval spiral involutes. Through two scans, the antenna angle that meets the threshold value for automatic tracking of satellite signals is found, and the antenna can instantly switch to automatic tracking and lock onto the satellite signal position.

[0098] The identification module is used to identify the positions of the first side lobe and the main lobe based on the preset first side lobe threshold value and the main lobe threshold value.

[0099] The main lobe of an antenna is the direction in which the antenna radiates the most concentrated energy; the other directions are called side lobes. The first side lobe is the outermost side lobe with the highest energy. It is closest to the main lobe and its radiated energy is second only to the main lobe. Theoretical calculations show that the first side lobe of a Fengyun geostationary meteorological satellite receiving antenna is generally about 15 dB lower than the main lobe. 1 dB corresponds to a 0.2V attenuation in the receiver's voltage level when tracking the antenna. Taking Fengyun-2 as an example, the receiver's voltage level is about 7V when tracking the main lobe. The theoretically calculated voltage level of the first side lobe is 7 - 0.2 × 15 = 4 (V), which is consistent with the actual receiver voltage level when tracking the first side lobe. Therefore, it can be seen that the equal-step spiral involute scanning method greatly improves search efficiency. The first side lobe threshold is 3V, and the main lobe threshold is 5V, in order to quickly identify the position of geostationary orbit satellites.

[0100] The relative positions of the main lobe and the first side lobe in space are determined by the antenna structure. These are relatively fixed and objective positions that are not affected by external factors. The side lobes of the antenna are outside the main lobe. During the search, the side lobes of the antenna must be found first. Therefore, if the first side lobe is found, the relative position of the main lobe must be near the side lobe. During the scan, the main lobe can be found quickly by performing a second scan based on the position of the first side lobe, without the need for a large-scale search. This saves search time and improves search efficiency.

[0101] Example 3:

[0102] This third embodiment provides a computing device for searching geostationary orbit satellites, including:

[0103] One or more processors;

[0104] A storage device for storing one or more programs that, when executed by one or more processors, enable the one or more processors to perform a method for searching for geosynchronous orbit satellites as described in Embodiment 1.

[0105] The components of a computing device for searching geosynchronous orbit satellites may include, but are not limited to: one or more processors or processing units, memory, and buses connecting different system components (including memory and processing units).

[0106] A bus refers to one or more of several bus architectures, including a memory bus or memory controller, a peripheral bus, a graphics acceleration port, a processor, or a local bus using any of the various bus architectures. Examples of 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.

[0107] Computing devices used for searching geostationary orbit satellites typically include a variety of computer-readable media. These media can be any available media that can be accessed by the computing devices used for searching geostationary orbit satellites, including volatile and non-volatile media, and removable and non-removable media.

[0108] 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 searching geostationary orbit satellites 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 (…). Figure 5 Not shown; usually referred to as a "hard drive"). Although Figure 5Not shown, disk drives for reading and writing to removable non-volatile disks (e.g., "floppy disks") and optical disc drives for reading and writing to removable non-volatile optical discs (e.g., CD-ROMs, DVD-ROMs, or other optical media) may be provided. In these cases, each drive may be connected to a bus via one or more data media interfaces. The memory may include at least one program product having a set (e.g., at least one) of program modules configured to perform the functions of the embodiments of the present invention.

[0109] A program / utility having a set (at least one) of program modules can be stored, for example, in memory. Such program modules include, but are not limited to, an operating system, one or more application programs, other program modules, and program data. Each or some combination of these examples may include an implementation of a network environment. The program modules typically perform the functions and / or methods described in the embodiments of this invention.

[0110] The computing device for searching geostationary orbit satellites can also communicate with one or more external devices (e.g., keyboards, pointing devices, displays, etc.), one or more devices that enable users to interact with the computing device, and / or any device that enables the computing device to communicate with one or more other computing devices (e.g., network interface cards, modems, etc.). This communication can be performed via input / output (I / O) interfaces. Furthermore, the computing device for searching geostationary orbit satellites can also communicate with one or more networks (e.g., local area networks (LANs), wide area networks (WANs), and / or public networks, such as the Internet) via a network adapter. As shown in the figure, the network adapter communicates with other modules of the computing device for searching geostationary orbit satellites via 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 searching geostationary orbit satellites, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0111] The processing unit executes various functional applications and data processing by running programs stored in the memory, such as implementing the method for searching for geostationary orbit satellites provided in any embodiment of the present invention. Specifically: the theoretical position to which the antenna points is calculated based on the nominal position of the launched satellite, wherein the launched satellite is a geostationary orbit satellite; starting from the theoretical position of the antenna, a pre-set step size and number of steps are performed, and a scanning search is conducted according to an equal-step spiral involute; during the first scan, the first sidelobe signal of the launched satellite is identified, and then a second scan is performed based on the position of the first sidelobe to identify the main lobe satellite signal, thereby locating the launched satellite.

[0112] Example 4:

[0113] This embodiment four provides a computer-readable storage medium storing a program that, when executed by a processor, implements the method for searching for geostationary orbit satellites as described in embodiment one.

[0114] This invention also provides a computer-readable storage medium storing a program that, when executed by a processor, implements a method for searching for geostationary orbit satellites as described in any embodiment of this invention. The method includes: calculating a theoretical position of an antenna based on the nominal position of a launched satellite, wherein the launched satellite is a geostationary orbit satellite; using the theoretical position of the antenna as a starting point, pre-setting a step size and number of steps, and performing a scanning search along an equal-step spiral involute; identifying the first sidelobe signal of the launched satellite during a single scan, and then performing a second scan based on the position of the first sidelobe to identify the main lobe satellite signal, thereby locating the launched satellite.

[0115] In summary, the method and system for searching geostationary orbit satellites of the present invention can calculate the theoretical position of the antenna pointing to the target, and perform a scanning search according to an equal-step spiral involute. During the first scan, the first side lobe of the launched satellite is identified, and a second scan is performed based on the position of the first side lobe to identify the main lobe satellite signal, thereby quickly locking onto the launched satellite. The computer storage medium in embodiments of the present invention can be any combination of one or more computer-readable media. A computer-readable medium can be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of computer-readable storage media (a non-exhaustive list) include: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this document, a computer-readable storage medium can be any tangible medium that contains or stores a program that can be used by or in connection with an instruction execution system, apparatus, or device.

[0116] Computer-readable signal media may include data signals propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. Computer-readable signal media may also be any computer-readable medium other than computer-readable storage media, capable of sending, propagating, or transmitting programs for use by or in connection with an instruction execution system, apparatus, or device.

[0117] Program code contained on a computer-readable medium may be transmitted using any suitable medium, including but not limited to wireless, wire, optical fiber, RF, etc., or any suitable combination thereof.

[0118] Computer program code for performing the operations of this invention can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, and C++, as well as conventional procedural programming languages ​​such as "C" or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone 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 remote computers, the remote computer can be connected to the user's computer 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 computer (e.g., via the Internet using an Internet service provider).

[0119] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for searching for geostationary orbit satellites, characterized in that, The methods include: The theoretical position to which the antenna points is calculated based on the nominal position of the launched satellite, wherein the launched satellite is a geostationary orbit satellite; Starting from the theoretical position of the antenna, the step size and number of steps are preset, and the scanning search is carried out according to the equal step size spiral involute. During a single scan, the first sidelobe signal of the launched satellite is identified. Then, a second scan is performed using the position of the first sidelobe as a reference to identify the main lobe satellite signal, thereby locating the launched satellite. The method for presetting the step distance and number of steps includes: When performing a scan, starting from the theoretical position of the antenna, the first step distance is set to be no greater than half of the antenna beamwidth; When performing a second scan, the second step is set to no more than one-quarter of the antenna beamwidth, starting from the position of the first sidelobe. The method of pre-setting the step distance and number of steps based on the theoretical position of the antenna includes: the step distance and the number of steps are inversely proportional; The expected search time t for the scanning search performed by unfolding the spiral involute with equal step intervals is: ， Where: the step distance of each antenna scan is q, the antenna running speed is v, the adjustment time for each scan is s, the search count is i, and the total number of search steps is N; The method for identifying the first sidelobe of the launched satellite during a single scan includes: The scanning and search program is initiated, and the antenna performs azimuth, elevation, and pointing scans according to the preset step distance and number of steps. Starting from the theoretical position of the antenna, within the equidistant spiral involute scanning space, if the signal level exceeds the first sidelobe threshold, the first sidelobe signal of the transmitting satellite is identified. The method for locating the launched satellite by performing a secondary scan based on the position of the first side lobe to identify the main lobe satellite signal includes: Starting from the position of the first side lobe, within the scanning space of the equidistant spiral involute, if the sum of the signal levels exceeds the threshold of the main lobe, the main lobe satellite signal is identified, thereby locating the launched satellite.

2. The method for searching for geostationary orbit satellites as described in claim 1, characterized in that, The method for calculating the theoretical position of the antenna based on the nominal position of the launched satellite includes: The theoretical position is the nominal position of the orbital insertion point of the launched satellite; The theoretical position that the antenna points to includes the azimuth angle of the pointing direction. θ A and pitch angle θ E The algorithm formulas are as follows: ， ， Wherein: the geographical longitude of the ground station is denoted as α1; the satellite longitude is α2; the station latitude is denoted as β; the Earth's radius is R; and the satellite altitude is H.

3. A system for searching for geostationary orbit satellites, based on the method for searching for geostationary orbit satellites as described in any one of claims 1-2, characterized in that, The system includes: The calculation module is used to calculate the theoretical position to which the antenna should point, based on the nominal position of the launched satellite; The search module is used to perform a scanning search according to a spiral involute with equal step spacing, based on a preset step spacing and number of steps. The identification module is used to identify the positions of the first side lobe and the main lobe based on the preset first side lobe threshold value and the main lobe threshold value; The method for presetting the step distance and number of steps includes: When performing a scan, starting from the theoretical position of the antenna, the first step distance is set to be no greater than half of the antenna beamwidth; When performing a second scan, the second step distance is set to no more than one-quarter of the antenna beamwidth, starting from the position of the first sidelobe.

4. A computing device for searching geostationary orbit satellites, characterized in that, include: One or more processors; A storage device for storing one or more programs, which, when executed by one or more processors, cause the one or more processors to implement the method of searching for geosynchronous orbit satellites as described in any one of claims 1-2.

5. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a program that, when executed by a processor, implements the method for searching for geosynchronous orbit satellites as described in any one of claims 1-2.

Images