Capture tracking control method, device and equipment in satellite-borne laser communication payload

Abstract

The present invention provides a capture tracking control method, device and equipment in a satellite-borne laser communication payload, comprising: respectively acquiring orbit information of a host star and orbit information of a target star, performing initial open-loop pointing, and capturing a beacon optical signal; based on the beacon optical signal, controlling a system of the host star and a system of the target star to enter a scanning and staring phase, and realizing double-end capture of the host star and the target star through open-loop scanning; based on double-end capture, detecting the beacon optical signal through a detector, maintaining the beacon optical signal within a preset range of the detector, and establishing coarse tracking; in the coarse tracking process, when the system optical axis is within a fine tracking field of view, the system enters a fine tracking phase, and realizes link establishment and communication between the host star and the target star. The capture tracking method of the present invention is adopted to realize double-end capture through open-loop pointing and open-loop scanning, and then link establishment is performed through coarse tracking and fine tracking, thereby effectively improving the capture tracking control efficiency in the satellite-borne laser communication payload.

Description

Technical Field

[0001] The present invention relates to the field of satellite communication technology, and in particular to a capture tracking control method, device and equipment in a satellite-borne laser communication payload. Background Art

[0002] The satellite-borne laser communication payload is carried on a medium-orbit satellite. Its main tasks include: first receiving the data sent by the router, then processing the data, amplifying the light and transmitting it to the optical head, and finally sending it to the target satellite; or receiving the laser data signal sent by the target satellite, converting the optical signal into an electrical signal, processing the data, restoring the original data and then sending it to the router.

[0003] Due to the diversity of system parameters, the complexity and uncertainty of satellite attitude control, the vibration of satellite platforms, the relative motion between satellites, etc., there are some problems that cannot be ignored in the communication process. For example, in the case of long-distance inter-satellite communication links (30,000km-36,000km), there are certain difficulties in aiming the receiver and transmitter. This not only strictly requires that the laser communication link system have very high pointing accuracy between the transmitting and receiving payloads, but also has extremely high technical requirements for the equipment's optical signal capture capability and high-precision tracking and aiming assistance mechanism, involving multi-disciplinary technologies such as optics, mechanics, and electronics.

[0004] Therefore, how to efficiently realize capture and tracking control in satellite-borne laser communication payloads has become a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0005] The present invention provides a capture tracking control method, device and equipment in a satellite-borne laser communication payload, so as to solve the defect of low capture tracking control efficiency in the satellite-borne laser communication payload in the prior art.

[0006] In a first aspect, the present invention provides a capture tracking control method in a satellite-borne laser communication payload, comprising:

[0007] Get the orbit information of the local star and the orbit information of the target star respectively;

[0008] Based on the orbit information of the own satellite and the orbit information of the target satellite, initial open-loop pointing is performed to capture the beacon optical signal;

[0009] Based on the beacon optical signal, the system of the host star and the system of the target star are controlled to enter a scanning and staring phase, and double-end capture of the host star and the target star is achieved through open-loop scanning;

[0010] Based on the double-ended capture, the beacon optical signal is detected by a detector, the beacon optical signal is maintained within a preset range of the detector, and a coarse tracking is established;

[0011] In the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking stage to achieve link establishment and communication between the local satellite and the target satellite.

[0012] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, the initial open-loop pointing is performed based on the orbit information of the own satellite and the orbit information of the target satellite, comprising:

[0013] Based on the acquired ephemeris, local time and attitude, confirm the initial pointing direction of the target star;

[0014] Determine the initial orientation of the optical system's boresight;

[0015] Based on the initial pointing of the target star and the initial pointing of the optical system visual axis, converting into the azimuth and elevation angles that need to be turned;

[0016] The driving motor is used to adjust the visual axis to point to the target star position pointed by the azimuth angle and the pitch angle, and initial open-loop pointing is performed.

[0017] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, the control of the system of the host star and the system of the target star to enter the scanning and staring phase comprises:

[0018] Control the systems of the own star and the target star to scan and track the beacon light signal;

[0019] Based on the beacon light signal, ephemeris and orbital parameters, controlling the own star and the target star to perform initial alignment;

[0020] After the initial alignment, the system controlling the local star controls the visual axis pointing to scan according to the real-time path, and the system controlling the target star stares.

[0021] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, the double-end capture of the local satellite and the target satellite is achieved by open-loop scanning, comprising:

[0022] The host star transmits a beacon light signal to search and scan the receiving site where the target star is located;

[0023] Based on the search scan, a double-end capture of the local star and the target star is established.

[0024] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, the dual-end capture of the local satellite and the target satellite is established based on the search scan, comprising:

[0025] When the target star is covered by the beacon light signal emitted by the own star, the error between the visual axis of the target star and the incident light beam is determined, and the target star is driven to adjust the light beam direction, and a response signal is sent to the own star at the same time, so as to realize single-end initial capture;

[0026] When the own star detects the response light of the target star, the visual axis direction of the own star is corrected based on the spot position of the response light;

[0027] After the correction, when the target star detects the incident light beam of the host star again, double-end capture of the host star and the target star is achieved.

[0028] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, before entering the fine tracking stage, the method further includes:

[0029] Closed-loop control is performed based on the miss distance between the target star and the center of the detector, and the angles of the pitch motor and azimuth motor are continuously adjusted to track the beacon light signal;

[0030] During the process of continuously tracking the beacon light signal, the fine tracking stage is entered until the system optical axis is within the fine tracking field of view.

[0031] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, after entering the fine tracking stage, the method further includes:

[0032] The light signal is captured by the detector of the fine tracking unit to determine the position of the light spot;

[0033] Based on the light spot position, determining an optimal light spot position of the sensor unit;

[0034] Based on the optimal spot position and the error signal fed back by the detector of the fine tracking unit, the fast reflection mirror in the fine tracking unit is controlled to adjust the communication accuracy.

[0035] According to a capture tracking control method in a satellite-borne laser communication payload provided by the present invention, after the system enters the fine tracking stage, the method further includes:

[0036] When the light spot escapes from the fine tracking field of view, the capture process of scanning gaze stage, double-end capture, coarse tracking and fine tracking is re-executed.

[0037] In a second aspect, the present invention further provides a capture tracking control device in a satellite-borne laser communication payload, comprising:

[0038] An acquisition module is used to obtain the orbit information of the local star and the orbit information of the target star respectively;

[0039] An open-loop pointing module, used to perform initial open-loop pointing based on the orbit information of the own satellite and the orbit information of the target satellite, and to capture the beacon optical signal;

[0040] An open-loop scanning module, used to control the system of the host star and the system of the target star to enter a scanning and staring phase based on the beacon optical signal, and to achieve dual-end capture of the host star and the target star through open-loop scanning;

[0041] A coarse tracking module, configured to detect the beacon optical signal through a detector based on the double-ended capture, maintain the beacon optical signal within a preset range of the detector, and establish coarse tracking;

[0042] The fine tracking module is used to, during the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking stage to achieve link establishment and communication between the local satellite and the target satellite.

[0043] In a third aspect, the present invention further provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the capture and tracking control method in a satellite-borne laser communication payload as described in any one of the above-mentioned methods is implemented.

[0044] In a fourth aspect, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a capture and tracking control method in a satellite-borne laser communication payload as described in any one of the above.

[0045] In a fifth aspect, the present invention further provides a computer program product, comprising a computer program, which, when executed by a processor, implements a capture and tracking control method in a satellite-borne laser communication payload as described in any one of the above.

[0046] The capture tracking control method, device and equipment in a satellite-borne laser communication payload provided by the present invention include: respectively acquiring orbit information of a local satellite and orbit information of a target satellite; performing initial open-loop pointing based on the orbit information of the local satellite and the orbit information of the target satellite, and capturing a beacon optical signal; based on the beacon optical signal, controlling the system of the local satellite and the system of the target satellite to enter a scanning and staring phase, and realizing double-end capture of the local satellite and the target satellite through open-loop scanning; based on double-end capture, detecting the beacon optical signal through a detector, maintaining the beacon optical signal within a preset range of the detector, and establishing coarse tracking; in the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking phase, and realizes link establishment and communication between the local satellite and the target satellite, and adopts the capture tracking method of the present invention, realizes double-end capture through open-loop pointing and open-loop scanning, and then establishes a link through coarse tracking and fine tracking, thereby effectively improving the capture tracking control efficiency in the satellite-borne laser communication payload. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0048] Figure 1 is a flow chart of a capture and tracking control method in a satellite-borne laser communication payload provided in this embodiment;

[0049] Figure 2 It is a capture and tracking circuit in the satellite-borne laser communication payload provided by this embodiment;

[0050] Figure 3 is a schematic diagram of the open-loop scanning capture principle provided by this embodiment;

[0051] Figure 4 is a schematic diagram of the precise tracking process provided by this embodiment;

[0052] Figure 5 is a schematic structural diagram of a capture and tracking control device in a satellite-borne laser communication payload provided in this embodiment;

[0053] Figure 6 It is a schematic diagram of the structure of the electronic device provided in this embodiment. DETAILED DESCRIPTION

[0054] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0055] Figure 1 is a flow chart of a capture and tracking control method in a satellite-borne laser communication payload provided in this embodiment, Figure 2 This is the capture and tracking circuit in the satellite-borne laser communication payload provided by this embodiment.

[0056] like Figure 1 As shown, the embodiment of the present invention provides a capture tracking control method in a satellite-borne laser communication payload, and the execution subject may be Figure 2 The circuit shown, Figure 2As shown, the circuit includes a signal acquisition unit, a signal processing unit, a fine tracking unit, a sensor unit and a motor drive unit, and is mainly composed of a power supply system, FPGA, MCU, AD, DA, operational amplifier, high-voltage operational amplifier, instrumentation operational amplifier, SRAM, MRAM, PWM drive circuit, current measurement sensor, magnetic isolator and corresponding interface circuit. The method mainly includes the following steps:

[0057] 101. Obtain the orbital information of the own star and the orbital information of the target star respectively.

[0058] In a specific implementation process, two satellites need to communicate by emitting lasers to each other, locking and capturing the lasers emitted by each other to establish a link, and then communicate. First, make sure that both the receiving satellite and the sending satellite are powered on, the sending satellite is the local satellite, and the receiving satellite is the target satellite. The device obtains the orbit information of the local satellite through GPS broadcast, and obtains the orbit information of the target satellite through remote control commands.

[0059] 102. Based on the orbit information of the own satellite and the orbit information of the target satellite, perform initial open-loop pointing and capture the beacon optical signal.

[0060] The signal processing unit in the center of the circuit is the core execution body. The signal processing unit confirms the initial pointing of the target star based on the acquired ephemeris, local time, attitude and other information; and then determines the initial pointing of the optical system's visual axis through calculation. Based on the initial pointing of the target star and the initial pointing of the optical system's visual axis, according to the calculation results fed back by the signal processing unit, it is converted into the azimuth and elevation angles that need to be turned, and the drive motor is used to adjust the visual axis to the target star position pointed by the azimuth and elevation angles, and perform initial open-loop pointing. Then position the telescope in the direction of the other terminal in order to capture the beacon light signal.

[0061] 103. Based on the beacon optical signal, the systems of the local star and the target star are controlled to enter the scanning and staring phase, and the dual-end capture of the local star and the target star is achieved through open-loop scanning.

[0062] After the two systems, the system of the host star and the system of the target star, complete the initial rotation of the line of sight, they enter the scanning and staring stage. The systems controlling the host star and the target star scan and track the beacon light signal; based on the beacon light signal, ephemeris and orbital parameters, the host star and the target star are controlled to perform initial alignment; after the initial alignment, the system controlling the host star controls the line of sight to scan according to the real-time path, and the system of the target star stares.

[0063] Figure 3It is a schematic diagram of the open-loop scanning capture principle provided in this embodiment. A and B represent the local star and the target star, respectively. A transmits a wide-beam beacon light signal to search and scan the receiving field of view FOV where B is located. When B is covered by the laser beam emitted by A, the detector of B detects the beam emitted by A, and solves the error between the visual axis of terminal B and the incident beam according to the position of the light spot, drives B to adjust the beam direction, and sends a response signal to A at the same time, to achieve single-end initial capture. When A detects the response light of B, the visual axis direction of terminal A is corrected according to the position of the light spot. When the detector of B detects the incident beam again, the initial capture of both ends, i.e., the local star and the target star, is achieved. At this time, there are targets in the detector fields of view of terminals A and B, and the open-loop scanning and capture process of link establishment is completed.

[0064] 104. Based on double-end capture, the beacon light signal is detected by the detector, the beacon light signal is maintained within the preset range of the detector, and coarse tracking is established.

[0065] After the initial capture is achieved at both ends, the tracking detector detects the light spot signal and establishes coarse tracking. Through continuous adjustment, the light spot is always maintained near the center of the detector. The detector can achieve rapid switching of frame rate and field of view through windowing technology. During the capture phase, the tracking system is in an open-loop state.

[0066] 105. During the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking stage to achieve link establishment and communication between the local satellite and the target satellite.

[0067] After receiving the beacon light, the tracking process begins. The signal processing unit will perform closed-loop control based on the miss distance between the target star and the center of the detector, and continuously adjust the angles of the pitch motor and azimuth motor to track the beacon light signal. During the continuous tracking of the beacon light signal, the system enters the fine tracking stage until the optical axis of the system is in the fine tracking field of view.

[0068] Figure 4 is a schematic diagram of the precise tracking process provided by this embodiment, such as Figure 4 As shown in the figure, after achieving dual-end capture, the light spot falls into the detector field of view, and then the light spot position is adjusted, and the copper drum performs large field of view and low frequency light spot adjustment, so that the light spot gradually falls into the precise tracking field of view. Then the closed-loop position is moved to the central detector, high-precision tracking is established, and the closed-loop position is moved to the tracking window, and the windowing mode is used to achieve high-precision closed-loop tracking at a high frame rate.

[0069] The signal acquisition unit captures the light signal through the detector of the fine tracking unit and calculates to determine the spot position; based on the spot position, the optimal spot position of the sensor unit is calculated and determined. At this stage, the signal processing unit controls the fast mirror in the fine tracking unit based on the optimal spot position and the error signal fed back by the detector of the fine tracking unit, and adjusts the communication accuracy so that the error reaches the accuracy required by the communication. Generally, the fine tracking accuracy is a few micro-radians. In this process, the tracking range is ±26° cone angle of the subsatellite point, the pointing / coarse tracking accuracy (including after E / F switching) is no more than 50urad, and the fine tracking accuracy is better than 3urad (3σ).

[0070] Furthermore, based on the above embodiment, this embodiment also includes: when the light spot escapes from the fine tracking field of view, the capture process of the scanning gaze stage, dual-end capture, coarse tracking and fine tracking is re-executed.

[0071] Specifically, when the light spot enters the field of view of the fine tracking detector, fine tracking is established, but the light spot may escape the fine tracking field of view, and the terminal needs to re-establish fine tracking through coarse tracking or even open-loop scanning. When the fine tracking is stable, the link between terminal A and B is successfully established and communicates. At this point, the intersatellite communication link is established. Since the satellite is constantly moving at high speed, the capture and tracking module continues to monitor the intersatellite laser communication. The fine tracking unit and the signal processing unit continuously repeat the above workflow to track the communication link signal to achieve the function of monitoring the communication link.

[0072] The capture tracking control method in the satellite-borne laser communication payload provided by the present invention has a broken link reconstruction function. The capture tracking keeps tracking the communication link and continuously reports the communication status. When the link is broken, it can autonomously start the link establishment workflow. The capture time is short and the capture probability is high. The capture is ≤15s@uncertain area 1mrad, and the capture probability is ≥95%. The detection terminal uses a detector with a large field of view (FOV) for detection, which increases the capture range and ultimately reduces the time for precise alignment of the two satellite terminals, establishes a stable link and realizes communication. It has the advantage of being resistant to radiation, and all circuit components are selected using aerospace-grade components.

[0073] Based on the same general inventive concept, the present invention also protects a capture tracking control device in a satellite-borne laser communication payload. The capture tracking control device in a satellite-borne laser communication payload provided by the present invention is described below. The capture tracking control device in the satellite-borne laser communication payload described below and the capture tracking control method in the satellite-borne laser communication payload described above can be referenced to each other.

[0074] Figure 5 It is a schematic diagram of the structure of the capture and tracking control device in the satellite-borne laser communication payload provided in this embodiment.

[0075] like Figure 5 As shown, this embodiment provides a capture tracking control device in a satellite-borne laser communication payload, comprising:

[0076] An acquisition module 501 is used to respectively acquire the orbit information of the own star and the orbit information of the target star;

[0077] An open-loop pointing module 502 is used to perform initial open-loop pointing based on the orbit information of the own satellite and the orbit information of the target satellite to capture the beacon optical signal;

[0078] An open-loop scanning module 503 is used to control the system of the host star and the system of the target star to enter a scanning and staring phase based on the beacon optical signal, and realize double-end capture of the host star and the target star through open-loop scanning;

[0079] A coarse tracking module 504 is used to detect the beacon optical signal through a detector based on the double-end capture, maintain the beacon optical signal within a preset range of the detector, and establish coarse tracking;

[0080] The fine tracking module 505 is used to, during the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking phase to achieve link establishment and communication between the local satellite and the target satellite.

[0081] Figure 6 It is a schematic diagram of the structure of the electronic device provided in this embodiment.

[0082] like Figure 6 As shown, the electronic device may include: a processor (processor) 610, a communication interface (Communications Interface) 620, a memory (memory) 630 and a communication bus 640, wherein the processor 610, the communication interface 620, and the memory 630 communicate with each other through the communication bus 640. The processor 610 can call the logic instructions in the memory 630 to execute the capture and tracking control method in the satellite-borne laser communication payload, which includes: respectively acquiring the orbit information of the own satellite and the orbit information of the target satellite; based on the orbit information of the own satellite and the orbit information of the target satellite, performing initial open-loop pointing and capturing the beacon optical signal; based on the beacon optical signal, controlling the system of the own satellite and the system of the target satellite to enter the scanning and staring stage, and realizing the double-end capture of the own satellite and the target satellite through open-loop scanning; based on the double-end capture, detecting the beacon optical signal through a detector, maintaining the beacon optical signal within the preset range of the detector, and establishing coarse tracking; during the coarse tracking process, when the system optical axis is in the fine tracking field of view, the system enters the fine tracking stage, and realizes the link establishment and communication between the own satellite and the target satellite.

[0083] In addition, the logic instructions in the above-mentioned memory 630 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc. Various media that can store program codes.

[0084] On the other hand, the present invention also provides a computer program product, which includes a computer program, and the computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the capture and tracking control method in the satellite-borne laser communication payload provided by the above methods, and the method includes: respectively obtaining the orbit information of the local satellite and the orbit information of the target satellite; based on the orbit information of the local satellite and the orbit information of the target satellite, performing initial open-loop pointing and capturing the beacon optical signal; based on the beacon optical signal, controlling the system of the local satellite and the system of the target star to enter the scanning and staring stage, and realizing the double-end capture of the local satellite and the target star through open-loop scanning; based on the double-end capture, detecting the beacon optical signal through a detector, maintaining the beacon optical signal within the preset range of the detector, and establishing coarse tracking; in the coarse tracking process, when the system optical axis is in the fine tracking field of view, the system enters the fine tracking stage, and realizes the link establishment and communication between the local satellite and the target star.

[0085] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the capture and tracking control method in the satellite-borne laser communication payload provided by the above-mentioned methods, the method comprising: respectively acquiring the orbit information of the local satellite and the orbit information of the target satellite; based on the orbit information of the local satellite and the orbit information of the target satellite, performing initial open-loop pointing and capturing a beacon optical signal; based on the beacon optical signal, controlling the system of the local satellite and the system of the target satellite to enter a scanning and staring phase, and realizing double-end capture of the local satellite and the target satellite through open-loop scanning; based on the double-end capture, detecting the beacon optical signal through a detector, maintaining the beacon optical signal within a preset range of the detector, and establishing coarse tracking; during the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters a fine tracking phase, and realizes link establishment and communication between the local satellite and the target satellite.

[0086] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0087] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0088] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention 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 make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A capture tracking control method in a satellite-borne laser communication payload, characterized in that: The circuit of the execution subject includes a signal acquisition unit, a signal processing unit, a fine tracking unit, a sensor unit and a motor drive unit, and the method includes: Acquire the orbit information of the own satellite and the orbit information of the target satellite respectively, including: acquiring the orbit information of the own satellite through GPS broadcast, and acquiring the orbit information of the target satellite through remote control commands; Based on the orbit information of the own satellite and the orbit information of the target satellite, initial open-loop pointing is performed to capture the beacon optical signal; Based on the beacon optical signal, the system of the host star and the system of the target star are controlled to enter a scanning and staring phase, and double-end capture of the host star and the target star is achieved through open-loop scanning; Based on the double-ended capture, the beacon optical signal is detected by a detector, the beacon optical signal is maintained within a preset range of the detector, and a coarse tracking is established; Based on the miss distance between the target star and the center of the detector, closed-loop control is performed to continuously adjust the angles of the pitch motor and the azimuth motor to track the beacon light signal; in the process of continuously tracking the beacon light signal, the fine tracking stage is entered until the optical axis of the system is within the fine tracking field of view; After achieving dual-end capture, the light spot falls into the detector field of view, and the light spot position is adjusted. By adjusting the large field of view and low frequency light spot, the light spot gradually falls into the precise tracking field of view, and then the closed-loop position is moved to the central detector to establish high-precision tracking. The closed-loop position is moved to the tracking window, and the windowing mode is used to achieve high-precision closed-loop tracking at a high frame rate. The detector of the fine tracking unit captures the light signal to determine the light spot position; based on the light spot position, the optimal light spot position of the sensor unit is determined; based on the optimal light spot position and the error signal fed back by the detector of the fine tracking unit, the fast reflection mirror in the fine tracking unit is controlled to adjust the communication accuracy; In the coarse tracking process, when the system optical axis is within the fine tracking field of view, the system enters the fine tracking stage to achieve link establishment and communication between the local satellite and the target satellite.

2. The capture tracking control method in a satellite-borne laser communication payload according to claim 1, characterized in that: The performing initial open-loop pointing based on the orbit information of the own satellite and the orbit information of the target satellite includes: Based on the acquired ephemeris, local time and attitude, confirm the initial pointing direction of the target star; Determine the initial pointing direction of the optical system's boresight; Based on the initial pointing of the target star and the initial pointing of the optical system visual axis, converting into the azimuth and elevation angles that need to be turned; The driving motor is used to adjust the visual axis to point to the target star position pointed by the azimuth angle and the pitch angle, and perform initial open-loop pointing.

3. The capture tracking control method in a satellite-borne laser communication payload according to claim 1, characterized in that: The system for controlling the local star and the system for controlling the target star enter the scanning and staring phase, including: Control the systems of the own star and the target star to scan and track the beacon light signal; Based on the beacon light signal, ephemeris and orbital parameters, controlling the own star and the target star to perform initial alignment; After the initial alignment, the system controlling the local star controls the visual axis pointing to scan according to the real-time path, and the system controlling the target star stares.

4. The capture tracking control method in a satellite-borne laser communication payload according to claim 3, characterized in that: The method of realizing double-end capture of the host star and the target star by open-loop scanning includes: The host star transmits a beacon light signal to search and scan the receiving site where the target star is located; Based on the search scan, a double-end capture of the local star and the target star is established.

5. The capture tracking control method in a satellite-borne laser communication payload according to claim 4, characterized in that: The step of establishing a dual-end capture of the host star and the target star based on the search scan includes: When the target star is covered by the beacon light signal emitted by the own star, the error between the visual axis of the target star and the incident light beam is determined, and the target star is driven to adjust the light beam direction, and a response signal is sent to the own star at the same time, so as to realize single-end initial capture; When the own star detects the response light of the target star, the visual axis direction of the own star is corrected based on the spot position of the response light; After the correction, when the target star detects the incident light beam of the host star again, double-end capture of the host star and the target star is achieved.

6. The capture tracking control method in a satellite-borne laser communication payload according to any one of claims 1 to 5, characterized in that: After the system enters the fine tracking stage, it also includes: When the light spot escapes from the fine tracking field of view, the capture process of scanning gaze stage, double-end capture, coarse tracking and fine tracking is re-executed.

7. A capture tracking control device in a satellite-borne laser communication payload, characterized in that: The circuit of the execution subject includes a signal acquisition unit, a signal processing unit, a fine tracking unit, a sensor unit and a motor drive unit, and the device includes: The acquisition module is used to respectively acquire the orbit information of the own satellite and the orbit information of the target satellite, including: acquiring the orbit information of the own satellite through GPS broadcasting, and acquiring the orbit information of the target satellite through remote control commands; An open-loop pointing module, used to perform initial open-loop pointing based on the orbit information of the own satellite and the orbit information of the target satellite, and to capture the beacon optical signal; An open-loop scanning module, used to control the system of the host star and the system of the target star to enter a scanning and staring phase based on the beacon optical signal, and to achieve dual-end capture of the host star and the target star through open-loop scanning; A coarse tracking module, configured to detect the beacon optical signal through a detector based on the double-ended capture, maintain the beacon optical signal within a preset range of the detector, and establish coarse tracking; The fine tracking module is used to perform closed-loop control based on the miss distance between the target star and the center of the detector, and continuously adjust the angle of the pitch motor and the azimuth motor to track the beacon light signal; in the process of continuously tracking the beacon light signal, until the system optical axis is in the fine tracking field of view, the fine tracking stage is entered; after the double-end capture is achieved, the light spot falls into the detector field of view, the light spot position is adjusted, and the light spot is gradually adjusted to the fine tracking field of view by performing a large field of view and low frequency light spot adjustment, and then the closed-loop position is moved to the central detector to establish high-precision tracking, and the closed-loop position is moved to the tracking window, and a windowing mode is adopted to achieve high-precision closed-loop tracking at a high frame rate; the detector of the fine tracking unit captures the light signal and determines the light spot position; based on the light spot position, the optimal light spot position of the sensor unit is determined; based on the optimal light spot position and the error signal fed back by the detector of the fine tracking unit, the fast reflection mirror in the fine tracking unit is controlled to adjust the communication accuracy; in the coarse tracking process, when the system optical axis is in the fine tracking field of view, the system enters the fine tracking stage to achieve link establishment and communication between the local star and the target star.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the capture tracking control method in the satellite-borne laser communication payload as described in any one of claims 1 to 6 is implemented.

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