Inter-satellite laser link capturing device and method based on front finger angle rotating mirror space scanning

Abstract

The invention discloses an inter-satellite laser link capturing device and method based on front finger angle rotating mirror space scanning, and belongs to the field of spacecraft laser capturing. A local-end satellite uses a front finger angle rotating mirror to control emergent laser beams to perform sub-region space scanning; a large-mass one-dimensional overall pointing deflection mechanism and a satellite platform are used for controlling emergent laser beams to execute primary driving so as to move the sub-regions; repeating the first step after moving the sub-region; and circularly carrying out regional scanning on the uncertain region until the far-end satellite receives the irradiation of the emergent laser beam so as to correct the direction of the far-end satellite and emit a retroreflection beam to the local-end satellite, and stopping scanning and correcting the direction of the local-end satellite after the local-end satellite receives the retroreflection beam. According to the inter-satellite laser link capturing device and method based on front finger angle rotating mirror space scanning, the purpose of greatly reducing the time cost of an inter-satellite laser link capturing task and the consumption cost of a propellant by fully utilizing limited beam pointing control resources on a satellite can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft laser capture, and in particular to an intersatellite laser link capture device and method based on space scanning of a forward-pointing angle rotating mirror. Background Art

[0002] In long-distance, high-precision intersatellite laser ranging interferometers, represented by space gravitational wave detectors, the inter-satellite distance reaches hundreds of thousands to millions of kilometers, and the measurement sensitivity of the inter-satellite distance change within a specific frequency band reaches the picometer level.

[0003] Due to the long distance between satellites, the laser beam with a certain divergence angle emitted by the local satellite needs to undergo a significant beam transmission time delay before it can reach the remote satellite. During the beam transmission time delay, if the flight distance of the remote satellite in orbit exceeds the coverage range of the laser beam divergence angle emitted by the local satellite, the remote satellite will not be able to receive the laser beam, and thus the laser link cannot be established. Therefore, it is necessary to offset the direction of the local laser beam with an angle relative to the direction of the line connecting the current positions of the two satellites before transmitting to ensure that the remote satellite can receive the laser beam. At the same time, the laser beam received by the local end is emitted by the remote satellite at the position before the beam transmission delay time, so the direction of the laser beam received by the local end is also offset relative to the direction of the line connecting the current positions of the two satellites. The angle synthesized by these two offsets is called the fore-pointing angle. Due to the non-ideality of orbital mechanics, the size and direction of the fore-pointing angle will change with the position of the satellite in orbit. Therefore, it is necessary to install a precision rotating mirror in the optical path so that the transmitted laser beam can be deflected relative to the received laser beam according to the size and direction of the forward pointing angle, so that the local satellite can align its line of sight with the direction of the received laser beam while the laser beam emitted by the local end can be received by the remote satellite. This precision rotating mirror is called a forward pointing angle rotating mirror.

[0004] For example, the intersatellite distances of the Tianqin and LISA missions in the space gravitational wave detection missions reached 170,000 kilometers and 2.5 million kilometers, respectively, and the corresponding intersatellite laser beam transmission time delays reached about 0.57 seconds and 8.3 seconds, respectively. The component of the Tianqin project's forward pointing angle in the constellation plane varies slightly around 23 μrad; the component perpendicular to the constellation plane varies slightly around 0 μrad. The half-angle of the divergence angle of the intersatellite laser beam in the Tianqin project is expected to be about 4.3 μrad, which is smaller than the component of the forward pointing angle in the constellation plane. If the forward pointing angle is not compensated, the intersatellite laser beam will not be able to illuminate the opposite satellite, so a forward pointing angle rotating mirror must be installed to compensate for the forward pointing angle in the constellation plane. The component of the fore-finger angle of the LISA program in the constellation plane varies slightly around 1.662 μrad, and the component perpendicular to the constellation plane varies greatly at 0 μrad, with a variation range of 6.8 μrad (±3.4 μrad). The half-angle of the divergence angle of the intersatellite laser beam of the LISA program is expected to be about 2 μrad. Therefore, the satellites of the LISA program must be equipped with a fore-finger angle rotating mirror to compensate for the fore-finger angle in the direction perpendicular to the constellation plane.

[0005] The above-mentioned intersatellite laser ranging interferometers have a measurement sensitivity of the order of picometers for intersatellite distance changes within a specific frequency band. In order to ensure the measurement sensitivity of the order of picometers, the measurement optical path of the laser ranging interferometer needs to be integrated and fixed as a whole on each satellite. Both the receiving optical path and the transmitting optical path are in the measurement optical path, and other movable parts other than the front finger angle mirror need to be avoided in the measurement optical path to avoid additional angle-translation coupling errors in the measurement optical path. In the space gravitational wave detection mission, a constellation is usually composed of multiple satellites. Each satellite in the constellation usually carries two sets of measurement optical paths, which form an intersatellite laser ranging interferometer with the measurement optical paths of the other two satellites to achieve intersatellite distance change measurement. When the multiple satellites that make up the constellation are in different orbital positions, the angle between the intersatellite lines will change. This angle is called the breathing angle. In order to compensate for the change of breathing angle and maintain the intersatellite laser link, it is necessary to deflect the intersatellite beam pointing direction of the laser ranging interferometer measurement optical path as a whole in the constellation plane, and the satellite platform drives the measurement optical path to deflect the intersatellite beam pointing direction in a direction perpendicular to the constellation plane, so as to realize the intersatellite beam pointing adjustment and alignment of the measurement optical path of the intersatellite laser ranging interferometer in the two-dimensional direction.

[0006] In the above-mentioned intersatellite laser ranging interferometers, there are three ways to deflect the pointing of the intersatellite laser beam: the pointing deflection of the outgoing laser beam by the front pointing angle mirror, the overall pointing deflection of the laser ranging interferometer in the constellation plane, and the overall pointing deflection of the laser ranging interferometer driven by the satellite platform in the direction perpendicular to the constellation plane.

[0007] After the satellite is launched into the predetermined orbital position, in order to realize the inter-satellite laser interferometry distance measurement, it is first necessary to establish an inter-satellite laser link. Due to factors such as orbit prediction errors, satellite attitude measurement and control errors, neither the local nor the remote satellite can accurately know the position of the other party, and the position of the other party is in an uncertain area according to a certain probability distribution. It is necessary to control the direction of the laser beam emitted by one of the satellites, and perform a two-dimensional scan in the uncertain area where the opposite satellite is located, so that both satellites can capture the laser beam emitted by the opposite satellite, and then establish an inter-satellite laser link. For common capture processes, refer to CN113507579A and CN115333605A. The present invention mainly relates to the two-dimensional scanning process in the capture process.

[0008] In the above-mentioned intersatellite laser ranging interferometers, the existing two-dimensional scanning process adopts the overall pointing deflection of the laser ranging interferometer in the constellation plane, and the satellite platform drives the overall pointing deflection of the laser ranging interferometer in the direction perpendicular to the constellation plane, so as to realize the two-dimensional scanning of the uncertain area where the opposite satellite is located; and the front pointing angle rotation mirror is only used to compensate for the front pointing angle caused by the time delay of the long-distance transmission of the laser beam between satellites, and does not participate in the two-dimensional scanning process of the intersatellite laser beam.

[0009] During the overall pointing deflection process of the laser ranging interferometer in the constellation plane, the laser ranging interferometer measurement optical path and its fixed support mechanical structure have a large mass of tens of kilograms, which generates a large reaction torque on the satellite platform during the deflection process; the satellite platform needs to use micro-thrusters to eject propellant to generate thrust to balance the reaction torque it receives, so as to maintain the satellite platform's own attitude stability. In order to achieve high pointing control accuracy at the nano-radian level, the overall pointing deflection process and the satellite platform's use of micro-thrusters to eject propellant to generate thrust to maintain its own attitude stability need to be repeated many times, resulting in a lot of time and propellant consumption costs.

[0010] The satellite platform drives the laser ranging interferometer to point and deflect perpendicular to the plane of the constellation, which is completely achieved by the micro-thrusters of the satellite platform ejecting propellants to generate thrust. Due to the large mass and moment of inertia of the satellite platform, repeated adjustments are required to achieve high pointing and deflection accuracy at the nano-radian level, which results in a high time cost and propellant consumption cost. Summary of the invention

[0011] The purpose of the present invention is to provide an inter-satellite laser link capture device and method based on forward-pointing angle rotating mirror space scanning to solve the problems mentioned in the above background technology.

[0012] To achieve the above-mentioned purpose, the present invention provides an intersatellite laser link capture device based on space scanning of a front pointing angle rotating mirror, comprising a satellite platform, on which two large-mass one-dimensional integral pointing and deflection mechanisms are arranged, and an intersatellite laser ranging interferometer measurement unit is arranged inside the two large-mass one-dimensional integral pointing and deflection mechanisms, a first driving unit is arranged on one side of the two large-mass one-dimensional integral pointing and deflection mechanisms, a front pointing angle rotating mirror and a second driving unit arranged on one side of the front pointing angle rotating mirror are installed in the intersatellite laser ranging interferometer measurement unit, and an intersatellite laser link capture controller, a micro-thruster and a propellant are also arranged on the satellite platform.

[0013] The intersatellite laser link acquisition method based on space scanning of the front-pointing angle rotating mirror comprises the following steps: S1, the local satellite controls the outgoing laser beam to perform sub-area spatial scanning; S2. When the spatial scanning of the sub-region is completed, a large-mass one-dimensional overall pointing deflection mechanism and a satellite platform are used to control the outgoing laser beam to perform a drive to move the sub-region; S3, after the sub-region is moved, the front finger angle rotating mirror is used to control the outgoing laser beam to perform spatial scanning of the sub-region; S4. Repeat steps S1-S3 to cyclically scan the uncertain area in different areas until the remote satellite receives the outgoing laser beam during the process, thereby correcting the remote satellite's pointing direction and transmitting a return beam to the local satellite. After receiving the return beam, the local satellite stops scanning and corrects its pointing direction.

[0014] Preferably, a front-pointing angle mirror is used in S1 to perform sub-region spatial scanning.

[0015] Preferably, the area that the front finger angle mirror can scan within the travel range in S1 is called a sub-area.

[0016] Preferably, the satellite platform and the large-mass one-dimensional integral pointing deflection mechanism scan the uncertain area by moving the sub-area.

[0017] Therefore, the present invention adopts the above-mentioned intersatellite laser link capture device and method based on the space scanning of the front-pointing angle rotating mirror, and uses the front-pointing angle rotating mirror that must be installed in the long-distance intersatellite laser ranging interferometer to perform rapid space scanning of the intersatellite laser beam, so that the opposite satellite can quickly receive the laser signal and establish an intersatellite laser link, so as to make full use of the limited beam pointing control resources on the satellite and greatly reduce the time cost and propellant consumption cost of the intersatellite laser link capture task.

[0018] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1It is a device diagram used in an intersatellite laser link capture device and method based on forward-pointing angle rotating mirror space scanning according to an embodiment of the present invention; Figure 2 It is a schematic diagram of using a front-pointing angle-rotating mirror to quickly control the direction of an outgoing laser beam to perform a two-dimensional sub-region spatial scanning in a two-dimensional direction according to Embodiment 1 of the present invention, and the sub-region is sufficient to cover an uncertain region; Figure 3 It is a schematic diagram of using a front-pointing angle-rotating mirror to quickly control the direction of an outgoing laser beam to perform one-dimensional sub-region spatial scanning in the yaw direction, and using a satellite platform to drive a laser ranging interferometer to perform one-dimensional driving in the pitch direction to move the sub-region according to Embodiment 2 of the present invention; Figure 4 It is a schematic diagram of Embodiment 3 of the present invention, which uses a front-pointing angle mirror to quickly control the direction of an outgoing laser beam to perform a two-dimensional sub-region spatial scanning in a two-dimensional direction, uses a large-mass one-dimensional overall pointing deflection mechanism to perform a one-dimensional drive in a yaw direction to move the sub-region, and uses a satellite platform to drive a laser ranging interferometer to perform a one-dimensional drive in a pitch direction to move the sub-region; Reference numerals 1. Satellite platform; 2. Intersatellite laser ranging interferometer measurement unit; 3. Large-mass one-dimensional overall pointing and deflection mechanism; 4. First drive unit; 5. Front pointing angle mirror; 6. Second drive unit; 7. Intersatellite laser link capture controller; 8. Microthruster; 9. Propellant; 10. Uncertain area; 11. Outgoing laser beam; 12. Main light beam scanning trajectory controlled by the front pointing angle mirror; 13. Yaw direction controlled by the front pointing angle mirror; 14. Pitch direction controlled by the front pointing angle mirror; 15. Main light beam scanning trajectory controlled by the satellite platform; 16. Pitch direction controlled by the satellite platform; 17. Main light beam scanning trajectory controlled by the large-mass one-dimensional overall pointing and deflection mechanism and the satellite platform; 18. Yaw direction controlled by the large-mass one-dimensional overall pointing and deflection mechanism. DETAILED DESCRIPTION

[0020] Example The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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.

[0021] Reference Figure 1-Figure 4The present invention discloses an intersatellite laser link capture device based on space scanning of a front-pointing angle rotating mirror. The device includes a satellite platform 1. Two large-mass one-dimensional integral pointing deflection mechanisms 3 are arranged on the satellite platform 1. An intersatellite laser ranging interferometer measurement unit 2 is arranged inside the two large-mass one-dimensional integral pointing deflection mechanisms 3. A first driving unit 4 is arranged on one side of the two large-mass one-dimensional integral pointing deflection mechanisms 3. A front-pointing angle rotating mirror 5 and a second driving unit 6 arranged on one side of the front-pointing angle rotating mirror 5 are installed in the intersatellite laser ranging interferometer measurement unit 2. An intersatellite laser ranging interferometer measurement unit 2 is also provided with an intersatellite laser link capture controller 7, a micro-thruster 8 and a propellant 9.

[0022] Intersatellite laser link acquisition method based on forward-pointing angle rotating mirror space scanning: The following steps are involved: S1, the local satellite uses the front-pointing angle mirror 5 to control the outgoing laser beam 11 to perform sub-area spatial scanning; Use the front pointing angle mirror 5 for space scanning, or use the front pointing angle mirror 5 installed in the intersatellite laser ranging interferometer measurement unit 2 and the satellite platform 1, and the large-mass one-dimensional overall pointing deflection mechanism 3 for space scanning at the same time; instead of using the satellite platform 1, the large-mass one-dimensional overall pointing deflection mechanism 3 for space scanning, or using a dedicated fast pointing mechanism for space scanning. The dedicated fast pointing mechanism is a mechanism that can adjust the receiving line of sight, or can adjust the direction of the outgoing laser beam 11, or can adjust the receiving line of sight and the direction of the outgoing laser beam 11 at the same time. The dedicated fast pointing mechanism is a device or a combination of devices specially installed for fast pointing. Under the premise that the laser link capture can be completed using the method proposed in this embodiment or other methods, the satellite without the dedicated fast pointing mechanism installed can still complete the scientific mission.

[0023] S2, when the spatial scanning of the sub-region is completed, the outgoing laser beam 11 is driven once to move the sub-region using the large-mass one-dimensional integral pointing deflection mechanism 3 and the satellite platform 1; Equidistant spiral scanning is currently recognized by the industry as the best spatial scanning method, because equidistant spiral scanning always gives priority to scanning the area with the highest probability density, and therefore has the lowest average capture time. However, considering that the spatial scanning speed of the front finger angle rotating mirror 5 is significantly better than that of the satellite platform 1 and the large-mass one-dimensional integral pointing deflection mechanism 3, this embodiment points out that the intersatellite laser ranging interferometer laser link capture method based on the rapid spatial scanning of the front finger angle rotating mirror 5 should use a spatial scanning method of divided area scanning, that is, the area that the front finger angle rotating mirror 5 can scan within its travel range is called a sub-area, and the satellite platform 1 and the large-mass one-dimensional integral pointing deflection mechanism 3 are always driven to move the sub-area after the sub-area has completed spatial scanning, and the satellite platform 1 and the large-mass one-dimensional integral pointing deflection mechanism 3 scan the uncertain area 10 by moving the sub-area.

[0024] S3, after the sub-region is moved, the front finger angle rotating mirror 5 is used to control the outgoing laser beam 11 to perform spatial scanning of the sub-region; S4. Repeat steps S1-S3 to cyclically scan the uncertain area 10 in different regions until the remote satellite receives the outgoing laser beam 11 during the process, thereby correcting the remote satellite's pointing direction and transmitting a reflected beam to the local satellite. After receiving the reflected beam, the local satellite stops scanning and corrects its pointing direction.

[0025] The following is an explanation in combination with three embodiments. Embodiment 3 describes a typical sub-regional scanning. Embodiment 2 describes a special sub-regional scanning, the special point of which is that the sub-region is a narrow rectangular area, and its spatial scanning method conforms to the general definition of the line-by-line scanning method while conforming to the sub-regional scanning method. Embodiment 1 describes a special sub-regional scanning, the special point of which is that the size of the sub-region itself is sufficient to cover the uncertain area 10, so the number of times the satellite platform 1 and the large-mass one-dimensional integral pointing deflection mechanism 3 move the sub-region is 0; and the spatial scanning method within the sub-region conforms to the definition of equidistant spiral scanning.

[0026] Embodiment 1: A typical capture condition is that the front finger angle mirror 5 can be driven two-dimensionally in two directions, namely, the yaw direction 13 controlled by the front finger angle mirror and the pitch direction 14 controlled by the front finger angle mirror, and while performing the front finger angle compensation, the remaining stroke of the front finger angle mirror 5 is sufficient to cover the uncertain area 10. Under this condition, the schematic diagram of the implementation process of this embodiment is as shown in FIG. Figure 2 , described as follows: The local satellite drives the front pointing angle turning mirror 5 installed in the intersatellite laser ranging interferometer measurement unit 2 in the yaw direction 13 and the pitch direction 14 controlled by the front pointing angle turning mirror, and controls the outgoing laser beam 11 to perform two-dimensional scanning along the main light scanning trajectory 12 controlled by the front pointing angle turning mirror until the remote satellite receives the outgoing laser beam 11 at a certain moment in the process, thereby correcting its pointing and transmitting a return beam to the local satellite. After receiving the return beam, the local satellite stops scanning and corrects its pointing.

[0027] Embodiment 2: A typical capture condition is that, since the front finger angle only needs to be dynamically compensated in one direction, the front finger angle mirror 5 is designed to be driven in one dimension (taking driving in the yaw direction as an example), and while performing the front finger angle compensation, the remaining stroke of the front finger angle mirror 5 is sufficient to cover the component of the uncertain area 10 in its driving direction. Under this condition, the schematic diagram of the implementation process of this embodiment is as follows Figure 3 , described as follows: The local satellite drives the front pointing angle rotating mirror 5 installed in the intersatellite laser ranging interferometer measuring unit 2 in the yaw direction 13 controlled by the front pointing angle rotating mirror, controls the outgoing laser beam 11 to perform one-dimensional scanning along the main light scanning trajectory 12 controlled by the front pointing angle rotating mirror, and when the one-dimensional scanning is completed, drives the satellite platform 1 in the pitch direction 16 controlled by the satellite platform, controls the outgoing laser beam 11 to perform one-dimensional driving along the main light scanning trajectory 15 controlled by the satellite platform, and then continues to drive the front pointing angle rotating mirror 5 installed in the intersatellite laser ranging interferometer measuring unit 2 in the yaw direction 13 controlled by the front pointing angle rotating mirror, controls the outgoing laser beam 11 to perform one-dimensional scanning along the main light scanning trajectory 12 controlled by the front pointing angle rotating mirror, and scans the uncertain area 10 line by line in a cycle until the remote satellite receives the irradiation of the outgoing laser beam 11 at a certain moment in the process, thereby correcting its pointing and transmitting a reflected beam to the local satellite, and the local satellite stops scanning and corrects its pointing after receiving the reflected beam.

[0028] Embodiment 3: A typical capture condition is that the front finger angle mirror 5 can be driven two-dimensionally in the yaw and pitch directions, and while the front finger angle compensation is performed, the remaining travel of the front finger angle mirror 5 is not enough to cover the uncertain area 10. Under this condition, the schematic diagram of the implementation process of this embodiment is as follows Figure 4 , described as follows: The local satellite drives the front-pointing angle rotating mirror 5 installed in the intersatellite laser ranging interferometer measurement unit 2 in the yaw direction 13 and the pitch direction 14 controlled by the front-pointing angle rotating mirror, and controls the outgoing laser beam 11 to perform two-dimensional scanning along the main light scanning trajectory 12 controlled by the front-pointing angle rotating mirror. However, the main light scanning trajectory 12 controlled by the front-pointing angle rotating mirror is not enough to cover the uncertain area 10, so the area covered by the main light scanning trajectory 12 controlled by the front-pointing angle rotating mirror is regarded as a sub-area, and the sub-area scanning is performed. When the front-pointing angle rotating mirror 5 installed in the intersatellite laser ranging interferometer measurement unit 2 controls the outgoing laser beam 11 to complete the two-dimensional scanning along the main light scanning trajectory 12 controlled by the front-pointing angle rotating mirror, a drive is performed along the main light scanning trajectory 17 controlled by the large-mass one-dimensional overall pointing deflection mechanism and the satellite platform. The main light scanning trajectory 17 controlled by the one-dimensional large-mass overall pointing deflection mechanism and the satellite platform is two-dimensional, including the pitch direction 16 controlled by the satellite platform and the yaw direction 18 controlled by the one-dimensional large-mass overall pointing deflection mechanism, which are respectively executed by the satellite platform 1 and the one-dimensional large-mass overall pointing deflection mechanism 3. After executing a drive along the main light scanning trajectory 17 controlled by the one-dimensional large-mass overall pointing deflection mechanism and the satellite platform, the front finger angle rotating mirror 5 installed in the intersatellite laser ranging interferometer measurement unit 2 controls the outgoing laser beam 11 to perform a two-dimensional scan along the main light scanning trajectory 12 controlled by the front finger angle rotating mirror, and the uncertain area 10 is scanned in a cycle in this way until the remote satellite receives the outgoing laser beam 11 at a certain moment in the process, thereby correcting its pointing and transmitting a reflected beam to the local satellite. After receiving the reflected beam, the local satellite stops scanning and corrects its pointing.

[0029] Therefore, the present invention adopts the above-mentioned intersatellite laser link capture device and method based on the space scanning of the front-pointing angle rotating mirror, and uses the front-pointing angle rotating mirror that must be installed in the long-distance intersatellite laser ranging interferometer to perform rapid space scanning of the intersatellite laser beam, so that the opposite satellite can quickly receive the laser signal and establish an intersatellite laser link, so as to make full use of the limited beam pointing control resources on the satellite and greatly reduce the time cost and propellant consumption cost of the intersatellite laser link capture task.

[0030] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. An intersatellite laser link capture device based on space scanning of a front-pointing angle rotating mirror, characterized in that: The invention comprises a satellite platform, on which two large-mass one-dimensional integral pointing and deflection mechanisms are arranged, wherein intersatellite laser ranging interferometer measurement units are arranged inside the two large-mass one-dimensional integral pointing and deflection mechanisms, wherein a first driving unit is arranged on one side of the two large-mass one-dimensional integral pointing and deflection mechanisms, wherein a front pointing angle rotating mirror and a second driving unit arranged on one side of the front pointing angle rotating mirror are installed in the intersatellite laser ranging interferometer measurement unit, and an intersatellite laser link capture controller, a micro-thruster and a propellant are also arranged on the satellite platform.

2. A method for applying the intersatellite laser link capture device based on forward-pointing angle rotating mirror space scanning as claimed in claim 1, characterized in that: The following steps are involved: S1, the local satellite controls the outgoing laser beam to perform sub-area spatial scanning; S2. When the spatial scanning of the sub-region is completed, a large-mass one-dimensional overall pointing deflection mechanism and a satellite platform are used to control the outgoing laser beam to perform a drive to move the sub-region; S3, after the sub-region is moved, the front finger angle rotating mirror is used to control the outgoing laser beam to perform spatial scanning of the sub-region; S4. Repeat steps S1-S3 to cyclically scan the uncertain area in different areas until the remote satellite receives the outgoing laser beam during the process, thereby correcting the remote satellite's pointing direction and transmitting a return beam to the local satellite. After receiving the return beam, the local satellite stops scanning and corrects its pointing direction.

3. The method for capturing an intersatellite laser link based on forward-pointing angle-rotating mirror space scanning according to claim 2 is characterized in that: In S1, a front-pointing angle-rotating mirror is used to perform sub-region spatial scanning.

4. The method for capturing an intersatellite laser link based on space scanning of a front-pointing angle rotating mirror according to claim 2, characterized in that: The sub-area in S1 is the area scanned by the front finger angle mirror within its travel.

5. The method for capturing an intersatellite laser link based on forward-pointing angle-rotating mirror space scanning according to claim 2, characterized in that: The satellite platform and the large-mass one-dimensional integral pointing deflection mechanism scan the uncertain area by moving the sub-area.

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