Microwave laser collaborative inter-satellite link rapid establishment method and system

Abstract

The invention provides a microwave-laser collaborative inter-satellite link rapid establishment method and system, and the method comprises the steps: preferentially establishing a microwave link in an inter-satellite communication link establishment stage, rapidly exchanging orbit parameters of two parties through the microwave link, calculating the direction vector of the other satellite in real time through the exchanged orbit data, and carrying out the calculation of the direction vector of the other satellite; and the laser terminal is directly guided to carry out high-precision pointing, track data are continuously updated through a microwave link in the laser link building process, and dynamic error compensation is achieved. The method breaks through the limitation of long time consumption of traditional laser scanning and capturing, improves the pointing precision, and shortens the laser link building time. The method is especially suitable for efficient inter-satellite link establishment scenes of large-scale constellation networking.

Description

Technical Field

[0001] This invention relates to the field of satellite communication technology, and more specifically, to a method and system for rapid establishment of inter-satellite links using microwave-laser coordination. Background Art

[0002] With the rapid deployment and continuous advancement of global low-Earth orbit (LEO) mega-constellations, inter-satellite links need to achieve "minute-level" network establishment over distances of hundreds or even thousands of kilometers. Traditional pure laser inter-satellite links rely on a scan-acquisition-tracking process, initially pointing based on outdated orbital parameters of the target satellite as recorded on the ground. This necessitates spiral or grating scans over a large airspace during the acquisition phase, which can take several minutes or even longer. Furthermore, they are highly sensitive to attitude control accuracy, thermal deformation, and orbit prediction errors, posing a risk of link establishment failure. The high relative speeds and low orbital information update frequency between LEO satellites make them highly susceptible to re-scanning after loss of capture, severely impacting inter-satellite link establishment time and even leading to inefficient operation of the entire network. While pure microwave inter-satellite links are easier to acquire, their bandwidth and antenna size limitations make it difficult to meet the transmission demands of services ranging from hundreds of megabits to gigabits. Therefore, balancing "rapid acquisition" and "high-speed transmission" during the rapid constellation deployment phase has become a key bottleneck restricting the development of next-generation space-based networks.

[0003] Existing technologies simply superimpose microwave and laser links, but they mostly remain at the level of independent use of microwaves and lasers, lacking real-time communication of orbital parameters and joint pointing correction mechanisms. This results in the laser still needing to scan a large area; or it uses ground-based telemetry and control to project the orbit, which leads to high latency and large errors. In addition, traditional laser scanning modes are fixed and fail to dynamically compress the scanning range based on the relative direction vector provided by the microwave in real time, resulting in low scanning efficiency and high power consumption.

[0004] In summary, there is an urgent need for a microwave-laser collaborative rapid link establishment method and system that can quickly complete orbital data exchange, accurately complete laser pre-pointing, and reduce the uncertainty area of ​​laser scanning.

[0005] Patent document CN111934743A (application number: 202010717043.7) discloses an inter-satellite link establishment method for an omnidirectional dynamic microwave-laser composite system, including the following steps: Orbital information uploading step: After the primary and secondary satellites enter orbit, their orbital parameters are determined by ground-based measurements and recursively calculated before being uploaded to the primary and secondary satellites respectively; Microwave link establishment step: The phased array antennas of the primary and secondary satellites perform microwave antenna pointing calculations based on the recursively calculated orbital parameters to establish a microwave link between the primary and secondary satellites; Laser link establishment step: The primary and secondary satellites exchange relative GNSS navigation information through the microwave link, and their laser terminals scan to complete bidirectional acquisition, thus establishing the laser link. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for rapid establishment of inter-satellite links using microwave laser coordination.

[0007] A method for rapid establishment of inter-satellite links using microwave-laser coordination, provided by the present invention, includes: Step S1: Establish an inter-satellite microwave link via a microwave communication link; Step S2: The two satellites exchange orbital parameters in real time via an inter-satellite microwave link; wherein, the orbital parameters include: satellite identifier, time, semi-major axis of orbit, orbital eccentricity, orbital inclination, ascending node right axis, perigee argument, and true perigee angle; Step S3: Based on the real-time exchanged orbital parameters, the relative direction vector of the binary stars is recursively calculated in real time; Step S4: Preset the pointing angle of the laser communication optical head based on the relative direction vector; Step S5: Based on the pointing angle of the laser communication optical head, trigger the laser communication optical head to scan, and at the same time continuously update the orbit data and dynamically correct the pointing angle of the laser communication optical head through the inter-satellite microwave link to establish the inter-satellite laser link.

[0008] Preferably, the inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication; Meanwhile, the signal-to-noise ratio threshold for establishing the inter-satellite microwave link is more than 10 dB lower than that for the inter-satellite laser link.

[0009] Preferably, step S3 includes: calculating the satellite's position vector in the geocentric equatorial inertial frame based on the orbital parameters exchanged in real time between the two satellites, including: satellite identifier ID, time t, orbital semi-major axis a, orbital eccentricity e, orbital inclination i, ascending node right axis Ω, perigee argument ω, and true perigee angle υ; and then calculating the relative direction vector between the two satellites. d and the corresponding unit direction vector d’ ; 1) Calculate the satellite's position vector in the geocentric equatorial inertial frame (ECI); (1) Calculate the satellite's position in the orbital plane coordinate system using the orbital six roots:

[0010]

[0011]

[0012]

[0013] Where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, and z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Transform the position in the orbital coordinate system to the geocentric equatorial inertial frame (ECI): Coordinate transformation is achieved through three rotations:

[0014] in, x, y, z represents the coordinates of the satellite in the geocentric equatorial inertial frame; The rotation matrices are as follows: Rotation around the Z-axis by -Ω degrees:

[0015] Rotate by -i degrees around the X-axis:

[0016] Rotation around the Z-axis by -ω degrees:

[0017] 2) Calculate the relative direction vectors of the two satellites; Let the position vector of this star in the Earth-centered equatorial inertial frame ECI be... r 1. The position vector of the opposing star in the Earth's central equatorial inertial frame (ECI) is: r 2; relative direction vector d for: .

[0018] Unit direction vector used for laser pointing d’ for: .

[0019] Preferably, step S5 includes: triggering the laser communication optical head to scan in any one of the following modes based on the laser communication optical head pointing angle: matrix spiral scanning mode, spiral scanning mode, random scanning mode, and concentric circle scanning mode.

[0020] Preferably, the method further includes: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link; The control and service data transmitted based on the constructed inter-satellite laser and microwave links include: Inter-satellite microwave links are used to transmit control data that meets preset requirements; inter-satellite laser links are used to transmit control data and service data. The control data transmitted via the inter-satellite microwave link that meets preset requirements includes: orbital parameters, link status, and mission information data in small amounts that meet preset requirements.

[0021] A microwave-laser coordinated inter-satellite link rapid establishment system according to the present invention includes: Inter-satellite microwave link construction module: Establishes inter-satellite microwave links through microwave communication links; Orbital parameter exchange module: The two satellites exchange orbital parameters in real time via an inter-satellite microwave link; wherein, the orbital parameters include: satellite identifier, time, semi-major axis of orbit, orbital eccentricity, orbital inclination, ascending node right axis, perigee argument, and true perigee angle; Direction vector acquisition module: Real-time recursive derivation of the relative direction vector of the binary stars based on the orbital parameters exchanged in real time; Optical head pointing angle pre-setting module: Presets the pointing angle of the laser communication optical head based on the relative direction vector; Inter-satellite laser link construction module: Based on the pointing angle of the laser communication optical head, the laser communication optical head is triggered to scan, and the orbital data is continuously updated and the pointing angle of the laser communication optical head is dynamically corrected through the inter-satellite microwave link to establish the inter-satellite laser link.

[0022] Preferably, the inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication; Meanwhile, the signal-to-noise ratio threshold for establishing the inter-satellite microwave link is more than 10 dB lower than that for the inter-satellite laser link.

[0023] Preferably, the direction vector acquisition module includes: calculating the satellite's position vector in the geocentric equatorial inertial frame based on the orbital parameters exchanged in real time between the two satellites, including: satellite identifier ID, time t, orbital semi-major axis a, orbital eccentricity e, orbital inclination i, ascending node right axis Ω, perigee argument ω, and true perigee angle υ; and then calculating the relative direction vector between the two satellites. d and the corresponding unit direction vector d’ ; 1) Calculate the satellite's position vector in the geocentric equatorial inertial frame (ECI); (1) Calculate the satellite's position in the orbital plane coordinate system using the orbital six roots:

[0024]

[0025]

[0026]

[0027] Where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, and z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Transform the position in the orbital coordinate system to the geocentric equatorial inertial frame (ECI): Coordinate transformation is achieved through three rotations:

[0028] in, x, y, z represents the coordinates of the satellite in the geocentric equatorial inertial frame; Represents a rotation matrix that rotates by -Ω degrees around the Z-axis; Represents a rotation matrix that rotates -i degrees around the X-axis; Represents a rotation matrix that rotates by -ω degrees around the Z-axis; The rotation matrices are as follows: Rotation around the Z-axis by -Ω degrees:

[0029] Rotate by -i degrees around the X-axis:

[0030] Rotation around the Z-axis by -ω degrees:

[0031] 2) Calculate the relative direction vectors of the two satellites; Let the position vector of this star in the Earth-centered equatorial inertial frame ECI be... r 1. The position vector of the opposing star in the Earth's central equatorial inertial frame (ECI) is: r 2; relative direction vector d for: .

[0032] Unit direction vector used for laser pointing d’ for: .

[0033] Preferably, the inter-satellite laser link construction module includes: triggering the laser communication optical head to scan in any one of the following modes based on the pointing angle of the laser communication optical head: matrix spiral scanning mode, spiral scanning mode, random scanning mode, and concentric circle scanning mode.

[0034] Preferably, the system further includes: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link; The control and service data transmitted based on the constructed inter-satellite laser and microwave links include: Inter-satellite microwave links are used to transmit control data that meets preset requirements; inter-satellite laser links are used to transmit control data and service data. The control data transmitted via the inter-satellite microwave link that meets preset requirements includes: orbital parameters, link status, and mission information data in small amounts that meet preset requirements.

[0035] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention enables rapid exchange and real-time extrapolation of orbital parameters via a microwave link, allowing the laser terminal to directly obtain a micro-radian-level preset direction, reducing the scanning uncertainty area, improving the first capture success rate, and shortening the link establishment time; 2. Laser reduces the number of scanning steps, and combined with programmable scanning modes such as matrix spiral and random, it reduces scanning power consumption, making it particularly suitable for power-constrained scenarios in micro and nano satellites; 3. By continuously injecting real-time orbit through microwave link, the orbit extrapolation error, attitude jitter and thermal deformation are dynamically compensated, the residual pointing error of laser link is reduced, and the pointing accuracy is continuously improved. 4. After the link is established, microwave is used to transmit small amounts of control data, while laser is used to carry large amounts of business data in parallel, realizing a collaborative working mode of parallel transmission of business and control data through dual links, laying the technical foundation for real-time routing and on-orbit collaboration of large-scale constellations. 5. This invention combines the speed of microwave links with the high bandwidth of laser communication, and solves the problem of precise laser pointing by dynamically transmitting orbital data, thereby enabling the rapid establishment of inter-satellite laser links and facilitating the efficient networking of large-scale constellations. Attached Figure Description

[0036] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of a microwave-laser hybrid communication system according to an embodiment of the present invention.

[0037] Figure 2 This is a flowchart illustrating the rapid establishment of inter-satellite links using microwave-laser coordination in an embodiment of the present invention. Detailed Implementation

[0038] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0039] Example 1 According to the present invention, a method for rapid establishment of inter-satellite links using microwave laser coordination is provided, such as... Figure 2 As shown, the following steps are included: Step S1: Establish an initial inter-satellite microwave link via a microwave communication link; Step S2: The two satellites exchange orbital parameters in real time via an inter-satellite microwave link; Step S3: Based on the orbits of the local star and the opposing star, the relative direction vector between the local star and the opposing star is calculated in real time; Step S4: Preset the laser communication optical head pointing angle based on the relative direction vector to achieve high-precision pointing; Step S5: Start the laser communication optical head scanning, and at the same time continuously update the orbit data and dynamically correct the pointing through the microwave link to establish an inter-satellite laser link; Step S6: Switch to dual-link collaborative working mode, where microwave transmits control data and laser transmits both service data and control data simultaneously.

[0040] Specifically, the microwave link includes, but is not limited to, X-band, Ka-band, Q-band, V-band, and W-band, and the link establishment threshold signal-to-noise ratio is more than 10 dB lower than that of the laser link.

[0041] Specifically, the orbital parameters exchanged in real time in step S2 include satellite identifier, time, orbital semi-major axis, orbital eccentricity, orbital inclination, ascending node right axis, perigee argument, and true perigee angle.

[0042] Specifically, in step S3, based on the orbital parameters exchanged in real time between the two satellites, including: satellite ID, time t, orbital semi-major axis a, orbital eccentricity e, orbital inclination i, ascending node right axis Ω, perigee argument ω, and true perigee angle υ, the position vector of the satellite in the geocentric equatorial inertial frame is calculated, and then the relative direction vector of the two satellites is calculated. d and the corresponding unit direction vector d’ ; 1) Calculate the satellite's position vector in the geocentric equatorial inertial frame (ECI); (1) Calculate the satellite's position in the orbital plane coordinate system using the orbital six roots:

[0043]

[0044]

[0045]

[0046] Where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, and z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Transform the position in the orbital coordinate system to the geocentric equatorial inertial frame (ECI): Coordinate transformation is achieved through three rotations:

[0047] in, x, y, z represents the coordinates of the satellite in the geocentric equatorial inertial frame; The rotation matrices are as follows: Rotation around the Z-axis by -Ω degrees:

[0048] Rotate by -i degrees around the X-axis:

[0049] Rotation around the Z-axis by -ω degrees:

[0050] 2) Calculate the relative direction vectors of the two satellites; Let the position vector of this star in the Earth-centered equatorial inertial frame ECI be... r 1. The position vector of the opposing star in the Earth's central equatorial inertial frame (ECI) is: r 2; relative direction vector d for: .

[0051] Unit direction vector used for laser pointing d’ for: .

[0052] Specifically, in step S5, the laser scanning range is compressed to an uncertain area of ​​±0.05° within the coarse alignment direction.

[0053] Specifically, the laser scanning range mode in step S5 can be a matrix spiral scanning mode, a spiral scanning mode, a random scanning mode, or a concentric circle scanning mode.

[0054] Specifically, in the dual-link collaborative mode in step S6, the control data transmitted by the microwave link consists of a small amount of data such as orbital parameters, link status, and task information. In addition to transmitting the same control data, the laser terminal also transmits a large amount of business data, including payload data.

[0055] The present invention also provides a microwave-laser coordinated inter-satellite link rapid establishment system. The microwave-laser coordinated inter-satellite link rapid establishment system can be implemented by executing the process steps of the microwave-laser coordinated inter-satellite link rapid establishment method. That is, those skilled in the art can understand the microwave-laser coordinated inter-satellite link rapid establishment method as a preferred embodiment of the microwave-laser coordinated inter-satellite link rapid establishment system.

[0056] Example 2 Example 2 is a preferred example of Example 1. like Figure 1 As shown, the first and second satellites establish inter-satellite microwave and inter-satellite laser links, and the main modules included are as follows: The first satellite comprises a first integrated processing module 101, a first microwave communication processing module 102, a first microwave communication control module 103, a first microwave communication antenna module 104, a first laser communication processing module 105, a first laser communication optical head module 106, and a first laser communication control module 107.

[0057] The second satellite comprises the second integrated processing module 201, the second microwave communication processing module 202, the second microwave communication control module 203, the second microwave communication antenna module 204, the second laser communication processing module 205, the second laser communication optical head module 206, and the second laser communication control module 207.

[0058] Combination Figure 1 The first and second satellites, and Figure 2 A rapid method for establishing inter-satellite links using microwave-laser coordination is presented, with detailed steps as follows.

[0059] Step S1: The first microwave communication control module 103 of the first satellite controls the first microwave communication antenna module 104 to point to the second microwave communication antenna module 204 of the second satellite. At the same time, the second microwave communication control module 203 of the second satellite controls the second microwave communication antenna module 204 to point to the first microwave communication antenna module 104 of the first satellite, and establishes an initial inter-satellite microwave link through the microwave communication link.

[0060] Step S2: The first integrated processing module 101 of the first satellite transmits the real-time orbit parameters P1 of the first satellite to the second microwave communication antenna module 204 and the second microwave communication processing module 202 of the second satellite through the first microwave communication processing module 102 and the first microwave communication antenna module 104, and finally to the second integrated processing module 201; the second integrated processing module 201 of the second satellite transmits the real-time orbit parameters P2 of the second satellite to the first microwave communication antenna module 104 and the first microwave communication processing module 102 of the first satellite through the second microwave communication processing module 202 and the second microwave communication antenna module 204, and finally to the first integrated processing module 101; the two satellites achieve real-time exchange of orbit parameters.

[0061] Step S3: The first integrated processing module 101 of the first satellite recursively calculates the first relative direction vector A1 from the satellite to the other satellite in real time based on the orbital parameters P1 of the satellite and the received orbital parameters P2 of the other satellite; the second integrated processing module 201 of the second satellite recursively calculates the second relative direction vector A2 from the satellite to the other satellite in real time based on the orbital parameters P2 of the satellite and the received orbital parameters P1 of the other satellite.

[0062] Step S4: The first integrated processing module 101 of the first satellite transmits the first relative direction vector A1, which is recursively pushed from the local satellite to the counterpart satellite, to the first laser communication control module 107. The first laser communication control module 107 performs coarse alignment by presetting the pointing angle of the first laser communication optical head module 106 based on the first relative direction vector A1. The second integrated processing module 201 of the second satellite transmits the second relative direction vector A2, which is recursively pushed from the local satellite to the counterpart satellite, to the second laser communication control module 207. The second laser communication control module 207 performs coarse alignment by presetting the pointing angle of the second laser communication optical head module 206 based on the second relative direction vector A2.

[0063] Step S5: The first satellite starts scanning with the first laser communication optical head module 106, while continuously updating orbit data and dynamically correcting the pointing via the microwave link; the second satellite starts scanning with the second laser communication optical head module 206, while continuously updating orbit data and dynamically correcting the pointing via the microwave link, thus establishing an inter-satellite laser link.

[0064] Step S6: Both the first and second satellites switch to dual-link collaborative working mode, with microwave transmitting control data and laser simultaneously transmitting service data and control data.

[0065] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0066] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for rapid establishment of inter-satellite links using microwave-laser coordination, characterized in that, include: Step S1: Establish an inter-satellite microwave link via a microwave communication link; Step S2: The two satellites exchange orbital parameters in real time via an inter-satellite microwave link; wherein, the orbital parameters include: satellite identifier, time, semi-major axis of orbit, orbital eccentricity, orbital inclination, ascending node right axis, perigee argument, and true perigee angle; Step S3: Based on the real-time exchanged orbital parameters, the relative direction vector of the binary stars is recursively calculated in real time; Step S4: Preset the pointing angle of the laser communication optical head based on the relative direction vector; Step S5: Based on the pointing angle of the laser communication optical head, trigger the laser communication optical head to scan, and at the same time continuously update the orbit data and dynamically correct the pointing angle of the laser communication optical head through the inter-satellite microwave link to establish the inter-satellite laser link.

2. The method for rapid establishment of inter-satellite links using microwave laser coordination according to claim 1, characterized in that, The inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication. Meanwhile, the signal-to-noise ratio threshold for establishing the inter-satellite microwave link is more than 10 dB lower than that for the inter-satellite laser link.

3. The method for rapid establishment of inter-satellite links using microwave laser coordination according to claim 1, characterized in that, Step S3 includes: calculating the satellite's position vector in the geocentric equatorial inertial frame based on the orbital parameters exchanged in real time between the two satellites, including: satellite ID, time t, orbital semi-major axis a, orbital eccentricity e, orbital inclination i, ascending node right axis Ω, perigee argument ω, and true perigee angle υ; and then calculating the relative direction vector between the two satellites. d and the corresponding unit direction vector d’ ; 1) Calculate the satellite's position vector in the geocentric equatorial inertial frame (ECI); (1) Calculate the satellite's position in the orbital plane coordinate system using the orbital six roots: Where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, and z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Transform the position in the orbital coordinate system to the geocentric equatorial inertial frame (ECI): Coordinate transformation is achieved through three rotations: Where x, y, and z are the coordinates of the satellite in the geocentric equatorial inertial frame, respectively; Represents a rotation matrix that rotates by -Ω degrees around the Z-axis; Represents a rotation matrix that rotates -i degrees around the X-axis; Represents a rotation matrix that rotates -ω degrees around the Z-axis; The rotation matrices are as follows: Rotation around the Z-axis by -Ω degrees: Rotate by -i degrees around the X-axis: Rotation around the Z-axis by -ω degrees: 2) Calculate the relative direction vectors of the two satellites; Let the position vector of this star in the Earth-centered equatorial inertial frame ECI be... r 1. The position vector of the opposing star in the Earth's central equatorial inertial frame (ECI) is: r 2; relative direction vector d for: ； The unit direction vector used for laser pointing is preset. d’ for: 。 4. The method for rapid establishment of inter-satellite links using microwave laser coordination according to claim 1, characterized in that, Step S5 includes: triggering the laser communication optical head to scan in any one of the following modes based on the laser communication optical head pointing angle: matrix spiral scanning mode, spiral scanning mode, random scanning mode, and concentric circle scanning mode.

5. The method for rapid establishment of inter-satellite links using microwave laser coordination according to claim 1, characterized in that, The method further includes: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link; The control and service data transmitted based on the constructed inter-satellite laser and microwave links include: Inter-satellite microwave links are used to transmit control data that meets preset requirements; inter-satellite laser links are used to transmit control data and service data. The control data transmitted via the inter-satellite microwave link that meets preset requirements includes: orbital parameters, link status, and mission information data in small amounts that meet preset requirements.

6. A microwave-laser coordinated inter-satellite link rapid establishment system, characterized in that, include: Inter-satellite microwave link construction module: Establishes inter-satellite microwave links through microwave communication links; Orbital parameter exchange module: The two satellites exchange orbital parameters in real time via an inter-satellite microwave link; wherein, the orbital parameters include: satellite identifier, time, semi-major axis of orbit, orbital eccentricity, orbital inclination, ascending node right axis, perigee argument, and true perigee angle; Direction vector acquisition module: Real-time recursive derivation of the relative direction vector of the binary stars based on the orbital parameters exchanged in real time; Optical head pointing angle pre-setting module: Presets the pointing angle of the laser communication optical head based on the relative direction vector; Inter-satellite laser link construction module: Based on the pointing angle of the laser communication optical head, the laser communication optical head is triggered to scan, and the orbital data is continuously updated and the pointing angle of the laser communication optical head is dynamically corrected through the inter-satellite microwave link to establish the inter-satellite laser link.

7. The microwave-laser coordinated inter-satellite link rapid establishment system according to claim 6, characterized in that, The inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication. Meanwhile, the signal-to-noise ratio threshold for establishing the inter-satellite microwave link is more than 10 dB lower than that for the inter-satellite laser link.

8. The microwave-laser coordinated inter-satellite link rapid establishment system according to claim 6, characterized in that, The direction vector acquisition module includes: calculating the satellite's position vector in the geocentric equatorial inertial frame based on the orbital parameters exchanged in real time between the two satellites, including: satellite ID, time t, orbital semi-major axis a, orbital eccentricity e, orbital inclination i, ascending node right axis Ω, perigee argument ω, and true perigee angle υ; and then calculating the relative direction vector between the two satellites. d and the corresponding unit direction vector d’ ; 1) Calculate the satellite's position vector in the geocentric equatorial inertial frame (ECI); (1) Calculate the satellite's position in the orbital plane coordinate system using the orbital six roots: Where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, and z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Transform the position in the orbital coordinate system to the geocentric equatorial inertial frame (ECI): Coordinate transformation is achieved through three rotations: in, x, y, z represents the coordinates of the satellite in the geocentric equatorial inertial frame; Represents a rotation matrix that rotates by -Ω degrees around the Z-axis; Represents a rotation matrix that rotates -i degrees around the X-axis; Represents a rotation matrix that rotates -ω degrees around the Z-axis; The rotation matrices are as follows: Rotation around the Z-axis by -Ω degrees: Rotate by -i degrees around the X-axis: Rotation around the Z-axis by -ω degrees: 2) Calculate the relative direction vectors of the two satellites; Let the position vector of this star in the Earth-centered equatorial inertial frame ECI be... r 1. The position vector of the opposing star in the Earth's central equatorial inertial frame (ECI) is: r 2; relative direction vector d for: ； The unit direction vector used for laser pointing is preset. d’ for: 。 9. The microwave-laser coordinated inter-satellite link rapid establishment system according to claim 6, characterized in that, The inter-satellite laser link construction module includes: triggering the laser communication optical head to scan in any one of the following modes based on the laser communication optical head pointing angle: matrix spiral scanning mode, spiral scanning mode, random scanning mode, and concentric circle scanning mode.

10. The microwave-laser coordinated inter-satellite link rapid establishment system according to claim 6, characterized in that, The system also includes: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link; The control and service data transmitted based on the constructed inter-satellite laser and microwave links include: Inter-satellite microwave links are used to transmit control data that meets preset requirements; inter-satellite laser links are used to transmit control data and service data. The control data transmitted via the inter-satellite microwave link that meets preset requirements includes: orbital parameters, link status, and mission information data in small amounts that meet preset requirements.

Images