Microwave laser cooperative inter-satellite link fast establishment method and system

Abstract

The application provides a microwave laser cooperative inter-satellite link fast establishment method and system, comprising: in the inter-satellite communication link establishment stage, a microwave link is established preferentially, and orbit parameters of both sides are exchanged quickly through the microwave link, orbit data after the exchange is used to calculate a direction vector of the other satellite in real time, a laser terminal is directly guided for high-precision pointing, and the orbit data is continuously updated through the microwave link in the laser link establishment process, so that dynamic error compensation is realized. The method breaks through the limitation of long time consumption of traditional laser scanning and acquisition, improves the pointing precision, and shortens the laser link establishment time. The method is particularly suitable for efficient inter-satellite link establishment scenes of large-scale constellation networking.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite communication, in particular to a microwave laser cooperative inter-satellite link rapid establishment method and system. BACKGROUND

[0002] With the rapid deployment and continuous advancement of global low-orbit mega constellation, inter-satellite links need to achieve "minute-level" networking within hundreds or even thousands of kilometers. Traditional pure laser inter-satellite links rely on scanning-acquisition-tracking procedures. The initial pointing is based on the "outdated" orbital parameters of the opposite satellite injected on the ground, which leads to spiral or raster scanning in a large airspace during the acquisition stage, which may take several minutes or even longer. Moreover, it is highly sensitive to attitude control accuracy, thermal deformation and orbital prediction error, and there is a risk of link establishment failure. The relative motion speed between low-orbit satellites is high, and the orbital information update frequency is low, which easily leads to re-scanning after missing the acquisition, seriously affecting the establishment time of the inter-satellite link, and even leading to inefficient operation of the entire network. Although pure microwave inter-satellite links are easy to acquire, they are difficult to meet the demand of hundreds of megabits to gigabit level business transmission due to the limitation of bandwidth and antenna size. Therefore, how to balance "fast acquisition" and "high-speed transmission" during the rapid networking stage of the constellation has become a key bottleneck restricting the next generation of space-based networks.

[0003] The prior art simply superimposes microwave and laser links, but mostly stays at the level of independent use of microwave and laser, lacks real-time mutual exchange of orbital parameters and joint pointing correction mechanism, leading to a large range of laser scanning; or uses ground measurement and control to inject orbital parameters, which is delayed and has large errors. In addition, the traditional laser scanning mode is fixed and cannot dynamically compress the scanning range according to 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 cooperative rapid link establishment method and system that can quickly complete orbital data exchange, high-precision laser preset pointing, and reduce the uncertainty area of laser scanning.

[0005] Patent document CN111934743A (application number: 202010717043.7) discloses a kind of omni-directional dynamic microwave laser complex system inter-satellite link chain establishment method, comprising the following steps: orbit injection information injection step: after the main star and the satellite enter the orbit, the orbital parameters of the main star and the satellite are determined by the ground and are recursively injected into the main star and the satellite after orbit recursion;Microwave link establishment step: the phased array antenna of the main star and the satellite carries out microwave antenna pointing calculation according to the orbital parameters of orbit recursion, and establishes the microwave link of the main star and the satellite;Laser link establishment step: the main star and the satellite interact relative GNSS navigation information through microwave link, and the laser terminal of the main star and the satellite scans, completes two-way acquisition, and completes laser link establishment. SUMMARY

[0006] Aiming at the defects in the prior art, the present application aims to provide a microwave laser cooperative inter-satellite link fast establishment method and system.

[0007] According to the microwave laser cooperative inter-satellite link fast establishment method provided by the present application, the method comprises the following steps:

[0008] Step S1: establishing an inter-satellite microwave link through a microwave communication link;

[0009] Step S2: exchanging orbit parameters in real time through the inter-satellite microwave link by the two satellites; wherein the orbit parameters comprise satellite identification, time, orbit semi-major axis, orbit eccentricity, orbit inclination, ascending node right ascension, perigee amplitude angle and true anomaly angle;

[0010] Step S3: real-time recursion of the relative direction vector of the two satellites according to the real-time exchanged orbit parameters;

[0011] Step S4: presetting a laser communication optical head pointing angle based on the relative direction vector;

[0012] Step S5: triggering the laser communication optical head scanning based on the laser communication optical head pointing angle, while continuously updating the orbit data through the inter-satellite microwave link and dynamically correcting the laser communication optical head pointing angle, to establish an inter-satellite laser link.

[0013] Preferably, the inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication;

[0014] Meanwhile, the inter-satellite microwave link chain establishment signal-to-noise ratio threshold value is lower than the inter-satellite laser link by more than 10 dB.

[0015] Preferably, the step S3 comprises: calculating the position vector of the satellite in the Earth-Centered Inertial (ECI) system according to the orbit parameters exchanged in real time by the two satellites, including satellite identification ID, time t, orbit semi-major axis a, orbit eccentricity e, orbit inclination i, ascending node right ascension Omega, perigee amplitude angle omega and true anomaly angle v, and then calculating the relative direction vector of the two satellites d and the corresponding unit direction vector d’ .

[0016] 1) Calculate the position vector of the satellite in the Earth-Centered Inertial (ECI) system;

[0017] (1) Calculate the position of the satellite in the orbit plane coordinate system from the six orbital elements:

[0018]

[0019]

[0020]

[0021]

[0022] wherein r is the instantaneous distance from the satellite to the earth center; x0, y0, z0 are the coordinates of the satellite in the orbit plane coordinate system respectively;

[0023] (2) Convert the position in the orbit coordinate system to the earth-centered equatorial inertial system ECI:

[0024] The coordinate transformation is realized by three rotations:

[0025]

[0026] wherein, x, y, z are the coordinates of the satellite in the earth-centered equatorial inertial system ECI respectively;

[0027] The rotation matrixes are respectively:

[0028] Rotating -Ω degrees around the Z axis:

[0029]

[0030] Rotating -i degrees around the X axis:

[0031]

[0032] Rotating -ω degrees around the Z axis:

[0033]

[0034] 2) Calculate the relative direction vector of the two satellites;

[0035] Let the position vector of the satellite in the earth-centered equatorial inertial system ECI be r 1, the position vector of the other satellite in the earth-centered equatorial inertial system ECI is r 2;

[0036] The relative direction vector d is:

[0037] .

[0038] The unit direction vector for laser pointing preset d’ is:

[0039] .

[0040] Preferably, the step S5 comprises: triggering the laser communication optical head to scan in any one mode including a matrix spiral scanning mode, a spiral scanning mode, a random scanning mode, a concentric circle scanning mode based on the laser communication optical head pointing angle.

[0041] Preferably, the method further comprises: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link;

[0042] The transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link comprises:

[0043] The control data satisfying the preset requirements is transmitted by the inter-satellite microwave link; the control data and service data are transmitted by the inter-satellite laser link.

[0044] The control data satisfying the preset requirements transmitted by the inter-satellite microwave link comprises: small data amount of orbit parameters, link state, task information data satisfying the preset requirements.

[0045] According to the application, a microwave laser collaborative inter-satellite link rapid establishment system is provided, comprising:

[0046] An inter-satellite microwave link construction module: an inter-satellite microwave link is established through a microwave communication link;

[0047] An orbit parameter exchange module: orbit parameters are exchanged in real time by two satellites through an inter-satellite microwave link; wherein the orbit parameters comprise: satellite identification, time, orbit semi-major axis, orbit eccentricity, orbit inclination, ascending node right ascension, perigee amplitude angle and true anomaly angle;

[0048] A direction vector acquisition module: a relative direction vector of two satellites is recursively calculated according to the real-time exchanged orbit parameters;

[0049] An optical head pointing angle presetting module: a laser communication optical head pointing angle is preset based on the relative direction vector;

[0050] An inter-satellite laser link construction module: a laser communication optical head is triggered to scan based on the laser communication optical head pointing angle, and at the same time, orbit data is continuously updated through an inter-satellite microwave link and the laser communication optical head pointing angle is dynamically corrected, so as to establish an inter-satellite laser link.

[0051] Preferably, the inter-satellite microwave link adopts X-band, Ka-band, Q-band, V-band or W-band for communication.

[0052] At the same time, the inter-satellite microwave link chain establishment signal-to-noise ratio threshold value is lower than that of the inter-satellite laser link by more than 10 dB.

[0053] Preferably, the direction vector acquisition module comprises: according to the orbit parameters exchanged in real time by two satellites, including satellite identification ID, time t, orbit semi-major axis a, orbit eccentricity e, orbit inclination i, ascending node right ascension Ω, perigee amplitude angle ω and true anomaly angle υ, the position vector of the satellite in the Earth-Centered Inertial System is calculated, and then the relative direction vector of the two satellites is calculated. d and the corresponding unit direction vector d’;

[0054] 1) Calculate the position vector of the satellite in the Earth-Centered Earth-Fixed Inertial Frame (ECI) ;

[0055] (1) Calculate the position of the satellite in the orbital plane coordinate system from the orbital elements:

[0056]

[0057]

[0058]

[0059]

[0060] where r is the instantaneous distance from the satellite to the Earth's center; x0, y0, z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively;

[0061] (2) Convert the position in the orbital coordinate system to the Earth-Centered Earth-Fixed Inertial Frame (ECI) :

[0062] The coordinate transformation is achieved by three rotations:

[0063]

[0064] where, x, y, z are the coordinates of the satellite in the Earth-Centered Earth-Fixed Inertial Frame (ECI), respectively; represents the rotation matrix around the Z-axis by -Ω degrees; represents the rotation matrix around the X-axis by -i degrees; represents the rotation matrix around the Z-axis by -ω degrees;

[0065] The rotation matrices are respectively:

[0066] Rotation around the Z-axis by -Ω degrees:

[0067]

[0068] Rotation around the X-axis by -i degrees:

[0069]

[0070] Rotation around the Z-axis by -ω degrees:

[0071]

[0072] 2) Calculate the relative direction vector of the two satellites;

[0073] Let the position vector of the satellite in the Earth-Centered Earth-Fixed Inertial Frame (ECI) be r 1, the position vector of the other satellite in the Earth-Centered Earth-Fixed Inertial Frame (ECI) is r2;

[0074] Relative direction vector d is:

[0075] .

[0076] Unit direction vector for laser pointing preset d’ is:

[0077] .

[0078] Preferably, the inter-satellite laser link construction module comprises: triggering a laser communication optical head to scan in any one of a matrix spiral scanning mode, a spiral scanning mode, a random scanning mode, a concentric circle scanning mode based on a laser communication optical head pointing angle.

[0079] Preferably, the system further comprises: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link;

[0080] The control data and service data transmitted based on the constructed inter-satellite laser link and inter-satellite microwave link comprise:

[0081] The control data satisfying the preset requirements is transmitted by the inter-satellite microwave link; the control data and service data are transmitted by the inter-satellite laser link;

[0082] The control data satisfying the preset requirements transmitted by the inter-satellite microwave link comprises: small data amount of orbit parameters, link state, task information data satisfying the preset requirements.

[0083] Compared with the prior art, the present application has the following beneficial effects:

[0084] 1. The present application directly obtains a micro-radian level preset pointing through the microwave link to quickly complete orbit parameter exchange and real-time extrapolation, reduces the scanning uncertainty region, improves the first acquisition success rate, and shortens the chain building time;

[0085] 2. The laser reduces the scanning step number, cooperates with the matrix spiral, random and other programmable scanning modes, reduces the scanning power consumption, and is particularly suitable for the micro-nano satellite power limited scene;

[0086] 3. The real-time orbit is continuously injected through the microwave link, the orbit extrapolation error, attitude jitter and thermal deformation are dynamically compensated, the residual error of the laser link pointing is reduced, and the pointing accuracy is continuously improved;

[0087] 4. After the chain is built, the microwave transmits small data amount control data, and the laser carries large data amount service data in parallel, realizes the cooperative working mode of double link service-control parallel transmission, and lays a technical foundation for large-scale constellation real-time routing and on-orbit cooperation;

[0088] 5、The application combines the rapidity of microwave link and the high bandwidth advantage of laser communication, solves the problem of accurate pointing of laser through dynamic mutual transmission of orbit data, realizes the rapid establishment of inter-satellite laser link, and helps the efficient networking of large-scale constellation. BRIEF DESCRIPTION OF DRAWINGS

[0089] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, when read in conjunction with the accompanying drawings:

[0090] Figure 1 Figure 1 is a schematic diagram of a microwave-laser hybrid communication system according to an embodiment of the application.

[0091] Figure 2 Figure 2 is a flowchart of the process of microwave-laser collaborative inter-satellite link rapid establishment according to an embodiment of the application. DETAILED DESCRIPTION

[0092] The application will be described in more detail with reference to specific embodiments. The following embodiments are helpful for those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the application. These all belong to the protection scope of the application.

[0093] Embodiment 1

[0094] According to the microwave-laser collaborative inter-satellite link rapid establishment method provided by the application, as shown in Figure 2, the method comprises the following steps: Figure 2

[0095] Step S1: Establish an initial inter-satellite microwave link through a microwave communication link;

[0096] Step S2: Real-time exchange of orbit parameters between the two satellites through the inter-satellite microwave link;

[0097] Step S3: Real-time recursion of the relative direction vector from the home satellite to the opposite satellite according to the orbits of the home satellite and the opposite satellite;

[0098] Step S4: High-precision pointing based on the relative direction vector to preset the pointing angle of the laser communication optical head;

[0099] Step S5: Start the scanning of the laser communication optical head, and at the same time, continuously update the orbit data through the microwave link and dynamically correct the pointing to establish the inter-satellite laser link;

[0100] Step S6: Switch to the dual-link collaborative working mode, and the microwave transmits control data, and the laser transmits both service data and control data.

[0101] ​Specifically, the microwave link includes but is not limited to X-band, Ka-band, Q-band, V-band, W-band, and the threshold SNR of the microwave link is lower than that of the laser link by more than 10 dB.

[0102] Specifically, the orbit parameters exchanged in real time in step S2 include satellite identification, time, orbit semi-major axis, orbit eccentricity, orbit inclination, ascending node right ascension, perigee argument, and true anomaly.

[0103] Specifically, in step S3, according to the orbit parameters exchanged in real time by the two satellites, including satellite identification ID, time t, orbit semi-major axis a, orbit eccentricity e, orbit inclination i, ascending node right ascension Ω, perigee argument ω, and true anomaly υ, the position vector of the satellite in the Earth-Centered Inertial (ECI) system is calculated, and then the relative direction vector of the two satellites is calculated d and the corresponding unit direction vector d’ ;

[0104] 1) Calculate the position vector of the satellite in the Earth-Centered Inertial (ECI) system;

[0105] (1) Calculate the position of the satellite in the orbit plane coordinate system from the six orbital elements:

[0106]

[0107]

[0108]

[0109]

[0110] where r is the instantaneous distance of the satellite to the Earth center; x0, y0, and z0 are the coordinates of the satellite in the orbit plane coordinate system, respectively;

[0111] (2) Convert the position in the orbit coordinate system to the Earth-Centered Inertial (ECI) system:

[0112] The coordinate transformation is realized by three rotations:

[0113]

[0114] where x, y, and z are the coordinates of the satellite in the Earth-Centered Inertial (ECI) system, respectively; x, y,

[0115] The rotation matrices are respectively:

[0116] Rotate -Ω degrees around the Z-axis:

[0117]

[0118] Rotate -i degrees around the X-axis: ​

[0119]

[0120] Rotate around Z axis -ω degrees:

[0121]

[0122] 2) Calculate the relative direction vector of the two satellites;

[0123] Let the position vector of the satellite in the ECI be r 1, the position vector of the other satellite in the ECI be r 2;

[0124] The relative direction vector d is:

[0125] .

[0126] The unit direction vector for laser pointing preset is d’ :

[0127] .

[0128] Specifically, the laser scanning range in step S5 is compressed to the ±0.05° uncertainty region of the coarse alignment direction.

[0129] Specifically, the mode of the laser scanning range in step S5 can adopt a matrix spiral scanning mode, a spiral scanning mode, a random scanning mode, or a concentric circle scanning mode.

[0130] Specifically, in the double-link cooperative mode in step S6, the control data transmitted by the microwave link is small data amount of orbit parameters, link states, task information and the like, and the laser terminal transmits large data amount of service data in addition to the same control data, including payload data.

[0131] The application also provides a microwave-laser cooperative inter-satellite link rapid establishment system, which can be realized by executing the process steps of the microwave-laser cooperative inter-satellite link rapid establishment method, i.e., the microwave-laser cooperative inter-satellite link rapid establishment method can be understood by those skilled in the art as a preferred embodiment of the microwave-laser cooperative inter-satellite link rapid establishment system.

[0132] Embodiment 2

[0133] Embodiment 2 is a preferred example of embodiment 1

[0134] As shown in Figure 1 , the first satellite and the second satellite establish an inter-satellite microwave link and an inter-satellite laser link, and the main modules contained are as follows:

[0135] 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.

[0136] 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.

[0137] 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.

[0138] 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.

[0139] 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.

[0140] 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.

[0141] Step S4: the first integrated processing module 101 of the first satellite transmits the first relative direction vector A1 from the first satellite to the second satellite to the first laser communication control module 107, and the first laser communication control module 107 presets the pointing angle of the first laser communication optical head module 106 based on the first relative direction vector A1 to complete the coarse alignment; the second integrated processing module 201 of the second satellite transmits the second relative direction vector A2 from the second satellite to the first satellite to the second laser communication control module 207, and the second laser communication control module 207 presets the pointing angle of the second laser communication optical head module 206 based on the second relative direction vector A2 to complete the coarse alignment.

[0142] Step S5: the first satellite starts scanning the first laser communication optical head module 106, and continuously updates the orbit data through the microwave link and dynamically corrects the pointing; the second satellite starts scanning the second laser communication optical head module 206, and continuously updates the orbit data through the microwave link and dynamically corrects the pointing, to establish the inter-satellite laser link.

[0143] Step S6: the first satellite and the second satellite are switched to the dual-link cooperative working mode, the microwave transmits the control data, and the laser transmits the service data and the control data at the same time.

[0144] Those skilled in the art know that, in addition to implementing the system, device and each module thereof provided by the present application in the form of pure computer readable program code, the same program can also be realized by logically programming the method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers and embedded microcontrollers. Therefore, the system, device and each module thereof provided by the present application can be considered as a hardware component, and the modules included therein for realizing various programs can also be considered as structures in the hardware component; the modules for realizing various functions can also be considered as both software programs for realizing methods and structures in the hardware component.

[0145] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other in any way without conflict.

Claims

1. A microwave laser cooperative inter-satellite link fast establishment method, characterized in that, Comprising: Step S1: establishing inter-satellite microwave link through microwave communication link; Step S2: real-time exchanging orbit parameters through inter-satellite microwave link by both satellites; wherein, the orbit parameters include: satellite identification, time, orbit semi-major axis, orbit eccentricity, orbit inclination, ascending node right ascension, argument of perigee and true anomaly; Step S3: real-time recursion of relative direction vector of both satellites according to real-time exchanged orbit parameters; Step S4: presetting laser communication optical head pointing angle based on relative direction vector; Step S5: triggering laser communication optical head scanning based on laser communication optical head pointing angle, while continuously updating orbit data through inter-satellite microwave link and dynamically correcting laser communication optical head pointing angle, to establish inter-satellite laser link; The step S3 comprises: according to the orbit parameters of the dual-satellite real-time exchange, including: satellite identification ID, time t, orbit semi-major axis a, orbit eccentricity e, orbit inclination i, ascending node redius Ω, perigee amplitude ω and true perigee angle υ, calculating the position vector of the satellite in the earth-centered equatorial inertial system, and then calculating the relative direction vector of the dual-satellite d and the corresponding unit direction vector d’ ; 1) calculating position vector of satellite in Earth-Centered Inertial (ECI) system; (1) calculating position of satellite in orbit plane coordinate system from six elements of orbit: Wherein, r is instantaneous distance of satellite to the center of the earth; x0, y0, z0 are respectively coordinates of satellite in orbit plane coordinate system; (2) converting position in orbit coordinate system to Earth-Centered Inertial (ECI) system: Coordinate transformation is realized by three rotations: wherein x, y, z are respectively coordinates of the satellite in the geocentric equatorial inertial system; denotes the rotation matrix that rotates -Ω degrees around the Z-axis; denotes the rotation matrix that rotates -i degrees around the X-axis; denotes the rotation matrix that rotates -ω degrees around the Z-axis; Rotation matrixes are respectively: Rotating -Ω degrees around Z axis: Rotating -i degrees around X axis: Rotating -ω degrees around Z axis: 2) calculating relative direction vector of both satellites; Let the position vector of the other star in the Earth-centered equatorial inertial system ECI be r 1, and the position vector of the other star in the Earth-centered equatorial inertial system ECI be r 2; Relative direction vector d is: ； Unit direction vector for laser pointing preset d’ is: ； The method further comprises: transmitting control data and service data based on constructed inter-satellite laser link and inter-satellite microwave link; The transmitting control data and service data based on constructed inter-satellite laser link and inter-satellite microwave link comprises: Transmitting control data meeting preset requirements by inter-satellite microwave link; transmitting control data and service data by inter-satellite laser link; The transmitting control data meeting preset requirements by inter-satellite microwave link comprises: small data amount of orbit parameters, link state, task information data meeting preset requirements.

2. The method of claim 1, wherein, The inter-satellite microwave link uses X band, Ka band, Q band, V band or W band for communication; Meanwhile, the inter-satellite microwave link has a chain building signal-to-noise ratio threshold value lower than inter-satellite laser link by more than 10 dB.

3. The method of claim 1, wherein, The step S5 comprises: triggering laser communication optical head to scan in any one mode of matrix spiral scanning mode, spiral scanning mode, random scanning mode, concentric circle scanning mode based on laser communication optical head pointing angle.

4. A microwave laser cooperative inter-satellite link quick establishment system, characterized in that, Comprising: Inter-satellite microwave link construction module: establishing inter-satellite microwave link through microwave communication link; Orbit parameter exchange module: real-time exchanging orbit parameters through inter-satellite microwave link by both satellites; wherein, the orbit parameters include: satellite identification, time, orbit semi-major axis, orbit eccentricity, orbit inclination, ascending node right ascension, argument of perigee and true anomaly; Direction vector acquisition module: real-time recursion of relative direction vector of both satellites according to real-time exchanged orbit parameters; Optical head pointing angle presetting module: presetting laser communication optical head pointing angle based on relative direction vector; Inter-satellite laser link construction module: triggering laser communication optical head scanning based on laser communication optical head pointing angle, while continuously updating orbit data through inter-satellite microwave link and dynamically correcting laser communication optical head pointing angle, to establish inter-satellite laser link; The direction vector obtaining module comprises: according to the orbit parameters exchanged in real time by the double satellites, including: satellite identification ID, time t, orbit semi-major axis a, orbit eccentricity e, orbit inclination i, ascending node redius Omega, perigee amplitude omega and true perigee angle u, the position vector of the satellite in the earth-centered equatorial inertial system is calculated, and then the relative direction vector of the double satellites is calculated d and the corresponding unit direction vector d’ ​ 1) Calculate the position vector of the satellite in the Earth-Centered Earth-Fixed Inertial (ECI) system; (1) Calculate the position of the satellite in the orbital plane coordinate system from the six orbital elements: Where r is the instantaneous distance of the satellite to the Earth center; x0, y0, z0 are the coordinates of the satellite in the orbital plane coordinate system, respectively; (2) Convert the position in the orbital coordinate system to the Earth-Centered Earth-Fixed Inertial (ECI) system: The coordinate transformation is realized by three rotations: wherein x, y, z are the coordinates of the satellite in the geocentric equatorial inertial system; Rz(-ω) denotes the rotation matrix that rotates about the Z axis by -ω degrees; Rx(i) denotes the rotation matrix that rotates about the X axis by -i degrees; Rz(-ω) denotes the rotation matrix that rotates about the Z axis by -ω degrees; The rotation matrixes are respectively: Rotate around the Z axis by -Ω degrees: Rotate around the X axis by -i degrees: Rotate around the Z axis by -ω degrees: 2) Calculate the relative direction vector of the two satellites; Let the position vector of the target star in the Earth-centered equatorial inertial system ECI be r 1, the position vector of the target star in the Earth-centered equatorial inertial system ECI is r 2; Relative direction vector d is: ； Unit direction vector for laser pointing preset d’ is: ； The system further comprises: transmitting control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link; The transmission of control data and service data based on the constructed inter-satellite laser link and inter-satellite microwave link comprises: Transmitting control data meeting the preset requirements using the inter-satellite microwave link; transmitting control data and service data using the inter-satellite laser link; The transmission of control data meeting the preset requirements using the inter-satellite microwave link comprises: small data amount of orbital parameters, link state, task information data meeting the preset requirements.

5. The microwave laser-cooperative inter-satellite link quick establishment system according to claim 4, characterized in that, The inter-satellite microwave link uses X-band, Ka-band, Q-band, V-band or W-band for communication; At the same time, the signal-to-noise ratio threshold value of the inter-satellite microwave link is lower than that of the inter-satellite laser link by more than 10 dB.

6. The microwave laser-cooperative inter-satellite link quick establishment system according to claim 4, characterized in that, The inter-satellite laser link construction module comprises: triggering the laser communication optical head based on the pointing angle of the laser communication optical head to scan in any one of the following modes: matrix spiral scanning mode, spiral scanning mode, random scanning mode, and concentric circle scanning mode.

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