Inter-satellite laser fast link establishment and transmission method based on microwave network guidance

Abstract

The application provides an inter-satellite laser fast link establishment and transmission method based on microwave network guidance, a source satellite sends a laser link establishment application frame to a destination satellite, carries satellite information, a path satellite node carries node information when forwarding, the destination satellite replies after receiving the application, realizes network layer connection establishment, and a laser terminal directly locks a target direction, thereby shortening link establishment time; the source satellite multicasts a link establishment instruction to path satellites and the destination satellite, each satellite performs link establishment operation, the path satellites and the destination satellite respectively reply a link establishment success / failure reply packet to the source satellite node after laser link establishment success / failure; after all link establishments are successful, laser link data transmission is started, and the laser link connection is released after a transmission task is completed. The application is based on a laser link super-long-distance transmission and service self-adaptive method of an end-to-end routing mechanism constructed by a microwave network, breaks through the distance limitation of a traditional microwave link, and realizes super-long-distance communication across an orbit plane and across constellation levels.

Description

Technical Field

[0001] This invention relates to the field of communication technology, specifically to a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. Background Technology

[0002] With the development of aerospace technology, inter-satellite communication has become an indispensable and important technology. Existing inter-satellite communication systems mainly rely on inter-satellite microwave links and inter-satellite laser links.

[0003] Inter-satellite microwave link systems use electromagnetic waves to transmit data in the microwave band. The technology is mature and stable, the link establishment is highly stable, the coverage is wide, and the energy consumption is low. However, the bandwidth is relatively limited, making it difficult to meet the transmission requirements of high-capacity payload services.

[0004] Inter-satellite laser link systems utilize laser beams as carriers for data transmission. Laser beams possess extremely high directionality and coherence, enabling high-speed, high-precision data transmission, and hold promise for very high data transmission rates in the future. However, their energy consumption is significant. To achieve long-distance transmission and sufficient receiving power, laser systems require high-power lasers; some systems also employ fiber optic amplifiers to enhance the signal, directly increasing system energy consumption. Furthermore, high-power lasers and optical components generate heat during operation, requiring energy for the cooling system itself. For onboard products that are not grounded, energy scarcity and heat dissipation challenges are two crucial issues. Since much data traffic is intermittent, inter-satellite laser links do not need to be continuously operational; they only need to be activated as needed when transmission is required.

[0005] The establishment of inter-satellite laser links is extremely complex. Laser link establishment relies on high-precision optical alignment, with an accuracy down to the microradian level. During the initial acquisition phase of link establishment, due to the narrow width of the laser beam, the two satellites need to locate each other and acquire each other's laser signals within a certain time and space window. If initial pointing information is lacking, the satellites need to search for the target through wide-angle scanning, similar to "blind scanning." This process can take several minutes to tens of minutes, severely impacting the time and reliability of inter-satellite laser link establishment.

[0006] With the current expansion of the number of satellites, ultra-long-distance communication across orbital planes and constellations presents even greater challenges.

[0007] Therefore, a method suitable for ultra-long-distance laser communication is needed. Summary of the Invention

[0008] This invention aims to solve the problem of ultra-long-distance laser communication by providing a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. Without adding new equipment, it only requires designing a multicast mechanism in the existing microwave network to carry laser link control signaling, realizing incremental design of laser link network management functions, and completing rapid laser link establishment and transmission.

[0009] This invention provides a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance, comprising the following steps:

[0010] S1. When the source satellite needs to transmit high-speed services to the destination satellite via multiple hops, the source satellite determines the optimal transmission path based on the inter-satellite communication routing protocol.

[0011] S2. The source satellite's task manager generates a laser link establishment request frame carrying the source satellite node information and the destination address, and forwards it to the destination satellite via the inter-satellite microwave link along the optimal transmission path. After receiving the frame, the destination satellite generates a laser link establishment reply frame carrying its own node information and the source satellite address, and returns it to the source satellite via the inter-satellite microwave link along the reverse path. After receiving the frame, the source satellite confirms that the transmission path is valid.

[0012] When each satellite node along the transmission path forwards the laser link establishment request frame and the laser link establishment reply frame, it dynamically fills in its own satellite node information. The source satellite node information, destination satellite node information, and local satellite node information all include time synchronization information, satellite position information, and attitude information. The time synchronization information is a timestamp, the satellite position information is an orbital satellite vector, and the attitude information is an attitude quaternion.

[0013] S3, the source satellite, the path satellite and the target satellite all use the timestamps of adjacent nodes and the orbital position vectors in the laser link establishment request frame and the laser link establishment response frame to obtain the relative velocity between the satellites. The target azimuth and elevation angles are obtained according to the attitude quaternions. The azimuth and elevation angles are then corrected by combining the relative velocity between the satellites, and the aiming angles of the laser transmitter and the laser receiver are adjusted.

[0014] S4. The source satellite's task manager, based on the confirmed transmission path, multicasts a laser link establishment command to the inter-satellite laser communication terminals of all satellites along the path via the inter-satellite microwave link. Upon receiving the command, each satellite's laser communication terminal synchronously opens the corresponding port's laser communication terminal and initiates the bidirectional acquisition, tracking, and establishment process of the laser link.

[0015] When the laser link is successfully established, the target satellite sends a link establishment success reply frame to the source satellite. The source satellite confirms that all laser links along the entire path have been successfully established and waits for the service transmission time.

[0016] When link establishment fails, the failed satellite node returns a link establishment failure reply frame containing an error code via the microwave link; the error code includes: the reason for failure and the location of failure; the source satellite or management node sends a re-establishment command to the failed node based on the link establishment failure reply frame, and dynamically adjusts the laser's pointing or emission power based on the error reason until the link establishment is successful;

[0017] S5. The source satellite transmits service data to the destination satellite through the established laser link;

[0018] S6. After the laser link service transmission task is completed, the source satellite's task manager sends a laser link release command to the inter-satellite laser communication terminals of all satellites in the path via inter-satellite microwave link. After receiving the release command, each satellite's laser communication terminal independently shuts down the laser communication terminal activated on the corresponding port of its own satellite, releasing communication resources. A method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance is thus completed.

[0019] The present invention discloses a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. In a preferred embodiment, in step S2, the laser link establishment application frame includes: packet type, source node SCID, destination node SCID, packet length, source node time synchronization information, satellite position information and attitude information, and path satellite node time synchronization information, satellite position information and attitude information.

[0020] The present invention discloses a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. In a preferred embodiment, in step S2, the laser link establishment response frame includes: packet type, source node SCID, destination node SCID, packet length, source node time synchronization information, satellite position information and attitude information, and path satellite node time synchronization information, satellite position information and attitude information.

[0021] In the preferred embodiment of the microwave network-guided inter-satellite laser rapid link establishment and transmission method described in this invention, in step S2, when the source satellite does not receive a laser link establishment response frame, it resends a laser link establishment request frame.

[0022] Source satellite node information, destination satellite node information, and local satellite node information are all used to enable the laser terminal to directly lock onto the target direction and shorten the link establishment time.

[0023] In the preferred embodiment of the microwave network-guided rapid inter-satellite laser link establishment and transmission method described in this invention, in step S3, the relative velocity between satellites is the ratio of the difference in orbital position vectors of adjacent satellites to the difference in timestamps of adjacent satellites.

[0024] The target azimuth angle φ and elevation angle θ are obtained by calculating the aiming angle in the body coordinate system through quaternion attitude transformation.

[0025] The azimuth angle φ is corrected by the calibration coefficient k, the transmission delay τ, and the y-axis component of the relative velocity between satellites.

[0026] The pitch angle θ is corrected using the calibration coefficient k, the transmission delay τ, and the z-axis component of the relative velocity between satellites.

[0027] The present invention provides a preferred method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance.

[0028]

[0029] in:

[0030]

[0031] Let t be the orbital position vectors of adjacent satellites 2 and 1 in the geocentric inertial frame. 卫星2 t 卫星1 These are the timestamps for the information transmitted by Satellite 2 and Satellite 1, respectively. The relative positions of adjacent satellites are given, and Δt is the time difference.

[0032] The quaternion attitude transformation method involves calculating the aiming angle in the body coordinate system.

[0033]

[0034] Where q is the attitude quaternion, q * For attitude quaternion conjugate, The target vector in the body coordinate system;

[0035] The azimuth angle φ and the elevation angle θ are:

[0036]

[0037]

[0038] Where, x b y b z b for x-axis, y-axis, and z-axis components:

[0039] Beam propagation delay is offset by velocity offset correction:

[0040] φ final =φ+k·v rel,y ·τ

[0041] θ final =θ+k·v rel,z ·τ

[0042] Where k is the calibration coefficient, τ = d / c is the transmission delay, d is the transmission distance, c is the speed of light, and v rel,y v rel,y They are respectively Velocity components on the y-axis and z-axis.

[0043] The present invention provides a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. In a preferred embodiment, in step S4, both the successful link establishment response frame and the failed link establishment response frame include: packet type, source node SCID, destination node SCID, packet length, link establishment status flag, laser parameters, and error code.

[0044] The error code in the successful link establishment reply frame is 0, and the laser parameters include: laser wavelength, laser power, bit error rate, and acquisition time; the laser parameters in the failed link establishment reply frame are 0.

[0045] In the preferred embodiment of the microwave network-guided rapid inter-satellite laser link establishment and transmission method described in this invention, in step S6, after the satellite releases communication resources, it sends a release success reply frame to the source satellite.

[0046] This invention relates to a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance. It controls the establishment and release of inter-satellite laser links by sending commands through the inter-satellite microwave links, achieving high-bandwidth inter-satellite communication with low resource consumption. A stable inter-satellite microwave link network enables unified control and path planning of the inter-satellite laser links. The inter-satellite microwave links provide a unified control plane, while the inter-satellite laser links provide a high-speed service plane, forming a hybrid network architecture. This solves the problems of complex laser link establishment and high resource consumption in existing technologies. This solution significantly reduces equipment load, improves on-board resource utilization, and is suitable for scenarios with large-capacity data transmission tasks in satellite constellations.

[0047] This invention addresses the challenges of limited microwave link bandwidth in satellite systems with simple network topologies and occasional large-volume service data transmission needs, which makes it difficult to meet the transmission requirements of high-capacity payload services. Furthermore, it addresses the issue of high energy consumption and unsuitability for long-term operation of laser communication equipment. The invention provides a microwave network-guided method for rapid inter-satellite laser link establishment and transmission. Without adding new equipment, it only requires designing a multicast mechanism within the existing microwave network to carry laser link control signaling, enabling incremental design of laser link network management functions and achieving rapid laser link establishment and transmission.

[0048] The technical solution of this invention addresses satellite systems with simple network topologies and occasional high-volume data transmission needs. It employs a dual-link design of microwave and laser inter-satellite connections. The microwave link maintains long-term stable connection establishment, transmitting essential network operation information such as configuration, status, and small amounts of slice information, achieving a unified control plane. The laser link, categorized as a service plane link, is powered off and released when not in use. When the system detects a large volume of data transmission, it sends a command via the microwave link to activate the high-bandwidth laser link. This command carries the initial pointing for laser alignment, including time synchronization information, satellite orbit parameters, and attitude quaternions, determining the position and pointing to assist in laser link establishment. After laser link establishment, the high-volume data transmission is completed via the laser link, realizing the service plane function. After the high-volume data transmission is complete, a command is sent via the microwave link to shut down the laser link, reducing resource consumption and increasing its lifespan. The microwave link enables unified network control and management of the laser link.

[0049] With the guidance of an inter-satellite microwave link, precise satellite position and attitude information can be transmitted in advance through the inter-satellite microwave network, enabling the laser terminal to directly lock onto the target direction, reducing the link establishment time to the second level.

[0050] For some satellite systems, the inter-satellite network topology is simple, and the inter-satellite data interface is stable. Most of the time, only a small amount of configuration information, status information, and slice information need to be transmitted to maintain network operation. Occasionally, there will be a large demand for business data transmission. The inter-satellite laser link can be activated as needed according to business requirements and deactivated after transmission is completed to reduce resource consumption and increase the lifespan of the inter-satellite laser link.

[0051] The specific steps are as follows:

[0052] (1) Microwave Link-Based Transmission Connection Request. The source satellite sends a transmission connection request frame to the destination satellite, carrying its own satellite information. Path satellite nodes also carry their own node information when forwarding the transmission connection request packet. Upon receiving the request, the destination satellite replies, establishing a connection at the network layer. Both the destination satellite's reply and the path satellite nodes' forwarding of the reply packet must carry their own node information. This node information includes time synchronization information, satellite position, and attitude information, enabling the laser terminal to directly lock onto the target direction and shorten the link establishment time. The source satellite confirms the transmission path based on the reply frame. If the source satellite does not receive a reply, it needs to resend the transmission connection request frame to ensure the reliability of the transmission connection request.

[0053] (2) Control the laser link establishment operation according to the detected path. The source satellite multicasts a link establishment command to the path satellites and the destination satellite. Upon receiving the link establishment command, the path satellites and the destination satellites perform the link establishment operation. After each satellite successfully or unsuccessfully establishes a laser link, it sends a link establishment success / failure reply packet (link establishment status reply packet) back to the source satellite node. If the link establishment is successful, the destination satellite needs to send back the link establishment status, laser transmission parameters (laser wavelength, laser power, number of errors, etc.), and acquisition time. If the link establishment fails, an error code needs to be sent back to notify the source satellite of the reason for the failure. The source satellite confirms whether all path satellites and the destination satellites have successfully established links.

[0054] (3) Once the source satellite confirms that all path satellites and the destination satellite have successfully established links, laser link data transmission is initiated. The source satellite generates service data and transmits it to the destination satellite through the established laser link.

[0055] (4) Upon completion of the transmission mission, the laser link connection is released. The source satellite multicasts a release command to the path satellites and the destination satellite. Upon receiving the release command, the path satellites and the destination satellite execute the release operation and shut down their current laser communication terminals. After successfully releasing, the path satellites and the destination satellite send a release success reply packet to the source satellite. The source satellite confirms that all path satellites and the destination satellite have successfully released. If the source satellite does not receive a reply packet, it needs to resend the release command to ensure the reliability of the release operation.

[0056] The present invention has the following advantages:

[0057] (1) Unified control plane design reduces network control complexity. The control plane is based on continuously running routes and uses microwave links for control signaling interaction to control laser link service transmission. Under the unified control plane, integrated control of both microwave and laser link service channels is achieved, reducing network control complexity.

[0058] (2) Laser link establishment on demand guided by microwave network saves on-board energy consumption. Reliable interaction of key signaling such as laser link establishment application and release is carried out by using microwave network. Based on microwave network guidance, a routing mechanism based on end-to-end connection is established for laser link, realizing the design goal of automatic control and adaptive transmission of laser link. It can be opened and closed on demand according to the needs of upper layer services, which greatly saves on-board energy consumption.

[0059] (3) A laser link ultra-long-distance transmission and service adaptation method based on an end-to-end routing mechanism constructed using microwave networks breaks through the distance limitations of traditional microwave links, realizing ultra-long-distance communication across orbital planes and constellation levels. Laser service paths are dynamically adjusted through microwave control signaling, supporting three adaptive transmission modes: cross-orbital plane transmission, multi-hop relay transmission, and dynamic service switching. This mechanism enables laser communication between non-coplanar orbits, extending coverage globally. Simultaneously, it ensures continuous and reliable data transmission, effectively improving the robustness and service continuity of the space laser communication network. Attached Figure Description

[0060] Figure 1 A flowchart of a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance;

[0061] Figure 2 This is a flowchart illustrating the execution of a microwave network-guided rapid inter-satellite laser link establishment and transmission method.

[0062] Figure 3 A schematic diagram of the frame format of the laser link establishment request frame and the laser link establishment response frame in a microwave network-guided inter-satellite laser rapid link establishment and transmission method.

[0063] Figure 4 This is a schematic diagram of the frame format of a microwave network-guided inter-satellite laser fast link establishment and transmission method, showing the successful link establishment response frame and the failed link establishment response frame.

[0064] Figure 5 This paper proposes a method for rapid inter-satellite laser link establishment and transmission guided by microwave networks, which obtains the optimal laser path map based on microwave network topology. Detailed Implementation

[0065] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0066] Example 1

[0067] like Figures 1-5 As shown, a method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance includes the following steps:

[0068] S1. The source satellite (Satellite 1) needs to transmit a large amount of service data (e.g., 50GB of remote sensing data) to the destination satellite (Satellite 4). Based on the inter-satellite communication routing protocol (e.g., based on the shortest distance principle), the optimal transmission path is determined to be Satellite 1 → Satellite 2 → Satellite 3 → Satellite 4. This request frame is forwarded to Satellite 4 via Satellite 2 and Satellite 3.

[0069] S2. Satellite 1's task manager generates a laser link establishment request frame destined for Satellite 4 and sends it via the inter-satellite microwave link. Upon receiving the request frame, Satellite 4 generates a laser link establishment reply frame and returns via the inter-satellite microwave link along the reverse path (Satellite 4 → Satellite 3 → Satellite 2 → Satellite 1). During the forwarding process, each intermediate node (Satellite 3, Satellite 2) dynamically fills in its real-time status information, including satellite orbit parameters, attitude quaternions, and high-precision time synchronization stamps, rather than pre-filling them. Satellite 1 ultimately receives the reply frame, confirming the validity of the transmission path.

[0070] S3. After receiving the reply frame, the source satellite (Satellite 1) uses the timestamps and corresponding position vectors of adjacent nodes within the frame (such as Satellite 1 and Satellite 2). Based on the timestamps and corresponding position vectors of adjacent nodes within the frame (such as Satellite 1 and Satellite 2), the relative velocity between the satellites is calculated using the following formula:

[0071]

[0072] in

[0073]

[0074] Δt=t 卫星2 -t 卫星1

[0075] In the formula, These are the orbital position vectors of Satellite 2 and Satellite 1 in the geocentric inertial frame, respectively, t 卫星2 t 卫星1 These are the timestamps for the information transmitted by Satellite 2 and Satellite 1, respectively. The relative positions of the two locations are given, and Δt is the time difference (the wave propagation time has an impact of <0.33% on the accuracy of the relative velocity, so the propagation delay is ignored in the calculation).

[0076] Combining the orbital position differences between adjacent satellites along the path, the calculated relative velocities, and attitude quaternion information, the aiming angle in the body coordinate system is calculated using the quaternion attitude transformation formula.

[0077]

[0078] Where q is the attitude quaternion, q * For attitude quaternion conjugate, This is the target vector in the body coordinate system. The corresponding azimuth angle φ and elevation angle θ are determined by the following formula:

[0079]

[0080]

[0081] Where xb y b z b for The amount;

[0082] To compensate for beam propagation delay, a velocity offset correction is introduced, with the final angle being:

[0083] φ final =φ+k·v rel,y ·τ

[0084] θ final =θ+k·v rel,z ·τ

[0085] Where k is the calibration coefficient, and τ = d / c is the transmission delay, where d is the transmission distance, c is the speed of light, and v rel,y v rel,y They are respectively Velocity components on the y-axis and z-axis.

[0086] This calculation significantly reduces the initial scanning range of the laser beam to within ±0.5°. Simultaneously, intermediate satellites in the path (Satellite 2 and Satellite 3) can also calculate the relative positions of the receiving and transmitting satellites in parallel using the same method, based on the content of the response frames they receive pointing to the next-hop satellites (such as Satellite 3 and Satellite 4), and adjust the aiming angles of the laser receiver and transmitter.

[0087] Based on the confirmed path, the task manager of S4 and Satellite 1 multicasts a laser link establishment command to the inter-satellite laser communication terminals of all satellites (Satellite 1 to Satellite 4) along the path via the inter-satellite microwave link. After receiving the command, the laser communication terminals of each satellite synchronously open the corresponding port of the laser communication terminal and start the bidirectional acquisition, tracking and establishment process of the laser link. Since step (2) has significantly reduced the scanning range, the link establishment time has been significantly shortened from about 100 seconds required by traditional blind scanning to about 15 seconds. Moreover, thanks to the multicast of the command and the parallel adjustment capability of each satellite, multiple laser links (Satellite 1-2, Satellite 2-3, Satellite 3-4) can be carried out simultaneously and the link establishment process can be completed within about 15 seconds. The reduction in scanning time also significantly reduces the energy consumption required for the link establishment process. If the link establishment is successful, the destination satellite (Satellite 4) sends a link establishment success reply frame to the source satellite (Satellite 1). Satellite 1 confirms that all laser links along the entire path (Satellite 1→Satellite 2→Satellite 3→Satellite 4) have been successfully established and waits for the service transmission time. If link establishment fails, the relevant node returns a response frame containing an error code via the microwave link. The error code includes: the reason for the failure (e.g., insufficient signal-to-noise ratio, excessive pointing deviation) and the location of the failure (identifying the satellite node that failed to establish the link). Based on this, the source satellite or management node sends a re-establishment command to the failed node and dynamically adjusts the laser's pointing or emission power according to the error reason until the link is successfully established.

[0088] S5. The source satellite (Satellite 1) transmits service data to the destination satellite (Satellite 4) via the established laser link. Since the transmission rate of the laser link (e.g., 5Gbps) is much higher than that of the inter-satellite microwave link (e.g., 100Mbps), the data transmission efficiency is greatly improved (e.g., the time required to transmit 50GB of data is reduced from about 4000 seconds with the microwave link to about 80 seconds with the laser link).

[0089] S6. After the laser link service transmission task is completed, the task manager of the source satellite (Satellite 1) sends a laser link release command via inter-satellite microwave link to the inter-satellite laser communication terminals of all satellites (Satellite 1 to Satellite 4) in the path through multicast. After receiving the release command, each satellite's laser communication terminal independently shuts down the laser communication terminal activated on the corresponding port of its own satellite, releases the relevant communication resources, and sends a release success reply frame to the source satellite.

[0090] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance, characterized in that: Includes the following steps: S1. When the source satellite needs to transmit high-speed services to the destination satellite via multiple hops, the source satellite determines the optimal transmission path based on the inter-satellite communication routing protocol. S2. The source satellite's task manager generates a laser link establishment request frame carrying the source satellite node information and the destination address, and forwards it to the destination satellite via the inter-satellite microwave link along the optimal transmission path. After receiving the frame, the destination satellite generates a laser link establishment reply frame carrying its own node information and the source satellite address, and returns it to the source satellite via the inter-satellite microwave link along the reverse path. After receiving the frame, the source satellite confirms that the transmission path is valid. The laser link establishment request frame includes: packet type, source node SCID, destination node SCID, packet length, source node time synchronization information, satellite position information and attitude information, path satellite node time synchronization information, satellite position information and attitude information; When each path satellite node forwards the laser link establishment request frame and the laser link establishment response frame, it dynamically fills in its own satellite node information. The source satellite node information, destination satellite node information, and local satellite node information all include time synchronization information, satellite position information, and attitude information. The time synchronization information is a timestamp, the satellite position information is an orbital satellite vector, and the attitude information is an attitude quaternion. S3, the source satellite, the path satellite and the target satellite all use the timestamps of adjacent nodes and the orbital position vectors in the laser link establishment request frame and the laser link establishment response frame to obtain the relative velocity between the satellites. The target azimuth and elevation angles are obtained according to the attitude quaternions. The azimuth and elevation angles are then corrected by combining the relative velocity between the satellites, and the aiming angles of the laser transmitter and the laser receiver are adjusted. The relative velocity between satellites is the ratio of the difference in orbital position vectors between adjacent satellites to the difference in timestamps between adjacent satellites; The target azimuth angle is obtained by calculating the aiming angle in the body coordinate system through quaternion attitude transformation. Pitch angle ; Beam propagation delay is offset by velocity bias correction, using calibration coefficient k and propagation delay. Azimuth angle is calculated from the y-axis component of the relative velocity between satellites. Correction; through calibration coefficient k, transmission delay Pitch angle based on the z-axis component of the relative velocity between satellites Corrections; S4. The source satellite's task manager, based on the confirmed transmission path, multicasts a laser link establishment command to the inter-satellite laser communication terminals of all satellites along the path via the inter-satellite microwave link. Upon receiving the command, each satellite's laser communication terminal synchronously opens the corresponding port's laser communication terminal and initiates the bidirectional acquisition, tracking, and establishment process of the laser link. S5. The source satellite transmits service data to the destination satellite through the established laser link; S6. After the laser link service transmission task is completed, the source satellite's task manager sends a laser link release command to the inter-satellite laser communication terminals of all satellites in the path via inter-satellite microwave link, thus completing a method for rapid inter-satellite laser link establishment and transmission guided by microwave network.

2. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: In step S2, the laser link establishment response frame includes: packet type, source node SCID, destination node SCID, packet length, source node time synchronization information, satellite position information and attitude information, and path satellite node time synchronization information, satellite position information and attitude information.

3. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: In step S2, if the source satellite does not receive a laser link establishment response frame, it retransmits a laser link establishment request frame. Source satellite node information, destination satellite node information, and local satellite node information are all used to enable the laser terminal to directly lock onto the target direction and shorten the link establishment time.

4. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: ； in: ； ； , These are the orbital position vectors of adjacent satellites 2 and 1 in the geocentric inertial frame, respectively. , These are the timestamps for the information transmitted by Satellite 2 and Satellite 1, respectively. The relative positions of adjacent satellites. For time difference; The quaternion attitude transformation method involves calculating the aiming angle in the body coordinate system. ； Where q is the attitude quaternion. For attitude quaternion conjugate, The target vector in the body coordinate system; Azimuth and pitch angle for: ； ； in, , , for of x axis, y axis, z Axis components: Beam propagation delay is offset by velocity offset correction: ； ； Where k is the calibration coefficient. d is the transmission delay, d is the transmission distance, and c is the speed of light. , They are respectively exist y axis, z The velocity component of the shaft.

5. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: In step S4, when the laser link establishment is successful, the target satellite sends a link establishment success reply frame to the source satellite. The source satellite confirms that all laser links along the entire path have been successfully established and waits for the service transmission time. When link establishment fails, the failing satellite node returns a link establishment failure response frame containing an error code via the microwave link; the error code includes: the reason for failure and the location of failure; The source satellite or management node sends a re-establishment command to the failed node based on the link establishment failure reply frame, and dynamically adjusts the laser's pointing or emission power based on the error reason until the link establishment is successful.

6. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 5, characterized in that: In step S4, both the successful link establishment response frame and the failed link establishment response frame include: packet type, source node SCID, destination node SCID, packet length, link establishment status flag, laser parameters, and error code. The error code in the successful connection establishment reply frame is 0, and the laser parameters include: laser wavelength, laser power, bit error rate, and acquisition time; the laser parameters in the failed connection establishment reply frame are 0.

7. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: In step S6, after receiving the laser link release command, the laser communication terminal of each satellite independently shuts down the laser communication terminal activated on the corresponding port of its own satellite, thereby releasing communication resources.

8. The method for rapid inter-satellite laser link establishment and transmission based on microwave network guidance according to claim 1, characterized in that: In step S6, after releasing the communication resources, the satellite sends a release success reply frame to the source satellite.

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