Integrated laser communication terminal, laser communication method and application thereof

Abstract

The invention relates to an integrated laser communication terminal, a laser communication method and application thereof, and relates to the technical field of laser communication.The integrated laser communication terminal comprises a relay cabin section, an integrated cabin section and an optical cabin section which are in butt joint with one another to form a closed structure, and a relay system is integrated in the relay cabin section; the system comprises a transmitting unit, a receiving unit, an accurate tracking unit, a first reflecting mechanism, a second reflecting mechanism and a light splitting mechanism, wherein an optical antenna mechanism is arranged in an optical cabin section; an emission light path passes through the second reflection mechanism, the light splitting mechanism and the first reflection mechanism from the emission unit to the optical antenna mechanism; a receiving light path is transmitted from the optical antenna mechanism to the receiving unit through the first reflection mechanism and the light splitting mechanism; the precise tracking light path is from the optical antenna mechanism to the precise tracking unit through the first reflection mechanism and the light splitting mechanism. Through the modularized integrated structure, the structure is compact, the size is small, the weight is light, the function is complete, and the overall performance and the application efficiency of the terminal are effectively improved.

Description

Technical Field

[0001] The present application relates to the field of laser communication technology, and in particular to an integrated laser communication terminal, a laser communication method and applications thereof. Background Art

[0002] Microsatellites, with their advantages of short development cycles, low costs, and flexible deployment, are seeing increasing demand in communications, remote sensing, navigation, and other fields. In particular, with the large-scale deployment of low-orbit satellites worldwide, the volume of data transmitted between satellites and between satellites and the ground is growing exponentially. Traditional radio frequency-based communication methods, limited by bandwidth, interference resistance, and spectrum resources, are no longer able to meet the demands for high-speed, high-capacity, and low-latency communications. Laser communication technology, with its high communication speeds, low power consumption, excellent real-time performance, strong anti-interception and anti-interference capabilities, and lightweight design, has become a key technology for building space-based information networks.

[0003] Currently, existing laser communication terminals primarily consist of an optical head and an integrated processor. The optical head, as the core component of a laser communication terminal, comprises a coarse pointing mechanism, an optical antenna, and a relay system. The integrated processor integrates the tracking and aiming control system, the communication processing system, and the fiber amplifier. Existing satellite-borne laser communication terminal coarse pointing mechanisms can be broadly categorized into four types based on their configuration: oscillating mirror, latitude and longitude, Kuddens, and periscope. Examples of the oscillating mirror configuration include the Swiss-developed OPTEL25 laser communication terminal; latitude and longitude configurations include the Japanese LUCE terminal and the German Mynaric CONDORMk3; Kuddens configurations include the American BlueMarble BMOT terminal and the Japanese LUCE terminal; and periscope configurations include the German LCT terminal, the Swiss OPTEL-μ terminal, and the Japanese NeLS terminal.

[0004] However, the system integration of existing satellite-borne laser communication terminals is low. The optical head and processor adopt a split structure, which makes the spatial layout loose. In addition, the number of optical components is large and the structure is complex, which makes it difficult to reduce the overall weight of the terminal. The load is complex, and it is difficult to achieve miniaturization and lightweighting of the terminal, which limits its application on small platforms. In addition, existing terminals are mostly designed according to specific mission scenarios, which makes the application scenarios of the terminals single and lacks versatility, making it difficult to meet the needs of different scenarios and different tasks. At the same time, the driving load is complex and the rotational optical inertia is large, which easily leads to dynamic coupling with the satellite platform, thereby reducing the satellite attitude and positioning accuracy, and then causing a decrease in system accuracy. The non-modular design is not conducive to product optimization and iterative updates, and the product structure is complex and the material utilization rate is low, resulting in a long product production cycle. Summary of the Invention

[0005] The purpose of this application is to provide an integrated laser communication terminal, a laser communication method and its application to solve the problems existing in the above-mentioned prior art.

[0006] To achieve the above objectives, the technical solutions adopted in this application are: The present application provides an integrated laser communication terminal, comprising: The relay compartment has an optical substrate inside, on which a relay system is integrated. The relay system includes a transmitting unit, a receiving unit, a fine tracking unit, a first reflecting mechanism, a second reflecting mechanism, and a spectrometer. The transmitting unit is used to transmit light signals, the receiving unit is used to receive light signals, the fine tracking unit is used to detect the position of the incident light spot, the first reflecting mechanism is used to deflect the light beam by a first angle, the second reflecting mechanism is used to deflect the light beam by a second angle, the second angle being smaller than the first angle, and the spectrometer is used to separate the light beams. The integrated compartment is fixedly connected to the relay compartment and includes an electronic module, which is connected to the relay system to provide power, control signals and optical signal processing to the relay system; The optical compartment is connected to the optical path exit end of the relay compartment and has an optical antenna mechanism inside; The shells of the relay module, integration module and optical module are docked with each other to form a closed terminal structure; The working optical path configuration of the terminal is: Transmitting optical path: The optical signal is emitted by the transmitting unit, passes through the second reflecting mechanism, the splitting mechanism, the first reflecting mechanism in sequence, and is then transmitted by the optical antenna mechanism; Receiving optical path: The optical signal is collected by the optical antenna mechanism, passes through the first reflection mechanism and the splitting mechanism in sequence, and reaches the receiving unit; Precision tracking optical path: The optical signal is collected by the optical antenna mechanism, passes through the first reflection mechanism and the splitting mechanism in sequence, and reaches the precision tracking unit.

[0007] Furthermore, the first reflecting mechanism includes a first bracket and a first reflector. The first bracket is fixed on the optical substrate. The first reflector is movably connected to the first bracket. The first bracket is provided with a first driving member. The first driving member is connected to the first reflector. Under the control of the electronic module, the first reflector can deflect the light beam to a first angle, and the first angle is ±3 degrees.

[0008] Furthermore, the second reflecting mechanism includes a second bracket and a second reflector. The second bracket is fixed on the optical substrate. The second reflector is movably connected to the second bracket. The second bracket is provided with a second driving member. The second driving member is connected to the second reflector. Under the control of the electronic module, the second reflector can deflect the light beam to a second angle, and the second angle is ±7 microradians.

[0009] Furthermore, the splitting mechanism includes a first splitting component and a second splitting component. The first splitting component is arranged in the transmitting optical path and the receiving optical path to separate the transmitting optical path and the receiving optical path. The second splitting component is arranged in the receiving optical path and the fine tracking optical path to separate the receiving optical path and the fine tracking optical path.

[0010] Furthermore, the first beam splitter assembly includes a third bracket and a first beam splitter, the third bracket is fixed on the optical substrate, and the first beam splitter is fixed on the third bracket; The second beam splitter assembly includes a fourth bracket and a second beam splitter. The fourth bracket is fixed on the optical substrate, the second beam splitter is fixed on the fourth bracket, and the third bracket and the fourth bracket are arranged in parallel in the receiving light path.

[0011] Furthermore, the electronic module includes a power driver module, a main control module and an EDFA module. The power driver module provides power for the relay system, the main control module is used to run the control algorithm and produce communication signals, and the EDFA module is used to amplify the communication optical signal. The power driver module, the main control module and the EDFA module are stacked in layers to form an integrated compartment.

[0012] Furthermore, the optical antenna mechanism includes an antenna mounting frame, an antenna lens barrel and a solar filter. One end of the antenna mounting frame is fixed on the optical substrate, and the other end is fixed to the antenna lens barrel. The antenna lens barrel is detachably connected to an antenna lens. The optical aperture of the antenna lens is 60-80mm. The antenna lens barrel is used to expand the outgoing light beam and shrink the incident light beam. The solar filter is installed at the end of the antenna lens barrel and is arranged on the outside of the antenna lens.

[0013] Furthermore, the outer shell of the relay compartment is provided with a first electrical interface, and the outer shell of the integrated compartment is provided with a second electrical interface, and the relay system is connected to the electronic module through the first electrical interface and the second electrical interface.

[0014] The present application also provides a laser communication method based on the above-mentioned integrated laser communication terminal, comprising the following steps: S1. The electronic module controls the first reflective mechanism to scan within a first angle range to capture beacon light; S2. The beacon light enters the fine tracking unit through the fine tracking optical path. The fine tracking unit detects the position of the light spot, and the electronic module controls the first reflective mechanism to deflect the light beam for tracking, thus establishing a stable link. S3. After the communication data is generated by the electronic module, the electronic module controls the transmitting unit to transmit the light beam, which is then transmitted through the optical antenna mechanism via the transmitting optical route; S4. The received optical signal enters the receiving unit through the optical antenna mechanism and the receiving optical path. The receiving unit receives the signal and sends it to the electronic module for demodulation.

[0015] The present application also provides an application based on the above-mentioned integrated laser communication terminal, which is used in spacecraft.

[0016] The beneficial effects of the technical solution provided by this application include at least: This application adopts a modular structure to connect the relay cabin, integration cabin and optical cabin to form a closed terminal structure, which realizes the lightweight and miniaturization of the terminal, makes the spatial layout more compact, and reduces the complexity of wiring between the two by fixing the relay cabin and the integration cabin side by side. The modular structure improves the utilization rate of materials and reduces the number and cost of optical support structures. The optical cabin is independent of the relay cabin and the integration cabin, so that the terminal can replace optical antenna solutions with different light apertures according to different scenarios and different tasks to meet the application needs of multiple scenarios and multiple working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are used to provide a further understanding of the present application and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the present application and do not constitute a limitation of the present application. In the accompanying drawings: Figure 1 2 is a schematic structural diagram of the integrated laser communication terminal from a first viewing angle in an embodiment of the present invention; Figure 2 1 is a schematic diagram of the dismissal of the integrated laser communication terminal from a second viewing angle in an embodiment of the present invention; Figure 3 is a schematic structural diagram of a relay system in one embodiment of the present invention; Figure 4 is a schematic diagram of an optical path of a relay system in one embodiment of the present invention; Figure 5 Schematic diagram of the installation structure of the relay system and the optical substrate in one embodiment of the present invention; Figure 6 It is a structural schematic diagram of an optical antenna mechanism in an embodiment of the present invention.

[0018] Description of main reference numerals: 100, relay compartment; 110, optical substrate; 120, first electrical interface; 200, relay system; 210, transmitting unit; 220, receiving unit; 230, fine tracking unit; 231, third reflector; 240, first reflector; 241, first bracket; 242, first reflector; 250, second reflector; 251, second bracket; 252, second reflector; 260, spectrometer; 261, first spectrometer assembly; 2611, third bracket; 2612, first Spectrometer; 262, second spectrometer assembly; 2621, fourth bracket; 2622, second spectrometer; 300, integrated compartment; 310, power driver module; 320, main control module; 330, EDFA module; 340, second electrical interface; 400, optical compartment; 410, optical antenna mechanism; 411, antenna mounting bracket; 412, antenna lens barrel; 413, antenna lens; 414, solar filter; 510, transmitting optical path; 520, receiving optical path; 530, precision tracking optical path. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0020] Among them, the same parts are represented by the same figure marks. It should be noted that the words "front", "rear", "left", "right", "up" and "down" used in the following description refer to the directions in the drawings of the present application specification, and the words "bottom" and "top", "inside" and "outside" refer to directions toward or away from specific parts, respectively. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present application specification, the meaning of "multiple" is two or more.

[0021] Example 1 Please refer to Figures 1-6 , an integrated laser communication terminal, comprising: The relay compartment 100 has an optical substrate 110 installed therein, on which a relay system 200 is integrated. The relay system 200 includes a transmitting unit 210, a receiving unit 220, a fine tracking unit 230, a first reflecting mechanism 240, a second reflecting mechanism 250, and a spectrometer 260. The transmitting unit 210 is used to transmit optical signals, the receiving unit 220 is used to receive optical signals, the fine tracking unit 230 is used to detect the position of the incident light spot, the first reflecting mechanism 240 is used to deflect the light beam by a first angle, the second reflecting mechanism 250 is used to deflect the light beam by a second angle, the second angle being smaller than the first angle, and the spectrometer 260 is used to separate the light beams. The integrated compartment 300 is fixedly connected to the relay compartment 100 and includes an electronic module connected to the relay system 200 to provide power, control signals, and optical signal processing to the relay system 200; The optical compartment 400 is connected to the optical path exit end of the relay compartment 100 and has an optical antenna mechanism 410 installed inside. The shells of the relay module 100, the integrated module 300, and the optical module 400 are connected to each other to form a closed terminal structure. The working optical path configuration of the terminal is: Transmitting optical path 510: The optical signal is emitted by the transmitting unit 210, passes through the second reflecting mechanism 250, the light splitting mechanism 260, the first reflecting mechanism 240 in sequence, and is then transmitted by the optical antenna mechanism 410; Receiving optical path 520: The optical signal is collected by the optical antenna mechanism 410, passes through the first reflecting mechanism 240 and the light splitting mechanism 260, and reaches the receiving unit 220; Fine tracking optical path 530: The optical signal is collected by the optical antenna mechanism, passes through the first reflection mechanism 240 and the light splitting mechanism 260 in sequence, and reaches the fine tracking unit 230.

[0022] In this embodiment, if Figure 1 、 Figure 2 、 Figure 3 、 Figure 4As shown, the laser communication terminal adopts a modular cabin structure, which is composed of three parts: the relay cabin 100, the integrated cabin 300 and the optical cabin 400, which are connected by a shell to form a closed overall structure. Among them, the relay cabin 100 is the core structure of the optical signal processing. An optical substrate 110 is provided inside it. The optical substrate 110 is a rectangular plate structure and can be used as the side wall of the relay cabin 100. The optical functional components of the relay system 200 are all integrated on the optical substrate 110 to achieve a compact structure. The relay system 200 includes a transmitting unit 210, a receiving unit 220, a fine tracking unit 230, a first reflecting mechanism 240, a second reflecting mechanism 250 and a splitting mechanism 260. Among them, the transmitting unit 210 can adopt a combination of a high-power laser and a collimating optical system, so as to output a stable modulated The optical signal receiving unit 220 can use a combination of a highly sensitive photodetector and a focusing lens group, so as to efficiently capture the incident optical signal. The fine tracking unit 230 can use a combination of a four-quadrant detector and a fast reflector, so as to achieve real-time detection of the light spot offset and make corrections. In addition, the fine tracking unit 230 also includes a third reflector 231, which is mounted on the optical substrate 110 and is located in front of the four-quadrant detector. The third reflector 231 receives the incident light beam from the splitter mechanism 260, which enters the four-quadrant detector after being reflected by the third reflector 231, thereby making the arrangement more compact. The first reflector mechanism 240 is a large-angle deflection mirror group that can achieve optical deflection within a first angle range, thereby meeting the wide-range capture requirements between satellites, and the second reflector mechanism 250 is a small-angle deflection mirror group that can achieve optical deflection within a second angle range, thereby cooperating with the first reflector mechanism 240 to complete the precise alignment of the light beam. The light splitting mechanism 260 may adopt a combination of a polarization beam splitter prism and a wavelength beam splitter, thereby achieving interference-free separation of the transmitted light beam, the received light beam and the precision tracking light beam.

[0023] The integrated cabin 300 is fixed on the back of the optical substrate 110 of the relay cabin 100, and the integrated cabin 300 and the relay cabin 100 are arranged side by side to achieve lightweight and miniaturization. An electronic module is integrated in the integrated cabin 300, which can provide power to the relay system 200, and can process the tracking control algorithm and communication protocol. At the same time, it can also drive the control circuit to form a closed-loop control link with the first reflection mechanism 240, the second reflection mechanism 250 and the fine tracking unit 230.

[0024] The optical compartment 400 is docked with the optical path exit end of the relay compartment 100 and is located on the same side as the integrated compartment 300. An optical antenna mechanism 410 is provided inside the optical compartment 400 to achieve efficient convergence and collimation of the laser beam.

[0025] In actual operation, the terminal realizes laser communication through the coordinated operation of the transmitting optical path 510, the receiving optical path 520 and the fine tracking optical path 530, wherein: In the transmitting optical path 510, the modulation circuit of the electronic module transmits the data to be transmitted to the transmitting unit 210. The transmitting unit 210 generates a modulated optical signal. The optical signal is collimated by the collimating lens of the transmitting unit 210 and then transmitted to the second reflecting mechanism 250. The optical path direction is adjusted by a small-angle deflection and enters the spectrometer mechanism 260. After being split by the spectrometer mechanism 260, it is incident on the first reflecting mechanism 240. After being deflected at a large angle, it enters the optical antenna mechanism 410. Finally, the optical antenna mechanism 410 transmits it to the target satellite or ground station.

[0026] In the receiving optical path 520, the target signal is captured by the optical antenna mechanism 410, converged by the optical antenna mechanism 410 and enters the relay compartment 100. Then, the light beam is incident on the first reflecting mechanism 240, deflected and then sent to the spectrometer mechanism 260. The spectrometer mechanism 260 separates the received light from other stray light and sends the light beam to the receiving unit 220. The receiving unit 220 converges the light beam onto the photosensitive surface of the photodetector, thereby realizing the conversion of the optical signal into the electrical signal, and then transmits it to the demodulation circuit of the electronic module to restore the communication data.

[0027] In the fine tracking optical path 530, the fine tracking optical path 530 and the receiving optical path 520 can share the front-stage optical path. After being separated by the spectrometer 260, the light is incident on the four-quadrant detector of the fine tracking unit 230. The four-quadrant detector detects the deviation between the center position of the light spot and the reference position in real time to generate a deviation signal, and transmits the deviation signal to the electronic module. The electronic module calculates the correction amount through the PID algorithm, thereby driving the fast reflection mirror of the fine tracking unit 230 to make real-time adjustments, and at the same time sends compensation instructions to the first reflection mechanism 240 and the second reflection mechanism 250 to form a three-level closed-loop control to ensure stable alignment of the light beam.

[0028] In the above structure, a modular structure is used to connect the relay module 100, the integrated module 300 and the optical module 400 to form a closed terminal structure, which realizes the lightweight and miniaturization of the terminal. By integrating the relay system 200 on the optical substrate 110, the spatial layout is made more compact. By fixing the relay module 100 and the integrated module 300 side by side, the complexity of the wiring between the two is effectively reduced, and the difficulty of satellite layout is reduced. In addition, due to the low center of mass of the whole machine, the dynamic coupling with the satellite platform is greatly reduced, and the satellite attitude and positioning accuracy are improved. In addition, the modular structure improves the utilization rate of materials, reduces the number and cost of optical support structural parts, and improves the structural rigidity of the product and the stability of the optical system. In addition, the modular structure makes the optical module 400 independent of the relay module 100 and the integrated module 300, so that the terminal can replace the optical antenna scheme with different light apertures according to different scenarios and different tasks to meet the application requirements of multiple scenarios and multiple working conditions. The three-level tracking and aiming architecture of large-angle coarse adjustment, small-angle fine adjustment and precise tracking is adopted, combined with the high-speed closed-loop control of the electronic module to improve the pointing accuracy of the light beam, effectively reduce the impact of satellite platform vibration on the communication link, and improve the stability of the link.

[0029] In the specific structure of the first reflecting mechanism 240, the first reflecting mechanism 240 includes a first bracket 241 and a first reflecting mirror 242. The first bracket 241 is fixed on the optical substrate 110. The first reflecting mirror 242 is movably connected to the first bracket 241. The first bracket 241 is provided with a first driving member, and the first driving member is connected to the first reflecting mirror 242. Under the control of the electronic module, the first reflecting mirror 242 can deflect the light beam to a first angle, and the first angle is ±3 degrees.

[0030] In this embodiment, if Figure 5 As shown, the first bracket 241 is a U-shaped frame structure, the bottom of which is fixedly connected to the optical base 110 by screws. A gasket can be installed between the connecting surfaces to fine-tune the optical axis angle. Flexible bearing mounting holes are symmetrically opened on the two side walls of the bracket. The first bracket 241 has a mounting cavity reserved for the first driver. The two sides of the first reflector 242 are connected to the flexible bearing mounting holes of the first bracket 241 via a rotating shaft. A photoelectric sensor mounting position is provided behind the rotating shaft to provide real-time feedback on the angular position of the first reflector 242. The first driver can be driven by a voice coil motor. The motor stator is fixed in the mounting cavity, and the mover is connected to the rotating shaft of the first reflector 242. The motor current can be adjusted by the PWM control signal output by the electronic module to drive the first reflector 242 to deflect the light beam within a range of ±3°.

[0031] With this structure, the first reflector 240 achieves high-precision angular adjustment within a ±3° deflection range, meeting the precision requirements for coarse beam pointing and effectively improving the success rate of initial inter-satellite link acquisition, thereby ensuring accurate transmission and reception of optical signals. The modular design allows for quick assembly of the first reflector 242 and first bracket 241, ensuring structural rigidity while facilitating maintenance and adjustment, thereby reducing assembly difficulty and maintenance costs.

[0032] Correspondingly, in the specific structure of the second reflecting mechanism 250, the second reflecting mechanism 250 includes a second bracket 251 and a second reflecting mirror 252. The second bracket 251 is fixed on the optical substrate 110. The second reflecting mirror 252 is movably connected to the second bracket 251. The second bracket 251 is provided with a second driving member, and the second driving member is connected to the second reflecting mirror 252. Under the control of the electronic module, the second reflecting mirror 252 can deflect the light beam to a second angle, and the second angle is ±7 microradians.

[0033] In this embodiment, if Figure 5 As shown, the second bracket 251 is also a U-shaped frame structure, the bottom of which is fixedly connected to the optical base 110 by screws, and a gasket can be installed between the connection surfaces to fine-tune the optical axis angle, and the second bracket 251 is located below the first bracket 241. Flexible bearing mounting holes are symmetrically opened on both side walls of the second bracket 251. A mounting cavity for the second driving member is reserved inside the second bracket 251. The two sides of the second reflector 252 are connected to the flexible bearing mounting holes of the second bracket 251 through a rotating shaft, and a position sensor mounting position is provided at the end of the rotating shaft. To provide real-time feedback on the angular position of the second reflector 252, the second driving component can adopt a combination of a piezoelectric ceramic actuator and a displacement amplification mechanism. The actuator is connected to the adapter of the second reflector 252 through a flexible hinge, and a diamond-shaped displacement amplification mechanism is connected in series in the middle, which can convert the micro-displacement of the piezoelectric ceramic into the angular deflection of the reflector. The second driving component has a built-in capacitive displacement sensor, which can monitor the angular position of the reflector in real time, and form a closed-loop control with the electronic module to drive the second reflector 252 to deflect the light beam within the range of ±7 microradians.

[0034] The above structure drives the second reflector 252 to deflect the light beam within the range of ±7 microradians. The ability to adjust the small angle enables more precise direction control of the light beam, thereby improving the accuracy and stability of communication.

[0035] In the specific structure of the spectrometer mechanism 260, the spectrometer mechanism 260 includes a first spectrometer component 261 and a second spectrometer component 262. The first spectrometer component 261 is arranged in the transmitting optical path 510 and the receiving optical path 520 to separate the transmitting optical path 510 and the receiving optical path 520. The second spectrometer component 262 is arranged in the receiving optical path 520 and the fine tracking optical path 530 to separate the receiving optical path 520 and the fine tracking optical path 530. Specifically, the first spectrometer component 261 includes a third bracket 2611 and a first spectrometer 2612, the third bracket 2611 is fixed on the optical substrate 110, and the first spectrometer 2612 is fixed on the third bracket 2611; the second spectrometer component 262 includes a fourth bracket 2621 and a second spectrometer 2622, the fourth bracket 2621 is fixed on the optical substrate 110, and the second spectrometer 2622 is fixed on the fourth bracket 2621, and the third bracket 2611 and the fourth bracket 2621 are arranged in parallel in the receiving optical path 520.

[0036] In this embodiment, if Figure 3 、 Figure 5 As shown, the optical splitting mechanism 260 is composed of a first optical splitting component 261 and a second optical splitting component 262 connected in series, so that the transmission, reception and precision tracking signals are transmitted independently. The first optical splitting component 261 is used to separate the transmission optical path 510 and the receiving optical path 520. The first optical splitting component 261 includes a third bracket 2611 and a first optical splitter 2612. The bottom of the third bracket 2611 is installed and connected with the optical substrate 110 by screws. The first optical splitter 2612 adopts a polarization splitting prism structure and can be fixed on the third bracket 2611 by a metal pressure ring. A polarization-splitting film is coated on the surface of a beam splitter 2612, with a transmittance of ≥98% for P-polarized light and a reflectance of ≥99% for S-polarized light. The optical signal of the transmitting optical path 510 is deflected by the second reflecting mechanism 250 and incident on the first beam splitting component 261 in the P-polarized state. More than 98% of the energy passes through the prism and enters the subsequent optical path. The optical signal of the receiving optical path 520 is deflected by the first reflecting mechanism 240 and incident on the first beam splitting component 261 in the S-polarized state. More than 99% of the energy is reflected to the second beam splitting component 262, thereby achieving polarization separation of the transmitted and received light.

[0037] The structure of the second beam splitter assembly 262 is similar to that of the first beam splitter assembly 261. The second beam splitter assembly 262 includes a fourth bracket 2621 and a second beam splitter 2622. The bottom of the fourth bracket 2621 is mounted and connected to the optical base 110 via screws, and the third bracket 2611 and the fourth bracket 2621 are arranged parallel to the optical path. The second beam splitter 2622 is used to separate the receiving optical path 520 from the fine tracking optical path 530. The second beam splitter 2622 is a combination of a wavelength beam splitter and a focusing lens. Its surface is coated with a two-color beam splitting film. The reflectivity of the second beam splitter 2622 for the 1550nm received light is ≥95%, and the transmittance of the 905nm fine tracking light is ≥90% (the fine tracking optical path 530 uses a 905nm laser as a beacon light). The reflected 1550nm received light can be focused onto the photosensitive surface of the photodetector of the receiving unit 220, while the transmitted 905nm fine tracking light remains a parallel beam incident on the fine tracking unit 230.

[0038] In this embodiment, the first optical splitter component 261 uses polarization characteristics to achieve efficient separation of transmitted light and received light, avoiding interference of the transmitted signal on the receiving end. The second optical splitter component 262 uses wavelength-selective optical splitting to improve the separation efficiency of received light and precision tracking light, ensuring that both types of signals can maintain a high signal-to-noise ratio transmission, providing dual protection for communication quality and tracking accuracy.

[0039] In the specific structure of the electronic module, the electronic module includes a power driving module 310, a main control module 320 and an EDFA module 330. The power driving module 310 provides power for the relay system 200, the main control module 320 is used to run the control algorithm and produce communication signals, and the EDFA module 330 is used to amplify the communication optical signal. The power driving module 310, the main control module 320 and the EDFA module 330 are stacked in layers to form an integrated compartment 300.

[0040] In this embodiment, if Figure 1 As shown, the electronic module adopts a layered stacked structure, consisting of a power driver module 310, a main control module 320, and an EDFA module 330 stacked in sequence. Metal struts and flexible cables provide electrical connections and structural fixation, forming the integrated module 300. The power driver module 310 integrates multiple DC-DC conversion circuits, overcurrent protection circuits, and voltage monitoring circuits. The main power conversion unit converts the 28V DC input from the satellite platform into multiple voltage levels required by the various components of the relay system 200. It provides a regulated 24V / 3A voltage to the transmitting unit 210, outputs ±15V / 1A driving voltage to the first reflector 240, the second reflector 250, and the fine tracking unit 230, and supplies 5V / 5A and 3.3V / 10A operating voltages to the main control module 320 and the EDFA module. The power driver module 310 has four positioning holes on its edge, which are rigidly connected to the main control module 320 via copper pillars.

[0041] The main control module 320 can use a Rogers high-frequency PCB board, which is the same size as the power drive module 310. It integrates a dual-core ARMCortex-A9 processor, an FPGA chip, a high-speed AD / DA converter and a Gigabit Ethernet interface. The processor has a built-in tracking control algorithm and communication protocol stack, which can process the spot offset data fed back by the fine tracking unit 230 in real time and generate drive instructions for the first reflection mechanism 240 and the second reflection mechanism 250; the FPGA chip is responsible for modulating and demodulating communication signals, and supports multiple modulation methods such as BPSK and QPSK. The module surface integrates an SMA RF interface for connecting the transmitting unit 210 and the receiving unit 220 of the relay system 200.

[0042] The EDFA module can be constructed using an aluminum-based PCB. Its core components include a pump laser (980nm wavelength, 300mW output power), an erbium fiber (5m length, 500ppm doping concentration), an optical isolator (isolation ≥40dB), and an optical attenuator (adjustable range 0-20dB). The module's input connects to the transmitter unit 210 via an FC / APC fiber connector. The received 1550nm communication optical signal is amplified by the erbium fiber.

[0043] In the above structure, by stacking the power drive module 310, the main control module 320 and the EDFA module 330 in layers, the volume of the electronic module is further compressed and the weight is reduced. Combined with the compact layout of the integrated compartment 300, the space occupied by the satellite platform is greatly reduced, further realizing the miniaturization of the terminal.

[0044] In the specific structure of the optical antenna mechanism 410, the optical antenna mechanism 410 includes an antenna mounting frame 411, an antenna lens barrel 412 and a solar filter 414. One end of the antenna mounting frame 411 is fixed on the optical substrate 110, and the other end is fixed to the antenna lens barrel 412. The antenna lens barrel 412 is detachably connected to the antenna lens 413. The optical aperture of the antenna lens 413 is 60-80 mm. The antenna lens barrel 412 is used to expand the outgoing light beam and shrink the incident light beam. The solar filter 414 is installed at the end of the antenna lens barrel 412 and is arranged on the outside of the antenna lens 413.

[0045] In this embodiment, if Figure 6As shown, the optical antenna mechanism 410 consists of an antenna mounting bracket 411, an antenna barrel 412, an antenna lens 413, and a solar filter 414. The fixed end of the antenna mounting bracket 411 is fixed to the optical substrate 110 via screws, and a gasket is installed between the connecting surfaces to fine-tune the optical axis. The antenna barrel 412 is precision-machined from aluminum-based silicon carbide. The inner wall can be blackened to reduce stray light reflections. A stepped positioning structure is provided inside the antenna barrel 412 for mounting the antenna lens 413. The antenna lens 413 and the antenna barrel 412 are detachably connected using epoxy resin glue. The antenna lens 413 is made of a glass-ceramic substrate with a 1550nm anti-reflection coating (transmittance ≥ 99.5%). The optical aperture can be selected to be 60mm, 70mm, or 80mm depending on communication requirements, with corresponding focal lengths of 200mm, 230mm, and 260mm. The lens barrel and antenna are fastened together with bolts. The removable structure facilitates replacement of lenses of varying apertures based on mission requirements. A solar filter 414 is mounted on the end of the antenna lens barrel 412, away from the mounting bracket. Made of a quartz glass substrate and coated with a multi-layer dielectric coating, it suppresses the 0.3-2.5μm band of the solar spectrum while maintaining a transmittance of ≥90% in the 1550nm communications band. A stainless steel pressure ring secures the solar filter 414 in a stepped groove at the end of the lens barrel.

[0046] In addition, the outer shell of the relay compartment 100 is provided with a first electrical interface 120, and the outer shell of the integrated compartment 300 is provided with a second electrical interface 340. The relay system 200 is connected to the electronic module through the first electrical interface 120 and the second electrical interface 340.

[0047] In this embodiment, if Figure 1 As shown, the first electrical interface 120 is located on the side of the relay compartment 100 housing and adopts an aviation plug structure. The pins of the first electrical interface 120 are connected to the functional units of the relay system 200 via an internal flexible cable. The second electrical interface 340 is located on the corresponding side of the integrated compartment 300 housing and is an aviation socket structure that matches the first electrical interface 120. It is connected to the electronic module via a direct connection to the PCB board. That is, the jack pins are directly soldered to the interface circuits of the power driver module 310 and the main control module 320 of the electronic module, reducing signal transmission path loss.

[0048] When the relay compartment 100 is docked with the integrated compartment 300, the first electrical interface 120 and the second electrical interface 340 can be connected through a flexible cable to form a complete electrical path: the multi-level voltage output by the power drive module 310 is transmitted to the relay system 200 through the second electrical interface 340 and the first electrical interface 120; the control signal generated by the main control module 320 is transmitted to the driving part of the reflection mechanism and the fine tracking unit 230 through the interface; the status feedback signal of the relay system 200 (such as the mirror rotation angle and the spot offset) is transmitted in reverse to the electronic module to realize two-way data interaction.

[0049] Example 2 The present application also provides a laser communication method based on the above-mentioned integrated laser communication terminal, comprising the following steps: S1. The electronic module controls the first reflective mechanism 240 to scan within a first angle range to capture beacon light. S2. The beacon light enters the fine tracking unit 230 through the fine tracking optical path 530. The fine tracking unit 230 detects the position of the light spot, and the electronic module controls the first reflective mechanism 240 to deflect the light beam for tracking, thereby establishing a stable link. S3. After the communication data is generated by the electronic module, the electronic module controls the transmitting unit 210 to transmit the light beam, which is then transmitted by the optical antenna mechanism 410 through the transmitting optical path 510. S4. The received optical signal enters the receiving unit 220 through the optical antenna mechanism 410 and the receiving optical path 520. The receiving unit 220 receives the signal and sends it to the electronic module for demodulation.

[0050] In this embodiment, at S1, the main control module 320 of the electronic module initiates the beacon capture program and sends a scanning control command to the driver of the first reflector mechanism 240. The first reflector 242 scans within a first angular range of ±3°. The scanning path is preset by the capture algorithm of the main control module 320 and covers the possible azimuth angle range of the target satellite. The solar filter 414 of the optical antenna mechanism 410 filters out background stray light, allowing only the beacon light (wavelength 905nm) to enter the antenna barrel 412. After being contracted and focused by the antenna lens 413, it is reflected by the first reflector mechanism 240 to the spectrometer mechanism 260. At this point, the wavelength splitter of the second spectrometer assembly 262 transmits the 905nm beacon light to the four-quadrant detector of the fine tracking unit 230. The detector initially senses the energy of the light spot and feeds back a signal indicating the presence of the light spot to the main control module 320, completing the initial capture of the beacon light.

[0051] In S2, the fine tracking unit 230 continuously detects the center position of the beacon light spot and transmits the spot offset in real time to the main control module 320 of the electronic module. Main control module 320 calculates the correction angle of the first reflector 240 using a PID control algorithm and drives the first reflector 242 for dynamic deflection to maintain the center of the light spot at the detector reference position. Simultaneously, the second reflector 250, responding to instructions from the main control module 320, performs high-frequency fine-tuning within a second angle range to compensate for minor angular offsets caused by satellite platform vibration. When the light spot stabilizes, the main control module 320 determines that the link is established and enters the stable tracking state.

[0052] In S3, an external data source (such as a satellite payload sensor) transmits communication data to the electronics module's main control module 320 via an Ethernet interface. Main control module 320 frames and encodes the data, then transmits the electrical signal to the modulator in the transmitter unit 210. The modulator applies the electrical signal to a 1550nm laser beam. The modulated laser beam is deflected at a small angle by the second reflector 250, passes through the polarization beam splitter prism (P-polarization transmission) in the first beam splitter assembly 261, and then is reflected by the first reflector 240 to the optical antenna mechanism 410. The antenna barrel 412 expands the beam, which is then transmitted to the target terminal via the antenna lens 413. The EDFA module automatically adjusts the output power based on the link distance.

[0053] In S4, the 1550nm communication optical signal emitted by the target terminal is captured by the optical antenna mechanism 410. After the solar filter 414 suppresses background light interference, it is contracted and focused by the antenna lens 413 and reflected to the spectrometer 260 by the first reflecting mechanism 240. The polarization splitter prism of the first spectrometer component 261 reflects the S-polarized state received light to the second spectrometer component 262. The wavelength splitter reflects the 1550nm received light to the receiving unit 220. The photodetector of the receiving unit 220 converts the optical signal into an electrical signal and transmits it to the demodulation circuit of the electronic module. The demodulation circuit completes signal demodulation and LDPC decoding, restores the original communication data, and outputs it to the satellite data processing center.

[0054] Example 3 The present application also provides an application based on the above-mentioned integrated laser communication terminal, which is used in spacecraft.

[0055] In the embodiments disclosed herein, terms such as "installed," "connected," "connected," and "fixed" should be interpreted broadly. For example, "connected" may refer to a fixed connection, a detachable connection, or an integral connection; and "connected" may refer to a direct connection or an indirect connection via an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments disclosed herein based on specific circumstances.

[0056] The above is only a preferred embodiment of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. An integrated laser communication terminal, characterized in that: include: A relay compartment, internally provided with an optical substrate, on which a relay system is integrated, comprising a transmitting unit, a receiving unit, a fine tracking unit, a first reflecting mechanism, a second reflecting mechanism, and a spectrometer. The transmitting unit is configured to transmit an optical signal, the receiving unit is configured to receive an optical signal, the fine tracking unit is configured to detect the position of an incident light spot, the first reflecting mechanism is configured to deflect the light beam by a first angle, the second reflecting mechanism is configured to deflect the light beam by a second angle, the second angle being smaller than the first angle, and the spectrometer is configured to separate the light beams. An integrated compartment, fixedly connected to the relay compartment, comprising an electronic module, which is connected to the relay system to provide power, control signals, and optical signal processing to the relay system; an optical compartment, docked with the optical path exit end of the relay compartment, and having an optical antenna mechanism disposed therein; The shells of the relay cabin, the integration cabin, and the optical cabin are connected to each other to form a closed terminal structure; The working optical path configuration of the terminal is: Transmitting optical path: the optical signal is emitted by the transmitting unit, passes through the second reflecting mechanism, the light splitting mechanism, the first reflecting mechanism in sequence, and is then transmitted by the optical antenna mechanism; Receiving optical path: the optical signal is collected by the optical antenna mechanism, passes through the first reflecting mechanism and the light splitting mechanism in sequence, and reaches the receiving unit; Precision tracking optical path: The optical signal is collected by the optical antenna mechanism, passes through the first reflection mechanism and the light splitting mechanism in sequence, and reaches the precision tracking unit.

2. The integrated laser communication terminal according to claim 1, characterized in that: The first reflecting mechanism includes a first bracket and a first reflector. The first bracket is fixed on the optical substrate. The first reflector is movably connected to the first bracket. The first bracket is provided with a first driving member. The first driving member is connected to the first reflector. Under the control of the electronic module, the first reflector can deflect the light beam to a first angle. The first angle is ±3 degrees.

3. The integrated laser communication terminal according to claim 2, characterized in that: The second reflecting mechanism includes a second bracket and a second reflector. The second bracket is fixed on the optical substrate. The second reflector is movably connected to the second bracket. The second bracket is provided with a second driving member. The second driving member is connected to the second reflector. Under the control of the electronic module, the second reflector can deflect the light beam to a second angle. The second angle is ±7 microradians.

4. The integrated laser communication terminal according to claim 1, characterized in that: The spectroscopic mechanism includes a first spectroscopic component and a second spectroscopic component. The first spectroscopic component is arranged in the transmitting optical path and the receiving optical path to separate the transmitting optical path and the receiving optical path. The second spectroscopic component is arranged in the receiving optical path and the fine tracking optical path to separate the receiving optical path and the fine tracking optical path.

5. The integrated laser communication terminal according to claim 4, characterized in that: The first beam splitter assembly includes a third bracket and a first beam splitter, the third bracket is fixed on the optical substrate, and the first beam splitter is fixed on the third bracket; The second beam splitter assembly includes a fourth bracket and a second beam splitter. The fourth bracket is fixed on the optical substrate. The second beam splitter is fixed on the fourth bracket. The third bracket and the fourth bracket are arranged in parallel in the receiving optical path.

6. The integrated laser communication terminal according to claim 1, characterized in that: The electronic module includes a power drive module, a main control module and an EDFA module. The power drive module provides power for the relay system, the main control module is used to run the control algorithm and produce communication signals, and the EDFA module is used to amplify the communication optical signal. The power drive module, the main control module and the EDFA module are stacked in layers to form the integrated compartment.

7. The integrated laser communication terminal according to claim 1, characterized in that: The optical antenna mechanism includes an antenna mounting frame, an antenna lens barrel and a solar filter. One fixed end of the antenna mounting frame is fixed to the optical substrate, and the other end is fixed to the antenna lens barrel. The antenna lens barrel is detachably connected to an antenna lens. The optical aperture of the antenna lens is 60-80mm. The antenna lens barrel is used to expand the outgoing light beam and shrink the incident light beam. The solar filter is installed at the end of the antenna lens barrel and is arranged on the outside of the antenna lens.

8. The integrated laser communication terminal according to claim 1, characterized in that: The outer shell of the relay compartment is provided with a first electrical interface, and the outer shell of the integrated compartment is provided with a second electrical interface. The relay system is connected to the electronic module through the first electrical interface and the second electrical interface.

9. A laser communication method based on the integrated laser communication terminal according to any one of claims 1 to 8, characterized in that: The following steps are involved: S1. The electronic module controls the first reflective mechanism to scan within the first angle range to capture beacon light; S2. The beacon light enters the fine tracking unit through the fine tracking optical path. The fine tracking unit detects the position of the light spot, and the electronic module controls the first reflective mechanism to deflect the light beam for tracking, thereby establishing a stable link. S3. After the communication data is generated by the electronic module, the electronic module controls the transmitting unit to transmit the light beam, and the light beam is transmitted from the optical antenna mechanism through the transmitting optical route; S4. The received optical signal enters the receiving unit through the optical antenna mechanism and the receiving optical path. The receiving unit receives the signal and sends the signal to the electronic module for demodulation.

10. An application of the integrated laser communication terminal according to any one of claims 1 to 8, characterized in that: For spacecraft.

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