Satellite platform integrated with laser communication load

Abstract

The invention discloses a satellite platform integrated with a laser communication load. The satellite platform comprises a satellite platform body and a laser communication light machine device. Power supply, signal modulation and demodulation, a star sensor and a thermal control module of a laser communication load are integrated and multiplexed with related systems of a satellite platform, and related subsystems of the satellite platform are improved and designed according to special requirements of the laser load, so that the problems of high weight, high power consumption, large size and high reliability of the current laser communication load as an independent single machine are solved. Relative isolation between an independent single machine and a platform has the problems that the laser self-control difficulty is increased due to the fact that the attitude error is increased when the platform attitude is transmitted through a structure, and the process is long and the efficiency is low due to the fact that a laser communication load and platform information interaction need to be subjected to multiple photoelectric conversion. According to the invention, the size, weight, power consumption and complexity of a laser communication load are greatly reduced, and a satellite platform is changed into a constellation satellite with inter-satellite networking capability from a single-satellite form.

Description

Technical Field

[0001] This invention belongs to the field of satellite platform and satellite communication technology, and in particular relates to a satellite platform that integrates a laser communication payload. Background Technology

[0002] In the field of remote sensing satellites, with the continuous development of remote sensing technology and the increasing demands for resolution and real-time performance of remote sensing data from various sectors of society, both domestic and international efforts have begun to design multi-satellite groups for collaborative imaging or to build remote sensing satellite constellations to achieve real-time global situational awareness. High-resolution remote sensing data is characterized by high data throughput. To achieve rapid exchange and transmission of remote sensing data, remote sensing satellites need to utilize increasingly mature inter-satellite laser communication technology to establish high-speed inter-satellite data transmission channels.

[0003] To achieve the high communication speed, low latency, and global coverage required by low-Earth orbit (LEO) communication satellites, the satellites in the LEO constellation must possess inter-satellite communication capabilities to enable satellite networking. Traditional microwave communication suffers from insufficient bandwidth and requires spectrum coordination, among other limitations, making it unsuitable for these requirements. In contrast, satellite laser communication technology, with its wide bandwidth, high security, and lack of spectrum limitations, has become an effective means of high-speed inter-satellite communication.

[0004] Satellite laser communication technology has moved from the technology verification stage to small-scale engineering applications. Various satellites, both domestically and internationally, are beginning to be equipped with laser communication payloads or are planning to be equipped with them. However, current applications of spaceborne laser communication payloads often involve installing them as independent units on the satellite platform, requiring separate power supplies, signal modulation and demodulation systems, star sensors, and thermal control modules. This increases the satellite's weight, power consumption, and size. As independent units relatively isolated from the platform, the platform's attitude information is introduced into the satellite platform's structure, leading to attitude accuracy errors and increasing the uncertainty in laser control, thus increasing the difficulty of inter-satellite link establishment. Furthermore, after receiving the optical signal, the laser communication payload, as a single unit, must perform photoelectric conversion, decoding, framing, and other operations before electro-optical conversion and transmission to the satellite platform's data exchange unit or onboard routing unit. This data transmission process is lengthy and involves numerous conversions, introducing risks such as bit errors and single points of failure. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a satellite platform that integrates laser communication payload, which greatly reduces the size, weight, power consumption and complexity of the laser communication payload, and the satellite platform is transformed from a single satellite into a constellation satellite with inter-satellite networking capabilities.

[0006] The objective of this invention is achieved through the following technical solution: A satellite platform integrating a laser communication payload, comprising: a satellite platform and a laser communication optomechanical device; wherein, the satellite platform: preheats the laser communication optomechanical device at a preset time to a preset temperature; after the laser communication optomechanical device has preheated, it powers on the laser communication optomechanical device; receives the orbital information of the peer satellite at a fixed time from the ground, obtains the orbital information of the peer satellite at the link establishment time based on the orbital information of the peer satellite at a fixed time from the ground, and extrapolates the orbital information of the peer satellite at the link establishment time to the laser communication optomechanical device; receives code disk readings, vibration... The system receives the position of the galvanometer and the CCD image, and obtains action commands based on the code disk reading, galvanometer position, and CCD image. These action commands are then transmitted to the laser communication optomechanical equipment. It receives space light, performs photoelectric conversion to obtain electrical signals, and processes these electrical signals digitally to obtain service data and relay commands. The laser communication optomechanical equipment performs self-testing and self-calibration upon power-up. It receives the orbital information of the peer satellite at the link establishment time and transmits the code disk reading, galvanometer position, and CCD image to the satellite platform. It receives action commands and performs actions accordingly. It also receives space light and couples it into the satellite platform via optical fiber transmission.

[0007] The aforementioned satellite platform integrating laser communication payload includes an integrated power supply system, an integrated thermal control system, an integrated modulation and demodulation communication module, and an integrated control subsystem. Specifically, the integrated thermal control system preheats the laser communication optomechanical equipment to a preset temperature within a pre-defined timeframe. The integrated power supply system powers the laser communication optomechanical equipment after preheating. The integrated control subsystem receives the orbital information of the peer satellite at a fixed time from the ground, obtains the orbital information of the peer satellite at the link establishment time based on this information, and extrapolates this information to the laser communication optomechanical equipment. It also receives code disk readings, galvanometer positions, and CCD images, obtains action commands based on these data, and transmits the action commands to the laser communication optomechanical equipment. The integrated modulation and demodulation communication module receives space light, performs photoelectric conversion to obtain electrical signals, and processes these electrical signals digitally to obtain service data and relay commands.

[0008] In the aforementioned satellite platform integrating laser communication payload, the laser communication optomechanical equipment includes a space optical coupling module and an optical telescope; wherein, the optical telescope receives space light and transmits the space light to the space optical coupling module, and the space optical coupling module couples the space light into the integrated modulation and demodulation communication module via optical fiber transmission.

[0009] In the aforementioned satellite platform that integrates laser communication payloads, the preset time is 10-20 minutes.

[0010] The satellite platform that integrates the laser communication payload has a preset temperature of 20℃-25℃.

[0011] In the aforementioned satellite platform that integrates laser communication payload, the extrapolation accuracy is better than 500m, and the extrapolation data frequency is greater than 4Hz.

[0012] In the aforementioned satellite platform that integrates laser communication payloads, digital signal processing includes analog-to-digital conversion, descrambling, decoding, and framing.

[0013] In the aforementioned satellite platform that integrates laser communication payloads, the orbital information of the peer satellite at the moment of link establishment includes the satellite's attitude, orbit, and the peer satellite's position.

[0014] In the aforementioned satellite platform integrating laser communication payload, the integrated modulation and demodulation communication module 4 includes a photoelectric conversion module and a modulation and demodulation module; wherein, the photoelectric conversion module: receives space light, performs photoelectric conversion on the space light to obtain an electrical signal, and transmits the electrical signal to the modulation and demodulation module; the modulation and demodulation module: receives the electrical signal, processes the electrical signal through digital signal processing to obtain service data and relay instructions.

[0015] In the aforementioned satellite platform that integrates laser communication payloads, the communication rate of the integrated modem communication module is greater than 10Gbps, and the big data throughput processing capability of the integrated modem communication module is greater than 10Gbps.

[0016] Compared with the prior art, the present invention has the following advantages: This invention integrates the power supply system, demodulation module, thermal control subsystem, and control subsystem of the laser communication payload with the relevant systems of the satellite platform, achieving an integrated spaceborne design. This reduces the laser communication payload to a single independent laser communication optomechanical device, significantly decreasing its size, weight, power consumption, and complexity. The satellite platform is transformed from a single-satellite configuration into a constellation of satellites capable of inter-satellite networking. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a schematic diagram of a satellite platform integrating a laser communication payload provided in an embodiment of the present invention. Detailed Implementation

[0018] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0019] Figure 1 This is a schematic diagram of a satellite platform integrating a laser communication payload provided in an embodiment of the present invention. Figure 1 As shown, the satellite platform integrating the laser communication payload includes: a satellite platform and laser communication optomechanical equipment. Specifically, the satellite platform: preheats the laser communication optomechanical equipment 6 to a preset temperature within a pre-defined time; after preheating, it powers on the equipment; receives the orbital information of the peer satellite at a fixed time from the ground, and obtains the orbital information of the peer satellite at the link establishment time based on this information, extrapolating it to the laser communication optomechanical equipment 6; receives code disk readings, galvanometer positions, and CCD images, and obtains action commands based on these data, transmitting them to the equipment; receives space light, performs photoelectric conversion to obtain electrical signals, and processes these signals digitally to obtain service data and relay commands.

[0020] Laser communication optomechanical equipment: After power-on, it begins self-testing and self-calibration; it receives the orbital information of the peer satellite at the time of link establishment and transmits the code disk reading, galvanometer position and CCD image to satellite platform 1; it receives action commands and performs actions according to the action commands; it receives space light and couples the space light into satellite platform 1 through optical fiber transmission.

[0021] The satellite platform includes an integrated power supply system 2, an integrated thermal control system 3, an integrated modem communication module 4, and an integrated control subsystem 5.

[0022] The laser communication optomechanical device 6 includes a heating element temperature sensor 7, a spatial optical coupling module 8, an optoelectronic code disk 9, and an optical telescope 10.

[0023] Integrated thermal control system 3: Preheats the laser communication optomechanical equipment 6 to a preset temperature within a pre-set time. The preset time is 10-20 minutes, preferably 15 minutes. The preset temperature is 20℃-25℃, preferably 20℃.

[0024] Integrated power supply system 2: After the laser communication optomechanical equipment 6 has finished preheating, power is supplied to the laser communication optomechanical equipment 6.

[0025] Integrated control subsystem 5: Receives the orbital information of the peer satellite at a fixed time from the ground, obtains the orbital information of the peer satellite at the link establishment time based on the fixed-time peer satellite orbital information from the ground, and extrapolates the peer satellite orbital information at the link establishment time to the laser communication optomechanical equipment 6. The extrapolation accuracy is better than 500m, and the extrapolation data frequency is greater than 4Hz. It also receives code disk readings, galvanometer positions, and CCD images, obtains action commands based on the code disk readings, galvanometer positions, and CCD images, and transmits the action commands to the laser communication optomechanical equipment 6. The peer satellite orbital information at the link establishment time includes the satellite attitude, orbit, and peer satellite position.

[0026] Integrated modulation and demodulation communication module 4: Receives spatial light, performs photoelectric conversion on the spatial light to obtain electrical signals, and processes the electrical signals into service data and relay instructions via digital signal processing. The digital signal processing includes analog-to-digital conversion, descrambling, decoding, and framing.

[0027] The laser communication optomechanical equipment includes a spatial optical coupling module 8 and an optical telescope 10; wherein, the optical telescope 10 receives spatial light and transmits the spatial light to the spatial optical coupling module 8, and the spatial optical coupling module 8 couples the spatial light into the integrated modulation and demodulation communication module 4 through optical fiber transmission.

[0028] The integrated modulation and demodulation communication module 4 includes a photoelectric conversion module and a modulation and demodulation module; wherein, the photoelectric conversion module: receives spatial light, performs photoelectric conversion on the spatial light to obtain an electrical signal, and transmits the electrical signal to the modulation and demodulation module; the modulation and demodulation module: receives the electrical signal, processes the electrical signal through digital signal processing to obtain service data and relay instructions.

[0029] The integrated modem communication module has a communication rate greater than 10Gbps and a large data throughput processing capability greater than 10Gbps.

[0030] This embodiment of the satellite platform integrating a laser communication payload includes a satellite platform and a laser communication optomechanical device. Compared to traditional laser communication payloads, the power supply, thermal control, modulation / demodulation communication module, and control system are eliminated. These functions are integrated with the satellite platform, reusing the satellite platform's power supply system, thermal control system, data transmission communication module, and control system. The laser communication payload is simplified to a single laser communication optomechanical device. The satellite platform has been redesigned to meet the specific needs of laser systems.

[0031] The satellite platform includes: an integrated modem communication module, an integrated control system, an integrated thermal control system, and an integrated power supply system. It also includes, but is not limited to, other onboard equipment such as payloads, onboard computers, switching units, and solar panels found on typical satellite platforms.

[0032] The integrated modem communication module is a shared module that integrates the modem communication module of the laser communication payload with the data transmission communication module of the satellite platform. To meet the communication requirements of the laser communication payload, the integrated modem communication module of the satellite platform should have the capability of ultra-high-speed communication rate (greater than 10Gbps) and large data throughput processing capability (greater than 10Gbps), and be compatible with multiple communication modes such as OOK, QPSK, and BPSK.

[0033] The integrated modulation and demodulation communication module incorporates a photoelectric conversion module. After the spatial light received by the laser communication optomechanical equipment couples into the optical fiber, it is directly connected to this photoelectric conversion module for photoelectric conversion. The converted light is then processed by the electrical signal processing module of the modulation and demodulation module, eliminating the need for a secondary electro-optical conversion between the laser payload and the platform-side optical module. This saves one photoelectric conversion process, improves efficiency, and reduces the risk of data errors.

[0034] The integrated control subsystem refers to the direct reuse of star sensors and gyroscopes from the satellite platform by the star sensors and gyroscopes used in the laser communication payload's optomechanical equipment. In addition to traditional platform attitude and orbit control functions, the satellite platform's control subsystem adds control functions for the laser communication optomechanical equipment (control bandwidth > 1kHz) and extrapolation of the peer satellite's position information (orbit extrapolation accuracy better than 500m@2000km). The laser communication optomechanical equipment is integrated with the platform's attitude sensors or rigidly connected to the same location. This eliminates the need for additional star sensors in the laser communication payload, saving weight and cost. The platform's attitude information is obtained through its attitude sensors. The control subsystem extrapolates the peer satellite's position at the link establishment time (extrapolation frequency of 1Hz) from the fixed-time peer satellite position annotated on the ground. All the above information is transmitted to the local laser communication optomechanical equipment via the information interface between the satellite platform and the laser optomechanical equipment. The optomechanical equipment uses this information to control its coarse tracking turntable and fine tracking galvanometer to begin link establishment. The rotation information of the optomechanical equipment is then fed back to the platform control system as input to control the next action of the optomechanical equipment, thus forming a closed-loop control. After initial pointing, scanning, tracking, bidirectional acquisition, and link establishment, an inter-satellite laser communication channel is established, enabling communication and information exchange between the two satellites.

[0035] The integrated thermal control subsystem refers to the thermal control module of the laser communication optomechanical equipment being directly controlled by the satellite platform's thermal control subsystem. The laser communication payload does not require a separate thermal control module, and laser heat preservation and preheating control do not require powering on the laser payload, saving weight (approximately 0.5 kg) and thermal control power consumption (approximately 20 W). The satellite platform's thermal control subsystem, in addition to traditional platform thermal control functions, also needs to perform heat preservation and timed preheating control (approximately 15 minutes advance time) on the laser communication optomechanical equipment. Compared to the platform's conventional thermal control requirements, the temperature control accuracy of the laser communication optomechanical equipment is relatively higher (better than ±1℃).

[0036] The integrated power supply subsystem refers to the secondary power supply module of the laser communication optomechanical equipment being directly provided by the satellite platform, eliminating the need for its separate configuration. This saves weight compared to the laser communication payload being a standalone unit (the power supply module weighs approximately 1 kg).

[0037] like Figure 1 As shown, this embodiment of the invention provides a satellite platform integrating a laser communication payload, including: a satellite platform 1 and a laser communication optomechanical device 6.

[0038] Satellite platform 1 includes: integrated power supply 2, integrated thermal control system 3, integrated data transmission and communication module 4, integrated control subsystem 5, etc.

[0039] The laser communication optomechanical equipment 6 includes a heating element temperature sensor 7, a spatial optical coupling module 8, an optoelectronic code disk 9, an optical telescope 10, etc.

[0040] The platform thermal control system 3 of satellite platform 1 preheats the laser communication optomechanical equipment 6 15 minutes in advance, raising its temperature from the insulation temperature of about 5°C to 20°C.

[0041] The orbital information of the counterpart satellite at a fixed time is input to the integrated control system 5 on the ground, and the orbital information of the counterpart satellite at the link establishment time is extrapolated from it. The extrapolation accuracy is better than 500m and the extrapolation data frequency is greater than 4Hz.

[0042] After the laser communication optomechanical equipment 6 has finished warming up, the integrated power supply 2 of the satellite platform 1 begins to power up the laser communication optomechanical equipment 6.

[0043] After being powered on, the laser communication optomechanical device 6 begins self-testing and self-calibration. Upon completion, it sends its status and awaits link establishment instructions from satellite platform 1.

[0044] The laser communication optomechanical device 6 acquires information such as satellite attitude, orbit, and peer satellite position transmitted by the integrated control subsystem 5 of the satellite platform 1, and feeds back its own code disk readings, galvanometer position, CCD image, and other information to the integrated control system 5 of the satellite platform 1. The integrated control system 5 calculates and issues action commands to the laser communication optomechanical device 6. Through a series of scanning-capture-tracking processes, laser link communication between the two satellites is established.

[0045] The spatial light received by the optical telescope 10 on the laser communication optomechanical equipment 6 enters the single-mode optical fiber through the spatial optical coupling module 8, and is transmitted to the integrated modulation and demodulation communication module 4 of the satellite platform 1 through the optical fiber interface.

[0046] The optical module in the integrated modulation and demodulation communication module 4 performs photoelectric conversion, converting the optical signal sent by the laser communication optomechanical device 6 into an electrical signal. After a series of digital signal processing processes such as analog-to-digital conversion, descrambling, decoding, and framing, the receiving steps of service data and relay instructions are realized.

[0047] This embodiment integrates the power supply system, demodulation module, thermal control subsystem, and control subsystem of the laser communication payload with the relevant systems of the satellite platform, achieving an integrated spaceborne design. This reduces the laser communication payload to a single independent laser communication optomechanical device, significantly decreasing its size, weight, power consumption, and complexity. The satellite platform is transformed from a single-satellite configuration into a constellation of satellites capable of inter-satellite networking.

[0048] This embodiment integrates and reuses the power supply, signal modulation and demodulation, star sensor, and thermal control modules of the laser communication payload with relevant systems on the satellite platform. Furthermore, it improves the design of relevant subsystems on the satellite platform to meet the specific needs of the laser payload. This solves the problems of the current laser communication payload being a standalone unit, resulting in large weight, power consumption, and size; the increased attitude error due to structural transmission of platform attitude as a standalone unit, leading to increased difficulty in laser control; and the long process and low efficiency caused by multiple photoelectric conversions required for information exchange between the laser communication payload and the platform. This invention significantly reduces the size, weight, power consumption, and complexity of the laser communication payload, and transforms the satellite platform from a single satellite into a constellation of satellites with inter-satellite networking capabilities.

[0049] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A satellite platform integrating a laser communication payload, characterized in that... include: Satellite platforms and laser communication optomechanical equipment; among which, The satellite platform: preheats the laser communication optomechanical equipment to a preset temperature within a pre-defined time; after preheating, it powers on the equipment; receives the orbital information of the peer satellite at a fixed time from the ground, obtains the orbital information of the peer satellite at the link establishment time based on this information, and extrapolates this information to the laser communication optomechanical equipment; receives code disk readings, galvanometer positions, and CCD images, obtains action commands based on these data, and transmits these commands to the laser communication optomechanical equipment; receives space light, performs photoelectric conversion to obtain electrical signals, and processes these signals digitally to obtain service data and relay commands. The laser communication optomechanical equipment: after being powered on, it begins to perform self-testing and self-calibration; it receives the orbit information of the peer satellite at the moment of link establishment, and transmits the code disk reading, galvanometer position and CCD image to the satellite platform; it receives action commands and performs actions according to the action commands; It receives space light and couples it into the satellite platform via optical fiber transmission.

2. The satellite platform integrating laser communication payload according to claim 1, characterized in that: The satellite platform includes an integrated power supply system, an integrated thermal control system, an integrated modem communication module, and an integrated control subsystem; among which, The integrated thermal control system preheats the laser communication optomechanical equipment at a preset time to raise the temperature to the preset temperature. The integrated power supply system: after the laser communication optomechanical equipment has finished preheating, it powers the laser communication optomechanical equipment; The integrated control subsystem: receives the orbital information of the peer satellite at a fixed time from the ground, obtains the orbital information of the peer satellite at the link establishment time based on the orbital information of the peer satellite at a fixed time from the ground, and extrapolates the orbital information of the peer satellite at the link establishment time to the laser communication optomechanical equipment; receives code disk readings, galvanometer positions and CCD images, obtains action commands based on the code disk readings, galvanometer positions and CCD images, and transmits the action commands to the laser communication optomechanical equipment; The integrated modulation and demodulation communication module receives spatial light, performs photoelectric conversion on the spatial light to obtain an electrical signal, and processes the electrical signal through digital signal processing to obtain service data and relay instructions.

3. The satellite platform integrating laser communication payload according to claim 2, characterized in that: The laser communication optomechanical equipment includes a spatial optical coupling module and an optical telescope; wherein... The optical telescope receives space light and transmits it to the space light coupling module. The space light coupling module then couples the space light through optical fiber into the integrated modulation and demodulation communication module.

4. The satellite platform integrating laser communication payload according to claim 1 or 2, characterized in that: The preset time is 10-20 minutes.

5. The satellite platform integrating laser communication payload according to claim 1 or 2, characterized in that: The preset temperature is 20℃-25℃.

6. The satellite platform integrating laser communication payload according to claim 1 or 2, characterized in that: The extrapolation accuracy is better than 500m, and the extrapolation data frequency is greater than 4Hz.

7. The satellite platform integrating laser communication payload according to claim 1 or 2, characterized in that: Digital signal processing includes analog-to-digital conversion, descrambling, decoding, and framing.

8. The satellite platform integrating laser communication payload according to claim 1 or 2, characterized in that: The orbital information of the peer satellite at the moment of link establishment includes the satellite's attitude, orbit, and the position of the peer satellite.

9. The satellite platform integrating laser communication payload according to claim 2, characterized in that: The integrated modulation and demodulation communication module 4 includes a photoelectric conversion module and a modulation and demodulation module; wherein... The photoelectric conversion module receives spatial light, performs photoelectric conversion on the spatial light to obtain an electrical signal, and transmits the electrical signal to the modulation and demodulation module. The modulation and demodulation module receives electrical signals and processes them through digital signal processing to obtain service data and relay instructions.

10. The satellite platform integrating laser communication payload according to claim 2, characterized in that: The integrated modem communication module has a communication rate greater than 10Gbps and a large data throughput processing capability greater than 10Gbps.

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