CN116760446A - Beacon-free inter-satellite laser terminal system suitable for space network nodes - Google Patents
Beacon-free inter-satellite laser terminal system suitable for space network nodes Download PDFInfo
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- H—ELECTRICITY
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- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
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- H04B10/50—Transmitters
- H04B10/501—Structural aspects
- H04B10/503—Laser transmitters
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- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/60—Receivers
- H04B10/66—Non-coherent receivers, e.g. using direct detection
- H04B10/69—Electrical arrangements in the receiver
- H04B10/691—Arrangements for optimizing the photodetector in the receiver
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- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
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Abstract
The invention relates to a beaconing-free inter-satellite laser terminal system suitable for a space network node, which comprises: an optical system, a PAT system, a master control and communication system and an optical amplification system; the optical system comprises a signal receiving and transmitting optical path and a CCD, and realizes space light emission and receiving, photoelectric conversion and receiving detection; the PAT system comprises a coarse sighting subsystem and a fine sighting subsystem, receives instructions of a main control and communication system, performs two-dimensional rotation, and realizes sighting, capturing and tracking control of space beam transceiving between the laser communication terminals between satellites through control and decoupling; the main control and communication system performs main time sequence and logic control, coarse aiming and fine aiming control and high-speed communication signal processing, and simultaneously performs communication data receiving and transmitting through a platform data bus. The invention is suitable for the non-beacon inter-satellite laser terminal system of the space network node, eliminates the special beacon light, adopts the signal light to simultaneously realize the capturing, tracking and communication of the laser terminal, reduces the weight and the power consumption of the whole machine, simplifies the processing difficulty and increases the reliability.
Description
Technical Field
The invention relates to a beaconing-free inter-satellite laser terminal system suitable for a space network node, and belongs to the technical field of space information communication.
Background
The space information network is a network system which takes a space platform (such as a synchronous satellite or a medium-low orbit satellite, a stratosphere balloon, a manned or unmanned plane and the like) as a carrier to acquire, transmit and process space information in real time. The space information network can support high-dynamic and broadband real-time transmission of earth observation downwards and ultra-long-distance and large-time reliable transmission of deep space exploration upwards while serving important applications such as ocean navigation, emergency rescue, navigation positioning, air transportation, aerospace measurement and control and the like, so that human science, culture and production activities are expanded to space, ocean and even deep space.
The development of the current space information network presents the characteristic of 'weak sky and strong earth', and with the rapid development of Beidou satellite navigation systems, high-resolution earth observation systems and broadband satellite communication, the establishment of a high-speed transmission and high-precision ranging subsystem between satellites is urgently required to be ensured. The space laser technology is a transmission mode which uses laser as an information terminal for transmitting an information carrier to finish high-speed communication, high-precision ranging, long-distance transmission, strong interference resistance and strong interception resistance, and is very suitable for links such as deep space, interstellar, star-ground, space-to-space, space-to-ground and the like.
When the laser terminal transmits, the accurate aiming, capturing and tracking of the light beam are required to be realized over thousands of kilometers, and high requirements are put on the design of a PAT (Pointing, capturing and tracking) system. For the traditional scheme, four light paths of beacon transceiving and signal transceiving are generally designed. The beacon laser with a large beam divergence angle is used for realizing rapid capturing and tracking maintenance of a laser link; and the narrow beam of scattered angle communication light is used for realizing the transmission of the laser terminal after the link is established. The multi-optical path design results in higher optical complexity and requires precise control over different axiality and thermal control accuracy. The beacon laser and the beacon light receiving and transmitting path of each laser terminal all need to occupy certain volume and power consumption. In order to realize constellation networking, four laser terminals are required to be carried on each satellite platform currently, so that the laser terminals bring greater weight and power consumption pressure to the satellite platforms.
Along with the development of laser transmission technology, the improvement of communication rate, the improvement of ranging accuracy and the requirements on miniaturization and light weight of terminals, the whole trend is that the beam width of beacon light is continuously reduced and the transition from beacon capturing to non-beacon capturing is carried out, so that the weight and the power consumption of the whole machine are reduced, the complexity of an optical system is simplified, and the installation and adjustment are easy.
Disclosure of Invention
The invention solves the problems that: the invention provides a beacon-free inter-satellite laser terminal system suitable for space network nodes, which cancels special beacon light, adopts signal light to simultaneously realize capturing, tracking and communication of a laser terminal, reduces the weight and the power consumption of the whole machine, simplifies the processing difficulty of an optical system and increases the reliability.
The technical scheme adopted by the invention is as follows:
a beaconing-free inter-satellite laser termination system for a spatial network node, comprising: an optical system, a PAT system, a master control and communication system and an optical amplification system;
the optical system comprises a signal receiving and transmitting optical path and a CCD unit, and realizes space light emission and receiving, photoelectric conversion and receiving detection;
the PAT system comprises a coarse sighting subsystem and a fine sighting subsystem, receives instructions of a main control and communication system, performs two-dimensional rotation, and realizes accurate sighting, capturing and tracking control of space beam transceiving between the laser communication terminals between satellites through control and decoupling of the coarse sighting subsystem and the fine sighting subsystem;
the main control and communication system performs main time sequence and logic control, coarse and fine aiming control, high-speed communication signal processing, working mode control, ephemeris and inertial navigation data injection, and simultaneously performs communication data receiving and transmitting through a platform data bus;
in the communication receiving process, the main control and communication system converts the received signal light into an electric signal and processes the electric signal, and then the electric signal is sent to the satellite platform main control through a data bus; in the communication transmitting process, the main control and communication system receives satellite platform communication data, modulates the satellite platform communication data to a signal light source, sends the satellite platform communication data to the optical amplification system and the optical system through optical fibers to form space beam transmission, and the optical amplification system performs power amplification on signal receiving and transmitting light and feeds received and transmitted light signals into the main control and communication system and the optical system respectively.
Furthermore, the optical system is matched with the PAT system to perform space aiming in the azimuth and pitching angle directions so as to realize the coverage of the laser beam on the angular variation range; the optical system comprises a primary mirror, a secondary mirror and an optical substrate;
the primary mirror and the secondary mirror are used for realizing the caliber beam expansion of the small caliber beam on the optical substrate, and the CCD unit and the fine sighting telescope of the PAT system are both arranged on the optical substrate;
the optical substrate collimates and combines the emitted signal light and the emitted beacon light, splits the received signal light and the received beacon light after passing through the optical antenna, respectively converges the received signal light and the received beacon light to the CCD unit and the signal receiving optical fiber, and deflects the emitted and received light beams through the fine sighting telescope to realize the beam combination and beam splitting of the emitted and received light beams.
Further, the optical system directly captures and tracks the signal light with 1550nm wave band.
Further, the optical system adopts an antenna structure in the form of a Cassegrain plus lens with a composite receiving and transmitting aperture.
Further, the optical substrate comprises a first fine sighting telescope, a second fine sighting telescope, a first lens group, a second lens group, a first spectroscope, a second spectroscope and a third lens group;
the first fine sighting telescope is a tracking fine sighting telescope, the second fine sighting telescope is a fine sighting telescope which is aligned in advance, and the signal light is emitted: after the light emitted by the emitting optical fiber is expanded through the first lens group, the light passes through the second fine sighting telescope, the first spectroscope and the first fine sighting telescope, and the primary and secondary mirrors are converted into space light for emission;
for the received signal light, after the space light is combined by the primary mirror and the secondary mirror, the space light is precisely regulated by the first fine sighting telescope, is transmitted and received by the first spectroscope and isolated, and is divided into two paths by the second spectroscope; the main path after light splitting is coupled into a single-mode optical fiber through the second lens group to finish signal light receiving, and the branch path is coupled into a 1550 nm-band CCD unit through the third lens group to realize capturing and tracking of signal light.
Further, the coarse aiming subsystem includes: the device comprises a controller, a PWM power amplifier driver, a permanent magnet synchronous motor and a photoelectric encoder;
the incident light firstly enters a CCD unit for image decoding, and the generated image data is sent to an upper computer through a serial bus; after the upper computer receives the image data, the target position data of the azimuth axis and the pitching axis are calculated respectively by combining the satellite attitude data and the ephemeris, and the target position data are sent to the controllers of the two axes respectively; meanwhile, the actual position data of the two-dimensional turntable measured by the photoelectric encoder is also sent to the controllers of the two shafts; the controller calculates corresponding control quantity after receiving the target position data and the actual position data, and drives the permanent magnet synchronous motor to drive the two-dimensional turntable to point to the target position through the PWM power amplifier, so that the control of the two-dimensional turntable is completed.
Further, the fine sighting subsystem comprises a galvanometer, a lens, a detector and a transimpedance amplifier; the light beam is deflected by the inclined vibrating mirror, converged by the lens and reaches the photosensitive surface of the detector, at the moment, the light spot signals are converted into four paths of photocurrent output by four quadrants of the detector, and then the four paths of photocurrent output are converted into voltage signals by the transimpedance amplifier.
Further, the CCD unit is a single detector scheme, namely the CCD unit comprises a CCD detector and a signal processing unit; the signal processing unit comprises an upper computer RAM and an ADC chip;
the CCD detector detects and receives the light image information, and outputs the light image information after being converted by the multipath parallel ADC chips; the main control and communication system configures a register using a CCD detector through an upper computer RAM, sets a frame frequency and captures window information; and the RAM of the upper computer processes the image information returned by the CCD detector to obtain spot position information and sends the spot position information to the main control and communication system.
Furthermore, the optical amplification system is realized by adding a front-end optical fiber in front of the receiving end so as to improve the sensitivity of the whole machine, and the front-end optical fiber is a single-mode optical fiber so as to realize front-end amplification.
Further, the single mode optical fiber adopts the specification of 9 μm.
Compared with the prior art, the invention has the advantages that:
(1) The invention provides a beacon-free inter-satellite laser terminal system suitable for a space network node, which is suitable for the beacon-free inter-satellite laser terminal system of the space network node, eliminates special beacon light, adopts signal light to simultaneously realize capturing, tracking and communication of a laser terminal, reduces the weight and the power consumption of the whole machine, simplifies the processing difficulty of an optical system and increases the reliability.
(2) The invention provides a beaconing-free inter-satellite laser terminal system suitable for a space network node, a catch-and-follow optical path adopts a 1550nm wave band CCD single detector scheme to detect a receiving light beam, and a CCD unit is divided into two parts: the CCD detector is the CCD detector, and the signal processing unit is based on the FPGA and the ADC.
(3) The invention provides a beaconing-free inter-satellite laser terminal system suitable for space network nodes, which has the characteristics of large data volume, heavy operation load and the like, and adopts an ARM processor, thereby not only meeting the operation requirement, but also reducing the size of the system and miniaturizing the system
(4) The invention provides a beaconing-free inter-satellite laser terminal system suitable for a space network node, which is characterized in that a low-noise optical amplifier (EDFA) is added at a receiving end and a transmitting end for improving receiving and transmitting sensitivity, and a single-mode fiber technology with smaller core diameter is adopted for coupling.
(5) The large-scale constellation networking is developed in a high-density, medium-low-orbit and high-density mode, the number of satellites is huge, and the mode of one arrow and multiple satellites is adopted when the satellites are transmitted, so that strict limits are put on the weight and the power consumption of each satellite. For the inter-satellite laser terminal, the beacon light laser and related devices are omitted, so that the quality is reduced, the power consumption is reduced, communication beams are directly adopted for capturing, the vibrating mirror is matched with the servo turntable to perform scanning operation, coverage of an uncertain region is realized, and the comprehensive performance of the system is improved.
Drawings
FIG. 1 is a block diagram of an inter-satellite laser terminal;
FIG. 2 is a schematic diagram of an optical system;
FIG. 3 is a block diagram of an antenna in the form of a transceived compound common bore Cassegrain plus lens;
FIG. 4 is a schematic diagram of a beaconing-free optical substrate;
FIG. 5 is a schematic diagram of a coarse targeting device;
FIG. 6 is a schematic diagram of a fine aiming device;
FIG. 7 is a block diagram of a CCD detection unit;
FIG. 8 is a schematic diagram of a single mode fiber coupling unit.
Detailed Description
As shown in fig. 1, the present invention provides a beaconing-free inter-satellite laser terminal system applicable to a spatial network node, which includes: optical system, PAT system, master control and communication system, optical amplification system. The red part of the dotted line frame, namely the beacon light receiving and transmitting path and the beacon laser, is a part which is different in hardware between a beaconing-free inter-satellite laser terminal system and a traditional beaconing inter-satellite laser terminal system, and the beacon light receiving and transmitting path, the laser and the accessory device are omitted, so that the weight and the power consumption are reduced.
As shown in fig. 1, the optical system includes a signal receiving and transmitting optical path and a CCD unit, and the optical system implements functions such as spatial light emission and reception, photoelectric conversion, reception detection, and the like. The PAT system comprises a coarse aiming subsystem and a fine aiming subsystem, receives instructions of a main control and communication system, performs two-dimensional rotation, and realizes accurate aiming, capturing and tracking control of space beam receiving and transmitting between the laser communication terminals between satellites through control and decoupling of the coarse and fine subsystems. The main control and communication system performs main time sequence and logic control, coarse and fine aiming control, high-speed communication signal processing, various working mode control, ephemeris and inertial navigation data injection of the product, and simultaneously performs communication data receiving and transmitting through a platform data bus.
In the communication receiving process, the main control and communication system converts the received signal light into an electric signal and processes the electric signal, and then the electric signal is sent to the satellite platform main control through a data bus; in the communication transmitting process, the main control and communication system receives satellite platform communication data, modulates the satellite platform communication data to a signal light source, sends the satellite platform communication data to an optical amplifying system and an optical system through an optical fiber to form a space beam transmitting optical amplifying system to amplify power of receiving and transmitting signal light, and feeds received and transmitting optical signals into a control and communication subsystem and the optical system respectively.
Module 1: the optical system realizes the functions of space light emission and receiving, photoelectric conversion, receiving detection and the like
In the inter-satellite laser communication terminal, an optical system is matched with a PAT system to perform space aiming in the azimuth and pitching angle directions so as to realize the coverage of the laser beam on the angular variation range. The optical system mainly comprises a primary mirror, a secondary mirror and an optical substrate, as shown in fig. 2.
1) The primary and secondary mirrors are used for realizing aperture beam expansion of small-aperture light beams on an optical substrate, and the invention adopts an antenna structure in the form of a Cassegrain plus lens with a composite receiving and transmitting aperture, as shown in fig. 3, and the main functions comprise: the beam divergence angle of the output beam is compressed, the gain of the transmitting antenna is improved, the effective caliber of the receiving system is increased, and the gain of the receiving antenna is improved.
2) The optical substrate comprises a receiving and transmitting optical path lens group, a light splitting and light filtering sheet and carries a fine sighting telescope for receiving the CCD and the PAT system. The main functions include: the method comprises the steps of collimating and beam-combining the transmitted signal light and the transmitted beacon light, splitting the received signal light and the received beacon light which pass through the optical antenna, converging the split beams to the CCD and the signal receiving optical fiber respectively, and turning the transmitted and received light beams through the fine sighting telescope to realize the beam-combining and beam-splitting of the transmission and the reception.
The invention adopts 1550nm wave band signal light to directly capture and track, adopts light splitting in the terminal to respectively capture and communicate, and adopts CCD single detector scheme to detect the receiving light beam. The volume and the power consumption of the terminal are effectively reduced, so that the miniaturization of the terminal is realized, and the terminal is easy to process and install. The specific design is shown in fig. 4.
The fine sighting telescope 1 is a tracking fine sighting telescope, and the fine sighting telescope 2 is an advanced alignment fine sighting telescope. For the emission signal light: after the beam of the emitted light of the emitting optical fiber is expanded through the lens group 1, the emitted light passes through the fine sighting telescope 2, the spectroscope 1 and the fine sighting telescope 1, and the primary and secondary mirrors are converted into space light for emission. For the received signal light, after the space light is combined by the primary mirror and the secondary mirror, the space light is accurately regulated by the fine sighting telescope 1, is transmitted and received by the light splitting sheet 1 and is separated into two paths by the light splitting sheet 2. The main path after light splitting is coupled into a single mode fiber through a lens group 2 to finish signal light receiving, and the branch path is coupled into a 1550nm wave band CCD through a lens group 3 to realize capturing and tracking of signal light. The main path and the branch path should have a proper light splitting ratio, and the power of the optical link of the received signal and the detection sensitivity of the CCD in 1550nm wave band should be considered in the specific design. In order to ensure the quality of the received signals, the receiving and transmitting isolation degree of the signals needs to be more than 100dB, and the isolation is realized mainly through an optical filter and different receiving and transmitting bands.
Module 2: the PAT system comprises a coarse aiming subsystem and a fine aiming subsystem, and the precise aiming, capturing and tracking control of the space beam receiving and transmitting between the inter-satellite laser communication terminals is realized through the control and the decoupling of the coarse and the fine subsystems.
The PAT system receives the instruction of the main control and communication system, and aims, captures and tracks the space light through coarse and fine two-stage compound control.
1) The rough sighting device comprises: the two-axis controller, the PWM power amplifier drive, the permanent magnet synchronous motor and the photoelectric encoder (the photoelectric encoder adopts a digital angle measuring device integrating light, machine and electricity), and the process of converting the rotating angle of a mechanical axis into digital quantity is realized by adopting a circular grating moire fringe and photoelectric conversion technology. The coarse aiming subsystem has low control bandwidth, can realize wide-range scanning and coarse pointing, and is used for initial acquisition and track control tracking.
The incident light firstly enters a CCD processor to perform image decoding, and the generated image data is sent to an upper computer through a serial bus; after the upper computer receives the image data, the target position data of the azimuth axis and the pitching axis are calculated respectively by combining the satellite attitude data and the ephemeris, and the target position data are sent to the controllers of the two axes respectively; meanwhile, the actual position data of the two-dimensional turntable measured by the photoelectric encoder is also sent to the controllers of the two shafts; after receiving the target position data and the actual position data, the controller calculates corresponding control quantity by utilizing a reasonable control algorithm, and drives the permanent magnet synchronous motor to drive the two-dimensional turntable to point to the target position through the PWM power amplifier, so that the control of the two-dimensional turntable is completed, as shown in fig. 5.
2) The fine sighting device comprises: the fine sighting device of the present invention is constituted as shown in fig. 6, and the light beam passes through a series of optical devices, is deflected by a fast tilting galvanometer, and is converged by a lens to reach the photosensitive surface of the detector. At this time, the four quadrants of the detector convert the light spot signals into four paths of photocurrent output, and then convert the four paths of photocurrent output into voltage signals through a transimpedance amplifier.
3) The beaconing-free tracking system relies on a Charge Coupled Detector (CCD) single detector to perform the receive path angle measurement. The single detector scheme adopts a method for decoupling CCD position information and simultaneously controls a coarse loop and a fine loop. To reduce the complexity of the circuit system, the project adopts a single detector scheme. The CCD unit is divided into two parts: the CCD detector is a signal processing unit based on the RAM and the ADC. The CCD unit detects and receives the light image information, and outputs the light image information after being converted by the multipath parallel ADC chips. The main control configures a register using a CCD chip through an upper computer RAM, and sets information such as frame frequency, capture window and the like. The RAM of the upper computer processes the image information returned by the CCD sensor to obtain spot position information, and sends the spot position information to the master control and communication system, as shown in fig. 7.
Module 3: the main control and communication system performs main time sequence and logic control, coarse and fine aiming control, high-speed communication signal processing, various working mode control, ephemeris and inertial navigation data injection of the product, and simultaneously performs communication data receiving and transmitting through a platform data bus;
for the main control and communication system, in the process of communication receiving, the main control and communication system converts received signal light into electric signals and processes the electric signals, and then the electric signals are sent to the satellite platform main control through a data bus; in the communication transmitting process, the main control and communication system receives the main control communication data of the satellite platform, modulates the main control communication data to a signal light source, and transmits the main control communication data to the optical amplifying system and the optical system through optical fibers to form space beam transmission. The photoelectric detector module (adopting 1550nm wave band signal light to conduct analysis) of the main control and communication system and the two fine sighting mirrors of the PAT system are both positioned in the optical system.
Module 4: the optical amplification system performs power amplification on the transmit-receive signal light and feeds the receive and transmit optical signals into the control and communication and system and the optical system, respectively.
For low-speed short-distance laser communication, a receiving end pre-amplifier does not need to be added, and a light spot is directly coupled into a 62.5-mu m-diameter single-mode fiber. Because the end face of the optical fiber is large, the coupling control difficulty is low, but the sensitivity of the whole machine is insufficient for the satellite laser communication terminal to develop in the directions of light and small size, high speed and long distance. The pre-optical fiber is realized by adopting a single-mode fiber, the main function is to realize pre-amplification, and the invention adopts a single-mode fiber with the diameter of 9 mu m, as shown in figure 8. The invention is not described in detail in the field of technical personnel common knowledge.
Claims (10)
1. A beaconing-free inter-satellite laser termination system for a spatial network node, comprising: an optical system, a PAT system, a master control and communication system and an optical amplification system;
the optical system comprises a signal receiving and transmitting optical path and a CCD unit, and realizes space light emission and receiving, photoelectric conversion and receiving detection;
the PAT system comprises a coarse sighting subsystem and a fine sighting subsystem, receives instructions of a main control and communication system, performs two-dimensional rotation, and realizes accurate sighting, capturing and tracking control of space beam transceiving between the laser communication terminals between satellites through control and decoupling of the coarse sighting subsystem and the fine sighting subsystem;
the main control and communication system performs main time sequence and logic control, coarse and fine aiming control, high-speed communication signal processing, working mode control, ephemeris and inertial navigation data injection, and simultaneously performs communication data receiving and transmitting through a platform data bus;
in the communication receiving process, the main control and communication system converts the received signal light into an electric signal and processes the electric signal, and then the electric signal is sent to the satellite platform main control through a data bus; in the communication transmitting process, the main control and communication system receives satellite platform communication data, modulates the satellite platform communication data to a signal light source, sends the satellite platform communication data to the optical amplification system and the optical system through optical fibers to form space beam transmission, and the optical amplification system performs power amplification on signal receiving and transmitting light and feeds received and transmitted light signals into the main control and communication system and the optical system respectively.
2. A beaconing-free inter-satellite laser termination system for a spatial network node according to claim 1, wherein: the optical system is matched with the PAT system to perform space aiming in the azimuth and pitching angle directions so as to realize the coverage of the laser beam on the angular variation range; the optical system comprises a primary mirror, a secondary mirror and an optical substrate;
the primary mirror and the secondary mirror are used for realizing the caliber beam expansion of the small caliber beam on the optical substrate, and the CCD unit and the fine sighting telescope of the PAT system are both arranged on the optical substrate;
the optical substrate collimates and combines the emitted signal light and the emitted beacon light, splits the received signal light and the received beacon light after passing through the optical antenna, respectively converges the received signal light and the received beacon light to the CCD unit and the signal receiving optical fiber, and deflects the emitted and received light beams through the fine sighting telescope to realize the beam combination and beam splitting of the emitted and received light beams.
3. A beaconing-free inter-satellite laser termination system for use in a spatial network node according to claim 2, wherein: the optical system adopts 1550nm wave band signal light to directly capture and track.
4. A beaconing-free inter-satellite laser termination system for use in a spatial network node according to claim 2, wherein: the optical system adopts an antenna structure in the form of a Cassegrain plus lens with a receiving-transmitting composite common caliber.
5. A beaconing-free inter-satellite laser termination system for use in a spatial network node according to claim 2, wherein: the optical substrate comprises a first fine sighting telescope, a second fine sighting telescope, a first lens group, a second lens group, a first spectroscope, a second spectroscope and a third lens group;
the first fine sighting telescope is a tracking fine sighting telescope, the second fine sighting telescope is a fine sighting telescope which is aligned in advance, and the signal light is emitted: after the light emitted by the emitting optical fiber is expanded through the first lens group, the light passes through the second fine sighting telescope, the first spectroscope and the first fine sighting telescope, and the primary and secondary mirrors are converted into space light for emission;
for the received signal light, after the space light is combined by the primary mirror and the secondary mirror, the space light is precisely regulated by the first fine sighting telescope, is transmitted and received by the first spectroscope and isolated, and is divided into two paths by the second spectroscope; the main path after light splitting is coupled into a single-mode optical fiber through the second lens group to finish signal light receiving, and the branch path is coupled into a 1550 nm-band CCD unit through the third lens group to realize capturing and tracking of signal light.
6. A beaconing-free inter-satellite laser termination system for a spatial network node according to claim 1, wherein: the coarse sighting subsystem comprises: the device comprises a controller, a PWM power amplifier driver, a permanent magnet synchronous motor and a photoelectric encoder;
the incident light firstly enters a CCD unit for image decoding, and the generated image data is sent to an upper computer through a serial bus; after the upper computer receives the image data, the target position data of the azimuth axis and the pitching axis are calculated respectively by combining the satellite attitude data and the ephemeris, and the target position data are sent to the controllers of the two axes respectively; meanwhile, the actual position data of the two-dimensional turntable measured by the photoelectric encoder is also sent to the controllers of the two shafts; the controller calculates corresponding control quantity after receiving the target position data and the actual position data, and drives the permanent magnet synchronous motor to drive the two-dimensional turntable to point to the target position through the PWM power amplifier, so that the control of the two-dimensional turntable is completed.
7. A beaconing-free inter-satellite laser termination system for a spatial network node according to claim 6, wherein: the fine sighting subsystem comprises a galvanometer, a lens, a detector and a transimpedance amplifier; the light beam is deflected by the inclined vibrating mirror, converged by the lens and reaches the photosensitive surface of the detector, at the moment, the light spot signals are converted into four paths of photocurrent output by four quadrants of the detector, and then the four paths of photocurrent output are converted into voltage signals by the transimpedance amplifier.
8. A beaconing-free inter-satellite laser termination system for a spatial network node according to claim 1, wherein: the CCD unit is a single detector scheme, namely the CCD unit comprises a CCD detector and a signal processing unit; the signal processing unit comprises an upper computer RAM and an ADC chip;
the CCD detector detects and receives the light image information, and outputs the light image information after being converted by the multipath parallel ADC chips; the main control and communication system configures a register using a CCD detector through an upper computer RAM, sets a frame frequency and captures window information; and the RAM of the upper computer processes the image information returned by the CCD detector to obtain spot position information and sends the spot position information to the main control and communication system.
9. A beaconing-free inter-satellite laser termination system for a spatial network node according to claim 1, wherein: the optical amplification system is realized by adding a front-end optical fiber in front of the receiving end so as to improve the sensitivity of the whole machine, and the front-end optical fiber is a single-mode optical fiber so as to realize front-end amplification.
10. A beaconing-free inter-satellite laser termination system for use with a spatial network node according to claim 9, wherein: the single mode optical fiber adopts the specification of 9 mu m.
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