CN109167632B - Satellite laser communication device - Google Patents
Satellite laser communication device Download PDFInfo
- Publication number
- CN109167632B CN109167632B CN201811163363.1A CN201811163363A CN109167632B CN 109167632 B CN109167632 B CN 109167632B CN 201811163363 A CN201811163363 A CN 201811163363A CN 109167632 B CN109167632 B CN 109167632B
- Authority
- CN
- China
- Prior art keywords
- light
- unit
- signal
- communication device
- laser communication
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- 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
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
Abstract
The invention discloses a satellite laser communication device which comprises an optical telescope, a shared light path unit, a first light path unit and a second light path unit, wherein a galvanometer and a spectrum spectroscope are arranged on the shared light path, the first light path unit is used for loading and modulating information to be transmitted input by a satellite platform to form signal light, the signal light is transmitted to a far mirror of the optical telescope through the spectrum spectroscope and the galvanometer in sequence and then output, the second light path unit is used for converting the signal light which is received by the far mirror of the optical telescope and then passes through the galvanometer and the spectrum spectroscope in sequence into an electric signal by an optical signal, decoding and reducing the electric signal and then transmitting the electric signal to the satellite platform. The invention provides a light and small satellite laser communication device, which solves the problems of large volume and heavy weight of the traditional device through a common light path unit, has simple structure, small volume and light weight, and is suitable for a microsatellite platform.
Description
Technical Field
The invention relates to the technical field of space laser communication, in particular to a satellite laser communication device.
Background
Laser communication refers to a process of encoding information to be transmitted, such as voice, data, images and the like, modulating the information onto an optical signal, entering a channel for transmission, and reaching a receiving end for demodulation and reduction to obtain original information.
Laser communication has the following advantages: l) the communication frequency band is wide, which is beneficial to realizing high-speed data transmission and is easy to realize the communication speed of dozens of Gbps; 2) the aperture of the antenna is small, so that the size and the weight of the communication terminal are reduced, and the requirement for carrying platform resources is reduced; 3) the divergence angle of the laser is small, so that the laser is difficult to intercept and is beneficial to the transmission of confidential information; 4) the anti-electromagnetic interference capability is strong, and is not restricted by the use of radio frequency. Therefore, laser communication is the most competitive and promising technical approach for spatial information transmission, and can meet the safe and efficient communication requirements for civil and military use.
At present, the international research on the space laser communication technology has become a popular research field, and with the satellite laser communication research as a key point, countries and regions such as the united states, europe, japan, and the like have performed a series of satellite laser communication tests and gradually enter the engineering application stage. With the development of commercial aerospace and microsatellites, on one hand, the volume, weight and power consumption of the conventional satellite laser communication device cannot meet the carrying requirements, so that the application of a laser communication load microsatellite platform is limited; on the other hand, the laser communication load device has larger volume and weight, which is not beneficial to reducing the emission cost and restricts the development of commercial aerospace. Therefore, it is of great significance to develop a light and small laser communication load device.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a satellite laser communication device, which solves the problems of large volume and heavy weight of the traditional device through a common light path unit.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
an optical telescope for transmission and reception of signal light;
the shared light path unit is provided with a galvanometer and a spectrum spectroscope;
the first light path unit is used for loading and modulating information to be transmitted input by a satellite platform to form signal light, and the signal light is transmitted to the optical telescope through the spectrum spectroscope and the galvanometer and then output;
and the second optical path unit is used for converting the signal light which is received by the optical telescope and sequentially passes through the galvanometer and the spectrum spectroscope into an electric signal from an optical signal, decoding and reducing the electric signal and transmitting the electric signal to the satellite platform.
On the basis of the above technical scheme, the satellite laser communication device further comprises a photoelectric tracking module, and the photoelectric tracking module comprises:
the periscopic servo mechanism is arranged on the optical telescope and shares an optical axis with the optical telescope;
the fine tracking unit is used for controlling the angle of the galvanometer and realizing the adjustment of the direction of the signal light received by the galvanometer;
a coarse tracking unit for controlling the periscopic servo mechanism to rotate;
and the charge coupled device CCD camera is used for receiving part of the signal light transmitted on the second light path unit, imaging the received part of the signal light and then transmitting the imaged part of the signal light to the fine tracking unit and the coarse tracking unit.
On the basis of the above technical solution, the first optical path unit includes:
the light source modulation unit is used for receiving the information input by the satellite platform, modulating the information and loading the information to a light source to form signal light;
and the optical fiber collimator is used for receiving the signal light output by the light source modulation unit, collimating and expanding the signal light beam and outputting the signal light beam.
On the basis of the above technical solution, the second optical path unit includes:
the energy spectroscope is used for receiving the signal light output by the spectrum spectroscope, reflecting and transmitting the signal light, and respectively forming reflected light and transmitted light;
an Avalanche Photodiode (APD) for receiving the reflected light output by the energy beam splitter and converting an optical signal into an electrical signal;
and the demodulation unit is used for receiving the electric signal converted by the avalanche photodiode APD, decoding and reducing the electric signal and transmitting the electric signal to the satellite platform.
On the basis of the technical scheme, the charge coupled device CCD camera is positioned below the energy spectroscope and is used for receiving the transmitted light formed after the transmission of the energy spectroscope.
On the basis of the above technical solution, the satellite laser communication device further includes a lens assembly, and the lens assembly includes:
a first lens group provided between the spectrum spectroscope and the fiber collimator, the first lens group being configured to collimate and shape the signal light transmitted from the fiber collimator to the spectrum spectroscope;
a second lens group provided between the energy beam splitter and the avalanche photodiode APD, the second lens group being configured to focus the reflected light transmitted from the energy beam splitter to the avalanche photodiode APD;
and the third lens group is arranged between the energy spectroscope and the charge coupled device CCD camera and is used for focusing the transmitted light transmitted from the energy spectroscope to the charge coupled device CCD camera.
On the basis of the above technical solution, the satellite laser communication device further includes a thermal control module, and the thermal control module includes:
the scattering surface is used for radiating the galvanometer, the light source modulation unit and the periscopic servo mechanism;
a thermistor for monitoring the temperatures of the common optical path unit, the first optical path unit, the second optical path unit, and the periscopic servo mechanism;
and an electric heater for heating the common optical path unit, the first optical path unit, the second optical path unit and the periscopic servo mechanism.
On the basis of the technical scheme, the satellite laser communication device further comprises a control module, and the control module is used for power management, thermal control management and state monitoring control management of the satellite laser communication device.
On the basis of the technical scheme, the management and control module comprises:
a power supply management and control unit for providing power supply for the satellite laser communication device;
the system management and control unit is used for monitoring the working state of the satellite laser communication device in real time and performing instruction control;
and the thermal control management and control unit is used for controlling the operation of the thermal control module.
On the basis of the technical scheme, the control module, the light source modulation unit, the demodulation unit, the fine tracking unit and the coarse tracking unit are all located in the electric cabinet.
Compared with the prior art, the invention has the advantages that:
(1) the invention provides a light and small satellite laser communication device, which divides a received signal light beam into two beams through an energy spectroscope, wherein one beam is used for communication detection, and the other beam is used for position detection, so that the satellite laser communication device can realize the functions of signal light and beacon light through a single laser; on the other hand, the device is provided with a common optical path unit, and when the device transmits and receives signals, the transmitted signals and the received signals are simultaneously transmitted in the common optical path unit, so that the optical path structure is simplified, the size of the satellite laser communication device is convenient to reduce, and the light and small design is realized.
(2) The invention provides a light and small satellite laser communication device, wherein a coarse tracking unit and a fine tracking unit share a Charge Coupled Device (CCD) camera, and the detection of coarse and fine tracking positions is realized by controlling windowing and using a single position detector; in addition, the device adopts a light source with a wave band of 780nm/850nm, so that the volume of the communication module is reduced, elements such as an optical amplifier and the like are not needed, and the volume and the weight of the satellite laser communication device can be optimized to the maximum extent by adopting the technology, thereby meeting the carrying requirement of a microsatellite.
Drawings
Fig. 1 is a block diagram of a light compact satellite laser communication device according to an embodiment of the present invention;
fig. 2 is a functional block diagram of a compact satellite laser communication device according to an embodiment of the present invention.
In the figure: the system comprises an optical telescope 1, a galvanometer 20, a spectral spectroscope 21, a photoelectric tracking module 3, a periscopic servo mechanism 30, a fine tracking unit 31, a coarse tracking unit 32, a charge coupled device CCD camera 33, a light source modulation unit 40, an optical fiber collimator 41, an energy spectroscope 50, an avalanche photodiode APD51, a demodulation unit 52, a first lens group 60, a second lens group 61, a third lens group 62, a thermal control module 7, a thermal control module 8, a power supply control unit 80, a system control unit 81 and a thermal control unit 82.
Detailed Description
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the embodiment of the invention provides a light and small satellite laser communication device, which is divided into a communication module, an optical module, a photoelectric tracking module 3, a thermal control module and a management and control module 8 according to functional modules, wherein the five modules cooperate with each other to realize the transmission and reception of satellite platform information, and the transmission and reception are generally performed simultaneously. Specifically, the communication module comprises a communication transmitting submodule and a communication receiving submodule; the optical module comprises an optical path relay sub-module and an optical telescope sub-module; the photoelectric tracking module 3 includes a coarse tracking unit 32 and a fine tracking unit 31.
As shown in fig. 2, when sending information, the communication transmitting sub-module receives a signal from the satellite platform, modulates and loads the received signal with laser to form signal light, and transmits the signal light to the optical path relay sub-module, the optical path relay sub-module performs beam expansion and collimation on the received signal light and transmits the signal light to the optical telescope, and the optical telescope performs beam expansion and collimation on the signal light, transmits the signal light to a space, outputs the signal light, and waits for a receiving party to receive the signal light. When receiving information, the optical telescope firstly receives and focuses signal light emitted by a receiver in communication cooperation with the optical telescope, then transmits the signal light to the optical path relay submodule, the optical path relay submodule reflects and transmits the signal light for light splitting, and simultaneously forms reflected light and transmitted light, wherein the reflected light enters the communication receiving submodule and then decodes the signal light to restore the original information which can be received by the satellite platform, and the transmitted light enters the coarse tracking unit and the fine tracking unit 31 for position positioning.
As shown in fig. 1-2, the communication transmitting sub-module mainly includes a light source modulation unit 40 and an optical fiber collimator 41, where the light source modulation unit 40 is specifically composed of a light source and a modulation sub-unit, and when the satellite platform needs to transmit a signal, the modulation sub-unit modulates the signal to be generated and loads the signal onto the light source, and the signal is incident on the optical fiber collimator 41 in the form of signal light. The light source is a laser emitter, and the laser emitter is a 780nm/850nm wave band laser emitter, compared with other wave bands, the laser emitter in the wave band is small in size and light in weight, and the size and the weight of the device are favorably reduced. The laser emitter is connected with the optical fiber collimator 41 through an optical fiber, and the optical fiber collimator 41 outputs the signal light through a space after receiving the signal light transmitted by the laser emitter and collimating and spreading the signal light. The light source modulation unit 40 and the optical fiber collimator 41 constitute a first optical path unit, which is mainly used for signal transmission when the device transmits a signal.
As shown in fig. 1-2, the optical module mainly includes some optical elements, a galvanometer 20, a spectrum spectroscope 21 and an energy spectroscope 50, wherein the galvanometer 20 is mainly used for fine tuning of the direction of the signal light received by the galvanometer 20, ensuring that each element in the device can accurately receive the signal light, ensuring good communication between the transmitting end and the receiving end during communication, and the galvanometer 20 is controlled by the fertilization tracking unit 31 in the device. The spectrum spectroscope 21 is mainly used for transmitting and reflecting wave bands with different wavelengths respectively, and because the device receives and transmits simultaneously when communicating, the device often adopts different wavelengths for transmitting light and receiving light when communicating, when the transmitting light passes through the spectrum spectroscope 21, the light can be reflected, the reflected light is transmitted to the vibrating mirror 20, the vibrating mirror 20 receives the signal light reflected by the spectrum spectroscope 21, the signal light is continuously transmitted to the optical telescope 1, the optical telescope 1 receives the signal light transmitted by the vibrating mirror 20, the signal light is further expanded and collimated and then transmitted through space, and the signal light is waited to be received by a receiving end.
The energy beam splitter 50 is disposed below the spectral beam splitter 21, located on a transmission optical path of the signal light passing through the spectral beam splitter 21, and located on two different optical paths with the optical fiber collimator 41. When the device receives signals, the satellite laser communication device is used as a receiving end at this time, the optical telescope 1 collects and focuses signal light emitted by the emitting end, the signal light is transmitted to the vibrating mirror 20 through space, and the vibrating mirror 20 finely adjusts the direction of the received signal light and transmits the signal light to the spectrum spectroscope 21. When the received signal light passes through the spectrum spectroscope 21, transmission occurs, so that the received signal light is prevented from entering the first light path unit for emitting the signal light, and smooth communication is ensured. The received signal light transmitted by the spectrum spectroscope 21 is transmitted to the energy spectroscope 50, the energy spectroscope 50 is mainly used for reflecting and transmitting the received signal light, after the received signal light is reflected and transmitted, the received signal light is sequentially divided into transmitted light and reflected light, the reflected light enters the communication receiving sub-module, and the transmitted light enters the photoelectric tracking and aiming module 3 to be matched with each other to complete the reception of the signal light.
As shown in fig. 1-2, the communication receiving sub-module mainly includes an avalanche photodiode APD51 and a demodulation unit 52, the avalanche photodiode APD51 is located on the optical path of the reflected light of the energy beam splitter 50, when the received signal light is reflected by the energy beam splitter 50 to form the reflected light, the avalanche photodiode APD51 receives the reflected light, converts the optical signal of the reflected light into a corresponding electrical signal, and transmits the converted electrical signal to the demodulation unit 52, and the demodulation unit 52 determines and decodes the received electrical signal to restore the original information to the satellite platform. Here, the avalanche photodiode APD51 and the demodulation unit 52 constitute a second optical path unit mainly used for signal reception and transmission operation when the apparatus receives a signal.
As shown in fig. 1 to 2, the photoelectric tracking module 3 mainly includes a fine tracking unit 31, a coarse tracking unit 32, a periscopic servo mechanism 30, and a CCD camera 33. The photoelectric tracking module 3 is mainly used for adjusting the optical path of the device when transmitting and receiving signals. When receiving information, the fine tracking unit 31 is mainly used for controlling the angle of the galvanometer 20 to realize small-angle high-precision adjustment of the direction of the signal light received by the galvanometer 20, the coarse tracking unit 32 is mainly used for controlling the rotation of the periscopic servo mechanism 30, the periscopic servo mechanism 30 is arranged on the optical telescope 1, is positioned in front of the optical telescope 1, is sleeved on the optical telescope 1 and is coaxial with the optical telescope 1, and can realize large-angle adjustment of the direction of the received signal light under the control of the coarse tracking unit 32. The CCD camera 33 is located on the light path of the transmitted light of the energy spectroscope 50, after the received signal light is transmitted through the energy spectroscope 50 to form the transmitted light, the CCD camera 33 performs imaging processing on the received transmitted light, and transmits the imaged image information to the photoelectric tracking module 3, so that position detection is realized.
Specifically, before the device receives the signal, since there may be a position deviation between the receiving end and the transmitting end, at this time, the coarse tracking unit 32 is in an on state, and the coarse tracking unit 32 controls the rotation of the periscopic servo mechanism 30 to capture the signal light. Correspondingly, when the rough tracking is performed, the CCD camera 33 is opened with a large window, the captured received signal light passes through the optical telescope 1, the galvanometer 20, the spectral beam splitter 21 and the energy beam splitter 50 in sequence and then is transmitted to the CCD camera 33, the CCD camera 33 performs low-frequency imaging processing on the received signal light and then transmits image information to the rough tracking unit 32, and the rough tracking unit 32 processes the image information to calculate the light spot miss distance. Adjusting according to the actually calculated light spot miss distance, if the miss distance exceeds the fine adjustment range, firstly, rotating the coarse tracking adjustment periscopic servo mechanism 30, and then, starting the fine tracking unit 31 to perform fine adjustment; and if the light spot miss distance is within the fine adjustment range, directly performing fine adjustment.
When fine adjustment is performed, the charge coupled device CCD camera 33 opens the small window, performs high-frequency imaging on the incident signal light, transmits image information after the high-frequency imaging to the fine tracking unit 31, calculates the spot miss amount by the fine tracking unit 31 after image processing, and controls the rotation of the galvanometer 20 according to the calculated spot miss amount, thereby achieving fine adjustment of the signal light beam direction.
According to the above, the galvanometer 20 and the spectrum spectroscope 21 constitute a common light path unit, when the device receives and emits signal light, the signal light needs to pass through the common light path unit, the emitted light and the received light sequentially enter the first light path unit and the second light path unit at the spectrum spectroscope 21, compared with the traditional device that the emitted light path and the received light path are set into two completely independent light path systems, a section of light path unit is shared for emission and reception, the light path setting of the device is greatly simplified, thereby the weight and the volume of the device are reduced, the emission cost is reduced, and the device is suitable for small and light satellites.
Furthermore, the device divides the received signal light beam into two beams through the energy spectroscope 50, one beam is used for communication, the other beam is used for position detection, so that the satellite laser communication device can simultaneously realize the functions of signal light and beacon light through a single laser, in addition, the fine tracking unit 31 and the coarse tracking unit 32 share the same Charge Coupled Device (CCD) camera 33, and the design can simplify the structure of the device per se to a great extent, so that the device has the characteristics of light and small size.
Further, the satellite laser communication device further comprises a lens assembly, wherein the lens assembly comprises three groups of lens groups, namely a first lens group 60, a second lens group 61 and a third lens group 62. The first lens group 60 is disposed between the spectrum beam splitter 21 and the fiber collimator 41, and is mainly used for collimating and shaping the signal light transmitted from the fiber collimator 41 to the spectrum beam splitter 21; the second lens group 61 is arranged between the energy beam splitter 50 and the avalanche photodiode APD51, and is mainly used for focusing the reflected light transmitted from the energy beam splitter 50 to the avalanche photodiode APD 51; the third lens group 62 is disposed between the energy beam splitter 50 and the CCD camera 33, and is mainly used for focusing the transmitted light transmitted from the energy beam splitter 50 to the CCD camera 33. The arrangement of the lens component enables signal light transmitted in the device to be more stable, mutual transmission among all components is facilitated, and smooth proceeding of communication is guaranteed.
As shown in fig. 1-2, the satellite laser communication device further includes a thermal control module 7, and the thermal control module 7 is mainly used for heating or heat dissipation of the device. Because the operating environment of the device is located in outer space, the ambient temperature is unstable, and high-temperature or low-temperature extreme environments are easy to occur, in addition, some components of the device are easy to generate heat in the operating process, if the components are not radiated in time, the components such as the spectrum spectroscope 21 and the energy spectroscope 50 can be damaged, and if the components are not radiated in time, the mirror surface can be irreversibly bent, so that the function of the device is seriously affected, and therefore, the existence of the thermal control module 7 is necessary.
The thermal control module 7 mainly comprises a scattering surface, a thermistor and an electric heater, wherein the scattering surface is mainly used for radiating the vibrating mirror 20, the light source modulation unit 40 and the periscopic servo mechanism 30, because the vibrating mirror 20 is constantly in a rotating or vibrating state, heat is easily generated, a laser transmitter in the light source modulation unit 40 easily generates heat, the periscopic servo mechanism 30 is similarly provided with a motor, high temperature can be generated after long-time operation, and the scattering surface conducts effective heat radiation on the heat sources through structural heat conduction. The thermistor is mainly used for monitoring the temperatures of the common light path unit, the first light path unit, the second light path unit and the relevant positions of the periscopic servo mechanism, and after the temperatures are fed back to the electric heater, the electric heater is used for heating the corresponding positions. Because the theoretical operating temperature of the optical module is about 20 ℃, if the temperature is too low or too high, the transmission of the signal light is affected, and the normal operation of communication is affected.
As shown in fig. 1-2, the satellite laser communication device further includes a management and control module 8, where the management and control module 8 is mainly used for power management, thermal control management, and state monitoring control management of the satellite laser communication device, and the management and control module 8 specifically includes a power management and control unit 80, a system management and control unit 81, and a thermal control management and control unit 82. The power supply control unit 80 is mainly used for providing power supply for each component of the satellite laser communication device which needs to be powered; the system management and control unit 81 is mainly used for monitoring the working state of each component of the satellite laser communication device in real time, performing instruction control on each component according to actual conditions and specific working states, and realizing the purpose of communication by mutually matching; the thermal control unit 82 is mainly used to control the operation of the thermal control module 7 and assist the thermal control module 7 in controlling the temperature of the device.
Further, the management and control module 8, the light source modulation unit 40, the demodulation unit 52, the fine tracking unit 31 and the coarse tracking unit 32 are all located in the electric cabinet, so that each unit is protected to a certain extent, and centralized management is facilitated.
To sum up, when transmitting a signal, the light source modulation unit 40 receives a signal to be transmitted by the satellite platform, modulates and loads the signal to be transmitted to the light source, and transmits the signal to the optical fiber collimator 41 in a form of signal light, after receiving the signal light transmitted by the laser transmitter, the optical fiber collimator 41 collimates and expands the signal light and outputs the signal light to the spectrum spectroscope 21 through the space, the spectrum spectroscope 21 reflects the received signal light to the galvanometer 20, the galvanometer 20 finely adjusts the direction of the received signal light under the control of the photoelectric tracking module 3 and transmits the signal light to the optical telescope 1, the optical telescope 1 receives the signal light transmitted by the galvanometer 20, and transmits the signal light through the space after further beam expansion and collimation, and waits for the receiving end to receive the signal light, and the transmission is completed. When the device transmits signal light, the signal light mainly passes through the first light path unit, the shared light path unit and the optical telescope, and the first light path unit, the shared light path unit and the optical telescope form a transmitting light path.
When receiving signals, the coarse tracking unit 32 controls the rotation of the periscopic servo mechanism 30 to capture and track signal light, the captured and tracked signal light is focused by the optical telescope 1 and then transmitted to the galvanometer 20, the galvanometer 20 finely adjusts the direction of the received signal light and then transmits the signal light to the spectral spectroscope 21, the spectral spectroscope 21 transmits the received light at the moment, the received signal light is transmitted by the spectral spectroscope 21 and then transmitted to the energy spectroscope 50, the energy spectroscope 50 reflects and transmits the received transmitted light to respectively form transmitted light and reflected light, wherein the transmitted light is transmitted to the charge coupled device CCD camera 33 for imaging processing to realize position detection, the reflected light is transmitted to the avalanche photodiode APD51, the avalanche photodiode APD51 converts the received reflected light from optical signals into electrical signals and then transmits the electrical signals to the demodulation unit 52, finally, the demodulation unit 52 determines and decodes the received electrical signal, restores the electrical signal to the original information, and transmits the original information to the satellite platform, and the reception is completed. When the device receives signal light, the signal light mainly passes through the optical telescope, the shared light path unit and the second light path unit, and the optical telescope, the shared light path unit and the second light path unit form a receiving light path.
The present invention is not limited to the above-mentioned preferred embodiments, and any other products in various forms can be obtained by anyone with the teaching of the present invention, but any changes in the shape or structure thereof, which have the same or similar technical solutions as the present invention, are within the protection scope.
Claims (8)
1. A satellite laser communication device for receiving and transmitting satellite platform information, comprising:
an optical telescope (1) for transmitting and receiving signal light;
the device comprises a common light path unit, wherein a galvanometer (20) and a spectrum spectroscope (21) are arranged on the common light path unit;
the first light path unit is used for loading and modulating information to be transmitted input by a satellite platform to form signal light, and the signal light is transmitted to the optical telescope (1) through the spectrum spectroscope (21) and the galvanometer (20) in sequence and then output;
the second optical path unit is used for enabling the received signal light of the optical telescope (1) to sequentially pass through the galvanometer (20) and the spectrum spectroscope (21), converting the signal light reflected by the energy spectroscope (50) into an electric signal from an optical signal, decoding and reducing the electric signal and transmitting the electric signal to the satellite platform;
the satellite laser communication device further comprises a photoelectric tracking module (3), wherein the photoelectric tracking module (3) comprises:
a periscopic servo mechanism (30) which is arranged on the optical telescope (1) and has a common optical axis with the optical telescope (1);
a fine tracking unit (31) for controlling the angle of the galvanometer (20) and adjusting the direction of the signal light received by the galvanometer (20);
a coarse tracking unit (32) for controlling the periscopic servomechanism (30) to rotate;
the charge coupled device CCD camera (33) is used for receiving the transmitted light transmitted by the energy spectroscope (50) on the second light path unit, imaging the received transmitted light and then transmitting the imaged transmitted light to the fine tracking unit (31) and the coarse tracking unit (32);
the second light path unit comprises an energy spectroscope (50) which is used for receiving the transmitted light output by the spectrum spectroscope (21), reflecting and transmitting the transmitted light to respectively form reflected light and transmitted light;
the CCD camera (33) is positioned below the energy beam splitter (50) and is used for receiving the transmitted light formed after the transmission of the energy beam splitter (50).
2. The satellite laser communication device according to claim 1, wherein the first optical path unit includes:
the light source modulation unit (40) is used for receiving the information input by the satellite platform, modulating the information and loading the information onto a light source to form signal light;
and the optical fiber collimator (41) is used for receiving the signal light output by the light source modulation unit (40), collimating and expanding the signal light and outputting the signal light.
3. The satellite laser communication device according to claim 2, wherein the second optical path unit further includes:
an Avalanche Photodiode (APD) (51) for receiving said reflected light output by said energy beam splitter (50) and converting an optical signal into an electrical signal;
and the demodulation unit (52) is used for receiving the electric signal converted by the avalanche photodiode APD (51), decoding and reducing the electric signal and transmitting the electric signal to the satellite platform.
4. The satellite laser communication device of claim 3, further comprising a lens assembly, the lens assembly comprising:
a first lens group (60) provided between the spectrum beam splitter (21) and a fiber collimator (41), the first lens group (60) being for collimating and shaping the signal light transmitted from the fiber collimator (41) to the spectrum beam splitter (21);
a second lens group (61) disposed between the energy beam splitter (50) and the avalanche photodiode APD (51), the second lens group (61) being for focusing the reflected light transmitted from the energy beam splitter (50) to the avalanche photodiode APD (51);
a third lens group (62) disposed between the energy beam splitter (50) and the CCD camera (33), the third lens group (62) being configured to focus the transmitted light transmitted from the energy beam splitter (50) to the CCD camera (33).
5. A satellite laser communication device according to claim 3, wherein the satellite laser communication device further comprises a thermal control module (7), the thermal control module (7) comprising:
a scattering surface for heat dissipation of the galvanometer (20), the light source modulation unit (40), and the periscopic servo mechanism (30);
a thermistor for monitoring the temperature of the common optical path unit, the first optical path unit, the second optical path unit and the periscopic servo mechanism (30);
and an electric heater for heating the common optical path unit, the first optical path unit, the second optical path unit, and the periscopic servo mechanism (30).
6. A satellite laser communication device according to claim 5, wherein: the satellite laser communication device further comprises a management and control module (8), and the management and control module (8) is used for power management, thermal control management and state monitoring control management of the satellite laser communication device.
7. The satellite laser communication device according to claim 6, wherein the management module (8) comprises:
a power supply management and control unit (80) for supplying power to the satellite laser communication device;
a system management and control unit (81) for monitoring the working state of the satellite laser communication device in real time and performing instruction control;
a thermal control management and control unit (82) for controlling the operation of the thermal control module (7).
8. A satellite laser communication device according to claim 7, wherein: the control module (8), the light source modulation unit (40), the demodulation unit (52), the fine tracking unit (31) and the coarse tracking unit (32) are all located in the electric cabinet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811163363.1A CN109167632B (en) | 2018-09-30 | 2018-09-30 | Satellite laser communication device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811163363.1A CN109167632B (en) | 2018-09-30 | 2018-09-30 | Satellite laser communication device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109167632A CN109167632A (en) | 2019-01-08 |
| CN109167632B true CN109167632B (en) | 2020-09-15 |
Family
ID=64877268
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811163363.1A Active CN109167632B (en) | 2018-09-30 | 2018-09-30 | Satellite laser communication device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109167632B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111865417A (en) * | 2019-04-24 | 2020-10-30 | 南京航星通信技术有限公司 | Satellite-ground satellite laser communication terminal facing cube star |
| CN110098874B (en) * | 2019-05-17 | 2023-12-26 | 中国科学院上海技术物理研究所 | Polarization-maintaining large-range pointing quantum communication optical device and method based on U-shaped optical path |
| CN110830116B (en) * | 2019-11-26 | 2020-12-15 | 中国电子科技集团公司第五十四研究所 | Wireless optical communication receiving/transmitting terminal and relay and time division receiving/transmitting method |
| CN113612534B (en) * | 2021-07-01 | 2022-05-20 | 中国科学院西安光学精密机械研究所 | Optical system of miniaturized space laser communication terminal and using method |
| CN114142942B (en) * | 2021-12-08 | 2023-07-14 | 长光卫星技术股份有限公司 | Large-breadth optical imaging and laser communication integrated terminal |
| CN116781168A (en) * | 2023-06-14 | 2023-09-19 | 蓝星光域(上海)航天科技有限公司 | Integrated laser communication terminal |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
-
2018
- 2018-09-30 CN CN201811163363.1A patent/CN109167632B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
Non-Patent Citations (3)
| Title |
|---|
| 星地激光通信复合轴APT系统仿真研究;杨宜等;《电子设计工程》;20131205(第23期);第27-30页 * |
| 星间激光通信技术研究;徐晓静等;《飞通光电子技术》;20020215;第2卷(第01期);第1-7页 * |
| 星间激光通信终端精跟踪性能地面测试和分析;宋义伟等;《制导与引信》;20170915(第03期);第29-33页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109167632A (en) | 2019-01-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109167632B (en) | Satellite laser communication device | |
| US6297897B1 (en) | Method and arrangement for optical information transmission via satellites | |
| US5465170A (en) | Alignment adjusting system for use in optical system of optical transceiver | |
| CN103384172A (en) | Laser wireless energy transfer communication and tracking integrating system and method | |
| CN108574533B (en) | Common-caliber laser communication optical transmitter and receiver based on optical phased array | |
| Biswas et al. | Status of NASA's deep space optical communication technology demonstration | |
| US20120002973A1 (en) | Dual band radio frequency (rf) & optical communications antenna and terminal design methodology and implementation | |
| CN108768516A (en) | The laser space communication terminal of wavelength fast tunable | |
| CN111147137A (en) | Light and small airborne high-speed laser communication method | |
| CN114142927B (en) | Beacon-free laser communication system with switchable light path and method | |
| CN102607717A (en) | Coherent detection system and method for homologous common beam of laser | |
| CN100454790C (en) | All optical satellite communication network route terminal | |
| Arimoto | Multi-gigabit free-space optical communication system with bidirectional beacon tracking | |
| Tomio et al. | Development and testing of the laser transmitter and pointing, acquisition, and tracking system for the CubeSat laser infrared crosslinK (CLICK) B/C mission | |
| US20230091751A1 (en) | Multi-link optical terabit terminal | |
| CN216391014U (en) | Beacon-free optical laser communication system | |
| CN106712846A (en) | Laser communication optical device capable of adapting to different working distances | |
| CN113296079B (en) | Remote photoelectric detection system | |
| CN114024605B (en) | Miniaturized unmanned aerial vehicle laser communication terminal | |
| Mai et al. | Wide field-of-view transceiver design for bidirectional free-space optical communication systems | |
| CN115396027A (en) | Inter-aircraft distance measurement and communication integrated device and method | |
| US20040032896A1 (en) | Miniaturized multi-functional laser resonator | |
| CN114142942A (en) | Large-breadth optical imaging and laser communication integrated terminal | |
| US7561813B2 (en) | Wide field of view heterodyne receiver | |
| CN115313128B (en) | Interference system based on multispectral mid-wave infrared picosecond all-fiber laser |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |