CN114189284B - On-orbit self-calibration device and calibration method of satellite-borne laser communication machine - Google Patents
On-orbit self-calibration device and calibration method of satellite-borne laser communication machine Download PDFInfo
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- CN114189284B CN114189284B CN202210141497.3A CN202210141497A CN114189284B CN 114189284 B CN114189284 B CN 114189284B CN 202210141497 A CN202210141497 A CN 202210141497A CN 114189284 B CN114189284 B CN 114189284B
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Abstract
The invention discloses an on-orbit self-calibration device of a satellite-borne laser communication machine and a calibration method thereof. The optical switch is opened to the receiving light path or the transmitting light path in sequence, and then the optical switch is reflected to the receiving light path through the pyramid to detect the optical power and the tracking light path to detect and compensate the centroid position of the light spot, so that the coaxial self-calibration of the receiving light path, the transmitting light path and the tracking light path is realized. The invention improves the tracking precision and the link transmission efficiency, and reduces the difficulty and the accuracy of debugging the laser communication machine when the satellite operates in orbit.
Description
Technical Field
The invention belongs to the technical field of satellite-borne laser communication equipment, and relates to an on-orbit self-calibration device of a satellite-borne laser communication machine and a calibration method of the self-calibration device.
Background
The spatial laser communication is a communication method for realizing wireless transmission of information such as voice, data, images and the like in a space by using laser as an information carrier and using the atmosphere as a transmission channel. The broadband wireless access method has the characteristics of optical fiber communication and microwave communication, also conforms to the development trend of satellite miniaturization and light weight under the communication performance of high communication rate, large communication capacity, strong anti-interference capability and strong anti-interception capability, becomes a novel broadband wireless access mode with great potential, and has great application requirements and wide application prospects in military and civil communication fields such as large-capacity and confidential satellite communication, local bandwidth access and the like.
With the rapid expansion and development of the international aerospace and aviation technology field, the research and breakthrough of the space laser communication technology are more and more emphasized by all countries in the world, and a series of research plans and project plans are successively started for better promoting the technology and rapidly occupying the international market, particularly developed countries such as the United states, Europe, Japan, Russia and the like, so that laser communication systems and communication terminals with different purposes, different types and different performances are respectively developed. China also struggles to pursue, starts to perform various space laser communication experiments, and obtains good results. However, in the satellite launching process, due to the influences of violent vibration of the rocket launching thruster, gravity release after entering a near-earth space and the like, when the satellite-borne laser communication machine runs in an orbit, a certain amount of deviation can be generated on the optical axes of the receiving light path, the tracking light path and the launching light path of the laser communication machine which are originally calibrated on the ground. In such ultra-long distance spatial communication, the very small deviation in the calibration of the transmitted and received light beams is amplified with the distance, which will seriously affect the efficiency and stability of the optical link, thereby increasing the difficulty in establishing the optical communication link between the satellites. At present, a satellite-borne laser communication terminal and a ground optical antenna are generally adopted to align and calibrate, and off-axis quantity of a receiving and transmitting optical axis is found out to carry out algorithm correction, however, the method is difficult to debug, beacon light and an optical system thereof are generally required to assist in pre-calibration, the adjustment period is long, and the position of the off-axis quantity is difficult to quickly and accurately position. Therefore, it is necessary to invent a device and a method for realizing on-orbit self-calibration of the beacon-free optical satellite-borne laser communication machine.
Disclosure of Invention
The invention aims to provide an on-orbit self-calibration device and an on-orbit self-calibration method of a satellite-borne laser communication machine, aiming at the defects of the prior art, the on-orbit self-calibration of a beacon-free optical satellite-borne laser communication machine can be realized, and the problems of high satellite-ground calibration difficulty and long calibration time of the conventional base number are solved.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the first aspect of the embodiment of the invention provides an on-orbit self-calibration device of a satellite-borne laser communication machine, which comprises a laser, an optical fiber isolator, an optical switch, a first optical fiber coupler, a communication receiving end, a receiving optical fiber, a receiving lens group, a beam splitter, a reflector, a tracking detector, a tracking lens group, a color separation film, a first fast reflector, a secondary mirror, a primary mirror, a two-dimensional swing mirror, a pyramid, a second fast reflector, an emission lens group, an emission optical fiber, a high-power amplifier, a second optical fiber coupler and a communication emission end, wherein the optical fiber isolator is arranged on the first optical fiber coupler; the laser transmits laser to two paths through the optical fiber isolator and the optical switch, and one path of laser sequentially passes through the first optical fiber coupler, the receiving optical fiber, the receiving lens group, the beam splitter, the reflector, the color separation sheet transmission, the first fast reflector, the secondary mirror, the primary mirror and the two-dimensional swinging mirror to reach the pyramid; the other path of laser sequentially passes through a second optical fiber coupler, a high-power amplifier, an emission optical fiber, an emission lens group, a second fast reflecting mirror and a color separation sheet to reach the first fast reflecting mirror; and the other ports of the beam combining ends of the first optical fiber coupler and the second optical fiber coupler are respectively connected with the communication receiving end and the communication transmitting end.
Furthermore, the pyramid realizes total reflection of incident light rays through angle control of the two-dimensional swing mirror; when the angle condition of the pyramid total reflection tolerance is met, the pyramid is in a total reflection open state; and when the angle condition of the total reflection tolerance of the pyramid is not met, the pyramid is in a total reflection closed state.
Further, when the pyramid is in a fully-reflecting open state, and the optical switch is communicated with the receiving light path, the optical switch is connected with the first optical fiber coupler, laser emitted by the laser is emitted to the receiving optical fiber through the optical fiber isolator, the optical switch and the first optical fiber coupler, and then is incident to the pyramid for reflection through the receiving lens group, the beam splitter, the reflector, the color separation sheet, the first fast reflection mirror, the secondary mirror, the primary mirror and the two-dimensional swing mirror in sequence, and then is divided into two beams through the two-dimensional swing mirror, the primary mirror, the secondary mirror, the first fast reflection mirror, the color separation sheet and the reflector to the beam splitter in sequence, one beam is focused through the tracking lens group to enter the tracking detector, and the other beam is focused and coupled to the receiving optical fiber through the receiving lens group and then reversely enters the communication receiving end through the first optical fiber coupler.
Further, when the pyramid is in a fully-reflecting open state, and the optical switch is communicated with the emission light path, the optical switch is connected with the second optical fiber coupler, laser emitted by the laser passes through the optical fiber isolator, the optical switch, the second optical fiber coupler and the high-power amplifier to be emitted to the emission optical fiber, then passes through the emission lens group and the second fast reflector to be reflected by the color separation sheet, then passes through the first fast reflector, the secondary mirror, the primary mirror and the two-dimensional oscillating mirror to be incident to the pyramid for reflection, then passes through the two-dimensional oscillating mirror, the primary mirror, the secondary mirror, the first fast reflector, the color separation sheet and the reflector to be separated into two beams by the beam splitter, one path of the laser passes through the tracking lens group for focusing and enters the tracking detector, and the other path of the laser passes through the receiving lens group for focusing and coupling to the receiving optical fiber and then reversely passes through the first optical fiber coupler to enter the communication receiving end.
Furthermore, the cone adopts an inner circular cone with the light transmission caliber of 12.5 mm-75 mm, the light transmission caliber of the cone is less than or equal to the caliber of the optical antenna, and the comprehensive angular difference of the cone is less than 1.5'; and the reflecting surface of the pyramid gold-plated film is coated with black finish paint.
Furthermore, the communication receiving end comprises a tracking system; the tracking and aiming system is used for monitoring power, extracting and processing a light spot mass center, and controlling pitching and deflecting angles of the first fast reflecting mirror, the second fast reflecting mirror and the two-dimensional swinging mirror.
Further, the secondary mirror 14 and the primary mirror 15 constitute a transmitting-receiving common-aperture optical antenna, and may be arranged in an off-axis optical antenna or a coaxial optical antenna manner. .
Further, the tracking detector is a CCD detector or a four-quadrant photoelectric detector.
Furthermore, the tracking and aiming system comprises a power detection module, a light spot mass center extraction module, a first fast reflecting mirror control module, a second fast reflecting mirror control module and a two-dimensional oscillating mirror control module which are respectively connected with the first optical fiber coupler, the tracking and aiming detector, the first fast reflecting mirror, the second fast reflecting mirror and the two-dimensional oscillating mirror.
The second aspect of the embodiment of the invention provides an on-orbit self-calibration method of a satellite-borne laser communication machine, which comprises the following steps:
and step S1, setting initial parameters of the track self-calibration device, calibrating the coordinates of the centroid of the light spot of the tracking and aiming system before laser emission, determining the initial value of power, turning on the laser, and setting the pyramid to be in a total reflection opening state.
Step S2, an optical switch is opened to a first optical fiber coupler, laser emitted by the laser is transmitted to a receiving optical fiber through an optical fiber isolator, the optical switch and the first optical fiber coupler, and then is sequentially transmitted through a receiving lens group, a beam splitter, a reflector, a color separation sheet, a first fast reflection mirror, a secondary mirror, a primary mirror and a two-dimensional swing mirror to be incident to a pyramid for reflection, and then is sequentially transmitted through the two-dimensional swing mirror, the primary mirror, the secondary mirror, the first fast reflection mirror, the color separation sheet and the reflector to the beam splitter to be divided into two beams, one beam is focused and coupled to the receiving optical fiber through the receiving lens group, and then reversely enters a communication receiving end through the first optical fiber coupler, and the optical power is monitored through a tracking system, and the incident light is determined to be in the total reflection working angle range of the pyramid; and the other path enters a tracking detector through the focusing of a tracking lens group, a light spot position is presented through the tracking detector, a light spot mass center coordinate is extracted and recorded through a light spot mass center extraction module in the tracking system, the calibrated light spot mass center coordinate before transmission is compared with the calibrated light spot mass center coordinate to obtain the deviation amount of the optical axis of the corresponding receiving light path and the optical axis of the tracking light path, the tracking deviation is corrected by using the obtained deviation amount of the optical axis, the corresponding initial parameter value is changed, and the coaxial calibration of the optical axes of the receiving light path and the tracking light path is completed.
And 4, turning off the laser and the optical switch.
The invention has the beneficial effects that: the invention provides an on-orbit self-calibration device and a calibration method of a satellite-borne laser communication machine, which are used for adjusting a two-dimensional swing mirror to realize total reflection of a pyramid on incident light, enabling an emission light path to completely return to a self-receiving system, introducing a laser and an optical switch into the system, and enabling a receiving optical fiber or an emission optical fiber in an optical system to emit laser respectively through the switching characteristics of the optical switch, so that the receiving light path, a tracking light path and an emission light path in the system are simultaneously coaxially self-calibrated, the emission light path and the tracking light path are coaxially self-calibrated respectively, and the on-orbit running deviation of the satellite-borne laser communication machine can be rapidly and accurately positioned and sequentially calibrated. The method does not need to realize optical axis deviation calibration by matching a ground optical system or other on-orbit satellite-borne laser communication machines, and also does not need beacon light auxiliary calibration, and ensures the tracking and aiming capability of the satellite-borne laser communication machine during operation by compensating the deviation obtained by self-calibration, thereby greatly reducing the time, labor and cost of debugging the laser communication machine during on-orbit operation, and solving the self-calibration problem of the satellite-borne laser communication machine during no-beacon light. In the system, laser emitted light is emitted from a receiving optical fiber and returns to a receiving system (the receiving optical fiber and a tracking detector) through a pyramid, so that coaxial self-calibration between a receiving optical path and a tracking optical path can be realized; the laser emission light is emitted from the emission optical fiber and returns to a receiving system (a receiving optical fiber and a tracking detector) through a pyramid, and coaxial self-calibration between an emission light path and a tracking light path can be realized. The pyramid and the two-dimensional oscillating mirror are positioned on different planes, total reflection of incident light by the pyramid can be realized by controlling the two-dimensional oscillating mirror to a certain specific angle, and when the pyramid is in an idle state at other angles, the laser communication machine can carry out normal communication; the two ends of the optical switch are respectively connected with the communication transmitting end and the communication receiving end through the coupler, when the optical switch is operated, the laser runs the optical switch to the communication transmitting end or the communication receiving end, when the optical switch is closed, the receiving and the transmitting of the optical path are still carried out through the optical coupler, and normal communication can be achieved. The invention provides an on-orbit self-calibration method of a satellite-borne laser communication machine, which can carry out coaxial self-calibration on a transmitting light path, a tracking light path and a receiving light path of the satellite-borne laser communication machine during on-orbit and can detect the working states of all parts before the laser communication machines communicate with each other.
Drawings
FIG. 1 is a schematic structural diagram of an on-orbit self-calibration device of a satellite-borne laser communication machine according to the invention;
FIG. 2 is a schematic structural diagram of a communication receiving end in an on-orbit self-calibration device of a satellite-borne laser communication machine according to the invention;
FIG. 3 is a schematic structural diagram of a tracking and aiming system in an on-orbit self-calibration device of a satellite-borne laser communication machine according to the invention;
reference numerals are as follows: 1-a laser, 2-a fiber isolator, 3-an optical switch, 4-a first fiber coupler, 5-a communication receiving end, 501-a low noise amplifier, 502-a tracking system, 5021-an optical power detection module, 5022-a light spot centroid extraction module, 5023-a first fast mirror control module, 5024-a second fast mirror control module, 5025-a two-dimensional swing mirror control module, 6-a receiving fiber, 7-a receiving lens group, 8-a beam splitter, 9-a reflector, 10-a tracking detector, 11-a tracking lens group, 12-a color separation plate, 13-a first fast mirror, 14-a secondary mirror, 15-a primary mirror, 16-a two-dimensional swing mirror, 17-a pyramid, 18-a second fast mirror, 19-a receiving lens group, 20-transmitting optical fiber, 21-high power amplifier, 22-second optical fiber coupler and 23-communication transmitting end.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the invention, as detailed in the appended claims.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It is to be understood that although the terms first, second, third, etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present invention. The word "if" as used herein may be interpreted as "at … …" or "when … …" or "in response to a determination", depending on the context.
The on-orbit self-calibration device and the calibration method of the satellite-borne laser communication machine provided by the invention are described in detail below with reference to the accompanying drawings and the detailed description. The features of the following examples and embodiments may be combined with each other without conflict.
The invention provides an on-orbit self-calibration device of a satellite-borne laser communication machine, which comprises a laser 1, an optical fiber isolator 2, an optical switch 3, a first optical fiber coupler 4, a communication receiving end 5, a receiving optical fiber 6, a receiving lens group 7, a beam splitter 8, a reflector 9, a tracking detector 10, a tracking lens group 11, a color separation sheet 12, a first fast reflector 13, a secondary mirror 14, a primary mirror 15, a two-dimensional oscillating mirror 16, a pyramid 17, a second fast reflector 18, a transmitting lens group 19, a transmitting optical fiber 20, a high-power amplifier 21, a second optical fiber coupler 22 and a communication transmitting end 23, wherein the optical switch is connected with the first optical fiber coupler 4 through a communication receiving end 5 and a receiving optical fiber 6. The laser 1 emits laser light which passes through the optical fiber isolator 2 and the optical switch 3 to reach two paths, and one path of laser light sequentially passes through the first optical fiber coupler 4, the receiving optical fiber 6, the receiving lens group 7, the beam splitter 8, the reflector 9, the color separation sheet 12 for transmission, the first fast mirror 12, the secondary mirror 14, the primary mirror 15 and the two-dimensional oscillating mirror 16 to reach the pyramid 17; the other path of laser sequentially passes through a second optical fiber coupler 22, a high-power amplifier 21, an emission optical fiber 20, an emission lens group 19, a second fast reflecting mirror 18 and a color separation sheet 12 to reach a first fast reflecting mirror 13; wherein, the other ports of the beam combining ends of the first optical fiber coupler 4 and the second optical fiber coupler 22 are respectively connected with the communication receiving end 5 and the communication transmitting end 23.
The receiving optical fiber 6 and the receiving lens group 7 form a receiving optical path. The tracking detector 10 and the tracking lens group 11 form a tracking light path. The emission lens group 19 and the emission optical fiber 20 form an emission optical path. In the device, the emitted light of the laser 1 is emitted from the receiving optical fiber 6 and returns to the receiving optical path through the pyramid 17, so that the coaxial self-calibration between the receiving optical path and the tracking optical path is realized; the laser 1 emits light from the emitting optical fiber 20 and returns to the receiving optical path through the pyramid 17, so that coaxial self-calibration between the emitting optical path and the tracking optical path can be realized.
Furthermore, the secondary mirror 14 and the primary mirror 15 form a transmitting-receiving common-aperture optical antenna, and may be arranged in an off-axis optical antenna or a coaxial optical antenna manner. By adopting the transceiving common-caliber optical antenna, the emitted light of the optical antenna can be completely emitted back to the antenna through the pyramid 10 without adjusting whether the receiving antenna and the emitting antenna are coaxial or not, and the transceiving common-caliber optical antenna can reduce the volume of the laser communication machine and improve the integration level.
Further, the tracking detector 10 is a CCD detector or a four-quadrant photodetector. The tracking detector 10 and the tracking lens group 11 form a tracking light path to track the center of mass of the light spot, so that the tracking light path is coaxial with the receiving light path.
The pyramid and the two-dimensional swing mirror are located on different planes, the functions of opening and closing the pyramid 17 can be realized by controlling the pitching and deflecting angles of the two-dimensional swing mirror 16, when the two-dimensional swing mirror 16 is controlled to enable laser emitted by a receiving light path or an emitting light path to reach the pyramid and the total reflection tolerance angle condition of the pyramid is met, the pyramid 17 is in a total reflection opening state, and when the two-dimensional swing mirror 16 is controlled to be at other angles, the pyramid 17 is in a total reflection closing state. When the pyramid 17 is in the fully reflective open state, there are two test states: two ends of the optical switch 3 are respectively connected with communication transmitting and communication receiving through a first optical fiber coupler 4 and a second optical fiber coupler 22; when the optical switch 3 is opened to the light receiving optical path to emit laser, the emitted laser is reflected back to the optical path through the pyramid 17, so that the coaxial self-calibration of the receiving optical path and the tracking optical path can be realized; when the optical switch 3 is opened to the emission light path to emit laser, the emitted laser is reflected back to the light path through the pyramid 17, and the coaxial self-calibration of the emission light path and the tracking light path can be realized. When the laser 1 and the optical switch 3 are closed, the receiving and transmitting of the optical path are still performed through the optical coupler, and normal communication can still be realized.
When the two-dimensional oscillating mirror 16 makes the pyramid be idle, the satellite-borne laser communication machine can carry out normal communication. Specifically, both ends of the optical switch 3 are connected to the communication transmitting end 23 and the communication receiving end 5, respectively, through couplers. When the laser works, the laser 1 runs, and the optical switch 3 is dialed to the communication transmitting terminal 23 or the communication receiving terminal 5; when the laser 1 and the optical switch 3 are turned off, the receiving and transmitting of the optical path are still performed through the zero port of the first optical fiber coupler 4 and the second optical fiber coupler 22, and normal communication can still be realized.
Furthermore, the cone 17 is an internal cone with a light-transmitting aperture of 12.5 mm-75 mm, the aperture of the internal cone is smaller than or equal to that of the optical antenna, and the comprehensive angular difference is smaller than 1.5'. The reflecting surface of the pyramid 17 gold-plated film is coated with black finish. The comprehensive angle error of the pyramid 17 is less than 1.5' and is used for ensuring the precision of the total reflection angle, thereby ensuring the precision of the precision method for the coaxial on-orbit self-calibration of the satellite-borne laser communication machine; the clear aperture of the pyramid 17 is set to be less than or equal to the aperture of the optical antenna, so that the weight of the pyramid 17 can be reduced under the condition of meeting the requirement of partial light total reflection light, and the load weight of the laser communication machine is reduced; the adoption scribbles gilt reflecting surface pyramid 17 of black finish paint can make the facula pattern that the tracking and aiming detector received be circular, can more accurate acquisition facula barycenter position for coaxial deviation's feedback.
As shown in fig. 2, the receiving end 5 includes a low noise amplifier 501 and a tracking system 502. As shown in fig. 3, the low noise amplifier 501 may amplify the received signal light for laser communicator communication. The tracking and aiming system 502 comprises a light power detection module 5021, a light spot centroid extraction module 5022, a first fast reflecting mirror control module 5023, a second fast reflecting mirror control module 5024 and a two-dimensional swing mirror control module 5025; the photoelectric detection module 5021 can detect, process and store the optical power of the communication receiving end 5 and the optical power entering the receiving optical fiber 6; the light spot centroid extraction module 5022 can extract the coordinates of the light spot centroid of the light spot position presented by the tracking detector 10, calculate the centroid deviation feedback value and store the centroid deviation feedback value; the first fast reflecting mirror control module 5023, the second fast reflecting mirror control module 5024 and the two-dimensional oscillating mirror control module 5025 can precisely control the pitch and yaw angles of the first fast reflecting mirror 13, the second fast reflecting mirror 18 and the two-dimensional oscillating mirror 16, respectively.
The invention provides an on-orbit self-calibration method of a satellite-borne laser communication machine, which adopts the on-orbit self-calibration device of the satellite-borne laser communication machine and comprises the following steps:
step S1, setting parameters of the in-orbit self-calibration device:
specifically, the satellite-borne laser communication machine starts to operate after receiving an instruction for debugging the satellite platform, and first sequentially starts and sets initial positions or parameters of the light amplification module 21, the tracking detector 10, the first fast reflecting mirror 13, the second fast reflecting mirror 18, the two-dimensional oscillating mirror 16, the communication receiving end 5 and the communication transmitting end 23 according to a sequence. Calibrating the centroid coordinate of the light spot of the tracking and aiming system before emission and determining the initial power value of the laser 1. The mode of the optical switch 3 is set, the laser 1 is turned on, and the pyramid 17 is set to the on state, and operation is started.
Step S2, calibrating the coaxiality of the receiving optical path and the tracking optical path:
specifically, an optical switch 3 is communicated with a receiving optical path, the optical switch 3 is connected with a first optical fiber coupler 4, laser emitted by a laser 1 is emitted from an optical fiber isolator 2, the optical switch 3 and the first optical fiber coupler 4 to a receiving optical fiber 6, and then enters a pyramid 17 through a receiving lens group 7, a beam splitter 8, a reflector 9, a color separation plate 12, a first fast reflection mirror 13, a secondary mirror 14, a primary mirror 15 and a two-dimensional swing mirror 16 in sequence for reflection, reflected light is divided into two beams through the two-dimensional swing mirror 16, the primary mirror 15, the secondary mirror 14, the first fast reflection mirror 13, the color separation plate 12, the reflector 9 to the beam splitter 8 in sequence, one beam is focused and coupled to the receiving optical fiber through the receiving lens group 7 and then enters a communication receiving end 5 through the first optical fiber coupler 4 in a reverse direction, monitoring the light power through a photoelectric detection module and a tracking system in a communication receiving end 5, and determining that the incident light is in the pyramid total reflection working angle range; the other path enters a tracking and aiming detector 10 through focusing of a tracking and aiming lens group 11, a light spot position is presented through the tracking and aiming detector 10, a tracking and aiming light spot center of mass extracting module in a tracking and aiming system extracts and records a light spot center of mass coordinate, the light spot center of mass coordinate calibrated before being transmitted in the step S1 is compared with the calibration light spot center of mass coordinate at the time, deviation between the optical axis of the corresponding receiving light path and the optical axis of the tracking and aiming light path is obtained, the tracking and aiming deviation is corrected by using the obtained deviation of the optical axis, the corresponding initial parameter value is changed, and the coaxial calibration of the optical axes of the receiving light path and the tracking and aiming light path is completed.
Step S3, calibrating the coaxial emission light path and tracking light path:
specifically, the optical switch 3 is opened to be communicated with a transmitting light path, the optical switch 3 is connected with a second optical fiber coupler 22, laser emitted by the laser 1 passes through an optical fiber isolator 2, the optical switch 3, the second optical fiber coupler 22 and a high-power amplifier 21 to be emitted to a transmitting optical fiber 20, passes through a transmitting lens group 19 and a second fast reflecting mirror 18 to be reflected to a color separation plate 12, passes through a first fast reflecting mirror 13, a secondary mirror 14, a primary mirror 15 and a two-dimensional oscillating mirror 16 to be incident to a pyramid 17 to be reflected, passes through a two-dimensional oscillating mirror 16, a primary mirror 15, a secondary mirror 14, a first fast reflecting mirror 13, a color separation plate 12, a reflector 9 to be separated into two beams by a beam splitter 8, one beam is focused and coupled to a receiving optical fiber through a receiving lens group 7, reversely passes through the first optical fiber coupler 4 to enter a communication receiving end 5, and monitors optical power through a detection photoelectric module and a tracking and sighting system in the communication receiving end 5, determining that the incident light is in the pyramid total reflection working angle range; and the other path enters a tracking detector 10 through focusing of a tracking lens group 11, a light spot position is presented through the tracking detector 10 and is connected with a tracking system, a light spot mass center coordinate is extracted through a tracking light spot mass center extraction module in the tracking system, the light spot mass center coordinate calibrated in the step S2 is compared with the light spot mass center coordinate at the time to obtain the deviation amount of the optical axis of the corresponding transmitting light path and the optical axis of the tracking light path, the deviation of the optical axes of the transmitting light path and the tracking light path is compensated by adjusting the second quick reflection mirror 18, the position of the second quick reflection mirror 18 after compensation is corrected is the initial position of the second quick reflection mirror, the corresponding initial parameter value is changed, and coaxial calibration of the transmitting light path and the tracking light path is completed.
Step S4, turning off the laser 1 and the optical switch 3.
In summary, the present invention provides an on-orbit self-calibration apparatus of a satellite-borne laser communication machine and a calibration method thereof, wherein a two-dimensional oscillating mirror 16 is adjusted to realize total reflection of an incident light ray by a pyramid 17, so that a transmitting light path is completely returned to a self-receiving system, a laser 1 and an optical switch 3 are introduced into the apparatus, and a receiving optical fiber 6 or a transmitting optical fiber 20 in an optical system respectively transmits laser light through the switching characteristics of the optical switch 3, thereby converting simultaneous coaxial self-calibration of the receiving light path, a tracking light path and the transmitting light path in the system into two steps of coaxial self-calibration of the receiving light path and the tracking light path, and coaxial self-calibration of the transmitting light path and the tracking light path, so that the on-orbit running deviation of the satellite-borne laser communication machine can be rapidly and accurately positioned and sequentially calibrated. The method of the invention does not need to realize optical axis deviation calibration by matching a ground optical system or other on-orbit satellite-borne laser communication machines, also does not need beacon light auxiliary calibration, and ensures the tracking and aiming capability of the satellite-borne laser communication machine during operation by compensating the deviation amount obtained by self-calibration, thereby greatly reducing the debugging time, labor and cost of the laser communication machine during on-orbit operation, and solving the self-calibration problem of the satellite-borne laser communication machine without beacon light.
The above embodiments are only used for illustrating the design idea and features of the present invention, and the purpose of the present invention is to enable those skilled in the art to understand the content of the present invention and implement the present invention accordingly, and the protection scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes or modifications based on the principles and design concepts disclosed herein are intended to be included within the scope of the present invention.
Claims (8)
1. An on-orbit self-calibration device of a satellite-borne laser communication machine is characterized by comprising a laser (1), a fiber isolator (2), an optical switch (3), a first fiber coupler (4), a communication receiving end (5), a receiving fiber (6), a receiving lens group (7), a beam splitter (8), a reflector (9), a tracking detector (10), a tracking lens group (11), a color separation sheet (12), a first fast reflector (13), a secondary mirror (14), a primary mirror (15), a two-dimensional swinging mirror (16), a pyramid (17), a second fast reflector (18), a transmitting lens group (19), a transmitting fiber (20), a high-power amplifier (21), a second fiber coupler (22) and a communication transmitting end (23); the laser device (1) emits laser to two paths through the optical fiber isolator (2) and the optical switch (3), and one path of laser sequentially passes through the first optical fiber coupler (4), the receiving optical fiber (6), the receiving lens group (7), the beam splitter (8), the reflector (9), the color separation sheet (12) for transmission, the first fast reflector (13), the secondary mirror (14), the primary mirror (15) and the two-dimensional swing mirror (16) to reach the pyramid (17); the other path of laser sequentially passes through a second optical fiber coupler (22), a high-power amplifier (21), an emission optical fiber (20), an emission lens group (19), a second fast reflecting mirror (18) and a color separation sheet (12) to reach a first fast reflecting mirror (13); the other ports of the beam combining ends of the first optical fiber coupler (4) and the second optical fiber coupler (22) are respectively connected with the communication receiving end (5) and the communication transmitting end (23); the communication receiving end (5) comprises a tracking system; the tracking and aiming system is used for monitoring power, extracting and processing a light spot center of mass, and controlling pitching and deflecting angles of the first fast reflecting mirror (13), the second fast reflecting mirror (18) and the two-dimensional swinging mirror (16); the tracking and aiming system comprises a power detection module, a light spot mass center extraction module, a first fast reflecting mirror control module, a second fast reflecting mirror control module and a two-dimensional oscillating mirror control module, and is respectively connected with a first optical fiber coupler (4), a tracking and aiming detector (10), a first fast reflecting mirror (13), a second fast reflecting mirror (18) and a two-dimensional oscillating mirror (16).
2. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 1, wherein the pyramid (17) realizes total reflection of incident light rays through angle control of a two-dimensional swing mirror (16); when the angle condition of the total reflection tolerance of the pyramid (17) is met, the pyramid (17) is in a total reflection open state; when the angle condition of the total reflection tolerance of the pyramid (17) is not satisfied, the pyramid (17) is in a total reflection closed state.
3. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 2, wherein when the pyramid (17) is in the fully-reflective open state, and the optical switch (3) is communicated with the receiving optical path, the optical switch (3) is connected with the first optical fiber coupler (4), the laser emitted by the laser (1) is transmitted to the receiving optical fiber (6) through the optical fiber isolator (2), the optical switch (3) and the first optical fiber coupler (4), and then sequentially enters the pyramid (17) through the receiving lens set (7), the beam splitter (8), the reflector (9), the color separation plate (12), the first fast reflector (13), the secondary mirror (14), the primary mirror (15) and the two-dimensional oscillating mirror (16) to be reflected, and then sequentially passes the two-dimensional oscillating mirror (16), the primary mirror (15), the secondary mirror (14), the first fast reflector (13), the color separation plate (12) and the reflector (9) to be separated into two beams through the beam splitter (8), one path enters a tracking detector (10) through a tracking lens group (11) in a focusing way, and the other path enters a communication receiving end (5) through a first optical fiber coupler (4) in a reverse direction after being coupled to a receiving optical fiber (6) through a receiving lens group (7) in a focusing way.
4. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 2, wherein when the pyramid (17) is in a fully-reflective open state, and the optical switch (3) is communicated with the emission light path, the optical switch (3) is connected with the second optical fiber coupler (22), the laser emitted by the laser (1) is transmitted to the emission optical fiber (20) through the optical fiber isolator (2), the optical switch (3), the second optical fiber coupler (22) and the high-power amplifier (21), reflected to the dichroic plate (12) through the emission lens group (19) and the second fast mirror (18), and then reflected to the pyramid (17) through the first fast mirror (13), the secondary mirror (14), the primary mirror (15) and the two-dimensional oscillating mirror (16), and then reflected through the two-dimensional oscillating mirror (16), the primary mirror (15), the secondary mirror (14), the first fast mirror (13), the dichroic plate (12) and the second fast mirror (14), The reflector (9) to the beam splitter (8) are divided into two beams, one beam is focused by the tracking lens group (11) and enters the tracking detector (10), and the other beam is focused and coupled to the receiving optical fiber by the receiving lens group (7) and reversely enters the communication receiving end (5) through the first optical fiber coupler (4).
5. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 1, wherein the pyramid (17) adopts an inner circular pyramid with a clear aperture of 12.5 mm-75 mm, and the comprehensive angular difference is less than 1.5'; and black finish paint is coated on the reflecting surface of the gold-plated film of the pyramid (17).
6. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 1, wherein the secondary mirror (14) and the primary mirror (15) form a transmitting-receiving common-caliber optical antenna, and are arranged in an off-axis optical antenna mode or a coaxial optical antenna mode.
7. The on-orbit self-calibration device of the satellite-borne laser communication machine according to claim 1, wherein the tracking detector (10) is a CCD detector or a four-quadrant photodetector.
8. An on-orbit self-calibration method of a satellite-borne laser communication machine, which is applied to the on-orbit self-calibration device of the satellite-borne laser communication machine as claimed in any one of claims 1 to 7, and is characterized by comprising the following steps:
step S1, setting initial parameters of the track self-calibration device, calibrating the coordinates of the centroid of the light spot of the tracking and aiming system before laser emission, determining the initial value of power, turning on the laser (1), and setting the pyramid (17) to be in a total reflection opening state;
step S2, an optical switch (3) is opened to a first optical fiber coupler (4), laser emitted by a laser (1) passes through an optical fiber isolator (2), the optical switch (3) and the first optical fiber coupler (4) to be emitted to a receiving optical fiber (6), and then sequentially passes through a receiving lens group (7), a beam splitter (8), a reflector (9), a color separation sheet (12), a first fast reflector (13), a secondary mirror (14), a primary mirror (15) and a two-dimensional oscillating mirror (16) to be incident to a pyramid (17) for reflection, and then sequentially passes through a two-dimensional oscillating mirror (16), a primary mirror (15), a secondary mirror (14), a first fast reflector (13), a color separation sheet (12) and a reflector (9) to be separated into two beams, one path of the two paths is focused and coupled to the receiving optical fiber through the receiving lens group (7), and then reversely enters a communication receiving end (5) through the first optical fiber coupler (4), and power of the optical tracking system is monitored, determining that the incident light is in the pyramid total reflection working angle range; the other path enters a tracking detector (10) through focusing of a tracking lens group (11), a light spot position is presented through the tracking detector (10), a tracking light spot mass center coordinate is extracted and recorded through a tracking light spot mass center extraction module in a tracking system, the calibrated light spot mass center coordinate before transmission is compared with the calibrated light spot mass center coordinate to obtain the deviation value of the optical axis of the corresponding receiving light path and the optical axis of the tracking light path, tracking deviation is corrected by using the obtained deviation value of the optical axis, and the corresponding initial parameter value is changed to finish the coaxial calibration of the optical axes of the receiving light path and the tracking light path;
step 3, the optical switch (3) is opened to a second optical fiber coupler (22), laser emitted by the laser (1) passes through the optical fiber isolator (2), the optical switch (3), the second optical fiber coupler (22) and the high-power amplifier (21) to be emitted to an emission optical fiber (20), is reflected to the dichroic filter (12) through the emission lens group (19) and the second fast reflection mirror (18) in sequence, is incident to the pyramid (17) to be reflected through the first fast reflection mirror (13), the secondary mirror (14), the primary mirror (15) and the two-dimensional swinging mirror (16) in sequence, is divided into two beams through the two-dimensional swinging mirror (16), the primary mirror (15), the secondary mirror (14), the first fast reflection mirror (13), the dichroic filter (12) and the reflector (9) to the beam splitter (8) in sequence, is focused and coupled to a receiving optical fiber through the receiving lens group (7), and reversely enters the communication receiving end (5) through the first optical fiber coupler (4), monitoring the light power through a communication receiving end (5) tracking system, and determining that the incident light is in the pyramid total reflection working angle range; the other path enters a tracking detector (10) through focusing of a tracking lens group (11), the position of a light spot is presented through the tracking detector (10), the coordinates of the center of mass of the light spot are extracted through a tracking system, the coordinates and the record of the center of mass at the moment are recorded, the coordinates of the center of mass of the light spot calibrated in the step (2) are compared with the coordinates of the center of mass of the light spot at the moment to obtain the deviation value of the optical axis of the corresponding emission light path and the optical axis of the tracking light path, the deviation of the optical axes of the two is compensated by adjusting a second quick reflection mirror (18), the position of the second quick reflection mirror (18) after the compensation is corrected is the initial position of the second quick reflection mirror, the corresponding initial parameter value is changed, and the coaxial calibration of the emission light path and the tracking light path is completed;
and 4, turning off the laser (1) and the optical switch (3).
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| CN115276801B (en) * | 2022-09-19 | 2022-12-23 | 西安空间无线电技术研究所 | Satellite laser communication link light spot tracking compensation method and signal transmission method |
| CN115426043B (en) * | 2022-11-04 | 2023-03-24 | 之江实验室 | On-orbit self-calibration system and method for optical axis of space laser communication terminal |
| CN115499064B (en) * | 2022-11-08 | 2023-04-07 | 南京英田光学工程股份有限公司 | Miniaturized multi-core transmitting-receiving laser communication device based on variable optical axis and design method |
| CN115833942B (en) * | 2023-02-17 | 2023-06-09 | 长春光客科技有限公司 | Wireless optical communication device and method adopting micro optical axis stabilizing mechanism |
| CN115996088B (en) * | 2023-03-23 | 2023-06-27 | 中国电子科技集团公司第五十四研究所 | On-orbit self-calibration device and method for satellite-borne laser communication terminal |
| CN117614518B (en) * | 2024-01-22 | 2024-04-09 | 北京融为科技有限公司 | Satellite-borne laser load receiving and transmitting coaxial calibration method and system |
| CN118054842B (en) * | 2024-04-15 | 2024-09-13 | 北京融为科技有限公司 | Method and device for dynamically correcting receiving and transmitting directions of satellite-borne laser communication load |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102185659A (en) * | 2011-03-23 | 2011-09-14 | 中国科学院上海技术物理研究所 | Quantum communication ATP (array transform processor) precise tracking system with optical axis self-calibrating function and calibrating method thereof |
| CN109150302A (en) * | 2018-08-20 | 2019-01-04 | 中国科学院上海技术物理研究所 | A kind of the optical axis self-calibrating device and method of optical communication system |
| CN109787686A (en) * | 2018-12-18 | 2019-05-21 | 中国科学院西安光学精密机械研究所 | A kind of satellite optical communication terminal on-orbit calibration and transmitting-receiving coaxiality correcting device and method |
| WO2020043142A1 (en) * | 2018-08-29 | 2020-03-05 | 中国科学院上海光学精密机械研究所 | Apparatus and method for coupling spatial light to optical fiber light for achieving stability of optical axis without position sensor |
| CN112564822A (en) * | 2020-11-18 | 2021-03-26 | 西安理工大学 | On-orbit self-calibration device and method for space laser communication terminal |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004015135A (en) * | 2002-06-04 | 2004-01-15 | Canon Inc | Optical space communication unit having direction regulating function |
| CN111337901B (en) * | 2020-04-03 | 2024-08-09 | 深圳煜炜光学科技有限公司 | Laser radar for remote detection and detection method thereof |
| CN111736358A (en) * | 2020-06-24 | 2020-10-02 | 黑龙江瑞霭科技有限公司 | Laser communication terminal transmitting-receiving coaxial real-time calibration method |
-
2022
- 2022-02-16 CN CN202210141497.3A patent/CN114189284B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102185659A (en) * | 2011-03-23 | 2011-09-14 | 中国科学院上海技术物理研究所 | Quantum communication ATP (array transform processor) precise tracking system with optical axis self-calibrating function and calibrating method thereof |
| CN109150302A (en) * | 2018-08-20 | 2019-01-04 | 中国科学院上海技术物理研究所 | A kind of the optical axis self-calibrating device and method of optical communication system |
| WO2020043142A1 (en) * | 2018-08-29 | 2020-03-05 | 中国科学院上海光学精密机械研究所 | Apparatus and method for coupling spatial light to optical fiber light for achieving stability of optical axis without position sensor |
| CN109787686A (en) * | 2018-12-18 | 2019-05-21 | 中国科学院西安光学精密机械研究所 | A kind of satellite optical communication terminal on-orbit calibration and transmitting-receiving coaxiality correcting device and method |
| CN112564822A (en) * | 2020-11-18 | 2021-03-26 | 西安理工大学 | On-orbit self-calibration device and method for space laser communication terminal |
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