CN103441798B - Space optical communication terminal aberration compensating method in-orbit - Google Patents
Space optical communication terminal aberration compensating method in-orbit Download PDFInfo
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Abstract
Space optical communication terminal aberration compensating method in-orbit, relates to space optical communication terminal aberration compensating method in-orbit.It causes the problem of the interruption of communication link in order to solve the new aberration of the whole generation of period in orbit of existing space optical communication.The ground test dummy run phase on space optical communication terminal in the impact of facula mass center location of various issuable aberration and correspondence thereof carry out analogue measurement, all data that stage of revising in-orbit was stored by the data that compare ground Master Control Center and receive and ground test dummy run phase, select the data similar to space optical communication terminal data in-orbit as imaging test result, corresponding lens error correction parameter is calculated according to this result, realize the correction in orbit to space optical communication terminal, invention increases terminal angle detection accuracy, reach the object that ensure that space optical communication communication link of whole period in orbit normally runs.The present invention is applicable to Aeronautics and Astronautics and the communications field.
Description
Technical field
The present invention relates to a kind of aberration compensating method, be specifically related to space optical communication terminal aberration compensating method in-orbit.
Background technology
Since nineteen sixty, laser was born, photoelectron cause starts flourish.Optics has started in numerous areas service societies such as medical treatment, industrial processes, measurement, communication, electric power.Along with modern society increases day by day to the demand of information, optical communication technique has become people and has paid close attention to the emphasis with research.
Along with the development of satellite technology, the demand of satellite to communication data rate also improves constantly.Satellite optical communication has become the focus of the U.S., Japan and the countries and regions such as European research because of advantages such as its communication data rate are high, good confidentiality, antijamming capability are strong, terminal volume is little, low in energy consumption.Optical communication is mainly divided into optical fiber communication and satellite optical communication (wireless light communication).Fibre Optical Communication Technology now comparative maturity, and to putting in the middle of social production life.Satellite optical communication is then still in positive exploration and practice.Compared with satellite optical communication communicates with conventional satellite (microwave communication), there is the feature of himself.The advantage of satellite optical communication is: communication data rate high (can reach 2 ~ 5Gb/s), antijamming capability are strong, good confidentiality, communication terminal volume, power consumption and weight are far smaller than microwave communication etc.Certainly, also there is himself problem in satellite optical communication, namely satellite affects larger with the laser communication link on ground by air and rainfall.But these problems can by adding ground station and being solved by optical communication networking technologys such as relay satellite communications.
In Intersatellite Optical Communication System, aiming at, catch, follow the tracks of (PAT) technology is be related to the key technology that can laser communication link set up.The key parameters affecting PAT technology is by the measurement of tracking transducer to alignment angle, its essence is by the calculating of imageing sensor to beacon hot spot gradation of image barycenter.
Satellite laser communications system is operated in highly sensitive communication system under optical diffraction limit, the communication distance limit and photodetection maximum conditions.For ensureing that communication link has good communication performance under exacting terms like this, system has high requirement to the property indices of satellite optical communication terminal and the quality of light beam.
Due to environmental impact in-orbit and the reason of some unpredictable factors after launching, even if satellite optical communication terminal carried out ground aberration compensation before launching with spacecraft 15, but still likely produce new aberration during in orbit, these aberrations are on the precision of the impact meeting hot spot gray scale center coordination of beacon hot spot imaging.Because hot spot gray scale barycenter is the critical quantity affecting angle detection, if therefore do not revised timely the impact that facula mass center is located the aberration of these new generations, the location of hot spot gray scale barycenter is inaccurate will directly affect the aiming acquisition and tracking process of communication, even may cause the interruption of communication link time serious.
Therefore, in order to realize high-quality space optical communication, need after launching with spacecraft 15, still to believe that the aberration of generation is to facula mass center positioning effects in elimination system at optical communication terminal.Carry out automatic calibration can realize above-mentioned purpose by installing Adaptable System in optical communication terminal optical system additional.But because Adaptable System not only involves great expense, and install this system in the terminal additional and also can bring extra power consumption, while increasing terminal volume and weight, too increase the cost of terminal transmission.Therefore space optical communication terminal is not also had to install the case of Adaptable System additional at present.
Summary of the invention
The present invention causes the problem of the interruption of communication link in order to solve the new aberration of the whole generation of period in orbit of existing space optical communication, thus proposes space optical communication terminal aberration compensating method in-orbit.
Space optical communication terminal aberration compensating method in-orbit, described space optical communication terminal comprises telescope, the first Amici prism, shaping lens group and cmos image sensor,
Be incident to telescopical light beam and be incident to the first Amici prism after compression,
Reference beam through the first Amici prism refraction is incident to cmos image sensor through shaping lens group,
The method comprises the ground test dummy run phase and revises two stages of stage in-orbit;
The described ground test dummy run phase comprises the steps:
Step one, employing main control computer send coded command to encoder, control semiconductor laser luminous simultaneously, encoder provides modulation signal for semiconductor laser, the fibre optical transmission head of described semiconductor laser is positioned in the focus of parallel light tube, the picture signal end of main control computer connects the picture signal end of cmos image sensor, performs step 2;
Step 2, Wavefront sensor is positioned over the light-emitting window of parallel light tube, the original beam through parallel light tube is made to be incident to the search coverage on Wavefront sensor surface, main control computer is measured according to the waveform signal of Wavefront sensor collection, obtain the zernike polynomial coefficient A of original beam wave front aberration, and store this zernike polynomial coefficient A, perform step 3;
Step 3, be 0rad by the alignment angle of the telescopical light inlet of space optical communication terminal and the light-emitting window of parallel light tube, make the laser through parallel light tube be incident to telescopical light inlet, perform step 4;
Step 4, the reference light picture signal adopting main control computer reading cmos image sensor to gather, using the facula mass center coordinate of described reference light picture signal as coordinate a
k, and store this facula mass center coordinate as coordinate a
k, perform step 5;
Wherein, k represents the number of times that the alignment angle of the light-emitting window of telescopical light inlet and parallel light tube adjusts, and the initial value of k is 1, k=1,2 ..., 120; a
kthe facula mass center coordinate of reference light picture signal during alignment angle for the light-emitting window of the kth time telescopical light inlet of adjustment and parallel light tube as coordinate,
Step 5, two-dimensional micromotion stage is placed on telescopical light-emitting window, the light beam through telescope light-emitting window is made to be incident to two-dimensional micromotion stage, the second Amici prism is incident to through spatial light modulator, light beam through the second Amici prism transmission is incident to Wavefront sensor, test beams through the second Amici prism refraction is incident to shaping lens group, test beams through shaping lens group shaping is incident to cmos image sensor
The micromotion platform drive singal output of main control computer is adopted to connect two-dimensional micromotion stage driver,
The control signal output of two-dimensional micromotion stage driver connects the control signal input of two-dimensional micromotion stage;
Adopt the light modulation driving signal input of the light modulation drive singal output connection space optical modulator driver of main control computer,
The control signal input of the control signal output connection space optical modulator of spatial light modulator driver,
Perform step 6;
Step 6, the test beams picture signal adopting main control computer reading cmos image sensor to gather, using the facula mass center coordinate of described test beams picture signal as coordinate a
k', the position of adjustment two-dimensional micromotion stage, spatial light modulator, the second Amici prism and shaping lens group, makes the facula mass center coordinate a of test beams picture signal
k' with the facula mass center coordinate a of reference light picture signal
kidentical, perform step 7;
Wherein, a
k' the facula mass center coordinate of test beams picture signal when representing the alignment angle of the light-emitting window of the kth time telescopical light inlet of adjustment and parallel light tube,
Step 7, employing main control computer, by controlling two-dimensional micromotion stage driver adjustment two-dimensional micromotion stage, make the working range of two-dimensional micromotion stage be in initial position,
Adopting main control computer by controlling spatial light modulator driver adjustment spatial light modulator, making the working range of spatial light modulator be in initial position,
Main control computer is adopted to read the analog picture signal of the test beams that cmos image sensor gathers, and store the information that this light beam analog picture signal comprises, the information that described light beam analog picture signal comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer to gather beam quality data by Wavefront sensor, described beam quality data are as zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 8;
Wherein, B
kjiexpression adjusts the light-emitting window of telescopical light inlet and parallel light tube in alignment angle, jth time adjustment spatial light modulator or beam quality data when regulating two-dimensional micromotion stage for i-th time in kth time, these beam quality data are as zernike polynomial coefficient; C
kjiexpression adjusts the light-emitting window of telescopical light inlet and parallel light tube at alignment angle, jth time adjustment spatial light modulator or true zernike polynomial coefficient when regulating two-dimensional micromotion stage for i-th time in kth time; The initial value of i is 0; The initial value of j is 0; The working range of two-dimensional micromotion stage is in the scope that X-axis and Y-axis surround, and the scope of X-axis and Y-axis is 0 μm-2 μm; Two-dimensional micromotion stage is that step units carries out 200 adjustments with 10nm, the initial position of two-dimensional micromotion stage is that X-axis keeps 1 μm of position always, Y-axis is in 0 μm of place and starts scanning, and the scope of two-dimensional micromotion stage scanning is: X-axis keeps 1 μm always, and Y-axis is from 0 μm to 2 μm; The working range of spatial light modulator is 0 gray value-255 gray value, and spatial light modulator stepping-in amount in units of 8 gray values is carried out 32 times and regulated, and the initial position of spatial light modulator is 0 gray value,
The inclination angle of step 8, adjustment two-dimensional micromotion stage, and adjust phase place and the gray scale of spatial light modulator simultaneously, the light beam of the test light that cmos image sensor is gathered produces perturbation, namely compensates wave front aberration by spatial light modulator and two-dimensional micromotion stage, performs step 9;
Step 9, the waveform signal adopting main control computer reading Wavefront sensor to gather, obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10;
New zernike polynomial coefficient C described in step 10, determining step nine
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 7; Then perform step 11 if not;
Wherein, λ represents the optical maser wavelength used in test process, is the wavelength of optical communication terminal beacon beam,
Step 11, the facula mass center coordinate b adopting the collection of main control computer reading cmos image sensor new
kji', and store this facula mass center coordinate b
kji', perform step 12;
Wherein, b
kji' represent that light-emitting window at the telescopical light inlet of kth time adjustment and parallel light tube is at alignment angle, the secondary adjustment spatial light modulator of jth or new facula mass center coordinate when regulating two-dimensional micromotion stage for i-th time,
Step 12, employing main control computer are through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 11 store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 13; Step 13, make two-dimensional micromotion stage adjust a step units backward from current location, make i=i+1, perform step 14;
Step 14, judge whether i equals 201, if perform step 10 six, perform step 15 if not;
Step 15, employing main control computer read the simulation aberration image of the test beams that cmos image sensor gathers, and store the information that this light beam analog image comprises, the information that described light beam analog image comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer to gather beam quality data by Wavefront sensor, described beam quality data are as zernike polynomial coefficient B
kji, and store this zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 10 six;
The inclination angle of step 10 six, adjustment two-dimensional micromotion stage, and adjust phase place and the gray scale of spatial light modulator simultaneously, the light beam of the test light that cmos image sensor is gathered produces perturbation, namely compensates wave front aberration by spatial light modulator and two-dimensional micromotion stage, performs step 10 seven;
Step 10 seven, the waveform signal adopting main control computer reading Wavefront sensor to gather, obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10 eight;
New zernike polynomial coefficient C described in step 10 eight, determining step 17
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 15; Then perform step 10 nine if not;
Step 10 nine, the facula mass center coordinate b adopting the collection of main control computer reading cmos image sensor new
kji', and store this facula mass center coordinate b
kji', perform step 2 ten;
Step 2 ten, employing main control computer are through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 10 nine store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 2 11;
Step 2 11, judge whether j equals 32, if perform step 2 13, perform step 2 12 if not;
Step 2 12, make spatial light modulator adjust a step units backward from current location, make j=j+1, i=0, perform step 15;
Whether step 2 13, the alignment angle judging the telescopical light inlet of space optical communication terminal and the light-emitting window of parallel light tube are 3mrad, if will telescope be rotated, make the alignment angle of the light-emitting window of this telescopical light inlet and parallel light tube for-3mrad, make k=k+1, perform step 4; Perform if not, step 2 14;
Step 2 14, rotation telescope, make the alignment angle of the light-emitting window of this telescopical light inlet and parallel light tube adjust 5 μ rad clockwise from current location, make k=k+1, perform step 2 15;
Whether step 2 15, the alignment angle judging the light-emitting window of telescopical light inlet and parallel light tube are 0mrad, revise the stage in-orbit, perform step 4 if not if perform;
In-orbit revise the stage time, space optical communication terminal with spacecraft in orbit, cmos image sensor for gathering the data of beacon beam,
Stage of revising in-orbit comprises the steps:
The data of the beacon beam of cmos image sensor collection are sent to ground Master Control Center by communication port by steps A, space optical communication terminal, perform step B;
The data that step B, ground Master Control Center send according to space optical communication terminal in orbit, all data that the ground test simulation stage stores are inquired about, with current space optical communication terminal data similarity dimensions in-orbit in 85% to 100% one is selected to form as test result, according to this composition as the corresponding lens error correction parameter of test result calculations, perform step C;
This lens error correction parameter to be sent to space optical communication terminal in-orbit by communication port by step C, ground Master Control Center, realizes the correction in orbit to space optical communication terminal.
The data of the beacon beam of cmos image sensor collection are sent to ground Master Control Center by communication repeating satellite and communication satellite ground telemetering base station by the spacecraft carrying optical communication terminal.
The data of the beacon beam of cmos image sensor collection are sent to ground Master Control Center by communication satellite ground telemetering base station by the spacecraft carrying optical communication terminal.
The data of the beacon beam of cmos image sensor collection are sent to ground Master Control Center by laser communication through base station, optical communication face by the spacecraft carrying optical communication terminal.
The aberration compensating method of space optical communication terminal in-orbit of the present invention the ground test dummy run phase by auxiliary equipment on space optical communication terminal in the impact of facula mass center location of various issuable aberration and correspondence thereof carry out analogue measurement, described auxiliary equipment comprises two-dimensional micromotion stage, two-dimensional micromotion stage driver, main control computer, spatial light modulator driver, spatial light modulator, second Amici prism, Wavefront sensor, encoder, parallel light tube and semiconductor laser, all data that stage of revising in-orbit was stored by the data that compare ground Master Control Center and receive and ground test dummy run phase, select the data similar to space optical communication terminal data in-orbit as imaging test result, corresponding lens error correction parameter is calculated according to this result, realize the correction in orbit to space optical communication terminal, invention increases terminal angle detection accuracy, because angle detection accuracy determines by facula mass center positioning precision, reach the object that ensure that space optical communication communication link of whole period in orbit normally runs.
Accompanying drawing explanation
Fig. 1 is the structural representation adjusted space optical communication terminal in the ground test dummy run phase;
Fig. 2 is the structural representation of space optical communication terminal;
Fig. 3 is the structural representation debugged parallel light tube 13;
Fig. 4 is the structural representation of space optical communication terminal stage and ground communication in-orbit.
Embodiment
Embodiment one, composition graphs 1 to Fig. 4 illustrate present embodiment, the aberration compensating method of space optical communication terminal in-orbit described in present embodiment, described space optical communication terminal comprises telescope 1, first Amici prism 2, shaping lens group 10 and cmos image sensor 11
The light beam being incident to telescope 1 is incident to the first Amici prism 2 after compression,
The reference beam reflected through the first Amici prism 2 is incident to cmos image sensor 11 through shaping lens group 10,
The method comprises the ground test dummy run phase and revises two stages of stage in-orbit;
The described ground test dummy run phase comprises the steps:
Step one, employing main control computer 5 send coded command to encoder 12, control semiconductor laser 14 luminous simultaneously, encoder 12 provides modulation signal for semiconductor laser 14, the fibre optical transmission head of described semiconductor laser 14 is positioned in the focus of parallel light tube 13, the picture signal end of main control computer 5 connects the picture signal end of cmos image sensor 11, performs step 2;
Step 2, Wavefront sensor 9 is positioned over the light-emitting window of parallel light tube 13, the original beam through parallel light tube 13 is made to be incident to the search coverage on Wavefront sensor 9 surface, the waveform signal that main control computer 5 gathers according to Wavefront sensor 9 is measured, obtain the zernike polynomial coefficient A of original beam wave front aberration, and store this zernike polynomial coefficient A, perform step 3;
Step 3, be 0rad by the alignment angle of the light inlet of the telescope 1 of space optical communication terminal and the light-emitting window of parallel light tube 13, make the laser through parallel light tube 13 be incident to the light inlet of telescope 1, perform step 4;
Step 4, employing main control computer 5 read the reference light picture signal that cmos image sensor 11 gathers, using the facula mass center coordinate of described reference beam picture signal as coordinate a
k, and store this facula mass center coordinate as coordinate a
k, perform step 5;
Wherein, k represents the number of times that the alignment angle of the light inlet of telescope 1 and the light-emitting window of parallel light tube 13 adjusts, and the initial value of k is 1, k=1,2 ..., 120; a
kthe facula mass center coordinate of reference beam picture signal during alignment angle for the kth time adjustment light inlet of telescope 1 and the light-emitting window of parallel light tube 13 as coordinate,
Step 5, two-dimensional micromotion stage 3 is placed on the light-emitting window of telescope 1, the light beam through telescope 1 light-emitting window is made to be incident to two-dimensional micromotion stage 3, the second Amici prism 8 is incident to through spatial light modulator 7, light beam through the second Amici prism 8 transmission is incident to Wavefront sensor 9, the test beams reflected through the second Amici prism 8 is incident to shaping lens group 10, test beams through shaping lens group 10 shaping is incident to cmos image sensor 11
The micromotion platform drive singal output of main control computer 5 is adopted to connect two-dimensional micromotion stage driver 4,
The control signal output of two-dimensional micromotion stage driver 4 connects the control signal input of two-dimensional micromotion stage 3;
Adopt the light modulation driving signal input of the light modulation drive singal output connection space optical modulator driver 6 of main control computer 5,
The control signal input of the control signal output connection space optical modulator 7 of spatial light modulator driver 6,
Perform step 6;
Step 6, employing main control computer 5 read the test beams picture signal that cmos image sensor 11 gathers, using the facula mass center coordinate of described test beams picture signal as coordinate a
k', the position of adjustment two-dimensional micromotion stage 3, spatial light modulator 7, second Amici prism 8 and shaping lens group 10, makes the facula mass center coordinate a of test light picture signal
k' with the facula mass center coordinate a of reference light picture signal
kidentical, perform step 7;
Wherein, a
k' the facula mass center coordinate of test light picture signal when representing the alignment angle of the kth time adjustment light inlet of telescope 1 and the light-emitting window of parallel light tube 13,
Step 7, employing main control computer 5 adjust two-dimensional micromotion stage 3 by controlling two-dimensional micromotion stage driver 4, make the working range of two-dimensional micromotion stage 3 be in initial position,
Adopting main control computer 5 to adjust spatial light modulator 7 by controlling spatial light modulator driver 6, making the working range of spatial light modulator 7 be in initial position,
Main control computer 5 is adopted to read the analog picture signal of the test beams that cmos image sensor 11 gathers, and store the information that this light beam analog picture signal comprises, the information that described light beam analog picture signal comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer 5 to gather beam quality data by Wavefront sensor 9, described beam quality data are as zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 8;
Wherein, B
kjito represent that at the kth time adjustment light inlet of telescope 1 these beam quality data are as zernike polynomial coefficient with the light-emitting window of parallel light tube 13 in alignment angle, the secondary adjustment spatial light modulator 7 of jth or beam quality data when regulating two-dimensional micromotion stage 3 for i-th time; C
kjito represent at the kth time adjustment light inlet of telescope 1 with the light-emitting window of parallel light tube 13 at alignment angle, the secondary adjustment spatial light modulator 7 of jth or true zernike polynomial coefficient when regulating two-dimensional micromotion stage 3 for i-th time; The initial value of i is 0; The initial value of j is 0; The working range of two-dimensional micromotion stage 3 is in the scope that X-axis and Y-axis surround, and the scope of X-axis and Y-axis is 0 μm-2 μm; Two-dimensional micromotion stage 3 is that step units carries out 200 adjustments with 10nm, the initial position of two-dimensional micromotion stage 3 is that X-axis keeps 1 μm of position always, Y-axis is in 0 μm of place and starts scanning, and the scope that two-dimensional micromotion stage 3 scans is: X-axis keeps 1 μm always, and Y-axis is from 0 μm to 2 μm; The working range of spatial light modulator 7 is 0 gray value-255 gray value, and spatial light modulator 7 stepping-in amount in units of 8 gray values is carried out 32 times and regulated, and the initial position of spatial light modulator 7 is 0 gray value,
The inclination angle of step 8, adjustment two-dimensional micromotion stage 3, and adjust phase place and the gray scale of spatial light modulator 7 simultaneously, the light beam of the test light that cmos image sensor 11 is gathered produces perturbation, namely compensates wave front aberration by spatial light modulator 7 and two-dimensional micromotion stage 3, performs step 9;
Step 9, employing main control computer 5 read the waveform signal that Wavefront sensor 9 gathers, and obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10;
New zernike polynomial coefficient C described in step 10, determining step nine
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 7; Then perform step 11 if not;
Wherein, λ represents the optical maser wavelength used in test process, is the wavelength of optical communication terminal beacon beam,
Step 11, employing main control computer 5 read cmos image sensor 11 and gather new facula mass center coordinate b
kji', and store this facula mass center coordinate b
kji', perform step 12;
Wherein, b
kji' to represent at the kth time adjustment light inlet of telescope 1 with the light-emitting window of parallel light tube 13 at alignment angle, the secondary adjustment spatial light modulator 7 of jth or new facula mass center coordinate when regulating two-dimensional micromotion stage 3 for i-th time,
Step 12, employing main control computer 5 are through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 11 store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 13; Step 13, make two-dimensional micromotion stage 3 adjust a step units backward from current location, make i=i+1, perform step 14;
Step 14, judge whether i equals 201, if step 10 six, perform step 15 if not;
Step 15, employing main control computer 5 read the simulation aberration image of the test beams that cmos image sensor 11 gathers, and store the information that this light beam analog image comprises, the information that described light beam analog image comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer 5 to gather beam quality data by Wavefront sensor 9, described beam quality data are as zernike polynomial coefficient B
kji, and store this zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 10 six;
The inclination angle of step 10 six, adjustment two-dimensional micromotion stage 3, and adjust phase place and the gray scale of spatial light modulator 7 simultaneously, the light beam of the test light that cmos image sensor 11 is gathered produces perturbation, namely compensates wave front aberration by spatial light modulator 7 and two-dimensional micromotion stage 3, performs step 10 seven;
Step 10 seven, employing main control computer 5 read the waveform signal that Wavefront sensor 9 gathers, and obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10 eight;
New zernike polynomial coefficient C described in step 10 eight, determining step 17
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 15; Then perform step 10 nine if not;
Step 10 nine, employing main control computer 5 read cmos image sensor 11 and gather new facula mass center coordinate b
kji', and store this facula mass center coordinate b
kji', perform step 2 ten;
Step 2 ten, employing main control computer 5 are through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 10 nine store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 2 11;
Step 2 11, judge whether j equals 32, if perform step 2 13, perform step 2 12 if not;
Step 2 12, make spatial light modulator 7 adjust a step units backward from current location, make j=j+1, i=0, perform step 15;
Whether step 2 13, the alignment angle judging the light inlet of the telescope 1 of space optical communication terminal and the light-emitting window of parallel light tube 13 are 3mrad, if telescope 1 will be rotated, make the alignment angle of the light inlet of this telescope 1 and the light-emitting window of parallel light tube 13 for-3mrad, make k=k+1, perform step 4; Perform if not, step 2 14;
Step 2 14, rotation telescope 1, make the alignment angle of the light-emitting window of the light inlet of this telescope 1 and parallel light tube 13 adjust 5 μ rad clockwise from current location, make k=k+1, perform step 2 15;
Whether the alignment angle of the light-emitting window of step 2 15, the light inlet judging telescope 1 and parallel light tube 13 is 0mrad, revises the stage in-orbit, perform step 4 if not if perform;
In-orbit revise the stage time, space optical communication terminal with spacecraft 15 in orbit, cmos image sensor 11 for gathering the data of beacon beam,
Stage of revising in-orbit comprises the steps:
The data of the beacon beam that cmos image sensor 11 is gathered by communication port by steps A, space optical communication terminal are sent to ground Master Control Center 18, perform step B;
The data that step B, ground Master Control Center send according to space optical communication terminal in orbit, all data that the ground test simulation stage stores are inquired about, with current space optical communication terminal data similarity dimensions in-orbit in 85% to 100% one is selected to form as test result, according to this composition as the corresponding lens error correction parameter of test result calculations, perform step C;
This lens error correction parameter to be sent to space optical communication terminal in-orbit by communication port by step C, ground Master Control Center, realizes the correction in orbit to space optical communication terminal.
Before carrying out aberration compensating method, interferometer and auxiliary CCD need be adopted to adjust the position of the fibre optical transmission head of semiconductor laser 14, the fibre optical transmission head of semiconductor laser 14 is placed in parallel light tube 13 focus.
In the step one of present embodiment, the beam shaping launched by semiconductor laser 14 by parallel light tube 13 is collimated light beam, what space optical communication terminal received in actual applications is collimated light beam from far field, the light beam divergence angle that semiconductor laser 14 sends is comparatively large, needs could be received by parallel light tube 13 shaping rear space optical communication terminal.
The difference of the aberration compensating method of space optical communication terminal in-orbit described in embodiment two, present embodiment and embodiment one is, described communication port is: the data of the beacon beam that cmos image sensor 11 gathers by the spacecraft 15 carrying optical communication terminal are sent to ground Master Control Center 18 by communication repeating satellite 16 and communication satellite ground telemetering base station 19.
The difference of the aberration compensating method of space optical communication terminal in-orbit described in embodiment three, present embodiment and embodiment one is, described communication port is: the data of the beacon beam that cmos image sensor 11 gathers by the spacecraft 15 carrying optical communication terminal are sent to ground Master Control Center 18 by communication satellite ground telemetering base station 19.
The difference of the aberration compensating method of space optical communication terminal in-orbit described in embodiment four, present embodiment and embodiment one is, described communication port is: the data of the beacon beam that cmos image sensor 11 gathers by the spacecraft 15 carrying optical communication terminal are sent to ground Master Control Center 18 by laser communication through base station, optical communication face 17.
Claims (4)
1. space optical communication terminal aberration compensating method in-orbit, described space optical communication terminal comprises telescope (1), the first Amici prism (2), shaping lens group (10) and cmos image sensor (11),
The light beam being incident to telescope (1) is incident to the first Amici prism (2) after compression,
The reference beam reflected through the first Amici prism (2) is incident to cmos image sensor (11) through shaping lens group (10),
It is characterized in that: the method comprises the ground test dummy run phase and revises two stages of stage in-orbit;
The described ground test dummy run phase comprises the steps:
Step one, employing main control computer (5) send coded command to encoder (12), control semiconductor laser (14) luminous simultaneously, encoder (12) provides modulation signal for semiconductor laser (14), the fibre optical transmission head of described semiconductor laser (14) is positioned in the focus of parallel light tube (13), the picture signal end of main control computer (5) connects the picture signal end of cmos image sensor (11), performs step 2;
Step 2, Wavefront sensor (9) is positioned over the light-emitting window of parallel light tube (13), the original beam through parallel light tube (13) is made to be incident to the search coverage on Wavefront sensor (9) surface, the waveform signal that main control computer (5) gathers according to Wavefront sensor (9) is measured, obtain the zernike polynomial coefficient A of original beam wave front aberration, and store this zernike polynomial coefficient A, perform step 3;
Step 3, be 0rad by the alignment angle of the light inlet of the telescope (1) of space optical communication terminal and the light-emitting window of parallel light tube (13), make the laser through parallel light tube (13) be incident to the light inlet of telescope (1), perform step 4;
Step 4, the reference light picture signal adopting main control computer (5) reading cmos image sensor (11) to gather, using the facula mass center coordinate of described reference light picture signal as coordinate a
k, and store this facula mass center coordinate as coordinate a
k, perform step 5;
Wherein, k represents the number of times that the alignment angle of the light inlet of telescope (1) and the light-emitting window of parallel light tube (13) adjusts, and the initial value of k is 1, k=1,2 ..., 120; a
kthe facula mass center coordinate of reference light picture signal during alignment angle for the light inlet of kth time adjustment telescope (1) and the light-emitting window of parallel light tube (13) as coordinate,
Step 5, two-dimensional micromotion stage (3) is placed on the light-emitting window of telescope (1), the light beam through telescope (1) light-emitting window is made to be incident to two-dimensional micromotion stage (3), the second Amici prism (8) is incident to through spatial light modulator (7), light beam through the second Amici prism (8) transmission is incident to Wavefront sensor (9), the test beams reflected through the second Amici prism (8) is incident to shaping lens group (10), test beams through shaping lens group (10) shaping is incident to cmos image sensor (11)
The micromotion platform drive singal output of main control computer (5) is adopted to connect two-dimensional micromotion stage driver (4),
The control signal output of two-dimensional micromotion stage driver (4) connects the control signal input of two-dimensional micromotion stage (3);
Adopt the light modulation driving signal input of light modulation drive singal output connection space optical modulator driver (6) of main control computer (5),
The control signal input of control signal output connection space optical modulator (7) of spatial light modulator driver (6),
Perform step 6;
Step 6, the test beams picture signal adopting main control computer (5) reading cmos image sensor (11) to gather, using the facula mass center coordinate of described test beams picture signal as coordinate a
k', adjust the position of two-dimensional micromotion stage (3), spatial light modulator (7), the second Amici prism (8) and shaping lens group (10), make the facula mass center coordinate a of test beams picture signal
k' with the facula mass center coordinate a of reference light picture signal
kidentical, perform step 7;
Wherein, a
k' the facula mass center coordinate of test beams picture signal when representing the alignment angle of the light inlet of kth time adjustment telescope (1) and the light-emitting window of parallel light tube (13),
Step 7, employing main control computer (5), by controlling two-dimensional micromotion stage driver (4) adjustment two-dimensional micromotion stage (3), make the working range of two-dimensional micromotion stage (3) be in initial position,
Adopting main control computer (5) by controlling spatial light modulator driver (6) adjustment spatial light modulator (7), making the working range of spatial light modulator (7) be in initial position,
Main control computer (5) is adopted to read the analog picture signal of the test beams that cmos image sensor (11) gathers, and store the information that this light beam analog picture signal comprises, the information that described light beam analog picture signal comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer (5) to gather beam quality data by Wavefront sensor (9), described beam quality data are as zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 8;
Wherein, B
kjito represent that at the light inlet of kth time adjustment telescope (1) these beam quality data are as zernike polynomial coefficient with the light-emitting window of parallel light tube (13) in alignment angle, the secondary adjustment spatial light modulator (7) of jth or beam quality data when regulating two-dimensional micromotion stage (3) for i-th time; C
kjito represent at the light inlet of kth time adjustment telescope (1) with the light-emitting window of parallel light tube (13) at alignment angle, the secondary adjustment spatial light modulator (7) of jth or true zernike polynomial coefficient when regulating two-dimensional micromotion stage (3) for i-th time; The initial value of i is 0; The initial value of j is 0; The working range of two-dimensional micromotion stage (3) is in the scope that X-axis and Y-axis surround, and the scope of X-axis and Y-axis is 0 μm-2 μm; Two-dimensional micromotion stage (3) is that step units carries out 200 adjustments with 10nm, the initial position of two-dimensional micromotion stage (3) is that X-axis keeps 1 μm of position always, Y-axis is in 0 μm of place and starts scanning, the scope that two-dimensional micromotion stage (3) scans is: X-axis keeps 1 μm always, and Y-axis is from 0 μm to 2 μm; The working range of spatial light modulator (7) is 0 gray value-255 gray value, and spatial light modulator (7) stepping-in amount in units of 8 gray values is carried out 32 times and regulated, and the initial position of spatial light modulator (7) is 0 gray value,
The inclination angle of step 8, adjustment two-dimensional micromotion stage (3), and adjust phase place and the gray scale of spatial light modulator (7) simultaneously, the light beam of the test light that cmos image sensor (11) is gathered produces perturbation, namely compensate wave front aberration by spatial light modulator (7) and two-dimensional micromotion stage (3), perform step 9;
Step 9, the waveform signal adopting main control computer (5) reading Wavefront sensor (9) to gather, obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10;
New zernike polynomial coefficient C described in step 10, determining step nine
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 7; Then perform step 11 if not;
Wherein, λ represents the optical maser wavelength used in test process, is the wavelength of optical communication terminal beacon beam,
Step 11, employing main control computer (5) read cmos image sensor (11) and gather new facula mass center coordinate b
kji', and store this facula mass center coordinate b
kji', perform step 12;
Wherein, b
kji' to represent at the light inlet of kth time adjustment telescope (1) with the light-emitting window of parallel light tube (13) at alignment angle, the secondary adjustment spatial light modulator (7) of jth or new facula mass center coordinate when regulating two-dimensional micromotion stage (3) for i-th time
Step 12, adopt main control computer (5) through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 11 store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 13; Step 13, make two-dimensional micromotion stage (3) adjust a step units backward from current location, make i=i+1, perform step 14;
Step 14, judge whether i equals 201, if perform step 10 six, perform step 15 if not;
Step 15, employing main control computer (5) read the simulation aberration image of the test beams that cmos image sensor (11) gathers, and store the information that this light beam analog image comprises, the information that described light beam analog image comprises comprises hot spot image, facula mass center position coordinates, gray value, pixel and light intensity maximum
Adopt main control computer (5) to gather beam quality data by Wavefront sensor (9), described beam quality data are as zernike polynomial coefficient B
kji, and store this zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do difference, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 10 six;
The inclination angle of step 10 six, adjustment two-dimensional micromotion stage (3), and adjust phase place and the gray scale of spatial light modulator (7) simultaneously, the light beam of the test light that cmos image sensor (11) is gathered produces perturbation, namely compensate wave front aberration by spatial light modulator (7) and two-dimensional micromotion stage (3), perform step 10 seven;
Step 10 seven, the waveform signal adopting main control computer (5) reading Wavefront sensor (9) to gather, obtain new zernike polynomial coefficient B
kji', by zernike polynomial coefficient A and new zernike polynomial coefficient B
kji' do difference, obtain new zernike polynomial coefficient C
kji', perform step 10 eight;
New zernike polynomial coefficient C described in step 10 eight, determining step 17
kji' entire system error whether be more than or equal to 1/20 λ, if then perform step 15; Then perform step 10 nine if not;
Step 10 nine, employing main control computer (5) read cmos image sensor (11) and gather new facula mass center coordinate b
kji', and store this facula mass center coordinate b
kji', perform step 2 ten;
Step 2 ten, adopt main control computer (5) through the facula mass center coordinate a of reference light picture signal
kthe new facula mass center coordinate b that coordinate amount and step 10 nine store
kji' coordinate amount do difference, obtain aberration produce coordinate offset amount, described coordinate offset amount is lens error correction parameter, stores this lens error correction parameter, perform step 2 11;
Step 2 11, judge whether j equals 32, if perform step 2 13, perform step 2 12 if not;
Step 2 12, make spatial light modulator (7) adjust a step units backward from current location, make j=j+1, i=0, perform step 15;
Whether step 2 13, the alignment angle judging the light inlet of the telescope (1) of space optical communication terminal and the light-emitting window of parallel light tube (13) are 3mrad, if telescope (1) will be rotated, make the alignment angle of the light inlet of this telescope (1) and the light-emitting window of parallel light tube (13) for-3mrad, make k=k+1, perform step 4; Perform if not, step 2 14;
Step 2 14, rotation telescope (1), make the alignment angle of the light-emitting window of the light inlet of this telescope (1) and parallel light tube (13) adjust 5 μ rad clockwise from current location, make k=k+1, performs step 2 15;
Whether the alignment angle of the light-emitting window of step 2 15, the light inlet judging telescope (1) and parallel light tube (13) is 0mrad, revises the stage in-orbit, perform step 4 if not if perform;
In-orbit revise the stage time, space optical communication terminal with spacecraft (15) in orbit, cmos image sensor (11) for gathering the data of beacon beam,
Stage of revising in-orbit comprises the steps:
The data of the beacon beam that cmos image sensor (11) is gathered by communication port by steps A, space optical communication terminal are sent to ground Master Control Center (18), perform step B;
The data that step B, ground Master Control Center send according to space optical communication terminal in orbit, all data that the ground test simulation stage stores are inquired about, with current space optical communication terminal data similarity dimensions in-orbit in 85% to 100% one is selected to form as test result, according to this composition as the corresponding lens error correction parameter of test result calculations, perform step C;
This lens error correction parameter to be sent to space optical communication terminal in-orbit by communication port by step C, ground Master Control Center, realizes the correction in orbit to space optical communication terminal.
2. the aberration compensating method of space optical communication terminal in-orbit according to claim 1, it is characterized in that, described communication port is: the data of the beacon beam that cmos image sensor (11) gathers by the spacecraft (15) carrying optical communication terminal are sent to ground Master Control Center (18) by communication repeating satellite (16) and communication satellite ground telemetering base station (19).
3. the aberration compensating method of space optical communication terminal in-orbit according to claim 1, it is characterized in that, described communication port is: the data of the beacon beam that cmos image sensor (11) gathers by the spacecraft (15) carrying optical communication terminal are sent to ground Master Control Center (18) by communication satellite ground telemetering base station (19).
4. the aberration compensating method of space optical communication terminal in-orbit according to claim 1, it is characterized in that, described communication port is: the data of the beacon beam that cmos image sensor (11) gathers by the spacecraft (15) carrying optical communication terminal are sent to ground Master Control Center (18) by laser communication through base station, optical communication face (17).
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