CN103441798A - Aberration compensation method of on-orbit space optical communication terminal - Google Patents
Aberration compensation method of on-orbit space optical communication terminal Download PDFInfo
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Abstract
The invention relates to an aberration compensation method of an on-orbit space optical communication terminal. According to the aberration compensation method, the problem of communication link interruption caused by the fact that new aberrations are generated during on-orbit operation of an existing space optical communication terminal is solved. At the ground test simulation stage, simulation measurement is performed on various aberrations which can be generated in the space optical communication terminal and influences on facula centroid location;at the on-orbit correction stage, the data received by a ground master control center are compared with all the data stored at the ground test simulation stage, the data similar to the data of the on-orbit space optical communication terminal are selected to be used as imaging test results, the corresponding aberration correction parameters are calculated according to the results, and therefore on-orbit operation correction of the space optical communication terminal is achieved. According to the aberration compensation method, terminal angle detecting precision is improved, the purpose that communication link normal operation during on-orbit operation of the space optical communication terminal is guaranteed is achieved, and the aberration compensation method is suitable for the fields of aviation, aerospace and communication.
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, the 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 and the emphasis of studying.
Along with the development of satellite technology, satellite also improves constantly the demand of communication data rate.Satellite optical communication because its communication data rate is high, good confidentiality, antijamming capability is strong, terminal volume is little, the advantage such as low in energy consumption has become the U.S., the focus of Japan and the countries and regions research such as European.Optical communication mainly is divided into optical fiber communication and satellite optical communication (wireless light communication).Fibre Optical Communication Technology is comparative maturity now, and to putting in the middle of the social production life.Satellite optical communication is still in positive exploration and practice.Satellite optical communication with conventional satellite, communicate by letter (microwave communication) compare, the characteristics of himself are arranged.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 the problem of himself in satellite optical communication, the laser communication link on satellite and ground be subject to atmosphere and precipitation affects larger.Yet these problems can be by adding ground station and solving by optical communication networking technologys such as relay satellite communications.
In Intersatellite Optical Communication System, (PAT) technology that aims at, catches, follows the tracks of is to be related to the key technology that can laser communication link be set up.A key parameters that affects the PAT technology is the measurement to alignment angle by tracking transducer, its essence is the calculating to beacon hot spot gradation of image barycenter by imageing sensor.
The satellite laser communications system is to be operated in highly sensitive communication system under optical diffraction limit, the communication distance limit and photodetection maximum conditions.For guaranteeing that communication link so has good communication performance under exacting terms, system has high requirement to the property indices of satellite optical communication terminal and the quality of light beam.
Reason due to some unpredictable factors after environmental impact in-orbit and emission, even the satellite optical communication terminal was carried out the ground aberration compensation before with spacecraft 15 emissions, but still likely produce new aberration during in orbit, the precision that affect meeting hot spot gray scale barycenter location of these aberrations on the imaging of beacon hot spot.Because hot spot gray scale barycenter is the critical quantity that affects angle detection, if therefore the aberration of these new generations is not revised timely on the impact of facula mass center location, the inaccurate aiming acquisition and tracking process that will directly affect communication in the location of hot spot gray scale barycenter, even may cause the interruption of communication link when serious.
Therefore, in order to realize high-quality space optical communication, need to still can in the elimination system, believe that the aberration produced is on the impact of facula mass center location after with spacecraft 15 emissions at optical communication terminal.By install Adaptable System additional in the optical communication terminal optical system, come automatic calibration can realize above-mentioned purpose.But because Adaptable System not only involves great expense, and install this system additional also can bring extra power consumption in terminal, also increased the cost of terminal emission when increasing terminal volume and weight.Therefore at present also do not have space optical communication terminal to install the case of Adaptable System additional.
Summary of the invention
The present invention produces new aberration during in orbit eventually and causes the problem of the interruption of communication link in order to solve existing space optical communication, thereby has proposed 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 after compression the first Amici prism,
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 in-orbit two stages of stage;
The described ground test dummy run phase comprises the steps:
Wherein, k means the number of times that the alignment angle of the light-emitting window of telescopical light inlet and parallel light tube is adjusted, and the initial value of k is 1, k=1,2 ..., 120; a
kbe the facula mass center coordinate of the reference beam picture signal while adjusting the alignment angle of light-emitting window of telescopical light inlet and parallel light tube for the k time as coordinate,
Adopt the micromotion platform of main control computer to drive signal output part to connect the 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 driving signal output part 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,
Execution step six;
Wherein, a
k' the facula mass center coordinate of test light picture signal while meaning to adjust for the k time the alignment angle of light-emitting window of telescopical light inlet and parallel light tube,
Step 7, employing main control computer are adjusted two-dimensional micromotion stage by controlling the two-dimensional micromotion stage driver, make the working range of two-dimensional micromotion stage in initial position,
Adopt main control computer to adjust spatial light modulator by controlling the spatial light modulator driver, make the working range of spatial light modulator in initial position,
Adopt main control computer to read the analog picture signal of the test beams of cmos image sensor collection, 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 the beam quality data by Wavefront sensor, described beam quality data are as the zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Execution step eight;
Wherein, B
kjibe illustrated in the beam quality data of light-emitting window when alignment angle, the j time adjusting spatial light modulator or the i time adjusting two-dimensional micromotion stage of adjusting telescopical light inlet and parallel light tube for the k time, these beam quality data are as the zernike polynomial coefficient; C
kjibe illustrated in the true zernike polynomial coefficient of light-emitting window when alignment angle, the j time adjusting spatial light modulator or the i time adjusting two-dimensional micromotion stage of adjusting telescopical light inlet and parallel light tube for the k 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 μ m-2 μ m; Two-dimensional micromotion stage be take 10nm and is carried out 200 times as step units and regulate, the initial position of two-dimensional micromotion stage is that X-axis keeps 1 μ m position always, Y-axis starts scanning in 0 μ m place, the scope of two-dimensional micromotion stage scanning is: X-axis keeps 1 μ m always, and Y-axis is from 0 μ m to 2 μ m; The working range of spatial light modulator is 0 gray value-255 gray value, and spatial light modulator be take 8 gray values and carried out 32 times as unit stepping amount and regulate, 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,, by spatial light modulator and two-dimensional micromotion stage compensation wave front aberration, performs step nine;
Wherein, λ represents the optical maser wavelength of using in test process, is optical communication terminal beacon light wavelength,
Wherein, b
kji' be illustrated in the new facula mass center coordinate of light-emitting window when alignment angle, the j time adjusting spatial light modulator or the i time adjusting two-dimensional micromotion stage of adjusting telescopical light inlet and parallel light tube for the k time,
Step 15, employing main control computer read the simulation aberration image of the test beams of cmos image sensor collection, 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 the beam quality data by Wavefront sensor, described beam quality data are as the 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 poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 16;
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,, by spatial light modulator and two-dimensional micromotion stage compensation wave front aberration, performs step 17;
Whether the alignment angle of the light-emitting window of step 2 13, the telescopical light inlet that judges space optical communication terminal and parallel light tube is 3mrad, if will rotate telescope, make the alignment angle of the light-emitting window of this telescopical light inlet and parallel light tube be-3mrad, make k=k+1, perform step four; Carry out if not step 2 14;
While revising the stage in-orbit, with spacecraft in orbit, cmos image sensor is used for gathering the data of beacon beam to space optical communication terminal,
The correction stage comprises the steps: in-orbit
Steps A, space optical communication terminal are sent to the ground Master Control Center by communication port by the data of the beacon beam of cmos image sensor collection, execution step B;
The data that step B, ground Master Control Center basis space optical communication terminal in orbit send, to the ground test simulation stage, all data of storage are inquired about, select with current space optical communication terminal data similarity scope in-orbit one forming as test result in 85% to 100%, form as the corresponding aberration corrected parameter of test result calculations execution step C according to this;
Step C, ground Master Control Center are sent to space optical communication terminal in-orbit by communication port by this aberration corrected parameter, realize the correction in orbit to space optical communication terminal.
The spacecraft that carries optical communication terminal is sent to the ground Master Control Center by the data of the beacon beam of cmos image sensor collection by communication repeating satellite and communication satellite ground telemetering base station.
The spacecraft that carries optical communication terminal is sent to the ground Master Control Center by the data of the beacon beam of cmos image sensor collection by communication satellite ground telemetering base station.
The spacecraft that carries optical communication terminal is sent to ground Master Control Center by laser communication through optical communication face base station by the data of the beacon beam of cmos image sensor collection.
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 various issuable aberrations and corresponding facula mass center location thereof carry out analogue measurement, described auxiliary equipment comprises two-dimensional micromotion stage, the two-dimensional micromotion stage driver, main control computer, the spatial light modulator driver, spatial light modulator, the second Amici prism, Wavefront sensor, encoder, parallel light tube and semiconductor laser, the data that the stage of revising in-orbit receives by comparison ground Master Control Center and all data of ground test dummy run phase storage, select the data similar to space optical communication terminal data in-orbit as the imaging test result, calculate corresponding aberration corrected parameter according to this result, the in orbit correction of realization to space optical communication terminal, the present invention has improved the terminal angle detection accuracy, because the angle detection accuracy determines by the facula mass center positioning precision, reached guaranteed space optical communication eventually in orbit during the purpose of the normal operation of communication link.
The accompanying drawing explanation
The structural representation of Fig. 1 in the ground test dummy run phase, space optical communication terminal being adjusted;
The structural representation that Fig. 2 is space optical communication terminal;
The structural representation of Fig. 3 for parallel light tube 13 is debugged;
Fig. 4 is the space optical communication terminal structural representation of stage and ground communication in-orbit.
Embodiment
Embodiment one, in conjunction with Fig. 1 to Fig. 4, illustrate present embodiment, the described space optical communication terminal in-orbit of present embodiment aberration compensating method, 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 that is incident to telescope 1 is incident to the first Amici prism 2 after compression,
Reference beam through the first Amici prism 2 refractions is incident to cmos image sensor 11 through shaping lens group 10,
The method comprises the ground test dummy run phase and revises in-orbit two stages of stage;
The described ground test dummy run phase comprises the steps:
Wherein, k means the number of times that the alignment angle of the light-emitting window of the light inlet of telescope 1 and parallel light tube 13 is adjusted, and the initial value of k is 1, k=1,2 ..., 120; a
kbe the facula mass center coordinate of the reference beam picture signal while adjusting the alignment angle of light-emitting window of the light inlet of telescope 1 and parallel light tube 13 for the k time as coordinate,
Adopt the micromotion platform of main control computer 5 to drive signal output part 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 driving signal output part 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,
Execution step six;
Wherein, a
k' the facula mass center coordinate of test light picture signal while meaning to adjust for the k time the alignment angle of light-emitting window of the light inlet of telescope 1 and parallel light tube 13,
Step 7, employing main control computer 5 are adjusted two-dimensional micromotion stages 3 by controlling two-dimensional micromotion stage driver 4, make the working range of two-dimensional micromotion stage 3 in initial position,
Adopt main control computer 5 to adjust spatial light modulator 7 by controlling spatial light modulator driver 6, make the working range of spatial light modulator 7 in initial position,
Adopt main control computer 5 to read the analog picture signal of the test beams of cmos image sensor 11 collections, 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 the beam quality data by Wavefront sensor 9, described beam quality data are as the zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Execution step eight;
Wherein, B
kjibe illustrated in the beam quality data of light-emitting window when alignment angle, the j time adjusting spatial light modulator 7 or the i time adjusting two-dimensional micromotion stage 3 of light inlet and the parallel light tube 13 of the k time adjustment telescope 1, these beam quality data are as the zernike polynomial coefficient; C
kjibe illustrated in the light inlet of the k time adjustment telescope 1 and the true zernike polynomial coefficient of light-emitting window when alignment angle, the j time adjusting spatial light modulator 7 or the i time adjusting two-dimensional micromotion stage 3 of parallel light tube 13; 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 μ m-2 μ m; Two-dimensional micromotion stage 3 be take 10nm and is carried out 200 times as step units and regulate, the initial position of two-dimensional micromotion stage 3 is that X-axis keeps 1 μ m position always, Y-axis starts scanning in 0 μ m place, the scope of two-dimensional micromotion stage 3 scannings is: X-axis keeps 1 μ m always, and Y-axis is from 0 μ m to 2 μ m; The working range of spatial light modulator 7 is 0 gray value-255 gray value, and spatial light modulator 7 be take 8 gray values and carried out 32 times as unit stepping amount and regulate, 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,, by spatial light modulator 7 and two-dimensional micromotion stage 3 compensation wave front aberrations, performs step nine;
Wherein, λ represents the optical maser wavelength of using in test process, is optical communication terminal beacon light wavelength,
Wherein, b
kji' be illustrated in the new facula mass center coordinate of light-emitting window when alignment angle, the j time adjusting spatial light modulator 7 or the i time adjusting two-dimensional micromotion stage 3 of the light inlet of adjusting telescope 1 for the k time and parallel light tube 13,
Step 15, employing main control computer 5 read the simulation aberration image of the test beams of cmos image sensor 11 collections, 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 the beam quality data by Wavefront sensor 9, described beam quality data are as the 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 poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 16;
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,, by spatial light modulator 7 and two-dimensional micromotion stage 3 compensation wave front aberrations, performs step 17;
Whether the alignment angle of the light-emitting window of step 2 13, the light inlet of telescope 1 that judges space optical communication terminal and parallel light tube 13 is 3mrad, if will rotate telescope 1, the alignment angle that makes the light-emitting window of the light inlet of this telescope 1 and parallel light tube 13 is-3mrad, make k=k+1, perform step four; Carry out if not step 2 14;
Whether the alignment angle of the light-emitting window of step 2 15, the light inlet that judges telescope 1 and parallel light tube 13 is 0mrad, if carry out, revises in-orbit the stage, performs step if not four;
While revising the stage in-orbit, with spacecraft 15 in orbit, cmos image sensor 11 is for gathering the data of beacon beam for space optical communication terminal,
The correction stage comprises the steps: in-orbit
The data of the beacon beam that steps A, space optical communication terminal gather cmos image sensor 11 by communication port are sent to ground Master Control Center 18, execution step B;
The data that step B, ground Master Control Center basis space optical communication terminal in orbit send, to the ground test simulation stage, all data of storage are inquired about, select with current space optical communication terminal data similarity scope in-orbit one forming as test result in 85% to 100%, form as the corresponding aberration corrected parameter of test result calculations execution step C according to this;
Step C, ground Master Control Center are sent to space optical communication terminal in-orbit by communication port by this aberration corrected parameter, realize the correction in orbit to space optical communication terminal.
Before carrying out aberration compensating method, need to adopt interferometer and auxiliary CCD to adjust the position of the optical fiber emitting head of semiconductor laser 14, the optical fiber emitting head of semiconductor laser 14 is placed on parallel light tube 13 focuses.
In the step 1 of present embodiment, by parallel light tube 13, by the beam shaping of semiconductor laser 14 emissions, be collimated light beam, what space optical communication terminal received in actual applications is the collimated light beam from far field, the light beam divergence angle that semiconductor laser 14 sends is larger, needs could receive by parallel light tube 13 shaping rear space optical communication terminals.
The difference of embodiment two, present embodiment and the described space optical communication terminal in-orbit of embodiment one aberration compensating method is, described communication port is: the data of carrying the beacon beam that the spacecraft 15 of optical communication terminal gathers cmos image sensor 11 are sent to ground Master Control Center 18 by communication repeating satellite 16 and communication satellite ground telemetering base station 19.
The difference of embodiment three, present embodiment and the described space optical communication terminal in-orbit of embodiment one aberration compensating method is, described communication port is: the data of carrying the beacon beam that the spacecraft 15 of optical communication terminal gathers cmos image sensor 11 are sent to ground Master Control Center 18 by communication satellite ground telemetering base station 19.
The difference of embodiment four, present embodiment and the described space optical communication terminal in-orbit of embodiment one aberration compensating method is, described communication port is: the data of carrying the beacon beam that the spacecraft 15 of optical communication terminal gathers cmos image sensor 11 are sent to ground Master Control Center 18 by laser communication through optical communication face base station 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 that is incident to telescope (1) is incident to the first Amici prism (2) after compression,
Reference beam through the first Amici prism (2) refraction 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 in-orbit two stages of stage;
The described ground test dummy run phase comprises the steps:
Step 1, 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 optical fiber emitting head of described semiconductor laser (14) is positioned on 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 two;
Step 2, Wavefront sensor (9) is positioned over to the light-emitting window of parallel light tube (13), make to be incident to through the original beam of parallel light tube (13) 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 three;
Step 3, by the alignment angle of the light-emitting window of the light inlet of the telescope of space optical communication terminal (1) and parallel light tube (13), be 0rad, make to be incident to through the laser of parallel light tube (13) light inlet of telescope (1), perform step four;
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 five;
Wherein, k means the number of times that the alignment angle of the light-emitting window of the light inlet of telescope (1) and parallel light tube (13) is adjusted, and the initial value of k is 1, k=1,2 ..., 120; a
kbe the facula mass center coordinate of the reference beam picture signal while adjusting the alignment angle of light-emitting window of the light inlet of telescope (1) and parallel light tube (13) for the k time as coordinate,
Step 5, two-dimensional micromotion stage (3) is placed on to the light-emitting window of telescope (1), make to be incident to two-dimensional micromotion stage (3) through the light beam of telescope (1) light-emitting window, be incident to the second Amici prism (8) through spatial light modulator (7), light beam through the second Amici prism (8) transmission is incident to Wavefront sensor (9), test beams through the second Amici prism (8) refraction is incident to shaping lens group (10), test beams through shaping lens group (10) shaping is incident to cmos image sensor (11)
Adopt the micromotion platform of main control computer (5) to drive signal output part 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 driving signal output part 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),
Execution step six;
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', 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 light picture signal
k' with the facula mass center coordinate a of reference light picture signal
kidentical, perform step seven;
Wherein, a
k' the facula mass center coordinate of test light picture signal while meaning to adjust for the k time the alignment angle of light-emitting window of the light inlet of telescope (1) and parallel light tube (13),
Step 7, employing main control computer (5) are adjusted two-dimensional micromotion stage (3) by controlling two-dimensional micromotion stage driver (4), make the working range of two-dimensional micromotion stage (3) in initial position,
Adopt main control computer (5) to adjust spatial light modulator (7) by controlling spatial light modulator driver (6), make the working range of spatial light modulator (7) in initial position,
Adopt main control computer (5) to read the analog picture signal of the test beams of cmos image sensor (11) collection, 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 the beam quality data by Wavefront sensor (9), described beam quality data are as the zernike polynomial coefficient B
kji,
By zernike polynomial coefficient A and zernike polynomial coefficient B
kjiidentical entry do poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Execution step eight;
Wherein, B
kjibe illustrated in the beam quality data of light-emitting window when alignment angle, the j time adjusting spatial light modulator (7) or the i time adjusting two-dimensional micromotion stage (3) of light inlet and the parallel light tube (13) of the k time adjustment telescope (1), these beam quality data are as the zernike polynomial coefficient; C
kjibe illustrated in the light inlet of the k time adjustment telescope (1) and the true zernike polynomial coefficient of light-emitting window when alignment angle, the j time adjusting spatial light modulator (7) or the i time adjusting two-dimensional micromotion stage (3) of parallel light tube (13); 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 μ m-2 μ m; Two-dimensional micromotion stage (3) be take 10nm and is carried out 200 times as step units and regulate, the initial position of two-dimensional micromotion stage (3) is that X-axis keeps 1 μ m position always, Y-axis starts scanning in 0 μ m place, the scope of two-dimensional micromotion stage (3) scanning is: X-axis keeps 1 μ m always, and Y-axis is from 0 μ m to 2 μ m; The working range of spatial light modulator (7) is 0 gray value-255 gray value, and spatial light modulator (7) be take 8 gray values and carried out 32 times as unit stepping amount and regulate, 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, by spatial light modulator (7) and two-dimensional micromotion stage (3) compensation wave front aberration, perform step nine;
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 poorly, obtain new zernike polynomial coefficient C
kji', perform step ten;
Step 10, the described new zernike polynomial coefficient C of determining step nine
kji' the entire system error whether be more than or equal to 1/20 λ, if perform step seven; Perform step 11 if not;
Wherein, λ represents the optical maser wavelength of using in test process, is optical communication terminal beacon light wavelength,
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' be illustrated in the new facula mass center coordinate of light-emitting window when alignment angle, the j time adjusting spatial light modulator (7) or the i time adjusting two-dimensional micromotion stage (3) of the light inlet of adjusting telescope (1) for the k time and parallel light tube (13),
Step 12, adopt the facula mass center coordinate a of main control computer (5) through the reference light picture signal
kthe new facula mass center coordinate b of coordinate amount and step 11 storage
kji' the coordinate amount do poorly, obtain the coordinate offset amount that aberration produces, described coordinate offset amount is the aberration corrected parameter, stores this aberration corrected parameter, performs step 13; Step 13, make two-dimensional micromotion stage (3) adjust backward a step units from current location, make i=i+1, perform step 14;
Step 14, judge whether i equals 201, if step 10 six performs step 15 if not;
Step 15, employing main control computer (5) read the simulation aberration image of the test beams of cmos image sensor (11) collection, 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 the beam quality data by Wavefront sensor (9), described beam quality data are as the 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 poorly, obtain the true zernike polynomial coefficient C of space optical communication terminal
kji, and store this zernike polynomial coefficient C
kji,
Perform step 16;
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, by spatial light modulator (7) and two-dimensional micromotion stage (3) compensation wave front aberration, perform step 17;
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 poorly, obtain new zernike polynomial coefficient C
kji', perform step 18;
Step 10 eight, the described new zernike polynomial coefficient C of determining step 17
kji' the entire system error whether be more than or equal to 1/20 λ, if perform step 15; Perform step 19 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 20;
Step 2 ten, adopt the facula mass center coordinate a of main control computer (5) through the reference light picture signal
kthe new facula mass center coordinate b of coordinate amount and step 10 nine storages
kji' the coordinate amount do poorly, obtain the coordinate offset amount that aberration produces, described coordinate offset amount is the aberration corrected parameter, stores this aberration corrected parameter, performs step 21;
Step 2 11, judge whether j equals 32, if perform step 23, perform step if not 22;
Step 2 12, make spatial light modulator (7) adjust backward a step units from current location, make j=j+1, i=0, perform step 15;
Whether the alignment angle of the light-emitting window of step 2 13, the light inlet of telescope (1) that judges space optical communication terminal and parallel light tube (13) is 3mrad, if will rotate telescope (1), the alignment angle that makes the light-emitting window of the light inlet of this telescope (1) and parallel light tube (13) is-3mrad, make k=k+1, perform step four; Carry out if not step 2 14;
Step 2 14, rotation telescope (1), the alignment angle of the light inlet that makes this telescope (1) and the light-emitting window of parallel light tube (13), from current location adjustment 5 μ rad clockwise, makes k=k+1, performs step 25;
Whether the alignment angle of the light-emitting window of step 2 15, the light inlet that judges telescope (1) and parallel light tube (13) is 0mrad, if carry out, revises in-orbit the stage, performs step if not four;
While revising the stage in-orbit, with spacecraft (15) in orbit, cmos image sensor (11) is for gathering the data of beacon beam for space optical communication terminal,
The correction stage comprises the steps: in-orbit
The data of the beacon beam that steps A, space optical communication terminal gather cmos image sensor (11) by communication port are sent to ground Master Control Center (18), execution step B;
The data that step B, ground Master Control Center basis space optical communication terminal in orbit send, to the ground test simulation stage, all data of storage are inquired about, select with current space optical communication terminal data similarity scope in-orbit one forming as test result in 85% to 100%, form as the corresponding aberration corrected parameter of test result calculations execution step C according to this;
Step C, ground Master Control Center are sent to space optical communication terminal in-orbit by communication port by this aberration corrected parameter, realize 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 spacecraft (15) that carries optical communication terminal is sent to ground Master Control Center (18) by the data of the beacon beam of cmos image sensor (11) collection 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 spacecraft (15) that carries optical communication terminal is sent to ground Master Control Center (18) by the data of the beacon beam of cmos image sensor (11) collection 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 spacecraft (15) that carries optical communication terminal is sent to ground Master Control Center (18) by laser communication through optical communication face base station (17) by the data of the beacon beam of cmos image sensor (11) collection.
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