CN103293959A - Method and device for simulating laser direction control technology for spatial laser interferometer system - Google Patents
Method and device for simulating laser direction control technology for spatial laser interferometer system Download PDFInfo
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Abstract
The invention provides a method for simulating a laser direction control technology for a spatial laser interferometer system. The method includes steps of generating collimated, monochromatic, intensity-controllable and phase-controllable linearly polarized incident laser and local laser; modulating the direction of the incident laser by the aid of a laser direction jitter simulation system to simulate jitter of directions of target signals; gathering the incident laser and the local laser by the aid of a differential interferometry circuit to form laser differential interferometry signals, converting the photoelectric signals by the aid of a four-quadrant photoelectric detector and simultaneously measuring phase information of four quadrants by the aid of a phase meter; collecting the phase information by the aid of a laser direction control system in real time, and precisely controlling an angle of the local laser by an optimized adaptive PID (proportion, integration and differentiation) control process so that two laser beams are strictly parallel to each other and spatial measurement requirements are met. The method has the advantages that a phase-sensitive angle measuring methodology is adopted, and the method is high in sensitivity as compared with an intensity-sensitive methodology, and high-precision laser direction control can be implemented conveniently.
Description
Technical field
The present invention relates to a kind of analogy method and device of space laser interference system laser guide control technology, relate to particularly that a kind of to can be used for the range finding of space double star laser heterodyne interference be analogy method and the device of laser guide control technology, in order to carry out the ground simulation experiment.
Background technology
Many space exploration projects of present European and American areas planned development, for example lunar gravimetry field explorer satellite of future generation plan, the advanced Gravity Satellite plan of the earth and space gravitational wave detection plan etc.China holds a meeting to discuss how to carry out gravitational wave detection specially, and the space gravitational wave detection also is put in the space science planning in 50 years of Chinese Academy of Sciences's formulation.Simultaneously, be subjected to the promotion of the immense success of Gravity Satellite GRACE plan, in order to catch up with international gravimetric trend, China also begins to inquire into the advanced Gravity Satellite system that builds laser interferometry between autonomous star.Because the high-precision requirement of space exploration, various countries have all taked between star the laser interference ranging technology as the basic methodology of acquisition of signal on the basis of optimizing contrast.
The methodology of laser interference has very high requirement to the collimation of laser between star, but because the complicacy of space environment, satellite is subjected to extraneous factor (such as atmospheric disturbance, solar wind and solar radiation etc.) interference, the laser that spacecraft sends can be shaken in exit direction, and this error in pointing is the final distance accuracy of influence directly.Error in pointing is to measuring the influence of phase place:
Wherein:
λ: optical maser wavelength;
D: wavefront curvature error;
D: telescope receives diameter;
θ
Dc: point to the static deflection error;
δ θ: laser guide shake.
Reduce the wavefront curvature error and can improve distance accuracy, but under certain processing technique, the wavefront curvature error is definite value.The reducing of telescope diameter can reduce phase error, but can cause weakening of received optical power, increased shot noise and improved the difficulty of photodetection.And the precision that improves laser guide control is to reduce the effective ways that point to phase error.
For advanced gravimetry project, the about 100Km of double star spacing, the about 300-400Km of orbit altitude is in the low vacuum environment, is subjected to atmospheric disturbance comparatively serious, and the disturbance of other nonconservative force is also very complicated simultaneously.Measure the requirement of project laser interference distance accuracy according to advanced gravity field, at signal frequency section 0.1mHz-0.1Hz, the laser guide control accuracy need be better than
This just requires the laser guide control system must possess performance requirements such as dynamic range is big, control accuracy is high, controlled frequency height; And for the gravitational wave detection plan of space, though the gravitational wave detection satellite is in deep space, external disturbance is little, but the double star spacing is very remote, be about 1,000,000 kilometers, the laser interference signal that double star receives is very faint, and this proposes higher requirement and challenge to the laser guide control accuracy, need realize being better than in the signal frequency section of 1mHz-1Hz
The laser guide control accuracy.Therefore, laser guide control has become the important technology bottleneck of the advanced Gravity Satellite of restriction and space gravitational wave detection.
Abroad, the gordian technique of space gravitational wave detection and advanced gravimetry project mainly is responsible for research and development by German eLISA/NGO research group.Previous eLISA/NGO group is dropped in phasometer, laser interferometer with main energy and does not have research field such as towing control, the research of laser guide control system lags behind, still be in computer mould and fit beforehand research and study carefully the stage, cause the test that soon all can't point to control technology in the LISA-Path-finder satellite of emission in 2015.
The space gravitational wave detection of China and the research of advanced Gravity Satellite are started late, and wherein the laser guide control system research of space laser precision measurement is not carried out as yet.But the Chinese Academy of Sciences gravity field is measured and gravitational wave detection is listed medium-term and long-term development plan in, intends reaching the gravity field with 100 kilometers spatial resolutions and 1mGal magnitude and distribute in the time in following seven to ten years, and realize
The space laser interference system of distance accuracy is for following gravitational wave detection and advanced gravity field measurement project lay the foundation.But China's existing attitude of satellite control technical indicator is
Need synchronized development laser guide control technology, to satisfy the requirement of space laser interfeerometry ranging.There is certain technological accumulation in China in laser aiming and the sensing control of applications such as laser communications, target following and military use.Their imaging methods or four-quadrant photo detector center and spot center coincidence method of adopting are learned as angle-measuring method more, and its precision generally exists
About, the measurement requirement that does not far reach space gravitational wave detection and advanced Gravity Satellite.Therefore, laser guide control has become the technical bottleneck of Chinese Space gravitational wave detection and the development of advanced Gravity Satellite.
Summary of the invention
The technical matters that the present invention solves provides a kind of analogy method of space laser interference system laser guide control technology, is used for accurately carrying out the ground simulation experiment of space laser interference system laser guide control.
Another technical matters that the present invention solves is exactly, and a kind of analogue means of space laser interference system laser guide control technology is provided, and ground simulation that can implementation space laser interference system laser guide control is tested.
In order to address the above problem, the invention provides a kind of analogy method of space laser interference system laser guide control technology, comprise the steps:
(a) produce collimation, monochrome, polarization state, intensity and controlled linear polarization incident laser and the local laser of phase place;
(b) by laser guide jitter simulation system, described incident laser direction is modulated, be used for the shake of simulated target sense;
(c) by the differential interferometry light path, intensity and the polarization state of incident laser and local laser are regulated and control, and described incident laser and described local laser are converged formation laser differential interference signal,
(d) by the angular-sensitive system, carry out the photosignal conversion, measure the phase information of each quadrant;
(e) by the laser guide control system, gather above-mentioned phase information in real time, utilize the self-adaptation proportional-integral-differential control method of optimizing, the direction of described local laser is carried out the control of high precision angle, realize the strict parallel of two bundle laser, and make its sensing deviation satisfy the space measurement requirement.
Further, described step (a) specifically comprises the steps:
1) open the 1064nm laser instrument, preheated one-section is opened frequency regulator and acousto-optic frequency shifters power supply after the time, laser instrument output 45 degree linearly polarized lights;
2) laser prevents laser return laser light device through first faraday isolator, influences the laser instrument operate as normal, and through the one 1/2 spectroscope, laser is divided into two-way, and two ways of optical signals is respectively as incident laser and local laser;
3) two-way laser is separately respectively through an acousto-optic frequency shifters, diaphragm, wedge, piezoelectricity beat mirror, linear polarizer, two-way laser produces frequency difference 1MHz, by diaphragm filtering interfering laser, wedged plate is corrected the laser direction deflection that causes because of acousto-optic frequency shifters, and linear polarizer is regulated laser polarization state and intensity;
Described step (b) specifically comprises the steps:
4) laser guide jitter simulation device is controlled the first deflection driven source the first piezoelectricity beat mirror is regulated and control, and simulates the shake of the laser direction that is launched by the far-end spacecraft;
Described step (c) specifically comprises the steps:
5) incident laser arrives the 2 1/2 spectroscope;
6) local laser arrives the 2 1/2 spectroscope;
7) through forming the laser differential interference signal behind the 2 1/2 spectroscope;
Described step (d) specifically comprises the steps:
8) four-quadrant photo detector is converted into electric signal with the difference light signal;
9) the four-way phasometer is accurately measured the phase information of each quadrant simultaneously
Described step (e) specifically comprises the steps:
10) the laser guide controller calculates left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize the phase place-angular relationship of demarcating then
(r wherein: four-quadrant photo detector photosurface radius; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, regulate the second deflection driven source by the Adaptive PID Control of optimizing, the second piezoelectricity beat mirror is controlled, carry out angle control, realize the strict parallel of two bundle laser.
The present invention also provides a kind of analogue means of space laser interference system laser guide control technology, comprises at least:
One incident laser arm is for generation of the controlled linear polarization incident laser of collimation, monochrome, polarization state, intensity and phase place;
One laser guide jitter simulation system links to each other with described incident laser arm, and described incident laser direction is modulated, and is used for simulated target sense shake;
One local laser arm is for generation of the local laser of the controlled linear polarization of collimation, monochrome, polarization state, intensity and phase place;
One differential interferometry light path links to each other with described incident laser arm and described local laser arm, is used for intensity and the polarization state of incident laser and local laser are regulated and control, and described incident laser and described local laser are converged formation laser differential interference signal;
One angular-sensitive system carries out the photosignal conversion, measures the phase information of each quadrant;
One laser guide control system is carried out analyzing and processing to the phase data that detects, and the direction of described local laser is carried out angle control, realizes the strict parallel of two bundle laser, namely points to control.
Further, described incident laser arm comprises and setting gradually along optical axis direction:
A 1064nm laser instrument is 1064nm45 degree linearly polarized laser for generation of wavelength;
First faraday isolator, incident polarization direction are 45 degree, and the outgoing polarization direction is 90 degree, utilizes Faraday effect, prevents laser return laser light device, influences the laser instrument operate as normal;
The one 1/2 spectroscope is divided into two-way after making laser incident, and light intensity reduces by half, and two ways of optical signals is respectively as incident laser and local laser;
First acousto-optic frequency shifters is carried out shift frequency to institute through laser;
First diaphragm is used for filtering interfering laser;
First wedged plate is corrected the laser direction deflection that is caused by first acousto-optic frequency shifters;
A first piezoelectricity beat mirror is made up of piezoelectricity beat platform and level crossing, and the laser through described first wedged plate is reflected;
First linear polarizer, regulation and control shoot laser intensity and polarization state;
Described laser guide jitter simulation system comprises:
A laser guide jitter simulation device, the shake of programming simulation incident laser direction, and regulate and control the first deflection driven source;
A first deflection driven source is used for receiving the laser dither modulating signal that described laser guide jitter simulation device sends, and the described first piezoelectricity beat mirror is modulated;
Described local laser arm comprises and setting gradually along optical axis direction:
A second sound optical frequency shifter carries out shift frequency to institute through laser;
First diaphragm is used for filtering interfering laser;
Second wedged plate is corrected the laser direction deflection that is caused by first acousto-optic frequency shifters;
A second piezoelectricity beat mirror is made up of piezoelectricity beat platform and level crossing, makes the laser reflection through described second wedged plate;
Second linear polarizer, regulation and control shoot laser intensity and polarization state;
Described differential interferometry light path comprises and setting gradually along optical axis direction:
The 2 1/2 spectroscope makes the laser through the laser after described first linear polarizer and described second linear polarizer of process form two-way differential interferometry laser signal from two surfaces after 45 degree incidents;
Described angular-sensitive system comprises:
A four-quadrant photo detector makes described two-way differential interferometry laser signal be converted into electric signal;
A four-way high accuracy number phasometer is for the phase information of each quadrant that the electric signal that imports into from described four-quadrant photo detector is comprised
Carrying out the while accurately measures;
Described laser guide control system comprises:
A laser guide controller is used for gathering, storing described four-way phase information that phasometer is surveyed
Real time data, calculate left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize the phase place-angular relationship of demarcating then
(r wherein: four-quadrant photo detector photosurface radius; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, generate angle control signal by pid control algorithm;
A second deflection driven source is used for receiving the described angle control signal that described laser guide controller sends, and the described second piezoelectricity beat mirror is controlled, and realizes the strict parallel of two bundle laser, namely points to control.
Advantage of the present invention is:
1) according to space device laser shake data, write control software, the first piezoelectricity beat platform is carried out the control of high precision angle, realize the modulation of incident laser direction high precision, come the received incident laser direction shake from the far-end spacecraft of Simulated Spacecraft.
2) adopt the phase sensitive angle-measuring method to learn, have higher sensitivity than the responsive methodology of light intensity.The total noise that this method can the part erasure signal improves the precision of laser guide control simultaneously.
3) the high precision phase information that detects of the real-time receiving phase meter of laser guide controller, utilize the methodology of phase sensitive angle measurement, by the self-adaptive PID feedback of optimizing, the second piezoelectricity beat platform is carried out the control of high precision angle, realize the strict parallel of two bundle laser, namely point to control.
Description of drawings
Fig. 1 is the analogue means figure of space laser interference system laser guide control technology of the present invention.
Fig. 2 is laser guide jitter simulation system flowchart of the present invention.
Fig. 3 is laser guide control system process flow diagram of the present invention.
Embodiment
Hereinafter will be elaborated to embodiments of the invention by reference to the accompanying drawings.Need to prove that under the situation of not conflicting, the embodiment among the application and the feature among the embodiment be combination in any mutually.
The invention provides the analogue means of a kind of space laser interference system laser guide control technology as shown in Figure 1, comprise at least:
One incident laser arm is for generation of the controlled linear polarization incident laser of collimation, monochrome, polarization state, intensity and phase place;
One laser guide jitter simulation system links to each other with the incident laser arm, to incident laser direction high precision modulation, is used for virtual space spacecraft incident laser direction shake (referring to Fig. 2);
One local laser arm is for generation of the local laser of the controlled linear polarization of collimation, monochrome, polarization state, intensity and phase place;
One differential interferometry light path links to each other with described incident laser arm and described local laser arm, is used for intensity and the polarization state of incident laser and local laser are regulated and control, and described incident laser and described local laser are converged formation laser differential interference signal;
One angular-sensitive system carries out the photosignal conversion, measures the phase information of each quadrant;
One laser guide control system, gather above-mentioned phase information in real time, utilize the self-adaptation proportional-integral-differential control method of optimizing, the direction of described local laser is carried out the control of high precision angle, realize the strict parallel of two bundle laser, and make its sensing deviation satisfy the space measurement requirement.
The incident laser arm comprises and setting gradually along optical axis direction:
A 1064nm laser instrument 1 is 1064nm45 degree linearly polarized laser for generation of wavelength;
The one 1/2 spectroscope 31 is divided into two-way after making laser incident, and light intensity reduces by half, and two ways of optical signals is respectively as incident laser and local laser;
First acousto-optic frequency shifters 41 is carried out shift frequency to institute through laser;
First wedged plate 61 makes by the deflection of the laser direction that causes behind first acousto-optic frequency shifters, 41 shift frequencies to obtain correcting;
A first piezoelectricity beat mirror 91 is made up of piezoelectricity beat platform and level crossing, and the laser through first wedged plate 61 is reflected;
First linear polarizer 111, regulation and control shoot laser intensity and polarization state;
Laser guide jitter simulation system comprises:
A laser guide jitter simulation device 71, the shake of programming simulation incident laser direction, and regulate and control the first deflection driven source;
A first deflection driven source 81 is used for receiving the laser dither modulating signal that laser guide jitter simulation device 71 sends, and the first piezoelectricity beat mirror 91 is modulated;
Local laser arm comprises and setting gradually along optical axis direction:
A second sound optical frequency shifter 42 makes by the laser of the one 1/2 spectroscope 31 transmissions through shift frequency later, and produces required frequency difference with laser through first acousto-optic frequency shifters 41;
Second wedged plate 62 is proofreaied and correct by the 42 laser direction deflections of second sound optical frequency shifter;
A second piezoelectricity beat mirror 92 is made up of piezoelectricity beat platform and level crossing, makes the laser reflection through second wedged plate 62;
Second linear polarizer 112, calibration of laser polarization state, the 90 degree linearly polarized lasers that shoot laser is maintained the standard;
The differential interferometry light path comprises and setting gradually along optical axis direction:
The 2 1/2 spectroscope 32, make through the laser after first linear polarizer 111 with after 45 degree incidents, form the differential interferometry laser signal from two surfaces through the laser of second linear polarizer 112;
The angular-sensitive system comprises:
A four-quadrant photo detector 12 is with laser differential signal switching electrical signals;
A four-way phasometer 13, the accurate phase information of measuring each quadrant of four-quadrant photo detector simultaneously
The laser guide control system comprises:
A laser guide controller 72 is used for gathering in real time four-way phasometer 13 phase informations of surveying
Calculate left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize the phase place-angular relationship of demarcating then
(r wherein: four-quadrant photo detector 12 photosurface radiuses; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, namely
Generate angle control signal by the Adaptive PID Control algorithm of optimizing (referring to Fig. 3);
A second deflection driven source 82 is used for receiving the angle control signal that laser guide controller 72 sends, and the second piezoelectricity beat mirror 92 is controlled, and realizes the strict parallel of two bundle laser, namely points to control.
The concrete operations step is:
1) open 1064nm laser instrument 1, preheated one-section is opened frequency regulator and acousto-optic frequency shifters power supply after the time, laser instrument output 45 degree linearly polarized lights;
2) laser prevents laser return laser light device through first faraday isolator 2, influences the laser instrument operate as normal, and through the one 1/2 spectroscope 31, laser is divided into two-way, and two ways of optical signals is respectively as incident laser and local laser;
3) two-way laser is separately respectively through an acousto-optic frequency shifters, diaphragm, wedge, piezoelectricity beat mirror, linear polarizer, two-way laser produces frequency difference 1MHz, by diaphragm filtering interfering laser, wedged plate is corrected the laser direction deflection that causes because of acousto-optic frequency shifters, and linear polarizer is regulated laser polarization state and intensity;
4) the 81 pairs of first piezoelectricity beat mirrors 91 in the laser guide jitter simulation device 71 control first deflection driven sources are regulated and control, and simulate the shake of the laser direction that is launched by the far-end spacecraft;
5) incident laser arrives the 2 1/2 spectroscope 32;
6) local laser arrives the 2 1/2 spectroscope 32;
7) form the differential interferometry laser signal through the 2 1/2 spectroscope 32 backs;
8) four-quadrant photo detector 12 is converted into electric signal with the difference light signal;
9) four-way phasometer 13 is accurately measured the phase information of each quadrant simultaneously
10) laser guide controller 72 calculates left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize the phase place-angular relationship of demarcating then
(r wherein: four-quadrant photo detector photosurface radius; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, regulate the second deflection driven source 82 by the Adaptive PID Control of optimizing, the second piezoelectricity beat mirror 92 is controlled, carry out the control of high precision angle, make two bundle laser strictnesses parallel, and make the sensing deviation satisfy the space measurement requirement.
The above is the preferred embodiments of the present invention only, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. the analogy method of a space laser interference system laser guide control technology is characterized in that, comprises the steps:
(a) produce collimation, monochrome, polarization state, intensity and controlled linear polarization incident laser and the local laser of phase place;
(b) by laser guide jitter simulation system, described incident laser direction is modulated, be used for the shake of simulated target sense;
(c) by the differential interferometry light path, intensity and the polarization state of incident laser and local laser are regulated and control, and described incident laser and described local laser are converged formation laser differential interference signal,
(d) by the angular-sensitive system, carry out the photosignal conversion, measure the phase information of each quadrant;
(e) by the laser guide control system, gather above-mentioned phase information in real time, utilize the self-adaptation proportional-integral-differential control method of optimizing, the direction of described local laser is carried out the control of high precision angle, realize the strict parallel of two bundle laser, and make its sensing deviation satisfy the space measurement requirement.
2. weigh the analogy method of 1 described space laser interference system laser guide control technology as claim, it is characterized in that described step (a) specifically comprises the steps:
1) open the 1064nm laser instrument, preheated one-section is opened frequency regulator and acousto-optic frequency shifters power supply after the time, laser instrument output 45 degree linearly polarized lights;
2) laser prevents laser return laser light device through first faraday isolator, influences the laser instrument operate as normal, and through the one 1/2 spectroscope, laser is divided into two-way, and two ways of optical signals is respectively as incident laser and local laser;
3) two-way laser is separately respectively through an acousto-optic frequency shifters, diaphragm, wedge, piezoelectricity beat mirror, linear polarizer, two-way laser produces frequency difference 1MHz, by diaphragm filtering interfering laser, wedged plate is corrected the laser direction deflection that causes because of acousto-optic frequency shifters, and linear polarizer is regulated laser polarization state and intensity;
Described step (b) specifically comprises the steps:
4) laser guide jitter simulation device is controlled the first deflection driven source the first piezoelectricity beat mirror is regulated and control, and simulates the shake of the laser direction that is launched by the far-end spacecraft;
Described step (c) specifically comprises the steps:
5) incident laser arrives the 2 1/2 spectroscope;
6) local laser arrives the 2 1/2 spectroscope;
7) through forming the laser differential interference signal behind the 2 1/2 spectroscope;
Described step (d) specifically comprises the steps:
8) four-quadrant photo detector transfers the difference light signal to electric signal;
9) the four-way phasometer is accurately measured the phase information of each quadrant simultaneously
Described step (e) specifically comprises the steps:
10) the laser guide controller calculates left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize phase place-angular relationship then
(r wherein: four-quadrant photo detector photosurface radius; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, regulate the second deflection driven source by the Adaptive PID Control of optimizing, the second piezoelectricity beat mirror is controlled, carry out angle control, realize the strict parallel of two bundle laser.
3. the analogue means of a space laser interference system laser guide control technology is characterized in that, comprises at least:
One incident laser arm is for generation of the controlled linear polarization incident laser of collimation, monochrome, polarization state, intensity and phase place;
One laser guide jitter simulation system links to each other with described incident laser arm, to the modulation of described incident laser direction, is used for the shake of simulated target sense;
One local laser arm is for generation of the local laser of the controlled linear polarization of collimation, monochrome, polarization state, intensity and phase place;
One differential interferometry light path links to each other with described incident laser arm and described local laser arm, is used for intensity and the polarization state of incident laser and local laser are regulated and control, and described incident laser and described local laser are converged formation laser differential interference signal;
One angular-sensitive system carries out the photosignal conversion, measures the phase information of each quadrant;
One laser guide control system is carried out analyzing and processing to the phase data that detects, and the direction of described local laser is carried out angle control, realizes the strict parallel of two bundle laser, namely points to control.
4. the analogue means of a kind of space laser interference system laser guide control technology as claimed in claim 3 is characterized in that:
Described incident laser arm comprises and setting gradually along optical axis direction:
A 1064nm laser instrument is 1064nm45 degree linearly polarized laser for generation of wavelength;
First faraday isolator, incident polarization direction are 45 degree, and the outgoing polarization direction is 90 degree, utilizes Faraday effect, prevents laser return laser light device, influences the laser instrument operate as normal;
The one 1/2 spectroscope is divided into two-way after making laser incident, and light intensity reduces by half, and two ways of optical signals is respectively as incident laser and local laser;
First acousto-optic frequency shifters is carried out shift frequency to institute through laser;
First diaphragm is used for filtering interfering laser;
First wedged plate is corrected the laser direction deflection that is caused by first acousto-optic frequency shifters;
A first piezoelectricity beat mirror is made up of piezoelectricity beat platform and level crossing, and the laser through described first wedged plate is reflected;
First linear polarizer, regulation and control shoot laser intensity and polarization state;
Described laser guide jitter simulation system comprises:
A laser guide jitter simulation device, the shake of programming simulation incident laser direction, and regulate and control the first deflection driven source;
A first deflection driven source is used for receiving the laser dither modulating signal that described laser guide jitter simulation device sends, and the described first piezoelectricity beat mirror is modulated;
Described local laser arm comprises and setting gradually along optical axis direction:
A second sound optical frequency shifter carries out shift frequency to institute through laser;
First diaphragm is used for filtering interfering laser;
Second wedged plate is corrected the laser direction deflection that is caused by first acousto-optic frequency shifters;
A second piezoelectricity beat mirror is made up of piezoelectricity beat platform and level crossing, makes the laser reflection through described second wedged plate;
Second linear polarizer, regulation and control shoot laser intensity and polarization state;
Described differential interferometry light path comprises and setting gradually along optical axis direction:
The 2 1/2 spectroscope makes the laser through the laser after described first linear polarizer and described second linear polarizer of process form two-way differential interferometry laser signal from two surfaces after 45 degree incidents;
Described angular-sensitive system comprises:
A four-quadrant photo detector makes described two-way differential interferometry laser signal be converted into electric signal;
A four-way phasometer is for the phase information of each quadrant that the electric signal that imports into from described four-quadrant photo detector is comprised
Carrying out the while accurately measures;
Described laser guide control system comprises:
A laser guide controller is used for gathering, storing phase information that described digital phasemeter is surveyed
Real time data, calculate left and right sides quadrant phase differential respectively
With last lower quadrant phase differential
Utilize phase place-angular relationship then
(r wherein: four-quadrant photo detector photosurface radius; λ: optical maser wavelength; α: the laser angle), obtain left and right sides angle of deflection
YawAngle of deflection up and down
Pitch, generate angle control signal by pid control algorithm;
A second deflection driven source is used for receiving the described angle control signal that described laser guide controller sends, and the described second piezoelectricity beat mirror is controlled, and realizes the strict parallel of two bundle laser, namely points to control.
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| CN116184518A (en) * | 2023-02-08 | 2023-05-30 | 中国科学院力学研究所 | Laser pointing and phase locking control simulation method and system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3501605B2 (en) * | 1996-12-27 | 2004-03-02 | キヤノン株式会社 | Interferometer and shape measuring device |
| CN101178336A (en) * | 2007-07-04 | 2008-05-14 | 长春理工大学 | optical profiletype simulate vibration movement platform device for space laser communication |
| CN102168944B (en) * | 2010-12-24 | 2012-10-10 | 中国科学院上海光学精密机械研究所 | Double frequency laser interferometer for absolute distance measurement and measurement method thereof |
| CN102768011B (en) * | 2012-07-16 | 2015-05-06 | 上海大学 | Heterodyne laser interferometer capable of eliminating nonlinearity |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109031250A (en) * | 2018-06-12 | 2018-12-18 | 南京理工大学 | It is a kind of to emit quantitative detection system in servo-actuated laser radar performance room |
| CN109031250B (en) * | 2018-06-12 | 2021-09-10 | 南京理工大学 | Indoor quantitative detection system for performance of laser radar capable of emitting follow-up laser |
| CN112504635A (en) * | 2020-11-18 | 2021-03-16 | 北京控制工程研究所 | Optical wedge type space high-precision pointing measuring instrument calibration device |
| CN112504635B (en) * | 2020-11-18 | 2021-10-01 | 北京控制工程研究所 | Optical wedge type space high-precision pointing measuring instrument calibration device |
| CN116184518A (en) * | 2023-02-08 | 2023-05-30 | 中国科学院力学研究所 | Laser pointing and phase locking control simulation method and system |
| CN116184518B (en) * | 2023-02-08 | 2024-04-16 | 中国科学院力学研究所 | Laser pointing and phase locking control simulation method and system |
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