CN105572685A - Bidirectional femtosecond pulse-based deep space gravitational wave detection method and device - Google Patents

Bidirectional femtosecond pulse-based deep space gravitational wave detection method and device Download PDF

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CN105572685A
CN105572685A CN201610084900.8A CN201610084900A CN105572685A CN 105572685 A CN105572685 A CN 105572685A CN 201610084900 A CN201610084900 A CN 201610084900A CN 105572685 A CN105572685 A CN 105572685A
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detection unit
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CN105572685B (en
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于亮
谭久彬
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Harbin Institute of Technology
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/02—Systems using the reflection of electromagnetic waves other than radio waves
    • G01S17/06—Systems determining position data of a target
    • G01S17/46—Indirect determination of position data
    • G01S17/48—Active triangulation systems, i.e. using the transmission and reflection of electromagnetic waves other than radio waves

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Abstract

The invention relates to a bidirectional femtosecond pulse-based deep space gravitational wave detection method and device and belongs to the gravitational wave detection field. According to the method, equal-arm length differential detection on gravitational wave signals is realized through scanning optical delay lines, and detection sensitivity can reach a sub nanometer level; and two measuring arms are both of a pulse time-domain lock type bidirectional measurement structure, so that light echo power of a system can be calculated according to a square attenuation function of the distance instead of an original biquadrate attenuation function of the distance, and therefore, detection of deep space gravitational waves at a scale of hundreds of millions of kilometers can be realized. The device comprises a measuring end at a master satellite, a No. 1 active reflector located at a slave satellite A and a No. 2 active reflector located at a slave satellite B. With the method and device adopted, problems in real-time communication and high-accuracy clock synchronization between satellites which are separated from each other by long distances can be solved.

Description

Based on deep space gravitational wave detection method and the device of two-way femtosecond pulse
Technical field
The invention belongs to gravitational wave detection field, relate generally to a kind of solar system yardstick deep space gravitational wave detection method based on femtosecond laser and device.
Background technology
For many years, gravitational wave detection is the study hotspot of countries in the world always, the detection of gravitational wave is the direct checking to general relativity prophesy, also be the Direct Test to its core concept, and the quantization and large unified model, research universe Origin and evolution inquiring into gravitational field is significant.The detection of gravitational wave directly facilitates the birth of gravitational astronomy, make to replace traditional electromagnetic wave means observation universe to become possibility with gravitational wave, this can provide the information that cannot obtain in the past in a large number, for people deepen to provide new approach to the understanding in universe further for us.
Remote accurate displacement detection is the core technology of gravitational wave detection, and current detection method is many based on laser interferometer.The ground gravitational waves such as the TAMA300 of the LIGO of the U.S., German GEO600, gondola VIRGO and Japan, ranging can reach tens kilometers; The spatial attraction wave detectors such as the LISA of the U.S., the NGO in Europe, ranging can reach millions of kilometer; The deep space gravitational wave ranging such as the ASTROD of China and European collaborative will reach more than one hundred million kilometer, and the ranging of its follow-up work is farther, will launch accurate displacement detection on outer solar system yardstick.
But in above-mentioned deep space gravitational wave detection task, because ranging is remote, with current beam shaping technology, even if the beam divergence angle of emergent light is only several microradian, when arriving remote destination end, hot spot also will spread extremely obvious; Add inevitable optical loss in light path, the light echo power of range measurement system and tested distance are that biquadratic relation acutely decays, and the light echo energy that system finally detects is only a part very little in emanated energy.Such as, the system light echo energy in spatial attraction ripple detection project LISA is only 1/10 of emergent light energy 10, the system light echo energy in ASTROD is only 3/10 of emergent light energy 14.The too small signal to noise ratio (S/N ratio) of range measurement system that will cause of light echo power significantly reduces, and then measuring accuracy cannot satisfy the demands, and cannot measure even at all.
In long distance laser range finding field, as 2002, JournalofGeodynamics the 34th volume third phase published an article " Asynchronouslasertranspondersforpreciseinterplanetaryran gingandtimetransfer "; And for example 2010, photoelectric project the 37th volume the 5th phase publishes an article " asynchronous response laser ranging technique ", all the pulse power of asynchronous transponder to range measurement system is adopted to amplify at tested end, make system light echo power become square attenuation function from the biquadratic attenuation function of tested distance, significantly extend system ranging.But, time domain delay and the nonsynchronous problem of clock is there is in the pulse train after the method amplification compared with former pulse train, the time-domain information of former pulse signal can not be retained while amp pulse power, can only be compensated by other means, cause distance accuracy to be difficult to break through millimeter magnitude.And the method needs to realize between apart from remote two measuring junctions the synchronous and real-time Communication for Power of high precision clock.
In gravitational wave detection field, as 2003, PhysicalReviewD the 67th volume the 12nd phase publishes an article " Implementationoftime-delayinterferometryforLISA "; And for example 2012, JournalofGeodesy the 86th volume the 12nd phase publishes an article " IntersatellitelaserranginginstrumentfortheGRACEfollow-on mission ", all propose two-way laser interference displacement detection method, measured by the main laser of the slave laser device conjunction measuring end of tested end, its ranging can reach five gigameters.But, two-way interferometer still cannot meet the ranging demand of the deep space gravitational wave detection tasks more than one hundred million kilometers such as ASTROD, and the method needs synchronous with high precision clock apart from realizing real-time Communication for Power between remote two measuring junctions, this is be difficult to realize on the distance scale of more than one hundred million kilometers.
In recent years, along with the development of femtosecond laser technology, femtosecond pulse distance-finding method has progressed into the visual field of people.Its main advantage is that pulse energy is very concentrated, can reach high peak power instantaneously.Compared to the continuous wave such as interferometry and two-way interferometry measuring method, under identical laser average power, system light echo power can improve multiple even more than ten magnitudes, is thus more suitable for overlength distance and measures.In addition, based on the distance-finding method of femtosecond laser compared to traditional pulse distance-finding method, higher precision can be reached.
In femtosecond laser range finding field, as 2010, NaturePhotonics the 4th volume the 10th phase published an article " Time-of-flightmeasurementwithfemtosecondlightpulses "; And for example 2012, Acta Physica Sinica the 61st volume the 24th phase publishes an article " any long absolute distance measurement based on femtosecond laser balance optical cross-correlation ", a kind of balance optical cross-correlation method for femtosecond pulse is all proposed, by the time domain locking between ranging pulse and reference pulse, achieve the distance accuracy of nanometer scale.But in overlength distance is measured, the method is still not enough to the ranging demand meeting deep space gravitational wave detection task, and along with the increase of tested distance, its measuring error linearly increases, cannot the accuracy requirement of meeting spatial gravitational wave detection task.In addition, in overlength distance is measured, because the two-way time of measuring light is very long, greatly have impact on the dynamic perfromance of measuring system, make the method to measure static object, displacement detection cannot be realized.
In sum, a kind of solar system yardstick deep space gravitational wave detection method based on femtosecond laser and device is lacked at present in gravitational wave detection field.
Summary of the invention
The present invention is directed to that above-mentioned gravitational wave detection and long distance laser measuring method and device detection sensitivity are lower, ranging needs to be improved further and apart from the problem such as be difficult to realize real-time Communication for Power between remote measuring junction and high precision clock is synchronous, propose and devise a kind of deep space gravitational wave detection method based on two-way femtosecond pulse and device.Utilize the brachium differential detection structures such as three satellites constitute on solar system track, two gage beams all have employed pulse temporal locking-type bidirectional measurement structure, achieve the deep space gravitational wave detection of more than one hundred million kilometers of yardsticks, detection sensitivity can reach sub-nanometer scale, avoids the real-time Communication for Power between remote satellite and high precision clock stationary problem simultaneously.
Object of the present invention is achieved through the following technical solutions:
A kind of two-way femtosecond pulse high precision displacement detection method, the method step is as follows:
A, by primary, launch from star A with from star B according to predetermined trajectory, three satellites are evenly distributed on solar system track, form the equilateral triangle that the length of side is about 2.7 hundred million kilometers; Primary respectively with from star A and the gage beam that forms the brachiums such as two from star B, precision detection is carried out to the relative change of two brachiums;
B, be arranged in the measuring junction of primary, the femto-second laser pulse sequence that femto-second laser sends is divided into two bundles after a light splitting optical path; First bundle is launched to remote from star A as measuring-signal A, and the second bundle is launched to remote from star B as measuring-signal B;
C, be arranged in an active reflector from star A, the femto-second laser pulse sequence that No. two femto-second lasers send is divided into two bundles after No. two light splitting optical paths; Wherein a branch ofly launch back remote primary as heliogram A, another bundle detects as together balancing photoelectric detection unit by No. two with reference to signal A with the measuring-signal A detected; Feedback signal is produced after balance photodetection is carried out to reference signal A and the measuring-signal A detected, and then the chamber progress row FEEDBACK CONTROL to No. two femto-second lasers, by changing its pulse repetition rate, realizing reference signal A and interlocking with the high-precision pulse time domain of the measuring-signal A detected; Meanwhile, be arranged in No. two active reflectors from star B, the femto-second laser pulse sequence that No. three femto-second lasers send is divided into two bundles after No. three light splitting optical paths; Wherein a branch ofly launch back remote primary as heliogram B, another bundle detects as together balancing photoelectric detection unit by No. three with reference to signal B with the measuring-signal B detected; Feedback signal is produced after balance photodetection is carried out to reference signal B and the measuring-signal B detected, and then the chamber progress row FEEDBACK CONTROL to No. three femto-second lasers, by changing its pulse repetition rate, realizing reference signal B and interlocking with the high-precision pulse time domain of the measuring-signal B detected;
D, be arranged in the measuring junction of primary, the heliogram A detected and heliogram B is together detected by a balance photoelectric detection unit; Produce feedback signal after carrying out balance photodetection to heliogram A and heliogram B, the mode scanned by optical delay line carries out FEEDBACK CONTROL to the light path of heliogram B, realizes the high-precision pulse time domain interlocking of heliogram A and heliogram B;
E, when gravitational wave is inswept with suitable angle, two gage beams all by producing very small reverse displacement, cause heliogram A and heliogram B to produce deviation in time domain; A control module controls the light path that optical delay line scanning element changes heliogram B, the pulse train of heliogram A and heliogram B is relocked, the displacement that then precision displacement table produces is the difference of the displacement that two gage beams produce, that is target gravitational wave signal.
Based on a deep space gravitational wave detecting device for two-way femtosecond pulse, its measuring junction comprises a femto-second laser, a light splitting optical path, balance photoelectric detection unit, a control module and an optical delay line scanning element; Be provided with an active reflector and No. two active reflectors respectively at two tested ends, form and wait brachium differential detection structure to gravitational wave signal, two isometric gage beams all have employed pulse temporal locking-type bidirectional measurement structure; A described active reflector is made up of No. two femto-second lasers, No. two light splitting optical paths, No. two balance photoelectric detection unit and No. two control modules; The output light of No. two femto-second lasers points to No. two light splitting optical paths; The output light of No. two light splitting optical paths points to the input end of measuring junction and No. two balance photoelectric detection unit respectively; The output terminal of No. two balance photoelectric detection unit is connected to the input end of No. two control modules; The output terminal of No. two control modules is connected to No. two femto-second lasers; Described No. two active reflectors are made up of No. three femto-second lasers, No. three light splitting optical paths, No. three balance photoelectric detection unit and No. three control modules; The output light of No. three femto-second lasers points to No. three light splitting optical paths; The output light of No. three light splitting optical paths points to the input end of measuring junction and No. three balance photoelectric detection unit respectively; The output terminal of No. three balance photoelectric detection unit is connected to the input end of No. three control modules; The output terminal of No. three control modules is connected to No. three femto-second lasers.
The structure of a described light splitting optical path is: the output light of a femto-second laser is divided into two bundles after a quarter-wave plate and a polarization spectroscope; Wherein through Beam directive active reflector after No. four quarter-wave plates and a beam-expanding collimation device; Another bundle reflected light directive No. two active reflectors after No. two quarter-wave plates and No. three beam-expanding collimation devices; Laser No. one, directive balance photoelectric detection unit after No. two beam-expanding collimation devices, No. five quarter-wave plates, No. two catoptrons and No. two polarization spectroscopes that an active reflector launches; Laser directive corner cube reflector after No. four beam-expanding collimation devices, No. three quarter-wave plates and a catoptron that No. two active reflectors launch; The reflected light of corner cube reflector also No. one, directive balance photoelectric detection unit after No. two polarization spectroscopes reflections.
The structure of described No. two light splitting optical paths is: the emergent light of No. two femto-second lasers is divided into two bundles after No. seven quarter-wave plates and No. four polarization spectroscopes; Wherein through Beam directive primary measuring junction after No. eight quarter-wave plates and No. six beam-expanding collimation devices; Another bundle reflected light is No. two, directive balance photoelectric detection unit after No. three polarization spectroscopes; Meanwhile, the laser launched from primary measuring junction also No. two, directive balance photoelectric detection unit after No. five beam-expanding collimation devices, No. six quarter-wave plates and No. three polarization spectroscopes.
The structure of described No. three light splitting optical paths is: the emergent light of No. three femto-second lasers is divided into two bundles after No. ten quarter-wave plates and No. six polarization spectroscopes; Wherein through Beam directive primary measuring junction after ride on Bus No. 11 quarter-wave plate and No. eight beam-expanding collimation devices; Another bundle reflected light is No. three, directive balance photoelectric detection unit after No. five polarization spectroscopes; Meanwhile, the laser launched from primary measuring junction also No. three, directive balance photoelectric detection unit after No. seven beam-expanding collimation devices, No. nine quarter-wave plates and No. five polarization spectroscopes.
The present invention has following characteristics and beneficial effect:
(1) two gage beam all have employed pulse temporal locking-type bidirectional measurement structure, system light echo power has been become square attenuation function from the biquadratic attenuation function of tested distance, achieve the overlength distance survey of deep space of more than one hundred million kilometers of yardsticks, detection sensitivity can reach sub-nanometer scale.
The impact that what (2) three satellites were formed wait brachium detecting structure to counteract laser frequency error to a great extent brings, by optical delay line scanning, FEEDBACK CONTROL is carried out to light path and achieve differential detection to gravitational wave signal, ensure that the detection sensitivity of overlength distance displacement detection process Central Asia nanometer scale.
(3) primary measuring junction and two are from relatively independent between star active reflector, avoid at a distance of remote intersatellite real-time Communication for Power and high precision clock stationary problem.
Accompanying drawing explanation
Fig. 1 is General allocation structure schematic diagram of the present invention.
Fig. 2 is apparatus structure schematic diagram of the present invention.
In figure, piece number illustrates: No. 1 balance photoelectric detection unit, No. 2 femto-second lasers, 3 No. three light splitting optical paths, 4 No. three balance photoelectric detection unit, 5 No. three control modules, 6 No. three femto-second lasers, 7 No. two balance photoelectric detection unit, 8 No. two control modules, 9 No. two femto-second lasers, 10 No. two light splitting optical paths, No. 11 light splitting optical paths, 12 optical delay line scanning elements, No. 13 control modules, No. 14 quarter-wave plates, No. 15 polarization spectroscopes, 16 No. two quarter-wave plates, 17 No. three beam-expanding collimation devices, 18 No. seven beam-expanding collimation devices, 19 No. nine quarter-wave plates, 20 No. five polarization spectroscopes, 21 No. three shaping circuits, 22 No. three control circuits, 23 No. ten quarter-wave plates, 24 No. six polarization spectroscopes, 25 ride on Bus No. 11 quarter-wave plates, 26 No. eight beam-expanding collimation devices, 27 No. four beam-expanding collimation devices, 28 No. three quarter-wave plates, 29 No. four quarter-wave plates, No. 30 beam-expanding collimation devices, 31 No. five beam-expanding collimation devices, 32 No. six quarter-wave plates, 33 No. three polarization spectroscopes, 34 No. two shaping circuits, 35 No. two control circuits, 36 No. seven quarter-wave plates, 37 No. four polarization spectroscopes, 38 No. eight quarter-wave plates, 39 No. six beam-expanding collimation devices, 40 No. two beam-expanding collimation devices, 41 No. five quarter-wave plates, 42 No. two catoptrons, 43 No. two polarization spectroscopes, No. 44 catoptrons, No. 45 shaping circuits, 46 corner cube reflectors, No. 47 control circuits, 48 precise linear guides, 49 precision displacement table.
Embodiment
Below in conjunction with accompanying drawing, the embodiment of the present invention is described in detail.
The deep space gravitational wave detecting device based on two-way femtosecond pulse of the present embodiment, Fig. 1 is its General allocation structure schematic diagram, Fig. 2 is its apparatus structure schematic diagram, and the measuring junction of this device comprises No. 11, one, a femto-second laser 2, light splitting optical path balance photoelectric detection unit 1, control module 13 and optical delay line scanning element 12; Be provided with an active reflector and No. two active reflectors respectively at two tested ends, form and wait brachium differential detection structure to gravitational wave signal, two isometric gage beams all have employed pulse temporal locking-type bidirectional measurement structure; A described active reflector balances photoelectric detection unit 7 by No. 10, two, No. two femto-second lasers 9, No. two light splitting optical paths and No. two control modules 8 form; The output light of No. two femto-second lasers 9 points to No. two light splitting optical paths 10; The output light of No. two light splitting optical paths 10 points to the input end of measuring junction and No. two balance photoelectric detection unit 7 respectively; The output terminal of No. two balance photoelectric detection unit 7 is connected to the input end of No. two control modules 8; The output terminal of No. two control modules 8 is connected to No. two femto-second lasers 9; Described No. two active reflectors balance photoelectric detection unit 4 by No. 3, three, No. three femto-second lasers 6, No. three light splitting optical paths and No. three control modules 5 form; The output light of No. three femto-second lasers 6 points to No. three light splitting optical paths 3; The output light of No. three light splitting optical paths 3 points to the input end of measuring junction and No. three balance photoelectric detection unit 4 respectively; The output terminal of No. three balance photoelectric detection unit 4 is connected to the input end of No. three control modules 5; The output terminal of No. three control modules 5 is connected to No. three femto-second lasers 6.
The structure of a described light splitting optical path 11 is: the output light of a femto-second laser 2 is divided into two bundles after a quarter-wave plate 14 and a polarization spectroscope 15; Wherein through Beam directive active reflector after No. four quarter-wave plates 29 and a beam-expanding collimation device 30; Another bundle reflected light directive No. two active reflectors after No. two quarter-wave plates 16 and No. three beam-expanding collimation devices 17; Laser No. one, directive balance photoelectric detection unit 1 after No. two beam-expanding collimation devices 40, No. five quarter-wave plates 41, No. two catoptrons 42 and No. two polarization spectroscopes 43 that an active reflector launches; Laser directive corner cube reflector 46 after No. four beam-expanding collimation devices 27, No. three quarter-wave plates 28 and a catoptron 44 that No. two active reflectors launch; Reflected light No. one, directive balance photoelectric detection unit 1 after No. two polarization spectroscopes 43 reflect of corner cube reflector 46.
The structure of described No. two light splitting optical paths 8 is: the emergent light of No. two femto-second lasers 9 is divided into two bundles after No. seven quarter-wave plates 36 and No. four polarization spectroscopes 37; Wherein through Beam directive primary measuring junction after No. eight quarter-wave plates 38 and No. six beam-expanding collimation devices 39; Another bundle reflected light is No. two, directive balance photoelectric detection unit 7 after No. three polarization spectroscopes 33; Meanwhile, the laser launched from primary measuring junction is also No. two, directive balance photoelectric detection unit 7 after No. five beam-expanding collimation devices 31, No. six quarter-wave plates 32 and No. three polarization spectroscopes 33 successively.
The structure of described No. three light splitting optical paths 3 is: the emergent light of No. three femto-second lasers 6 is divided into two bundles after No. ten quarter-wave plates 23 and No. six polarization spectroscopes 24; Wherein through Beam directive primary measuring junction after ride on Bus No. 11 quarter-wave plate 25 and No. eight beam-expanding collimation devices 26; Another bundle reflected light is No. three, directive balance photoelectric detection unit 4 after No. five polarization spectroscopes 20; Meanwhile, the laser launched from primary measuring junction is also No. three, directive balance photoelectric detection unit 4 after No. seven beam-expanding collimation devices 18, No. nine quarter-wave plates 19 and No. five polarization spectroscopes 20 successively.
Based on a deep space gravitational wave detection method for two-way femtosecond pulse, the method step is as follows:
A, by primary, launch from star A with from star B according to predetermined trajectory, three satellites are evenly distributed on solar system track, form the equilateral triangle that the length of side is about 2.7 hundred million kilometers; Primary respectively with from star A and the gage beam that forms the brachiums such as two from star B, precision detection is carried out to the relative change of two brachiums.
B, be arranged in the measuring junction of primary, the femto-second laser pulse sequence sent from a femto-second laser 2 has become circularly polarized light from linearly polarized light after a quarter-wave plate 14, and its wavelength X is 1550nm; Pulse repetition rate f is 100MHz; Recurrence interval T is 10 -8s; Pulse width w is 10fs.This circularly polarized light is divided into two bundles after a polarization spectroscope 15, and the P light be transmitted, as measuring-signal A, is designated as S ma, after No. four quarter-wave plates 29, become circularly polarized light, then launch after the beam-expanding collimation of a beam-expanding collimation device 30 distally from star A; By the S light that reflects as measuring-signal B, be designated as S mb, after No. two quarter-wave plates 16, become circularly polarized light, then after the beam-expanding collimation of No. three beam-expanding collimation devices 17, launch distally from star B.
C, be arranged in an active reflector from star A, the S in step b maafter the propagation of about 2.7 hundred million kilometers, received by No. two light splitting optical paths 10.The measuring-signal A detected, is designated as S ma', after No. five beam-expanding collimation devices 31 and No. six quarter-wave plates 32, become P light, again No. two, directive balance photoelectric detection unit 7 after the transmission of No. three polarization spectroscopes 33.The femto-second laser pulse sequence sent from No. two femto-second lasers 9 has become circularly polarized light from linearly polarized light after No. seven quarter-wave plates 36, its wavelength X afor 1550nm; Pulse repetition rate f aabout 100MHz; Recurrence interval T aabout 10 -8s; Pulse width w afor 10fs.This circularly polarized light is divided into two bundles after No. four polarization spectroscopes 37, and the P light be transmitted, as heliogram A, is designated as S ba, after No. eight quarter-wave plate 38, become circularly polarized light, then after the beam-expanding collimation of No. six beam-expanding collimation devices 39, launch back the primary in a distant place; By the S light that reflects as with reference to signal A, be designated as S ra, No. two, directive balance photoelectric detection unit 7 after the reflection of No. three polarization spectroscopes 33.S ma' and S rafeedback signal A is produced after overbalance photodetection.Feedback signal A in No. two shaping circuits 34 after filtering, amplify and shaping after, enter No. two control circuits 35; Produce control signal by No. two control circuits 35, FEEDBACK CONTROL is carried out to the pulse repetition rate of No. two femto-second lasers 9, thus realizes S raand S ma' real-time overlap in time domain and locking, that is S baand S ma' between pulse temporal interlocking.
Similarly, No. two active reflectors from star B are being arranged in, the S in step b mbafter the propagation of about 2.7 hundred million kilometers, received by No. three light splitting optical paths 3.The measuring-signal B detected, is designated as S mb', after No. seven beam-expanding collimation devices 18 and No. nine quarter-wave plates 19, become P light, again No. three, directive balance photoelectric detection unit 4 after the transmission of No. five polarization spectroscopes 20.The femto-second laser pulse sequence sent from No. three femto-second lasers 6 has become circularly polarized light from linearly polarized light after No. ten quarter-wave plates 23, its wavelength X bfor 1550nm; Pulse repetition rate f babout 100MHz; Recurrence interval T babout 10 -8s; Pulse width w bfor 10fs.This circularly polarized light is divided into two bundles after No. six polarization spectroscopes 24, and the P light be transmitted, as heliogram B, is designated as S bb, after ride on Bus No. 11 quarter-wave plate 25, become circularly polarized light, then after the beam-expanding collimation of No. eight beam-expanding collimation devices 26, launch back the primary in a distant place; By the S light that reflects as with reference to signal B, be designated as S rb, No. two, directive balance photoelectric detection unit 7 after the reflection of No. five polarization spectroscopes 20.S mb' and S rbfeedback signal B is produced after overbalance photodetection.Feedback signal B in No. three shaping circuits 21 after filtering, amplify and shaping after, enter No. three control circuits 22; Produce control signal by No. three control circuits 22, FEEDBACK CONTROL is carried out to the pulse repetition rate of No. three femto-second lasers 6, thus realizes S rband S mb' real-time overlap in time domain and locking, that is S bband S mb' between pulse temporal interlocking.
D, in primary, the S in step c baafter the propagation of about 2.7 hundred million kilometers, received by primary light splitting optical path 11.The heliogram A detected, is designated as S ba', be circularly polarized light, after No. two beam-expanding collimation devices 40 and No. five quarter-wave plates 41, become P light, again No. one, directive balance photoelectric detection unit 1 after No. two catoptrons 42 and No. two polarization spectroscopes 43.
Meanwhile, the S in step c bbafter the propagation of about 2.7 hundred million kilometers, received by primary light splitting optical path 11.The heliogram B detected, is designated as S bb', be circularly polarized light, after No. four beam-expanding collimation devices 27 and No. three quarter-wave plates 28, become S light, again No. one, directive balance photoelectric detection unit 1 after a catoptron 44, corner cube reflector 46 and No. two polarization spectroscopes 43.
S ba' and S bb' after overbalance photodetection, produce feedback signal, this feedback signal in a shaping circuit 45 after filtering, amplify and shaping after enter a control circuit 47.Produce control signal by a control circuit 47, FEEDBACK CONTROL is carried out to the position of precision displacement table 49, that is to S bb' light path finely tune with Subnano-class resolving power, and then ensure S ba' and S bb' between pulse temporal interlocking.
E, when intensity be 10 -21gravitational wave signal inswept with suitable angle time, two gage beams one extend a shortening, and the displacement difference of generation is sub-nanometer scale.Now, S ba' and S bb' pulse will produce deviation in time domain, this deviation is detected by a balance photoelectric detection unit 1, and then causes main control circuit 47 to produce the feedback signal of corresponding approximate DC, controls optical delay line scanning element 12 couples of S bb' light path finely tune, two pulse trains are relocked, then precision displacement table 49 produce displacement be tested displacement:
Δ D = U c 2 k - - - ( 1 )
Wherein, feedback voltage U=4 μ V, c is the light velocity in vacuum, and feedback signal sensitivity k is 3mV/fs, then the displacement D detected is 0.2nm.Because primary is to from star A and substantially equal from the distance of star B, then the laser pulse period error caused by atomic frequency uncertainty can be offset largely, makes the displacement detection sensitivity of the method can reach sub-nanometer level.

Claims (2)

1. a two-way femtosecond pulse high precision displacement detection method, is characterized in that: the method step is as follows:
A, by primary, launch from star A with from star B according to predetermined trajectory, three satellites are evenly distributed on solar system track, form the equilateral triangle that the length of side is about 2.7 hundred million kilometers; Primary respectively with from star A and the gage beam that forms the brachiums such as two from star B, precision detection is carried out to the relative change of two brachiums;
B, be arranged in the measuring junction of primary, the femto-second laser pulse sequence that femto-second laser (2) sends is divided into two bundles after a light splitting optical path (11); First bundle is launched to remote from star A as measuring-signal A, and the second bundle is launched to remote from star B as measuring-signal B;
C, be arranged in an active reflector from star A, the femto-second laser pulse sequence that No. two femto-second lasers (9) send is divided into two bundles after No. two light splitting optical paths (10); Wherein a branch ofly launch back remote primary as heliogram A, another bundle detects as together balancing photoelectric detection unit (7) by No. two with reference to signal A with the measuring-signal A detected; Feedback signal is produced after balance photodetection is carried out to reference signal A and the measuring-signal A detected, and then the chamber progress row FEEDBACK CONTROL to No. two femto-second lasers (9), by changing its pulse repetition rate, realizing reference signal A and interlocking with the high-precision pulse time domain of the measuring-signal A detected; Meanwhile, be arranged in No. two active reflectors from star B, the femto-second laser pulse sequence that No. three femto-second lasers (6) send is divided into two bundles after No. three light splitting optical paths (3); Wherein a branch ofly launch back remote primary as heliogram B, another bundle detects as together balancing photoelectric detection unit (4) by No. three with reference to signal B with the measuring-signal B detected; Feedback signal is produced after balance photodetection is carried out to reference signal B and the measuring-signal B detected, and then the chamber progress row FEEDBACK CONTROL to No. three femto-second lasers (6), by changing its pulse repetition rate, realizing reference signal B and interlocking with the high-precision pulse time domain of the measuring-signal B detected;
D, be arranged in the measuring junction of primary, the heliogram A detected and heliogram B is together detected by balance photoelectric detection unit (1); Produce feedback signal after carrying out balance photodetection to heliogram A and heliogram B, the mode scanned by optical delay line carries out FEEDBACK CONTROL to the light path of heliogram B, realizes the high-precision pulse time domain interlocking of heliogram A and heliogram B;
E, when gravitational wave is inswept with suitable angle, two gage beams, by producing very small reverse displacement, cause heliogram A and heliogram B to produce deviation in time domain; A control module (13) controls the light path that optical delay line scanning element (12) changes heliogram B, the pulse train of heliogram A and heliogram B is relocked, the displacement that then precision displacement table (49) produces is the difference of the displacement that two gage beams produce, that is target gravitational wave signal.
2., based on a deep space gravitational wave detecting device for two-way femtosecond pulse, its measuring junction comprises a femto-second laser (2), a light splitting optical path (11), balance photoelectric detection unit (1), a control module (13) and an optical delay line scanning element (12); It is characterized in that: be provided with an active reflector and No. two active reflectors respectively at two tested ends, form and wait brachium differential detection structure to gravitational wave signal, two isometric gage beams all have employed pulse temporal locking-type bidirectional measurement structure; A described active reflector is made up of No. two femto-second lasers (9), No. two light splitting optical paths (10), No. two balances photoelectric detection unit (7) and No. two control modules (8); The output light of No. two femto-second lasers (9) points to No. two light splitting optical paths (10); The output light of No. two light splitting optical paths (10) points to the input end of measuring junction and No. two balances photoelectric detection unit (7) respectively; The output terminal of No. two balances photoelectric detection unit (7) is connected to the input end of No. two control modules (8); The output terminal of No. two control modules (8) is connected to No. two femto-second lasers (9); Described No. two active reflectors are made up of No. three femto-second lasers (6), No. three light splitting optical paths (3), No. three balances photoelectric detection unit (4) and No. three control modules (5); The output light of No. three femto-second lasers (6) points to No. three light splitting optical paths (3); The output light of No. three light splitting optical paths (3) points to the input end of measuring junction and No. three balances photoelectric detection unit (4) respectively; The output terminal of No. three balances photoelectric detection unit (4) is connected to the input end of No. three control modules (5); The output terminal of No. three control modules (5) is connected to No. three femto-second lasers (6);
The structure of a described light splitting optical path (11) is: the output light of a femto-second laser (2) is divided into two bundles after a quarter-wave plate (14) and a polarization spectroscope (15); Wherein through Beam directive active reflector after No. four quarter-wave plates (29) and a beam-expanding collimation device (30); Another bundle reflected light directive No. two active reflectors after No. two quarter-wave plates (16) and No. three beam-expanding collimation devices (17); Laser No. one, directive balance photoelectric detection unit (1) after No. two beam-expanding collimation devices (40), No. five quarter-wave plates (41), No. two catoptrons (42) and No. two polarization spectroscopes (43) that an active reflector launches; Laser directive corner cube reflector (46) after No. four beam-expanding collimation devices (27), No. three quarter-wave plates (28) and a catoptron (44) that No. two active reflectors launch; Reflected light No. one, directive balance photoelectric detection unit (1) after No. two polarization spectroscope (43) reflections of corner cube reflector (46);
The structure of described No. two light splitting optical paths (8) is: the emergent light of No. two femto-second lasers (9) is divided into two bundles after No. seven quarter-wave plates (36) and No. four polarization spectroscopes (37); Wherein through Beam directive primary measuring junction after No. eight quarter-wave plates (38) and No. six beam-expanding collimation devices (39); Another bundle reflected light No. two, directive balance photoelectric detection unit (7) after No. three polarization spectroscopes (33); Meanwhile, the laser launched from primary measuring junction successively after No. five beam-expanding collimation devices (31), No. six quarter-wave plates (32) and No. three polarization spectroscopes (33) also No. two, directive balance photoelectric detection unit (7);
The structure of described No. three light splitting optical paths (3) is: the emergent light of No. three femto-second lasers (6) is divided into two bundles after No. ten quarter-wave plates (23) and No. six polarization spectroscopes (24); Wherein through Beam directive primary measuring junction after ride on Bus No. 11 quarter-wave plate (25) and No. eight beam-expanding collimation devices (26); Another bundle reflected light No. three, directive balance photoelectric detection unit (4) after No. five polarization spectroscopes (20); Meanwhile, the laser launched from primary measuring junction successively after No. seven beam-expanding collimation devices (18), No. nine quarter-wave plates (19) and No. five polarization spectroscopes (20) also No. three, directive balance photoelectric detection unit (4).
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