CN108540235A - Spatial chaos laser communication system ground based terminal error in pointing calibration system and method - Google Patents
Spatial chaos laser communication system ground based terminal error in pointing calibration system and method Download PDFInfo
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- CN108540235A CN108540235A CN201810127541.9A CN201810127541A CN108540235A CN 108540235 A CN108540235 A CN 108540235A CN 201810127541 A CN201810127541 A CN 201810127541A CN 108540235 A CN108540235 A CN 108540235A
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- 238000004891 communication Methods 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000012545 processing Methods 0.000 claims abstract description 19
- 230000003287 optical effect Effects 0.000 claims description 10
- 239000000835 fiber Substances 0.000 claims description 5
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 claims description 3
- 230000008685 targeting Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 4
- 230000001105 regulatory effect Effects 0.000 abstract description 2
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Classifications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/60—Receivers
- H04B10/66—Non-coherent receivers, e.g. using direct detection
- H04B10/69—Electrical arrangements in the receiver
- H04B10/691—Arrangements for optimizing the photodetector in the receiver
- H04B10/6911—Photodiode bias control, e.g. for compensating temperature variations
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/60—Receivers
- H04B10/66—Non-coherent receivers, e.g. using direct detection
- H04B10/67—Optical arrangements in the receiver
- H04B10/671—Optical arrangements in the receiver for controlling the input optical signal
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18517—Transmission equipment in earth stations
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/20—Arrangements for detecting or preventing errors in the information received using signal quality detector
- H04L1/203—Details of error rate determination, e.g. BER, FER or WER
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/20—Arrangements for detecting or preventing errors in the information received using signal quality detector
- H04L1/205—Arrangements for detecting or preventing errors in the information received using signal quality detector jitter monitoring
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses spatial chaos laser communication system ground based terminal error in pointing calibration system and methods.The system includes ground Laser emission end, collimation and pre- sighting device, photodetector and the anti-lens device in angle being arranged on selected satellite；The laser of ground Laser emission end transmitting is collimated to be emitted with pre- sighting device to selected satellite, the laser reflection for reaching satellite is gone back to ground by the anti-lens device in angle on satellite, the reflected light for returning to ground is received by a photoelectric detector rear incoming data processing module, data processing module calculates error in pointing, and the parameter at ground Laser emission end is adjusted accordingly, realize the calibration of error in pointing.The present invention carries out the calibration of ground launch base station using existing ICBM SHF satellite terminal, and system structure is simple, of low cost, is of great significance for the Testing And Regulating of ground base station.
Description
Technical field
The invention belongs to laser communication fields, more particularly to spatial chaos laser communication system ground based terminal errors in pointing
Calibration system and method.
Background technology
In recent years, spatial chaos laser communication technology develops rapidly, and mainly has unit by telecommunication satellite, ground base station etc.
At wherein telecommunication satellite has communication function, is usually seated in the space on tens thousand of kilometers of ground, is used as ground hair
The relay station for the signal being shot out can receive the signal transmitted in the air, amplified and be emitted again, it is, in general, that logical
Letter satellite can be divided into two kinds for the earth, synchronize fixed service satellite and relatively-stationary fixed statellite；Ground base station is again
Referred to as earth station, major function are for emitting, receiving satellite-signal, and ground base station is using satellite antenna for telecommunication satellite
Track very convenient, apparatus is also both economical, generally for specified target area, using base station to the antenna of satelloid
Wave beam is very easy to, and can be communicated within continuous 24 hours.
In spatial chaos laser communication uplink, light beam is transmitted by tellurian space station, and by being mounted on satellite
The optical signal receiver of terminal receives, and down going channel is exactly the opposite.In transmission process, communication link can be by error in pointing
It influences, this will cause communication optical axis that can not precisely align, and largely effect on communication quality.
Error in pointing includes the optical axis and jitter error two parts.A part is the fixed mistake generated due to mechanical system design
Difference, the referred to as optical axis, this fixed range deviation between receiving terminal center and beam center；Another part is then since machinery is
The randomized jitter of system also results in the random variation for receiving range deviation between position and beam center.Do not considering other
When factor, influence of the error in pointing for communication uplink and downlink is identical.Due to the shadow of error in pointing
It rings, the randomized jitter of spot center will lead to the random variation for receiving distance between position and beam center, so as to cause difference
The variation of the probability density for the light intensity that receiving terminal receives under jitter conditions.
Invention content
In order to solve the technical issues of above-mentioned background technology proposes, the present invention is intended to provide spatial chaos laser communication system
Ground based terminal error in pointing calibration system and method, by accurately determining the error in pointing of communication link with to spatial chaos laser
Communication system is calibrated.
In order to achieve the above technical purposes, the technical scheme is that：
A kind of spatial chaos laser communication system ground based terminal error in pointing calibration system, including ground launch module,
Transmitting module on face receiving module, data processing module and star, the ground launch module include ground Laser emission end and standard
Directly with pre- sighting device, the ground receiver module includes photodetector, and transmitting module is that setting is defended selected on the star
The anti-lens device in angle on star；The laser of ground Laser emission end transmitting is collimated to be emitted with pre- sighting device to selected satellite, is defended
The laser reflection that the anti-lens device in angle on star will reach satellite goes back to ground, return to ground reflected light be received by a photoelectric detector after
Incoming data processing module, data processing module calculate error in pointing, and adjust the parameter at ground Laser emission end accordingly.
Further, the anti-lens device in the angle includes the anti-minute surface in angle of multiple directions.
Further, the diameter of the anti-minute surface in the angle in each direction reach satellite spot diameter 5/1000ths or less.
Further, the ground receiver module further includes erbium-doped fiber amplifier and converging device, is returned from satellite reflection
Optical signal be received by a photoelectric detector after erbium-doped fiber amplifier and converging device successively.
Further, the photodetector is avalanche photodiode array.
Based on the method for above-mentioned spatial chaos laser communication system ground based terminal error in pointing calibration system, including following step
Suddenly：
(1) Laser emission end in ground emits laser, considers orbit altitude, the cycle of operation and the communication of selected satellite
Linkage length carries out collimation and pre- targeting process with pre- sighting device by collimation to laser so that when the laser reaches satellite,
The anti-lens device in angle on satellite is exactly near spot center；
(2) laser for reaching satellite is reflected back ground through the anti-lens device in angle, is finally received by a photoelectric detector, photodetection
Hot spot that device receives is simultaneously imperfect, therefore the Intensity Probability Density curve acquired is incomplete Gaussian curve；
(3) for photodetector by the signal incoming data processing module of acquisition, data processing module is bent to incomplete Gauss
Line is fitted, and obtains complete Gaussian curve, then the peak position on the curve is spot center position, this is actually measured
Spot center position and the obtained deviation at facula position center of theoretical calculation be error in pointing；
(4) parameter that ground Laser emission end is adjusted according to error in pointing, realizes spatial chaos laser communication system ground
The calibration of terminal error in pointing.
Further, in step (3), data processing module uses more during being fitted to incomplete Gaussian curve
It is secondary to measure the mode being averaged.
Further, selected satellite is high rail satellite, and high rail satellite is geostationary satellite.
The advantageous effect brought using above-mentioned technical proposal：
Based on the emitted satellite of current many partly carry the anti-mirror in angle, when ground launch base station construction is checked and accepted,
Not only in order to can be tested with physical link, but also terminal on star need not be re-emitted lead to high experiment test expense
With, the present invention carries out the calibration of ground launch base station using existing ICBM SHF satellite terminal, and system structure is simple, of low cost, for
The Testing And Regulating of ground base station is of great significance.
Description of the drawings
Fig. 1 is Laser emission in the present invention, reflection schematic diagram；
Fig. 2 is the flow chart of the present invention.
Specific implementation mode
Below with reference to attached drawing, technical scheme of the present invention is described in detail.
Existing spatial chaos laser communication system is directed toward since channel condition, the design of system itself and adjustment problem exist
Error, this will cause communication link optical axis that can not precisely align, and largely effect on the communication quality of system.Currently, to transmitting
In the calibration for holding error in pointing, since terminal-pair system carries out practical measurement expense costliness on transmitting star, thus it is most of to being directed toward
The research of error be based on theoretical calculation and numerical simulation, or by build thousands of meters of ground free-space communication link into
Row simulation test.There are larger errors for above-mentioned estimation mode, therefore, by expense relative moderate in a manner of survey spatial chaos swash
Error in pointing in optical communication link designs system significant.
A kind of spatial chaos laser communication system ground based terminal error in pointing calibration system, including ground launch module,
Transmitting module on face receiving module, data processing module (computer) and star.The ground launch module includes that ground is swashed
Light emitting end and collimation and pre- sighting device, the ground receiver module includes photodetector, and transmitting module is on the star
The anti-lens device in angle being arranged on selected satellite.The laser of ground Laser emission end transmitting is collimated emit with pre- sighting device to
Selected satellite, the laser reflection that the anti-lens device in angle on satellite will reach satellite goes back to ground, as shown in Figure 1, returning to the anti-of ground
It penetrates light and is received by a photoelectric detector rear incoming data processing module, data processing module calculates error in pointing, and adjusts accordingly
The parameter at ground Laser emission end.
The anti-lens device in angle includes the anti-minute surface in angle of multiple directions, such as the anti-lens device in octahedral prism-shaped angle, to ensure no matter
Laser gets to satellite from which direction has light beam to be reflected.Also, to meet the requirement of Modern Satellite lighting, miniaturization,
The diameter of the anti-mirror in angle should reach 5/1000ths of the spot diameter of satellite hereinafter, specifically can use 100mm.
Photodetector selects avalanche diode (APD) array.Since the receiving area of the anti-mirror in angle is much smaller than arrival satellite
When facula area, this light intensity smaller that receiving terminal will be caused to receive, and APD itself has dark noise, to avoid APD dark noises
To the larger impact of result of detection, can erbium-doped fiber amplifier (EDFA) and converging device be set in face before the detectors, to signal
Light is amplified and converges.
Method based on above system, as shown in Fig. 2, steps are as follows.
Step 1：Ground Laser emission end emits laser, consider the orbit altitude of selected satellite, the cycle of operation and
Communication link length carries out collimation and pre- targeting process so that laser arrival is defended with pre- sighting device by collimation to laser
When star, the anti-lens device in angle on satellite is exactly near spot center.
Step 2：The laser for reaching satellite is reflected back ground through the anti-lens device in angle, is finally received by a photoelectric detector, due to
The size of the spaceborne anti-mirror in angle is much smaller than the spot size for reaching satellite, therefore photodetector detects hot spot and imperfect, light intensity
Probability density curve is the Gaussian curve of incompleteness.
Step 3：Photodetector is by the signal incoming data processing module of acquisition, and data processing module is to incomplete Gauss
Curve is fitted, and obtains complete Gaussian curve, then the peak position on the curve is spot center position, the practical survey
The deviation at the facula position center that the spot center position and theoretical calculation obtained obtains is error in pointing；Fit procedure can be more
Secondary duplicate measurements is averaged, and avoids randomized jitter from generating large error so that result is more accurate.
Step 4：The parameter at ground Laser emission end is adjusted according to error in pointing, with realizing spatial chaos laser communication system
The calibration of face terminal error in pointing.
High rail satellite is geostationary satellite, and without the concern for the ground satellite cycle of operation, pre- aiming process is relatively easy.
But it for low orbit satellite, orbit altitude, satellite period etc. where satellite need to be considered, calculates relative complex.
Due to spatial chaos laser communication system design problem, can there are intrinsic error in pointing, i.e. optical axis deviation, and
The randomized jitter error that transmitting terminal shake generates caused by being shaken due to environment, constant error and random error can cause light beam
Offset, be referred to as error in pointing.It is h=38000km apart from ground level, transmitting light beam is by accurate by taking high rail satellite as an example
After direct line system, it is assumed that angle of divergence θ is the μ rad of θ=30, when reaching high rail, spot diameter D,
To calculate herein return spot center should position.Assuming that the precision of the angle of divergence is increased to 1 μ rad, it is computed, obtains
Deviation can make the direction deviation of beam center (optical axis) generation r=38m；
Embodiment is merely illustrative of the invention's technical idea, and cannot limit protection scope of the present invention with this, it is every according to
Technological thought proposed by the present invention, any change done on the basis of technical solution, each falls within the scope of the present invention.
Claims (8)
1. a kind of spatial chaos laser communication system ground based terminal error in pointing calibration system, it is characterised in that：It is sent out including ground
Module, ground receiver module, transmitting module on data processing module and star are penetrated, the ground launch module includes ground laser hair
End and collimation and pre- sighting device are penetrated, the ground receiver module includes photodetector, and transmitting module is setting on the star
The anti-lens device in angle on selected satellite；The laser of ground Laser emission end transmitting is collimated to be emitted with pre- sighting device to selected
Satellite, the laser reflection that the anti-lens device in angle on satellite will reach satellite go back to ground, return to the reflected light on ground by photodetection
Incoming data processing module after device receives, data processing module calculates error in pointing, and adjusts ground Laser emission end accordingly
Parameter.
2. spatial chaos laser communication system ground based terminal error in pointing calibration system, feature exist according to claim 1
In：The anti-lens device in angle includes the anti-minute surface in angle of multiple directions.
3. spatial chaos laser communication system ground based terminal error in pointing calibration system, feature exist according to claim 2
In：The diameter of the anti-minute surface in angle in each direction is 5/1000ths or less of the spot diameter for reaching satellite.
4. spatial chaos laser communication system ground based terminal error in pointing calibration system, feature exist according to claim 1
In：The ground receiver module further includes erbium-doped fiber amplifier and converging device, and the optical signal returned from satellite reflection passes through successively
It is received by a photoelectric detector after crossing erbium-doped fiber amplifier and converging device.
5. spatial chaos laser communication system ground based terminal error in pointing calibration system, feature exist according to claim 1
In：The photodetector is avalanche photodiode array.
6. based on the method for spatial chaos laser communication system ground based terminal error in pointing calibration system described in claim 1,
It is characterized in that, includes the following steps：
(1) Laser emission end in ground emits laser, considers orbit altitude, the cycle of operation and the communication link of selected satellite
Length carries out collimation and pre- targeting process with pre- sighting device by collimation to laser so that when the laser reaches satellite, satellite
On the anti-lens device in angle be exactly near spot center；
(2) laser for reaching satellite is reflected back ground through the anti-lens device in angle, is finally received by a photoelectric detector, photodetector connects
The hot spot that receives is simultaneously imperfect, therefore the Intensity Probability Density curve acquired is incomplete Gaussian curve；
(3) photodetector is by the signal incoming data processing module of acquisition, data processing module to incomplete Gaussian curve into
Row fitting, obtains complete Gaussian curve, then the peak position on the curve is spot center position, the actually measured light
The deviation at the facula position center that spot center and theoretical calculation obtain is error in pointing；
(4) parameter that ground Laser emission end is adjusted according to error in pointing, realizes spatial chaos laser communication system ground based terminal
The calibration of error in pointing.
7. method according to claim 6, it is characterised in that：In step (3), data processing module is bent to incomplete Gauss
Line is fitted in the process in such a way that multiple measurement is averaged.
8. method according to claim 6, it is characterised in that：Selected satellite is high rail satellite, and high rail satellite is Geo-synchronous
Satellite.
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| CN110690918A (en) * | 2019-09-28 | 2020-01-14 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for adjusting aerospace measurement and control link parameters |
| CN112713932A (en) * | 2020-12-21 | 2021-04-27 | 中国科学院西安光学精密机械研究所 | Laser communication terminal optical path relay unit assembling and detecting system and detecting method based on same |
| CN113296128A (en) * | 2021-05-28 | 2021-08-24 | 中国科学院微小卫星创新研究院 | System and method for establishing laser communication link between high-capture-rate low-orbit satellites |
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| CN113296128A (en) * | 2021-05-28 | 2021-08-24 | 中国科学院微小卫星创新研究院 | System and method for establishing laser communication link between high-capture-rate low-orbit satellites |
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