CN106788763A - airborne laser communication equipment and its control method - Google Patents
airborne laser communication equipment and its control method Download PDFInfo
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- CN106788763A CN106788763A CN201611230417.2A CN201611230417A CN106788763A CN 106788763 A CN106788763 A CN 106788763A CN 201611230417 A CN201611230417 A CN 201611230417A CN 106788763 A CN106788763 A CN 106788763A
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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
- H04B10/50—Transmitters
- H04B10/501—Structural aspects
- H04B10/503—Laser transmitters
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- 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
- H04B7/18502—Airborne stations
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Abstract
A kind of airborne laser communication equipment and its control method, two kinds of light sources of beacon beam and information source light are received by same reception antenna, afterwards control module is transferred to after separating, processing, by the beacon beam and pitching and the orientation angles of information source optical signal adjusting device that receive, carry out the tracking of signal, the beacon beam of feedback is launched respectively with information source optical signal by two different transmitting terminals, thereby guarantees that the exchange work of both sides' signal.Solving traffic rate present in prior art, image resolution ratio can not meet requirement, and can not simultaneously ensure the technical problem of covering wide and real-time Transmission.
Description
Technical field
The invention is related to a kind of communication equipment and its control method, especially a kind of airborne laser communication equipment and its
Control method.
Background technology
The main battle ground of future war will be the solid space of space, near space, aviation, ground, ocean, more and more
Country recognizes and grasps space to winning the importance of future war.The reconnaissance platforms such as current Aeronautics and Astronautics forward direction high-altitude
Between the compound direction such as scout of resolution ratio, high time resolution, high spectral resolution and multisensor develop, in the urgent need to by magnanimity
Initial data is directly transmitted with lossless manner from reconnaissance platforms or relay transmission is to terminal is accused, meets modern military real-time
It is required that.
Current Primary communication pattern is radio communication, and its transmission rate much can not meet required communication rate, must not
Do not take data compression technique, although real-time Transmission can be ensured, but compression of images will cause the reduction of image resolution ratio；Separately
Mass storage buffer mode can be carried out outward to carry out data transmission, although the spatial discrimination of regional area can be ensured
Rate, but it cannot be guaranteed that covering wide and real-time Transmission), improved so as to constrain the overall of the level of IT application.Although radio communication
Speed is also in continuous improvement, but because its communication bandwidth in theory is taken limitation, its traffic rate is already close to the limit.
The content of the invention
In order to solve the above-mentioned technical problem, the invention provides a kind of airborne laser communication equipment and its controlling party
Method, two kinds of light sources of beacon beam and information source light are received by same reception antenna, are transferred to after separating, processing afterwards
Control module, by the beacon beam and pitching and the orientation angles of information source optical signal adjusting device that receive, carry out signal with
Track, the beacon beam of feedback is launched respectively with information source optical signal by two different transmitting terminals, thereby guarantees that both sides' signal
Exchange work.Solving traffic rate present in prior art, image resolution ratio can not meet requirement, and can not protect simultaneously
Card covering wide and the technical problem of real-time Transmission.
To achieve these goals, the technical scheme of the invention use is：Airborne laser communication equipment, includes cabin
Interior and two parts out of my cabin, are the electron process module of system in cabin, are out of my cabin light machine testing and servo-drive system, it is characterised in that：
Described partly includes housing out of my cabin, the radome fairing on housing, and in housing, radome fairing corresponding position is provided with optics and puts down
Platform, optical table is connected on two-dimentional Chang Pingtai by pitch axis, realizes the pitch rotation of optical table；Two-dimentional Chang Pingtai passes through
The azimuth axis connection housing and the rotating mechanism of outside on top, realize the synchronous plane of shell, two dimension Chang Pingtai and optical table
Rotate；Visible Light Camera, reception antenna, transmitting antenna and infrared camera are installed on optical table；
Described electron process module mainly includes communication antenna circuit, and operation bench circuit；
In communication antenna circuit, the optical signal transmission that information source Optical Receivers and beacon Optical Receivers will be received to behaviour
Treatment is analyzed in control platform circuit, information source light emission module and beacon light emission module are by the optical signal launch after reception processing
Go out, thus complete the accurate alignment of both sides；Pitching shafting and azimuth axle receive the signal output of operation bench circuit, and pass through
Receive signal control motor to rotate, adjusting device alignment position；
The communications processor element and communications processor element connection being connected with communication antenna circuit are provided with operation bench circuit
Main control unit, the human-computer exchange unit being connected with host computer and the external control bar being controlled are included in main control unit.
Beacon beam and information source optical signal are received by reception antenna simultaneously in described optical table, by filters filter
Afterwards, by spectroscope light splitting, signal is exported by the thick capture detector for setting or smart tracking detector respectively arrive logical afterwards
In information source Optical Receivers and beacon Optical Receivers in letter antenna circuit.
Described housing upper is provided with damping isolation, for carrying out passive vibration isolation treatment.
Azimuth axis gyro and pitch axis gyro are provided with described communication antenna circuit, as elimination thrashing shadow
Ring.
A kind of control method of airborne laser communication equipment, it is characterised in that：
1), the reception of signal：
1a), information source light and beacon beam that distant terminal is launched are received simultaneously using same optical reception antenna；
1b), in reception antenna rear end, relaying light path part passes through wave filter after filtering, afterwards will by quick titling mirror
Optical signal is reflexed in spectroscope, carries out information source light and beacon beam is separated；
1c), in communication source photo-detector is transferred to after wave filter, communication source photo-detector will for the information source light after separating
The optical signal for capturing is uploaded in the information source Optical Receivers in communication antenna circuit, is uploaded to after carrying out data regulation treatment
Operation bench circuit, is processed；
Beacon beam after separation by the way that after wave filter, the beacon beam of a part reaches coarse alignment detector by light splitting piece,
Being uploaded to operation bench circuit by communication antenna circuit afterwards carries out coarse alignment analysis and Control, and the beacon beam of another part is by dividing
Mating plate reaches smart tracking detector, and being uploaded to operation bench circuit by communication antenna circuit afterwards carries out fine alignment analysis and Control；
2), equipment adjustment：To in communication source photo-detector, communication source photo-detector will catch the optical signal transmission for receiving
The optical signal for arriving uploads operation bench circuit, and pitching shafting and azimuth axle in information to the communication antenna circuit of feedback are controlled
System, and will control adjustment signal output, so as to adjust receiving device luffing angle and orientation angles, signal is carried out in real time with
Track, it is ensured that the beacon beam and information source light of both sides can real-time tranception it is unimpeded；
3), the transmitting of signal：Beacon beam and information source light are launched respectively, and the information source light of output first passes around intensity modulated
And amplify, relay optical system collimator and extender is then used, then after quick titling mirror reflects, sent out using without burnt telescope
Penetrate；Flashlight then directly carries out collimator and extender and launches.
The beneficial effect of the invention is：
(1) system should realize stabilization, the reliable communication under Various Complex atmospheric conditions, high security, anti-interference energy high
Power, with full-duplex communication ability.
(2) influence of the weather conditions to communication system is weakened using adaptive optical technique, rational control technology.
(3) the optical laying error by optical table in scanning process is reduced to minimum, while also by external pneumatic stream
Interference be reduced to minimum.
(4) use with the active optic central extract system of the rate gyroscope as core devices in broadband, low drifting, to low frequency, big
Amplitude disturbance is effectively suppressed.
(5) tracked to realize Dynamic High-accuracy, using coarse-fine composite shaft ATP tracking techniques.Rough tracking ring has larger
Visual field and relatively low servo bandwidth, to realize fast Acquisition and stablize rough tracking；Essence tracking ring have less dynamic range, compared with
Servo bandwidth and tracking accuracy high high, to ensure quick and high-precision alignment and tracking.
Brief description of the drawings
Fig. 1：It is schematic structural view of the invention.
Fig. 2：It is optical table fundamental diagram of the present invention.
Fig. 3：It is present invention treatment communication system fundamental diagram.
Fig. 4：It is communication antenna circuit theory diagrams of the present invention.
Fig. 5：It is operation bench circuit theory diagrams of the present invention.
Specific embodiment
Airborne laser communication equipment, includes in cabin and two parts out of my cabin, is the electron process module of system, out of my cabin in the cabin in
It is light machine testing and servo-drive system, its structure is：Described partly includes housing out of my cabin, the radome fairing 1 on housing, in housing
Interior, the corresponding position of radome fairing 1 is provided with optical table 4, and optical table 4 is connected on two-dimentional Chang Pingtai 6 by pitch axis, real
The pitch rotation of existing optical table 4；Two-dimentional Chang Pingtai 6 connects the rotating mechanism of housing and outside by the azimuth axis on top, real
Existing shell, two dimension Chang Pingtai 6 are rotated with the synchronous plane of optical table 4；Visible Light Camera 5 is installed on optical table 4, is received
Antenna 3, transmitting antenna 2 and infrared camera 10.
Specifically, being partly additionally provided with Servo Turret 7 out of my cabin, gondola is set to carry out orientation rotation and pitching rotation, can
System pointing and optical signalling transmission-receiving function are realized, is lifted in cabin and be provided with damping isolation between fitting surface 9 and Servo Turret 7
8, for carrying out passive vibration isolation treatment.
Described electron process module mainly includes communication antenna circuit 12, and operation bench circuit 11.
Azimuth axle module, pitching shafting module, information source Optical Receivers, information source light are included in communication antenna circuit 12
Transmitter module, beacon Optical Receivers, beacon light emission module.In communication antenna circuit 12, information source Optical Receivers and beacon
The optical signal transmission that Optical Receivers will be received is to being analyzed treatment, information source light emission module and letter in operation bench circuit 11
Mark light emission module goes out the optical signal launch after reception processing, thus completes the accurate alignment of both sides；Azimuth axle and bow
The signal output that shafting receives operation bench circuit 11 is faced upward, and is rotated by receiving signal control motor, adjusting device alignment position.
Left limit switch, right limit switch, retainer, azimuth-drive motor and orientation rotation is included in azimuth axle module to become
The Derivative limit on the left or on the right position of device, wherein left and right limit switch control rotary shaft motion, when extreme position is had been pivoted into by side
The position upward transmission information of shafting module, and stop operating, azimuth-drive motor receives the operation bench electricity that communication antenna circuit 12 is received
The information of road 11, drives the rotation of azimuth axis.
Upper limit position switch, lower position switch, pitching motor and pitching rotation are included in pitching shafting module and becomes device, wherein on
The high-low limit position of lower position switch control rotary shaft motion, pitching shafting module is passed through when extreme position is had been pivoted into
Upward transmission information, and stop operating, pitching motor receives the information of operation bench circuit 11 that communication antenna circuit 12 is received, band
The rotation of dynamic pitch axis.
The information source light that information source Optical Receivers will be received by information source Optical Transceiver Card after information source photo-detector by being sent out
Give operation bench circuit 11.
The beacon beam part that beacon Optical Receivers will be received is carried out by after the treatment of beacon beam receiving optics
Imaging and locating and tracking, another part are carried out in exporting operation bench circuit 11 after opto-electronic conversion joint carries out opto-electronic conversion
Follow-up treatment.
Beacon light emission module by beacon light laser, sends out feedback optical signal by beacon beam optical transmitting system
Penetrate.The optical signal of feedback is amplified and adjusted by information source light emission module by fibre-optical amplifier module, is launched by information source light afterwards
Optical system is launched.
Azimuth axis gyro and pitch axis gyro, azimuth axis gyro and pitch axis gyro are also included in communication antenna circuit 12
Information transfer to signal transducer, transfer information to be processed in operation bench circuit 11 afterwards, trembled as elimination system
Dynamic influence.
The communications processor element and communications processor element being connected with communication antenna circuit 12 are provided with operation bench circuit 11
The main control unit of connection, includes the human-computer exchange unit being connected with host computer and the external control being controlled in main control unit
Bar.
Beacon beam and information source optical signal are received by reception antenna 2 simultaneously in optical table 4, by after filters filter,
By spectroscope light splitting, signal is exported to communication day by the thick capture detector for setting or smart tracking detector respectively afterwards
In information source Optical Receivers and beacon Optical Receivers in line circuit 12.Information source light and beacon are additionally provided with optical table 4
Light transmitting antenna respectively, the transmitting distinguished the optical signal after transmission feedback.
The control method of airborne laser communication equipment, it is characterised in that：
1st, the reception of signal：
1a, the information source light and beacon beam that receive distant terminal transmitting simultaneously using same optical reception antenna 3；
1b, the rear end of reception antenna 3 relaying light path part by wave filter after filtering, afterwards by quick titling mirror will
Optical signal is reflexed in spectroscope, carries out information source light and beacon beam is separated；
In communication source photo-detector is transferred to after wave filter, communication source photo-detector will for information source light after 1c, separation
The optical signal for capturing is uploaded in the information source Optical Receivers in communication antenna circuit 12, is uploaded after carrying out data regulation treatment
To operation bench circuit 11, processed；
Beacon beam after separation by the way that after wave filter, the beacon beam of a part reaches coarse alignment detector by light splitting piece,
Being uploaded to operation bench circuit 11 by communication antenna circuit 12 afterwards carries out coarse alignment analysis and Control, and the beacon beam of another part leads to
Cross light splitting piece and reach smart tracking detector, being uploaded to operation bench circuit 11 by communication antenna circuit 12 afterwards carries out fine alignment point
Analysis control；
2nd, equipment adjustment：To in communication source photo-detector, communication source photo-detector will catch the optical signal transmission for receiving
The optical signal for arriving uploads operation bench circuit 11, and azimuth axle and pitching shafting in information to the communication antenna circuit 12 of feedback enter
Row control, and will control adjustment signal output, so as to adjust receiving device bow orientation angles and luffing angle, reality is carried out to signal
When track, it is ensured that the beacon beam and information source light of both sides can real-time tranception it is unimpeded；
3rd, the transmitting of signal：Beacon beam and information source light are radiated respectively, and the information source light of output first passes around intensity modulated
And amplify, then with ultimate photosystem collimator and extender, after being reflected by quick titling mirror, put using without burnt telescope
Penetrate；Flashlight is launched after then directly carrying out collimator and extender.
Communication terminal of the present invention uses symmetrical structure, an optical antenna for larger caliber to receive distant terminal hair simultaneously
The flashlight and beacon beam penetrated, and complete wavelength isolation in day line back end relaying light path part；Beacon beam and flashlight are adopted respectively
With the laser of different wave length, flashlight and beacon beam use independent transmitting aperture, and flashlight transmitting and receiving branch share one
Individual quick titling mirror.
On transmitting branch, flashlight first passes around intensity modulated and amplifies, and then uses relay optical system collimator and extender,
Launched without burnt telescope with one after quick titling mirror reflects again；Beacon beam then directly carries out collimator and extender and transmitting.
On receiving branch, optics primary antenna receives flashlight and beacon beam simultaneously, passes sequentially through quick titling mirror and colour splitting prism, then
Flashlight and beacon beam are processed respectively.Wherein beacon beam is performed by entering to catch after narrow band interference filter with detector
Capture and following function；Flashlight after narrow band interference filter then by using APD direct detections and carrying out signal demodulation.
When signal is received, signal laser is focused on communication detecting device APD by optical receiver antenna.First pass around
Photodetector is converted into radio-frequency current, then feed-in radio frequency detector device, finally demodulates original signal by decoder.Using certainly
Dynamic sighting system, to ensure when space channel media variations cause spot drift, adjust automatically optical antenna, it is ensured that both sides are begun
Eventually in the state of alignment.After optical antenna receives optical signal, by optical beam splitting, a part to the coarse alignment of beacon beam is detected
Device, output signal completes coarse alignment by coarse alignment control, driving coarse alignment mechanism；Another part of beacon beam is through fine alignment machine
Structure, light splitting piece, beam splitting chip to smart detector, by fine alignment controller control fine alignment mechanism, complete the accurate alignment of both sides with
Tracking.
When specifically used：
Operation wavelength is selected：
To make atmosphere laser communication system have farther communication distance, security higher, laser communication is to optical maser wavelength
It is overriding concern aspect to be typically chosen " atmospheric window " frequency range, secondly also to avoid the high frequency radiation frequency range in environment.
The principal element of the transmitance that influence laser is transmitted in an atmosphere has：Atmospheric Absorption and atmospheric scattering.
If not using narrow band filter slice, what the most very noisy source of atmosphere laser communication system was formed from sun light scattering
Background radiation.In order to avoid the influence of sun light scattering, while being also contemplated for the requirement of confidentiality, infrared laser turns into optional ripple
Section.The conventional infrared communication wave band in atmospheric window has：810~860nm, 980~1060nm and 1550~
1600nm, will also avoid the heat radiation of the earth in addition, this wave band substantially in 900~1000nm, therefore 810~860nm and
1550~1600nm is relatively reasonable frequency range.
When communication window is selected, for horizontal transport, the leading decay of lower atmosphere layer is based on Mie scattering.This
When.Can be represented with the empirical equation relevant with visibility, its form is：
In formula, V is visibility, and λ is transmission wavelength.Q is relevant with visibility, it is considered that：
Infer that the wavelength attenuation coefficient more long of light extraction is smaller by above formula.To mitigate influence of the air to Laser Transmission, Ying Xuan
Select the laser of infrared wavelength.
Meanwhile, laser in the transmitting procedure of vacant lot, in order to ensure to eye-safe, according to the rule of international standard IEC60825
It is fixed, wavelength X>0.4 μm of laser is the laser wavelength of eye-safe, the more common 830nm ripples of the firm power of 1550nm laser
Length wants 2 orders of magnitude high.
In order that Laser Transmission loss is minimum and meets the requirement of eye-safe, the transmitting of military atmosphere laser communication system
Wavelength should select 1550nm wavelength.Simultaneous selection 1550nm laser communication technologies, can use for reference the wavelength-division multiplex technique of current maturation,
Its device, component oneself through commercialization so that 1550nm free Space Laser Communication Technologies compared with other wavelength light wireless communication systems be applicable
Property and autgmentability are more preferable.
Communication distance：
According to FSO operating distance computing formula, have
Pr=Ltotal+Pt+Lmargin (1)
Wherein, LtotalIt is total losses luminous power, has
LspaceFor space geometry is lost, LatmosphereIt is atmospheric loss, LtIt is the loss of optical transmitting system, LrTo receive
The loss of optical system, DrIt is Receiver aperture, l is communication distance, θtIt is beam divergence angle, α is atmosphere attenuation coefficien, and taking to see
Degree 23km, Tt、TrIt is respectively transmitting, the transmitance of receiving optics, PtIt is the transmitting luminous power of emitter, PrIt is receiver
Detectivity, LmarginIt is system power surplus.
When airborne communication terminal is receiving terminal, and ground communication terminal is transmitting terminal, design parameter is taken：Dr=0.08m, l
=40km, θt=0.3mrad, α=0.1km-1, Tt=0.9, Tr=0.6, Pr=-40dBm, Pt=33dBm.By design parameter
Substituting into above formula can obtain：
Under the weather condition of visibility 23km, when communication distance is 40km, ground surface end machine-to-machine carries terminal communication
Power headroom is 6.4dB, can meet overall objective.
When ground communication terminal equipment is receiving terminal, and airborne communication terminal is transmitting terminal, design parameter is taken：Dr=0.18m, l
=40km, θt=0.6mrad, α=0.1km-1, Tt=0.9, Tr=0.6, Pr=-40dBm, Pt=27dBm.By design parameter
Substituting into above formula can obtain:
Under the weather condition of visibility 23km, when communication distance is 40km, airborne terminal communicates to ground terminal
Power headroom is 1.45dB, can meet overall objective.
Transmission rate and the bit error rate：
Air to surface wireless light communication belongs to atmospheric optical communication, influence of the air to beam Propagation mainly include Atmospheric Absorption,
The additional modulation that the energy attenuation that causes of scattering and atmospheric turbulance are produced, thus can by atmospheric channel be divided into atmospheric attenuation channel and
Atmospheric turbulence channels.Atmospheric attenuation channel is generally represented with atmosphere attenuation coefficien, and atmospheric turbulence channels then can be with current noise
Form its effect is described.
Usually, lasercom link equation is
In formula, PrAnd PtIt is respectively to receive and launch luminous power, D is Receiver aperture, L is communication distance, TrAnd TtIt is respectively
Receive and optical transmitting system transmitance, θtIt is laser divergence angle, α is atmosphere attenuation coefficien, for 1550nm optical maser wavelengths, is had
α=2.14/V, V are visibility.
In actual laser communication system, communication receiver need to carry out opto-electronic conversion to optical signal, after amplified shaping
By signals revivification it is data signal by Clock Extraction judging circuit, therefore the signal to noise ratio of receiving circuit is not only decided by receiver
Portion's noise, it is also closely related with atmospheric turbulance noise and ambient noise.
Generally from avalanche photodide and PIN photodiode as communication photodetector, photodetector
Signal code is relevant with detector responsivity and received optical power, there is is=rPr。isIt is signal photoelectric current, r is explorer response
Degree.For intensity modulated/direct detection mode, output noise power PnFor
In formula,WithIt is respectively signal photoelectric current, background photo current, dark current, electricity
The noise power spectrum that resistance temperature is produced.They are expressed as
In formula, q=1.601 × 10-19C；For PIN photodiode, F=1；BWfOptical filter line width is respectively with Δ f
And detector bandwidth；HbIt is background radiation brightness；θrIt is field of view of receiver angle；idIt is detector dark current；kBFor Boltzmann is normal
Number；WithLight intensity fluctuation caused by expression atmospheric turbulance on detector target surface, is called atmospheric scinillation index, takesIt is normalizing
Change light-intensity oscillation variance, have
WithIt is respectively the variance of bit 1 and bit 0,Refer to that signal is not exclusively modulation, generally take modulation deep
Degree η is 90%, then have
The bit error rate of system can be given by：
In formula, IthIt is threshold value, when signal sampling value is more than IthWhen, system is judged to 1, is otherwise 0.
Take wavelength 1550nm, transmission power 500mW, beam divergence angle 0.6mrad, Receiver aperture 180mm, receiving sensitivity-
40dBm, transmitting, the transmitance of receiving optics are respectively 0.9,0.6, above formula are substituted into, under different visibility weather conditions
Maximum communication rate calculated.When visibility is 20km, the maximum communication distance of 155Mbps traffic rates is
45km；When visibility is 10km, the ultimate range of the speed is 27km, and when visibility is 5km, the ultimate range of the speed is
16km。
Atmospheric turbulance has quite serious influence for the deterioration of the bit error rate in practice, withIncrease, system miss
Code check is increased dramatically, and when more than 0.4, change curve tends to be steady.When atmospheric scinillation indexWhen being respectively 0.11 and 0.07,
Accessible minimum bit-error rate is 10-6 and 10-9.
From the angle analysis of parts selection, the light source of signal of communication is using main shake power amplifier (MOPA) structure, local oscillator radiant
Selection distributed feedback (DFB) semiconductor laser, modulation system is directly modulation, and the maximum bandwidth of modulation drive circuit is
500MHz, then light source can meet the requirement of 155Mbps message transmission rates.
Receive flashlight detector using avalanche photodide it is integrated before put component, its responsive bandwidth be 470MHz,
Then receiving circuit disclosure satisfy that the data receiver of 155Mbps message transmission rates.
According to above-mentioned analysis, it is known that air to surface radio optical communication system equipment can realize the transmission rate of 155Mbps.
Light source type selecting：
Light source is MOPA structures, and local oscillator radiant is the DFB semiconductor laser of power output 2dBm, and power-amplifier stage is adopted
Large-power optical fiber amplifier module is used, operation wavelength is 1550nm, and Single-Mode Fiber Coupling is exported, and its maximum output luminous power is
27dBm~33dBm.Using MOPA as light source, the requirement of high modulation bandwidth can be both met, can realize that high-power signal light is defeated again
Go out, the need for meeting telecommunication.
Aerial platform type selecting：
Optional aerial platform type includes：Fixed-wing unmanned aerial vehicle, rotary wings depopulated helicopter, helicopter and scouting fortune
Defeated machine.Selecting the foundation of aerial platform includes：Payload, flying height, cruising speed, the cloud level, cruising time and application are special
Point, the cloud level is different according to different geographical, Various Seasonal and weather, and usually the cloud level is about 3~4km.The index of each platform
It is as follows.
For the application of air to surface wireless light communication, aerial platform should have the characteristics that：
(1) with certain cruise ability；
(2) payload is big；
(3) flying height is less than the cloud level, it is to avoid influence of the cloud layer to wireless light communication；
(4) cruise time is long.
Compare upper table, it can be found that fortune eight is the optimal selection of wireless light communication aerial platform.Therefore, it is suggested that early stage is installed additional
Platform can progressively be extended to other such as unmanned plane, helicopter kinds of platform based on eight platforms of fortune.
Tracking angular rate without degradation：
It is 1km that ground communication terminal is taken with the minimal communications distance of airborne communication terminal, and the helicopter speed of a ship or plane is 300km/h,
Then ATP system maximum tracking angular rate is
That is the tracking angular rate without degradation of ATP system should be greater than 4.74 °/s, therefore, guarantor's precision of airborne communication terminal with
Track angular speed is 5 °/s, and the tracking angular rate without degradation of ground communication terminal is 10 °/s.
ATP system peak response frequency range：
The peak response frequency range of ATP system is determined by laser beam divergence, minimum air route and platform relative velocity.It is closed
It is formula as follows：
The laser beam divergence of ground communication terminal is 0.3mrad, and B=277.7Hz is obtained in substitution formula.Therefore, ground leads to
The peak response frequency range for believing terminal ATP system is 277.7Hz.
The laser beam divergence of airborne communication terminal is 0.6mrad, and B=138.8Hz is obtained in substitution formula.Therefore, ground leads to
The peak response frequency range for believing terminal ATP system is 138.8Hz.
2nd, subsystem is constituted：
Subsystem out of my cabin：
As shown in figure 1, subsystem is specially structure for pod out of my cabin, the bottom leading edge of its fuselage for being located at platform aircraft
Position, gondola can carry out positive and negative 190 degree of orientation rotation and carry out the pitching rotation of+10 to -90 degree, be provided with to terminal
More than the viewing area of hemisphere.Gondola glass window should plate the anti-reflection film for meeting military standard, the curvature of its glass window
To match with gondola, and near-zero focal power can be accomplished.It is this to be designed to optical table in scanning process
Optical laying error be reduced to minimum, while the interference of external pneumatic stream also is reduced into minimum.
Gondola determines level and the luffing angle position of gondola with two angle displays, by two shafts
Gear and DC motor Driver.
Optical table subsystem：
Optical subsystem includes two small-bore flashlights and beacon beam transmitting antenna, a larger caliber (diameter
Optical receiver antenna 150mm) and corresponding optical relay system, complete the collimation/focus on, expand/shrink beam of light beam, send out
Penetrate/receive capabilities.Optical antenna should ensure that the quality of optical imaging requirement close to diffraction limit.
Each optical component is arranged on a composite construction, and this composite construction can be synthesized by the carbon of flatness shrinkage
Thing is manufactured, and various optics firmwares are fixed with invar.
In order to reduces cost and adaptation airborne platform, optical antenna can use Cassegrain telescope, primary mirror is using throwing
Parabolic mirror, secondary mirror uses hyperbolic speculum.And folding axial light path can be increased with the volume of further compressing terminal.
ATP subsystems：(ATP is Acquisition, Tracking and Pointing, ATP subsystems be capture,
Tracking and aim subsystem)
The major function caught with mechanism is by adjusting terminal itself attitude, coordinating optical antenna to change beam propagation side
To mode realize the foundation of communication terminal laser communication link.It is to meet end that the dynamic of this direction of beam propagation changes
The performance requirement that end is aimed at, captures and tracked, specific requirement is as follows：
Aim at：In this mode, terminal optical axis points to predetermined direction (in the uncertain region that distant terminal occurs
The heart), pointing accuracy should be less than the half of the signal broadening of beacon beam, to ensure the beacon beam of distant terminal during aiming state at oneself
In the FOV of acquisition of square terminal.
Capture：The flashlight (having signal output on capture detector) of distant terminal is captured, and it is straight to carry out error correction
There is signal output on to communication detecting device.Acquisition procedure firstly the need of by one have enough for a long time come exchange aircraft position,
The RF data link of speed and gps time shares the position data from GPS and inertial sensor.Once the tracking of beacon beam
Lose, recapture will be automatically begun to.Once rough tracking beacon beam is observed, immediately begin to calculate beacon beam in rough tracking spy
The center of gravity surveyed on device, center of gravity is the boresight direction for representing target aircraft, and rough tracking servo control mechanism starts to track target aircraft
The laser communication terminal optical axis, until beacon beam enters smart tracking detector.
Tracking：The error signal calculated with this terminal tracks the communication beam of distant terminal.Target laser communication is eventually
The optical axis (center of gravity) at end will be applied to drive quick titling mirror with the difference of the optical axis of communications reception light path, lead to target laser
Believe that the optical axis of terminal tends to the boresight direction of communications reception light path.The closed-loop bandwidth of the servo control mechanism is more than hundreds of hertz, specifically
Value is depending on tracking error and the rumble spectrum of platform.
Communication subsystem：
The major function of communication subsystem is to complete the transmission of flashlight and receive.Mainly by laser module, receiver
Module, modulation /demodulation module, optical module and mechanical encapsulation are constituted.
On communication transmitting branch, signal modulation circuit control modulator carries out direct intensity modulation to signal laser, so
The flashlight after modulation is amplified to about 500mW afterwards, to obtain enough transmitting laser powers.Optical system should be with simultaneously
High light quality completes expanding and shaping for signal laser, its angle of divergence is controlled less than 100 microradians.
On communications reception branch road, signal laser passes sequentially through optical receiver antenna, quick titling mirror, dichronic mirror, arrowband
Interference light filter, is then focused on communication detecting device.The electric signal changed from communication detecting device is adjudicated is demodulated to letter
Number stream, and the code stream is decoded and bit error rate assessment.
Terminal control unit：
Terminal control unit is the core component of terminal system electron process module, and its major function includes three parts：Realize
Aim at, capture and following function；Realize the terminal top layer control function (letter between terminal work mode switching and each submodule
Breath scheduling)；System state data is monitored.
Controller can undertake Core Feature with several digital signal processors.Overall control DSP (Digital Signal Processing
Digital Signal Processing, abbreviation DSP) receive microprocessor controller produce all orders, when order complete or
Prompting microprocessor is responded when person's order is wrong.Overall control is processed and come as inertial sensor and the GPS (whole world simultaneously
Alignment system) unit and RF data link information, and information is transmitted to by its globally shared storage by capture and gondola
DSP。
The DSP for being responsible for gondola servo-drive system is controlled to acquisition procedure.It receives GPS/ from two laser communication terminals
INS position, the speed and aircraft elevation information of itself, then calculates target aircraft position, and these data are used for driving gondola
Complete capturing function.In addition gondola servo DSP is also positioned and monitored to gondola attitude.
Thick capture servo DSP responds to thick capture servo loop, and the loop includes rough tracking receiver, gyrocontrol
Device and gimbal positioning execution unit.Coarse servo DSP controls the camera gain and center of gravity threshold value of rough tracking receiver.It is also
The azimuth axis and pitching direction of principal axis of gimbal are calculated from the pixel gray value of rough tracking receiver.Occur in the center of gravity of target terminal
After in the visual field of smart track receiver, coarse servo DSP by the control of gimbal gyro and execution unit hand to essence with
Track servo DSP.
Smart tracking servo DSP responds to the state of smart track loop, and the loop mainly includes：Smart track receiver,
Gyroscopic stabilizer, gimbal positioning execution unit and quick tilting mirror.After the signal that coarse servo DSP is delivered is received, smart servo
Loop realizes the beacon beam of tenacious tracking to target aircraft, it is ensured that signal luminous energy is stably received.The smart servo DSP controls
The camera gain and center of gravity threshold value of essence tracking center of gravity positioning camera.
The diagnostic data labeled upper time that all DSP are returned, sequence number and source identification number.These information are led to
Cross microprocessor controller to be transferred on LAN, and store on a hard disk for diagnosis computer, and pass to test flight
On the memory of device systems.Other users can also access these data by the LAN on aircraft.Diagnostic data
Number amount and type are controlled by user, and the diagnosis computer has the original frame data and whole for showing and including obtaining from camera
The ability of intermediate data.
Assistant subsystem：
Assistant subsystem is for the normal work of airborne laser communication terminal provides power supply and carries out thermal control.Ensure laser communication
Terminal must be able to be run within the temperature range of -62 degree to+55 degree, and adapt in humidity from the change near zero to heavy rain.
3rd, mode of operation：
Park mode：
Power consumption (P is reduced by closing a terminal power supply<1W), terminal platform thermal control keeps terminal temperature in trouble free service model
In enclosing, only terminal control unit is in standby mode.
Standby mode：
Terminal maintains low power consumpting state, and terminal control unit and thermal control subsystem are started working, and wait Wait Order to be input into.
Run-up mode：
Except power amplifier and motor, remaining end fitting is all started power up, and terminal can be switched at any time
Working condition.
Acquisition mode：
Terminal whole part all enters working condition, and antenna points to target terminal to obtain the flashlight of other side, and carries out
Error correction is until the smart tracking detector of one's own side has signal output.
Communication pattern；
Terminal all-the-time stable tracks the beacon beam of distant terminal, keeps communication connection status.
Diagnostic mode：
Terminal is capable of the working condition of diagnostic system, and can have the default mistake for the treatment of.
When specifically used, gondola glass window should plate the anti-reflection film for meeting military standard, the curvature of its glass window
To match with gondola, and near-zero focal power can be accomplished.It is this to be designed to optical table in scanning process
Optical laying error be reduced to minimum, while the interference of external pneumatic stream also is reduced into minimum.For reduces cost and suitable
Airborne platform, optical antenna is answered to use Cassegrain telescope, primary mirror to use parabolic mirror, secondary mirror to be reflected using hyperbolic
Mirror, and folding axial light path is used with the volume of further compressing terminal.Thermal control design is set using passive thermal control design and Active thermal control
Meter wants the method for coordinating, and implements to be thermally isolated by follower, three parts of electronic unit and optical component as far as possible, and respectively to it
Take corresponding thermal control measure.To realize the stabilization of the optical axis, stabilization, irrotational displacement are carried out to the optical axis using the passive braking measure of master
Specific rubber realizes passive vibration damping, suppresses influence of the dither component of platform to the optical axis；Use with the speed in broadband, low drifting
Rate gyro for core devices active optic central extract system, to low frequency, significantly disturbance effectively suppressed.To realize high accuracy
Dynamic tracking, using coarse-fine composite shaft ATP tracking techniques.Rough tracking ring has larger visual field and relatively low servo bandwidth, with
Realize fast Acquisition and stablize rough tracking；Essence tracking ring has less dynamic range, servo bandwidth higher and tracking essence high
Degree, to ensure quick and high-precision alignment and tracking.
Claims (5)
1. airborne laser communication equipment, includes in cabin and two parts out of my cabin, is the electron process module of system in the cabin in, out of my cabin for
Light machine testing and servo-drive system, it is characterised in that：Described partly includes housing out of my cabin, the radome fairing on housing（1）, in shell
In vivo, radome fairing（1）Corresponding position is provided with optical table（4）, optical table（4）Two-dimentional Chang Ping is connected to by pitch axis
Platform（6）On, realize optical table（4）Pitch rotation；Two-dimentional Chang Pingtai（6）Housing and outside are connected by the azimuth axis on top
Rotating mechanism, realize shell, two dimension Chang Pingtai（6）With optical table（4）Synchronous plane rotate；Optical table（4）Upper peace
Equipped with Visible Light Camera（5）, reception antenna（3）, transmitting antenna（2）And infrared camera（10）；
Described electron process module mainly includes communication antenna circuit（12）, and operation bench circuit（11）；
Communication antenna circuit（12）In, the optical signal transmission that information source Optical Receivers and beacon Optical Receivers will be received to behaviour
Control platform circuit（11）In be analyzed treatment, information source light emission module and beacon light emission module are by the optical signal after reception processing
Launch, thus complete the accurate alignment of both sides；Pitching shafting and azimuth axle receive operation bench circuit（11）Signal it is defeated
Go out, and rotated by receiving signal control motor, adjusting device alignment position；
Operation bench circuit（11）In be provided with and communication antenna circuit（12）The communications processor element and communications processor element of connection
The main control unit of connection, includes the human-computer exchange unit being connected with host computer and the external control being controlled in main control unit
Bar.
2. airborne laser communication equipment according to claim 1, includes in cabin and two parts out of my cabin, is system in the cabin in
Electron process module, is out of my cabin light machine testing and servo-drive system, it is characterised in that：Described optical table（4）In by receive
Antenna（2）Beacon beam and information source optical signal are received simultaneously, by after filters filter, by spectroscope light splitting, afterwards by signal
The thick capture detector or smart tracking detector by setting are exported to communication antenna circuit respectively（12）In information source light-receiving
In module and beacon Optical Receivers.
3. airborne laser communication equipment according to claim 1, includes in cabin and two parts out of my cabin, is system in the cabin in
Electron process module, is out of my cabin light machine testing and servo-drive system, it is characterised in that：Described housing upper is provided with damping isolation
（8）, for carrying out passive vibration isolation treatment.
4. airborne laser communication equipment according to claim 1, includes in cabin and two parts out of my cabin, is system in the cabin in
Electron process module, is out of my cabin light machine testing and servo-drive system, it is characterised in that：Described communication antenna circuit（12）Middle setting
There are azimuth axis gyro and pitch axis gyro, influenceed as thrashing is eliminated.
5. the control method of the airborne laser communication equipment described in a kind of utilization claim 1, it is characterised in that：
1）, signal reception：
1a）, use same optical reception antenna（3）The information source light and beacon beam of distant terminal transmitting are received simultaneously；
1b）, in reception antenna（3）Rear end relaying light path part passes through wave filter after filtering, afterwards will by quick titling mirror
Optical signal is reflexed in spectroscope, carries out information source light and beacon beam is separated；
1c）, information source light after separation in communication source photo-detector is transferred to after wave filter, communication source photo-detector will catch
To optical signal be uploaded to communication antenna circuit（12）In information source Optical Receivers in, uploaded to after carrying out data regulation treatment
Operation bench circuit（11）, processed；
Beacon beam after separation is by the way that after wave filter, the beacon beam of a part reaches coarse alignment detector by light splitting piece, afterwards
By communication antenna circuit（12）It is uploaded to operation bench circuit（11）Coarse alignment analysis and Control is carried out, the beacon beam of another part leads to
Cross light splitting piece and reach smart tracking detector, afterwards by communication antenna circuit（12）It is uploaded to operation bench circuit（11）Carry out essence right
Quasi- analysis and Control；
2）, equipment adjustment：To in communication source photo-detector, communication source photo-detector will be captured the optical signal transmission for receiving
Optical signal uploads operation bench circuit（11）, the information of feedback to communication antenna circuit（12）In pitching shafting and azimuth axle enter
Row control, and by control adjustment signal output, so as to adjust receiving device luffing angle and orientation angles, signal is carried out in real time
Tracking, it is ensured that the beacon beam and information source light of both sides can real-time tranception it is unimpeded；
3）, signal transmitting：Beacon beam and information source light are launched respectively, and the information source light of output first passes around intensity modulated and puts
Greatly, relay optical system collimator and extender is then used, then after quick titling mirror reflects, is launched using without burnt telescope；
Beacon beam then directly carries out collimator and extender and launches.
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| CN201611230417.2A CN106788763B (en) | 2016-12-28 | 2016-12-28 | Airborne laser communication device and control method thereof |
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| CN112034877A (en) * | 2020-09-28 | 2020-12-04 | 中国电子科技集团公司第五十四研究所 | Laser-assisted unmanned aerial vehicle autonomous take-off and landing terminal, system and method |
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| CN114024605B (en) * | 2021-11-03 | 2023-09-01 | 浙江大学湖州研究院 | Miniaturized unmanned aerial vehicle laser communication terminal |
| CN114024605A (en) * | 2021-11-03 | 2022-02-08 | 浙江大学湖州研究院 | Miniaturized unmanned aerial vehicle laser communication terminal |
| CN114221702A (en) * | 2021-12-03 | 2022-03-22 | 航天恒星科技有限公司 | All-solid-state space laser communication terminal based on laser phased array |
| CN114353830B (en) * | 2021-12-27 | 2023-11-14 | 北京遥感设备研究所 | Optical path switching device and switching method for constant star calibration |
| CN114353830A (en) * | 2021-12-27 | 2022-04-15 | 北京遥感设备研究所 | Light path switching device and switching method for fixed star calibration |
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