CN113242090B - Space laser communication far-field simulation ground testing device and testing method - Google Patents
Space laser communication far-field simulation ground testing device and testing method Download PDFInfo
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- CN113242090B CN113242090B CN202110754376.1A CN202110754376A CN113242090B CN 113242090 B CN113242090 B CN 113242090B CN 202110754376 A CN202110754376 A CN 202110754376A CN 113242090 B CN113242090 B CN 113242090B
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Abstract
The invention provides a space laser communication far-field simulation ground testing device and a testing method. The testing device comprises an optical terminal A/B and a far-field simulation computer; the optical terminal A/B generates a terminal A/B optical power amplification input signal and a far-field simulation optical path input signal through a 1:1 optical splitter; the CMOS camera A/B detects the offset of the optical axis sent by the terminal A/B at the exit pupil of the optical terminal A/B; and accurately simulating the deviation angle of the spatial optical axis according to the exponential attenuation characteristic by using the controllable optical attenuator A/B. Adding space background stray light to the optical signal subjected to the numerical control attenuation through an optical combiner A/B; then a plurality of reflectors are incident to a vibrating mirror at the front end of the terminal B/A, and the vibrating mirror simulates the micro-vibration environment of the satellite; and the direction of an optical axis reaching the receiving end B/A is ensured to be unchanged through an independent far-field simulation optical path. The invention ensures the consistency and repeatability of the test result.
Description
Technical Field
The invention relates to a space laser communication far field simulation ground test device and a test method, which can perform high-precision numerical control simulation on complex environments such as space light far field characteristics, inter-different-orbit optical axis lead, space background light, satellite micro-vibration and the like, and belongs to the field of space laser communication.
Background
The space laser communication is the most effective broadband communication means for realizing thousands of kilometers to tens of thousands of kilometers, but the laser communication terminal displays completely different test results under the space long-distance communication environment and the ground short-distance test environment. The main reason is that the influence of the far field in the actual communication environment and the near field in the ground test on the position of the APT optical axis in the laser communication terminal is greatly different.
For two laser communication terminals in the long-distance space, the optical axis of each terminal for receiving optical signals points to the connection direction of the centers of the two terminals, and is not related to the adjustment of the optical axis of the transmitting terminal. The beam spread angle of laser communication is small, typically from tens of urads to tens of urads, so that the spot at the receiving end is small even if transmitted over long distances: typically from tens to hundreds of meters. When the optical axis adjustment is performed at the transmitting terminal, energy generation at the receiving end varies.
And for two laser communication terminals in a short distance on the ground, the size of a light spot in a near field has small change during transmission due to a tiny beam divergence angle. Thus, when the transmitting optical axis of the transmitting terminal is adjusted, the size and energy of the light beam entering the receiving terminal are almost kept unchanged. At the same time, the change is immediately detected at the receiving terminal due to the optical axis adjustment of the transmitting terminal.
The far field influence is closely related to APT system error and communication distance, and APT tracking error is generally required to be smaller than that of APT in order to ensure APT bidirectional stable tracking
(wherein
Is the full angle of the beam spread of the emitted light). As shown in fig. 1, in the far field, it is generally required that the ratio of the aperture of the receiving-end antenna to the distance between two terminals should be much smaller than the tracking error of APT:
in the above formula:
Dthe aperture of the receiving end antenna;
λis the communication wavelength;
lis the distance between two laser communication terminals.
That is, the communication distance of the terminal is required to satisfy the following equation and is considered as far-field transmission:
in practice, the relationship of 10 times as above is taken as the boundary between the near field and the far fieldl min At this time, there are:
for the laser communication terminal parameters which are commonly used at present: terminal caliber ofD=80mmAt a communication wavelength ofλ=1500nmWhen it is required tol min =135Km。
Thus, the reality of testing in a laboratory or near field bi-directional versus far field in space is quite different. In order to verify the actual tracking and communication results in a space laser communication far-field environment on the ground, a mountain peak with a certain height is generally searched in the field, and a far-field experiment is performed in the ground environment. However, in this case, the effect of the atmosphere on the laser energy: the turbulence, absorption, etc. of the atmosphere are very severe, which can cause the light spot on the detector at the receiving end to flicker. This environment, in turn, is very different from the actual environment of spatial laser communication.
In order to perform ground on-track Test simulation on a laser communication terminal in the european silix project, a stb (system Test bed) Test platform is designed. STB was reported in the SPIE journal of 1999 in the article "simple final ground testing and in-flight performance assessment". The STB platform can perform a one-way simulation with high fidelity to far-field light: the simulator truly evaluates the luminous beam of the laser communication terminal and emits the luminous beam to the laser communication terminal in a quasi-authentic beam.
Besides europe, research institutions related to japan, the united states and the like also perform a lot of work in the field of ground test and evaluation of spatial laser communication, and these works can perform a lot of far-field simulation and test on spatial laser communication in the ground stage, thereby providing an excellent experimental environment for ensuring the success of spatial laser communication.
At present, the ground far field simulation test mode of the space laser communication terminal mainly comprises the following steps: firstly, a ground remote simulation test is carried out; in addition, the far field distribution is obtained by optical Fourier transform and a light beam amplifying component; and a fiber-optic probe is adopted to acquire an optical signal with far-field characteristics. The first method is affected by atmospheric turbulence, which is present even in a sunny environment. The second and third methods require more optical components, are complex to adjust in practice, have poor system stability, and have certain errors with the actual far field.
Disclosure of Invention
The method aims at the problems existing in the ground far-field simulation test environment of the current space laser communication terminal: the invention provides a space laser communication far-field simulation ground testing device and a testing method, and solves the problems of complexity in implementation, poor stability of the testing device and inconsistency in testing of the existing ground far-field simulation technology.
The above purpose is realized by the following technical scheme:
the space laser communication far-field simulation ground testing device comprises an optical terminal A, an optical terminal B, two laser communication terminals and a far-field simulation computer;
the optical modulator of the optical terminal A is connected with a 1:1 optical splitter A through an optical fiber, one of two paths of outputs of the 1:1 optical splitter A passes through an optical amplifier of the optical terminal A in a normal mode, and the other path of outputs is used as an input optical signal of a far-field simulation test device; a transmitting light signal at the exit pupil of the optical terminal A reaches the CMOS camera A through the wave splitter A and the attenuation plate A, and the offset of the optical axis of a light beam at the exit pupil of the terminal A is detected through the CMOS camera A; the offset passes through a controllable optical attenuator A after equivalent time delay between terminals, and meanwhile, the ideal advance calculated by the orbit model is also sent to the controllable optical attenuator A; the optical signal with the controlled level reaches a vibrating mirror B simulating the micro-vibration of the satellite through a plurality of reflectors A; finally, the light beam passes through the partial wave plate B and reaches the entrance pupil of a receiving terminal B;
the optical modulator of the optical terminal B is connected with a 1:1 optical splitter B through an optical fiber, one of two paths of outputs of the 1:1 optical splitter B passes through an optical amplifier of the optical terminal B in a normal mode, and the other path of outputs is used as an input optical signal of a far-field simulation test device; a transmitting light signal at the exit pupil of the optical terminal B reaches the CMOS camera B through the wave splitter B and the attenuation plate B, and the offset of the optical axis of a light beam at the exit pupil of the terminal B is detected through the CMOS camera B; the offset passes through a controllable optical attenuator B after equivalent delay between terminals, and meanwhile, the ideal lead calculated by the orbit model is also sent to the controllable optical attenuator B; the optical signal with the controlled level reaches a vibrating mirror A simulating the micro-vibration of the satellite through a plurality of reflectors B; finally, the light beam passes through the partial wave plate A and reaches the entrance pupil of the receiving terminal A;
the far-field simulation computer comprises a satellite micro-vibration controller A connected with the vibration mirror A, a satellite micro-vibration controller B connected with the vibration mirror B, a spatial light attenuation simulator A connected with the CMOS camera A, a spatial light attenuation simulator B connected with the CMOS camera B, a time delay A connected with the spatial light attenuation simulator A, a time delay B connected with the spatial light attenuation simulator B and a spatial orbit generation module.
Further, the output of the controllable optical attenuator A and the ASE noise source A simulate background light are combined in the combiner A, the output of the combiner A forms space parallel light beams through the collimator A, then parallel light beams equivalent to the receiving aperture are formed through the beam expander A, and the parallel light beams enter the vibrating mirror B through the reflector A; the output of the controllable optical attenuator B and the ASE noise source B simulation background light are combined in a combiner B, the output of the combiner B forms space parallel light beams through a collimator B, then the space parallel light beams form parallel light beams with the same receiving caliber through a beam expander B, and the parallel light beams enter a vibrating mirror A through a reflector B.
Further, exit pupil signal light of the optical terminal A enters the CMOS camera A through the wave splitter A, the attenuator A and the lens A; the CMOS camera A is positioned on the focal plane of the lens A; the exit pupil signal light of the optical terminal B enters the CMOS camera B through the wave splitter B, the attenuator B and the lens B; the CMOS camera B is in the focal plane of the lens B.
Further, the optical terminal a and the optical terminal B respectively include an optical modulator, an optical amplifier, an optical detector, and a transmitting/receiving optical system.
The method for carrying out the space laser communication far-field simulation ground test by using the space laser communication far-field simulation ground test device comprises the following steps:
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera A in the spatial light analog attenuator A to obtain a receiving optical axis offset angle of an optical terminal B, and outputting a receiving level attenuation value of the optical terminal B according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer A according to the receiving level attenuation value of the optical terminal B according to the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer A controls the level of a light signal received by the optical terminal B through the controllable optical attenuator A; the satellite micro-vibration controller A controls the vibration of the galvanometer A according to the satellite micro-vibration model;
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera B in the space optical analog attenuator B to obtain a receiving optical axis offset angle of the optical terminal A, and outputting a receiving level attenuation value of the optical terminal A according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer B according to the receiving level attenuation value of the optical terminal A and the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer B controls the level of a light signal received by the optical terminal A through the controllable optical attenuator B; and the satellite micro-vibration controller B controls the vibration of the galvanometer B according to the satellite micro-vibration model.
Has the advantages that:
1. the light modulation signal of the optical terminal A passes through a 1:1 optical splitter A, wherein one path passes through an optical amplifier of the terminal A in a normal mode, and a sending optical axis at the exit pupil of the optical terminal A is adjusted by the optical terminal A, which is a variable quantity; the other path of the optical modulation signal is used as an input optical signal of a far-field simulation testing device, the signal reaches an optical terminal B through links such as a collimator A and a beam expander A of the testing device, the optical axis cannot change due to adjustment of the optical axis of the optical terminal A, the receiving optical axis reaching the optical terminal B is a fixed direction, and similarly, the receiving optical axis of the optical modulation signal reaching the optical terminal B is also a fixed direction.
2. The method comprises the steps of calculating the ideal lead pointed by an optical terminal A according to satellite orbit parameters, and completing the control of far-field received optical energy together with the offset of an optical axis sent by the optical terminal A; by the mechanism, the correctness of the optical axis lead of the transmission in the different-rail communication environment can be tested.
3. The invention simulates the transmission time of the light transmitted by the optical terminal A to the optical terminal B through the long-distance spatial transmission by setting the time delay of the far-field received optical signal energy control quantity; the transmission time will affect the stability of the bidirectional closed loop tracking of the laser communication terminal. According to the exponential decay relation between the detected transmitting optical axis offset (considering the influence of the lead) of the optical terminal A and the far-field receiving level, testing the accuracy of the optical axis lead of the transmitting terminal A by the track parameters; adding space background stray light into the optical signal subjected to the numerical control attenuation through the optical combiner A; then, a plurality of reflectors are incident to a vibrating mirror at the front end of the terminal B, and the vibrating mirror simulates the micro-vibration environment of the satellite; and the optical axis direction reaching the receiving end B is ensured to be unchanged through an independent far-field simulation optical path. Accurately controlling the far field level received by the optical terminal B by using the corrected digital controllable optical attenuator; the control range is not less than 30dB, which meets the requirement of the current space laser communication.
4. For space optical transmission from an optical terminal A to an optical terminal B, the invention realizes satellite micro-vibration simulation of the terminal B by using a galvanometer B; the vibration model can test the performance of the APT tracking technology in a complex micro-vibration model environment.
5. The invention can perform systematic accurate simulation test on the optical axis lead under the space laser communication far-field environment and the different orbit environment, the satellite micro-vibration environment and the space background light environment.
Drawings
Fig. 1 is a laser communication far field distance diagram.
FIG. 2 is a block diagram of the spatial laser communication far-field simulation ground testing device of the present invention.
Detailed Description
As shown in fig. 1-2, the spatial laser communication far-field simulation ground testing apparatus of the present embodiment mainly considers the following factors when designing a spatial laser communication far-field simulation system:
(1) the direction of an optical axis received by the receiving terminal in a far field is parallel to a central connecting line of the two terminals, and the adjustment of a light emitting axis of the sending terminal does not influence the direction of the light receiving axis of the receiving terminal;
(2) when the receiving optical axis of the terminal in the far field deviates from the transmitting optical axis of the transmitting terminal, the received signal level decays exponentially:
wherein:
the original received signal level; z is the spatial distance between the two terminals;αthe angle of the receiving terminal from the center of the light beam;ω 0is the divergence angle half-angle of the transmitted light;P t optical power transmitted for the terminal;
transmitting the optical path loss for the terminal;
(3) micro-vibration of the receiving terminal can cause the change of the position of a light spot of a CMOS camera or a QD detector, and the received signal quantity can be kept unchanged as long as the angular position of the receiving terminal in a receiving field is unchanged;
(4) the error of the advanced aiming angle in the off-track mode will also affect the signal level received by the terminal, and the advanced aiming angle is:
(Here)vIs the relative lateral velocity of the two terminals,cis the speed of light);
(5) the laser communication terminal detector is also affected by the spatial background light, but the energy of the laser communication terminal detector on the detection is basically kept unchanged.
The space laser communication far-field simulation ground testing device comprises an optical terminal A, an optical terminal B, two laser communication terminals and a far-field simulation computer;
as shown in fig. 2, the optical splitter outputs two optical signals, wherein the first optical signal is output to the input end of the optical amplifier of the optical terminal a through the optical fiber; the second path is output to a controllable optical attenuator A through an optical fiber. In order to simulate the influence of the spatial background light on the laser communication, the output of the controllable optical attenuator A and the ASE noise source A simulate the background light to be combined in the combiner A. The output of the combiner is formed into a space parallel light beam by a collimator A, and then the space parallel light beam is formed into a parallel light beam equivalent to a receiving aperture by a beam expander A. The parallel light enters a vibrating mirror B through a 45-degree reflector A (the position and the number of the reflectors depend on the spatial distribution of an actual light path), and finally reaches the entrance pupil of a receiving terminal B through a partial wave plate B;
the optical modulation signal in the optical terminal B is input to the 1:1 optical splitter B via an optical fiber. The optical splitter outputs two paths of optical signals, wherein the first path of optical signals is output to the input end of an optical amplifier of an optical terminal B through an optical fiber; the second path is output to a controllable optical attenuator B through an optical fiber. In order to simulate the influence of the spatial background light on the laser communication, the output of the controllable optical attenuator B and the ASE noise source B simulate the background light to be combined in a combiner B. The output of the combiner is formed into a space parallel light beam by a collimator B, and then the space parallel light beam is formed into a parallel light beam equivalent to a receiving aperture by a beam expander B. The parallel light enters a galvanometer A through a 45-degree reflector B (the position and the number of the reflectors depend on the spatial distribution of an actual light path);
the invention adopts a 1:1 3dB optical splitter to split the output signal of the optical modulator into two paths of signal light. The first path of output signal light of the optical splitter is still connected with the optical amplification module. APC constant power output is used for the optical amplifier. Under the configuration, the influence of the receiving and transmitting isolation of the laser communication terminal on the performance under a far-field test environment can be tested. The second path of the optical splitter will be optically processed appropriately to form a far-field signal received at the opposite end.
The far-field simulation computer comprises a satellite micro-vibration controller A connected with the vibrating mirror A, a satellite micro-vibration controller B connected with the vibrating mirror B, a spatial light attenuation simulator A connected with the CMOS camera A, a spatial light attenuation simulator B connected with the CMOS camera B, a time delay A connected with the controllable light attenuator A, a time delay B connected with the controllable light attenuator B and a spatial orbit generation module.
Further, the output of the controllable optical attenuator A and the ASE noise source A simulate background light are combined in the combiner A, the output of the combiner A forms space parallel light beams through the collimator A, then parallel light beams equivalent to the receiving aperture are formed through the beam expander A, and the parallel light beams enter the vibrating mirror B through the reflector A; the output of the controllable optical attenuator B and the ASE noise source B simulation background light are combined in a combiner B, the output of the combiner B forms space parallel light beams through a collimator B, then the space parallel light beams form parallel light beams with the same receiving caliber through a beam expander B, and the parallel light beams enter a vibrating mirror A through a reflector B.
Further, exit pupil signal light of the optical terminal A enters the CMOS camera A through the wave splitter A, the attenuator A and the lens A; the CMOS camera A is positioned on the focal plane of the lens A; the exit pupil signal light of the optical terminal B enters the CMOS camera B through the wave splitter B, the attenuator B and the lens B; the CMOS camera B is in the focal plane of the lens B.
Further, the optical terminal a and the optical terminal B respectively include an optical modulator, an optical amplifier, an optical detector, and a transmitting/receiving optical system.
The method for carrying out the space laser communication far-field simulation ground test by using the space laser communication far-field simulation ground test device comprises the following steps:
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera A in the spatial light analog attenuator A to obtain a receiving optical axis offset angle of an optical terminal B, and outputting a receiving level attenuation value of the optical terminal B according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer A according to the receiving level attenuation value of the optical terminal B according to the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer A controls the level of a light signal received by the optical terminal B through the controllable optical attenuator A; the satellite micro-vibration controller A controls the vibration of the galvanometer A according to the satellite micro-vibration model;
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera B in the space optical analog attenuator B to obtain a receiving optical axis offset angle of the optical terminal A, and outputting a receiving level attenuation value of the optical terminal A according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer B according to the receiving level attenuation value of the optical terminal A and the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer B controls the level of a light signal received by the optical terminal A through the controllable optical attenuator B; and the satellite micro-vibration controller B controls the vibration of the galvanometer B according to the satellite micro-vibration model.
Test cases:
the communication distance between two satellites is 20000Km, the aperture of the terminal antenna is 80mm, and the beam divergence angle (total angle) is 41 urad. The two-way communication rate is 5Gbps and the receiver sensitivity is-52.4 dBm when a coherent mode is adopted. The output optical power of the terminal optical modulation module is-3 dBm. The minimum input optical power of the optical amplifier is-10 dBm, and the 1:1 shunt mode can be adopted externally.
The output of the optical modulation module is connected to the optical attenuation module after being divided by 1: 1. The optical attenuation module adopts a mode of combining a fixed attenuator JW3303 of Jiahui company with a controllable attenuator V1550A of ThorLabs company. Considering that the laser communication terminal generally works in a far field half-power angle range when performing bidirectional tracking, and meanwhile, the system margin generally takes 3 dB. Thus, the total attenuation of the fixed attenuation module is as follows:
the V1550A spatial light attenuation simulator supports spectral ranges of: 1250nm-1650nm, and the maximum attenuation reaches 30 dB. In consideration of the nonlinear relationship between the attenuation amount of the block and the input voltage, the input control amount needs to be linearly corrected. The minimum attenuation for the controllable attenuator needs to be as aboveLTo compensate. And combining the attenuated optical signal with an ASE noise source LSM-ASE-C-F of APEAK company through a combiner, and controlling the size of noise to finish simulating the space stray light. And a Jiahui company optical power meter JW8102 is used for accurate optical power measurement, and the optical power of an output signal is ensured to be-46.6 dBm when the adjustable attenuator is set at 0 dB.
For the detection of the transmitting optical axis of the laser communication terminal, a 1550nm short-wave infrared camera is adopted, a threshold value adjustable centroid algorithm is adopted for light spot calculation, and the centroid calculation precision requirement is not lower than 0.25 pixel. By solving for the angle
The attenuation of the adjustable attenuator is determined by the following formula
And (3) controlling:
and precisely delaying the delay quantity of the attenuator control quantity in software according to the actual distance between the two terminals.
The collimator, the beam expander, the lens and the attenuation sheet in the light path can adopt a standardized optical module or a customized module. The position and the number of the reflecting mirrors depend on the requirement of an actual light path, and the micro-vibration simulation galvanometer can adopt a voice coil galvanometer in a large angle range or a piezoelectric galvanometer in a small angle range.
When the micro-vibration environment is simulated, a mode of combining three discrete spectrum components and a continuous spectrum component is adopted. Wherein the dispersion spectrum is: the discrete component with the frequency of 1Hz and the amplitude of 100urad corresponds to the motion simulation of the satellite platform solar sailboard; the amplitudes of 4urad and 0.6urad at 100Hz and 200Hz respectively correspond to the simulation of the fundamental wave and the second harmonic of the satellite flywheel. And simulating the vibration continuous spectrum component of the satellite platform by adopting the following functions:
in the above formula:S（f) Is expressed in frequencyfThe amplitude of the vibration of (c).
The light path accurately simulates the space far field, micro-vibration and bidirectional laser communication environment, and can provide a reliable test environment for space laser communication.
The above embodiments are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical solution according to the technical idea of the present invention falls within the protection scope of the present invention. The technology not related to the invention can be realized by the prior art.
Claims (5)
1. A space laser communication far-field simulation ground testing device comprises an optical terminal A, an optical terminal B, two laser communication terminals and a far-field simulation computer; the method is characterized in that:
the optical modulator of the optical terminal A is connected with a 1:1 optical splitter A through an optical fiber, one of two paths of outputs of the 1:1 optical splitter A passes through an optical amplifier of the optical terminal A in a normal mode, and the other path of outputs is used as an input optical signal of a far-field simulation test device; the transmitted light signal at the exit pupil of the optical terminal A reaches the CMOS camera A through the wave splitter A and the attenuator A, and the offset of the optical axis of the light beam at the exit pupil of the optical terminal A is detected through the CMOS camera A; the offset passes through a controllable optical attenuator A after equivalent time delay between terminals, and meanwhile, the ideal advance calculated by the orbit model is also sent to the controllable optical attenuator A; the optical signal with the controlled level reaches a vibrating mirror B simulating the micro-vibration of the satellite through a plurality of reflectors A; the light beam reaches the entrance pupil of the receiving terminal B through the partial wave plate B;
the optical modulator of the optical terminal B is connected with a 1:1 optical splitter B through an optical fiber, one of two paths of outputs of the 1:1 optical splitter B passes through an optical amplifier of the optical terminal B in a normal mode, and the other path of outputs is used as an input optical signal of a far-field simulation test device; a transmitting light signal at the exit pupil of the optical terminal B reaches the CMOS camera B through the wave splitter B and the attenuation plate B, and the offset of the optical axis of a light beam at the exit pupil of the terminal B is detected through the CMOS camera B; the offset passes through a controllable optical attenuator B after equivalent delay between terminals, and meanwhile, the ideal lead calculated by the orbit model is also sent to the controllable optical attenuator B; the optical signal with the controlled level reaches a vibrating mirror A simulating the micro-vibration of the satellite through a plurality of reflectors B; the light beam reaches the entrance pupil of the receiving terminal A through the partial wave plate A;
the far-field simulation computer comprises a satellite micro-vibration controller A connected with the vibration mirror A, a satellite micro-vibration controller B connected with the vibration mirror B, a spatial light attenuation simulator A connected with the CMOS camera A, a spatial light attenuation simulator B connected with the CMOS camera B, a time delay A connected with the spatial light attenuation simulator A, a time delay B connected with the spatial light attenuation simulator B and a spatial orbit generation module.
2. The space laser communication far-field simulated ground testing device according to claim 1, wherein the output of the controllable optical attenuator A is combined with the ASE noise source A simulated background light in a combiner A, the output of the combiner A forms a spatial parallel light beam through a collimator A, and then forms a parallel light beam with a receiving aperture equivalent to the receiving aperture through a beam expander A, and the parallel light beam enters a vibrating mirror B through a reflecting mirror A; the output of the controllable optical attenuator B and the ASE noise source B simulation background light are combined in a combiner B, the output of the combiner B forms space parallel light beams through a collimator B, then the space parallel light beams form parallel light beams with the same receiving caliber through a beam expander B, and the parallel light beams enter a vibrating mirror A through a reflector B.
3. The space laser communication far-field simulation ground testing device according to claim 1, wherein an exit pupil signal light of the optical terminal A enters the CMOS camera A through the wave splitter A, the attenuator A and the lens A; the CMOS camera A is positioned on the focal plane of the lens A; the exit pupil signal light of the optical terminal B enters the CMOS camera B through the wave splitter B, the attenuator B and the lens B; the CMOS camera B is in the focal plane of the lens B.
4. The space laser communication far-field simulation ground test device according to claim 1, wherein the optical terminal a and the optical terminal B respectively comprise an optical modulator, an optical amplifier, an optical detector, and a transceiver optical system.
5. A method for performing space laser communication far-field simulation ground test by using the space laser communication far-field simulation ground test device as claimed in any one of the preceding claims, wherein the method comprises the following steps:
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera A in the spatial light analog attenuator A to obtain a receiving optical axis offset angle of an optical terminal B, and outputting a receiving level attenuation value of the optical terminal B according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer A according to the receiving level attenuation value of the optical terminal B according to the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer A controls the level of a light signal received by the optical terminal B through the controllable optical attenuator A; the satellite micro-vibration controller A controls the vibration of the galvanometer A according to the satellite micro-vibration model;
the space orbit generation module is used for calculating theoretical lead according to satellite orbit models of the optical terminal A and the optical terminal B; carrying out vector addition on the theoretical lead and the offset of a transmitting optical axis detected by the CMOS camera B in the space optical analog attenuator B to obtain a receiving optical axis offset angle of the optical terminal A, and outputting a receiving level attenuation value of the optical terminal A according to the exponential attenuation characteristic of the offset angle; meanwhile, the analog computer simulates the transmission delay in the delayer B according to the receiving level attenuation value of the optical terminal A and the distance between the optical terminal A and the optical terminal B; the attenuation quantity output by the delayer B controls the level of a light signal received by the optical terminal A through the controllable optical attenuator B; and the satellite micro-vibration controller B controls the vibration of the galvanometer B according to the satellite micro-vibration model.
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| CN101131430A (en) * | 2007-10-10 | 2008-02-27 | 中国科学院上海光学精密机械研究所 | Laser radar double-pass optical transmission simulation and ranging performance detection device |
| CN103353387A (en) * | 2013-06-28 | 2013-10-16 | 哈尔滨工业大学 | Light-spot image processing detection system and method for detecting light-spot gray scale centroid and conventional gray-scale image-noise removal effect |
| CN104539349A (en) * | 2014-11-28 | 2015-04-22 | 北京大学 | Multifunctional laser space communication ground test system and static parameter test method |
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| CN101131430A (en) * | 2007-10-10 | 2008-02-27 | 中国科学院上海光学精密机械研究所 | Laser radar double-pass optical transmission simulation and ranging performance detection device |
| CN103353387A (en) * | 2013-06-28 | 2013-10-16 | 哈尔滨工业大学 | Light-spot image processing detection system and method for detecting light-spot gray scale centroid and conventional gray-scale image-noise removal effect |
| CN104539349A (en) * | 2014-11-28 | 2015-04-22 | 北京大学 | Multifunctional laser space communication ground test system and static parameter test method |
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