CN109946712B - Synthetic aperture optical imaging test system for extrasystematic planet detection - Google Patents
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Abstract
The invention discloses an optical synthetic aperture imaging test system for extrasystematic planet detection, which comprises: the fixed star-planet light source simulator outputs two beams of parallel light with certain angle difference and different brightness; the controllable aperture array comprises a plurality of individually controlled sub-apertures; the focusing imaging module converges the optical signal output by the controllable aperture array and sends the optical signal to the microscopic imaging module; the microscopic imaging module generates and amplifies interference fringe signals and sends the interference fringe signals to the data processing module; and the data processing module records interference fringes and controls the controllable aperture array to execute the on and off of the next sub-aperture combination so as to simulate the change of a base line, and when the change of the base line is enough for imaging UV coverage, imaging calculation is carried out according to the recorded interference fringes. The invention utilizes the controllable aperture array to introduce equivalent sub-aperture space motion, effectively reduces the complexity and cost of system simulation, and simultaneously avoids additional errors caused by surface type difference in a multi-mirror system.
Description
Technical Field
The invention belongs to the technical field of sparse aperture optical imaging, and relates to an optical synthetic aperture imaging test system for extrasystematic planet detection, which is used for ground tests.
Background
The search for an environment suitable for human survival outside the earth is a dream of human beings, and the existence of life outside the solar system is a subject of human interest. In 1995, Mayor and Queloz of the geneva extrados planet probe group in switzerland found the first planets of the muxing mass order near the quasar-like star (femtostation 51), a significant finding that uncovered the sequential screen for human search extrados planets. With the great discovery of extrageneous planets, exploration and theoretical research of extrageneous planets have become one of the hot areas of international astronomy.
The extrasystematic planetary detection method is divided into indirect detection and direct imaging. The extrasystematic planet indirect detection method mainly comprises a Doppler apparent velocity method, a satellite method, a micro-gravity lens method, a ring fixed star dust disc method, a celestial body measurement method and a pulsar timing method. The indirect detection method cannot acquire planet photons and perform spectral analysis on planet atmosphere, so that whether life signals exist on the planet is difficult to judge. The direct imaging technology of the solar extra-system planet (namely, the direct detection of photons from the planet) is expected to finally realize the detection of the planet in the earth, and meanwhile, the position of the planet can be accurately observed without the problem of the viewing angle (namely, the information such as the radius, the quality and the like of the planet orbit can be accurately obtained), and the spectral analysis is further carried out on the shot extra-system planet, so that the important information such as the life signal and the like of the composition, the surface temperature and even the existence of the life signal of the planet can be obtained.
In direct imaging, in order to improve the angular resolution of an imaging system, the aperture of the system is generally increased, however, the increase of the aperture of the system is limited by the processing technology, the manufacturing cost is also greatly increased, the processing cost of the system is proportional to the aperture to the power of 2.76, and the aperture of the system cannot be expanded without limit due to the limitation of the volume and the emission quality of a payload cabin of an aircraft, so that the direct imaging of the extrasystematic planets is limited. To overcome the above-mentioned contradiction, an optical synthetic aperture imaging technique has been proposed, which uses a plurality of small-aperture optical systems, which may be separate lenses or independent optical systems, to obtain high-resolution imaging. By changing the arrangement structure of the sub-apertures, the optical transfer function of the optical synthetic aperture imaging system can be flexibly controlled, and the method becomes one of the most development potential technical directions of out-of-system planet detection.
Currently, optical synthetic aperture imaging test systems are involved in computer simulation or static ideal imaging simulation. The computer simulation is to use the mathematical model of interference imaging to carry out simulation calculation, the method can only verify the imaging theory and method, the static ideal imaging simulation is to use the preset mask plate to simulate the sub-aperture in the imaging, the light beam emitted from the light source passes through the sub-aperture on the mask plate to interfere at the image surface of the focusing telescope to generate the interference fringe pattern, and then the interference fringe pattern is received by the CCD camera after being amplified by the microscope lens to simulate the point spread function intensity distribution diagram under the ideal condition. This experimental system does not take the situation of motion into account and cannot study the effect of changes in baseline on imaging.
Synthetic aperture optical interference imaging faces two major requirements:
(1) the design of the experimental system must take into account the requirements of the interferometric imaging method verification. Starting from the principle of optical synthetic aperture interference imaging, the optical synthetic aperture interference imaging technology relates to three key technologies, namely a closed phase technology, a UV (ultraviolet) covering technology and an image reconstruction technology, and a ground experimental system design must provide an experimental platform for verification of the key technologies. In actual observation, based on the requirement of satellite collision avoidance design and the consideration of observation time, when in spatial interference imaging, the aperture of the sub-telescope is inevitably different from the aperture corresponding to the diffraction limit resolution to be realized, and the sparsity is very large.
(2) The design of the experimental system must take into account the complexity and realizability of the system. For reconstructing an image with high precision, the position precision of each imaging subsystem is generally required to reach 1/10 λ, taking 500nm blue light as an example, the position precision is about 50nm, and if a motion scheme of a high-precision turntable simulation sub-mirror is added to a ground experimental system, the jitter degree of the turntable can reach the magnitude of several wavelengths, which brings very high challenges to the measurement and real-time compensation of optical path difference, and simultaneously makes an optical path system extremely complex. With the existing technical conditions, the synthetic aperture light interference experiment under the simulated static condition is seriously difficult, and the difficulty of simulating the dynamic imaging process is more conceivable.
Disclosure of Invention
In order to solve the problems, the invention provides a synthetic aperture optical imaging test system for extrasystem planet detection, which can simulate the radiation light signals of extrasystem stars and planets, introduce equivalent subaperture spatial motion by using a controllable aperture array, effectively reduce the complexity and cost of system simulation, avoid additional errors caused by surface type differences in a multi-mirror system, and solve the problems in the prior art.
The technical scheme adopted by the invention is that an optical synthetic aperture imaging test system for out-of-system planet detection is characterized by comprising the following components:
the star-planet light source simulator is used for outputting two beams of parallel light with certain angle difference and different brightness and simulating light signals generated by the outer star and the planet;
a controllable aperture array for receiving an optical signal generated by a star-planet light source simulator, comprising a plurality of individually controlled sub-apertures;
the focusing imaging module is used for converging the optical signals output by the controllable aperture array and sending the optical signals to the microscopic imaging module;
the microscopic imaging module is used for generating and amplifying interference fringe signals and sending the interference fringe signals to the data processing module;
and the data processing module is used for recording interference fringes and controlling the controllable aperture array to execute the on and off of the next sub-aperture combination so as to simulate the change of a base line, and when the change of the base line is enough for imaging UV coverage, imaging calculation is carried out according to the recorded interference fringes so as to reconstruct the image information of the star-planet light source.
Furthermore, the data processing module adopts an FPGA + DSP combined framework, stores geometric arrangements of different sub-aperture combinations in advance and generates a control instruction, and sends the control instruction to the controllable aperture array according to a certain exposure time so as to control the on and off of the corresponding sub-aperture combination; the exposure time is determined according to the detected brightness of the target source.
Furthermore, the controllable aperture array adopts a liquid crystal array, the liquid crystal array comprises a plurality of liquid crystal units, the sub-apertures are liquid crystal units, and two electrodes of each liquid crystal unit are powered on or powered off according to a control instruction received by the controllable aperture array.
Further, the liquid crystal cells in the liquid crystal array are hexagonal or circular.
Furthermore, the fixed star-planet light source simulator comprises a light source, the light source is arranged in the center of the integrating sphere, a first light through hole and a second light through hole which are perpendicular to each other are formed in the spherical surface of the integrating sphere, the second light through hole is connected with one end of a U-shaped sleeve, a small-hole diaphragm is installed at the other end of the sleeve, an attenuator is arranged in the sleeve, a first plane mirror and a second plane mirror are sequentially arranged in the sleeve at a bent position along the direction of a light path, light output by the small-hole diaphragm and the first light through hole is refracted to the plane mirror by a beam splitter prism, and two beams of parallel light with a certain angle difference and different brightness are output through twice reflection of the plane mirror and an off-axis parabolic mirror.
Furthermore, the angle difference between the light emitted from the first light through hole and the light emitted from the small hole diaphragm entering the beam splitter prism is less than 1 arc second.
Furthermore, the small hole diaphragm is fixedly connected with the sleeve through a locking lock.
Further, the effective area of the controllable aperture array is equal to the light collecting area of the focusing imaging module, and the area of each sub-aperture is 1/1000-1/16 of the light collecting area.
Furthermore, the focusing imaging module adopts a convex lens, and the processing error of the surface type is controlled within 1/10 wavelength.
Furthermore, the controllable aperture array, the focusing imaging module and the microscopic imaging module are all installed in a vacuum optical darkroom, a vacuum sealing window is arranged on the vacuum optical darkroom, an optical signal output by the fixed star-planet light source simulator is allowed to penetrate through and be transmitted to the controllable aperture array, the microscopic imaging module is connected with the data processing module through a second vacuum sealing joint, and the data processing module is connected with the controllable aperture array through a first vacuum sealing joint; the star-planet light source simulator, the vacuum optical darkroom and the data processing module are all arranged on the vibration reduction table.
Compared with the traditional invention, the invention has the following advantages:
(1) motion equivalence is introduced, most of the traditional ground experiment systems are static, and the motion simulation can greatly increase the technical complexity and the economic cost and also introduce a great number of motion errors; in the invention, the programmed variable aperture array is adopted to simulate the motion situation of the sub-apertures of the space satellite, the controllable aperture array is utilized to control the on and off of the sub-apertures, different sub-aperture combinations can be equivalent to the space motion of the sub-apertures, and the error problems caused by vibration, mechanical surface jump, thermal environment and the like due to the motion simulation of factor aperture rotation, expansion and contraction and the like are avoided; because the controllable aperture array is fixed, the change of the optical path of the transmission signal cannot be caused, and the extra optical path difference cannot be brought by the movement, so that the research of the interference imaging algorithm is facilitated, and meanwhile, the experiment cost is effectively reduced.
(2) And additional errors caused by surface type differences in a multi-mirror system are avoided. In a multi-mirror interferometric system, the profile error of each sub-mirror adds additional error to the experimental system. In order to obtain a good imaging effect, the surface accuracy of the optical device is required to be better than 1/50 lambda, so that the processing period and the economic cost are greatly increased. In the invention, only one group of focusing imaging modules is adopted, and the system error is effectively controlled under the condition of ensuring the surface type precision.
(3) The target light source is simulated more accurately. The traditional light source simulation directly utilizes a collimator to simulate a single-point light source, but the invention provides a method for realizing the simulation of a double light source by a light folding mode, the output of a star-planet simulator is two beams of parallel light instead of a single beam of parallel light, one beam of the parallel light simulates the radiation light of a planet, the other beam of the parallel light simulates the radiation light of a star, and the contrast is high.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a star-planetary light source simulator in an embodiment of the present invention.
FIG. 3a is a diagram of a circular configuration of an embodiment in which a controllable aperture array employs a liquid crystal array.
FIG. 3b is a diagram of a hexagonal structure of a liquid crystal array used in the controllable aperture array in the embodiment.
In the figure, 1, a star-planet light source simulator, 2, a controllable aperture array, 21, a liquid crystal unit, 3, a focusing imaging module, 4, a microscopic imaging module, 5, a data processing module, 6, a vacuum optical darkroom, 7, a vibration reduction table, 61, a vacuum sealing window, 62, a first vacuum sealing joint, 63, a second vacuum sealing joint, 11, a light source, 12, an integrating sphere, 13, a first light through hole, 14, a second light through hole, 15, an attenuator, 16, a first plane mirror, 17, a sleeve, 18, a second plane mirror, 19, a locking lock, 110, a small aperture diaphragm, 111, a beam splitter prism, 112, a plane reflector and 113, an off-axis parabolic mirror.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention relates to a synthetic aperture optical imaging test system for extrasystematic planet detection, which comprises a fixed star-planet light source simulator 1, a synthetic aperture optical imaging test system and a synthetic aperture optical imaging test system, wherein the fixed star-planet light source simulator is used for simulating radiation light signals of extrasystematic fixed stars and planets and has high contrast; the controllable aperture array 2 is used for controlling on and off of sub apertures, different sub aperture combinations can be equivalent to spatial movement of the sub apertures, the focusing imaging module 3 converges light signals penetrating through the controllable aperture array 2 to the microscopic imaging module 4 to perform imaging, amplification and output interference fringes, and the data processing module 5 reconstructs image information of the fixed star-planet light source according to the interference fringes.
The invention discloses a synthetic aperture optical imaging test system for extrasystematic planet detection, which comprises a fixed star-planet light source simulator 1, a controllable aperture array 2, a focusing imaging module 3, a microscopic imaging module 4, a data processing module 5, a vacuum optical darkroom 6 and a vibration reduction table 7, as shown in figure 1.
The star-planet light source simulator 1 is used for outputting two beams of parallel light with certain angle difference and different brightness and simulating light signals generated by the outer star and the planet.
The structure of the star-planet light source simulator 1 is shown in fig. 2, and comprises a light source 11, the light source 11 is arranged at the center of the sphere of an integrating sphere 12, a first light through hole 13 and a second light through hole 14 which are perpendicular to each other are arranged on the spherical surface of the integrating sphere 12, the second light through hole 14 is connected with one end of a U-shaped sleeve 17, the other end of the sleeve 17 is provided with a small-hole diaphragm 110, the small-hole diaphragm 110 is fixedly connected with the sleeve 17 through a stop lock 19, an attenuator 15 is arranged in the sleeve 17, a first flat mirror 16 and a second flat mirror 18 are sequentially arranged at a bent part in the sleeve 17 along the light path direction, a beam splitter prism 111 deflects the light output by the small-hole diaphragm 110 and the first light through hole 13 to a flat reflector 112, two parallel lights with a certain angle difference and different brightness are output by two reflections of the flat reflector 112 and an off-axis parabolic mirror 113, rather than a single parallel light, wherein one beam simulates, another beam of radiation simulating a star; the attenuator 15 attenuates the optical signal output from the second light passing hole 14, the attenuation coefficient is set according to the brightness ratio of the star-planet, and the attenuation coefficient of the attenuator 15 is adjusted to simulate the brightness difference of the star-planet. The two beams of light after passing through the beam splitter prism 111 are reflected twice by the plane mirror 112 and the off-axis parabolic mirror 113 respectively, and the twice reflection type is adopted to convert the light rays so as to reduce the volume of the equipment and eliminate chromatic aberration. Under the general off-axis use condition of the traditional spherical mirror, spherical aberration and astigmatism exist, which are important reasons causing the low resolution of the optical splitter, and the off-axis parabolic mirror mode is adopted, so that the aberrations can be completely eliminated in principle, and high resolution can be realized in an optical instrument with short focal distance.
Two beams of parallel light with small angle difference simulated by the system are distinguished and guaranteed by the difference of incident angles of light emitted by the first light through hole 13 and light emitted by the small-hole diaphragm 110 entering the light splitting prism 111, angles of the two beams of light entering the light splitting prism 111 need to be designed according to requirements, and in order to effectively simulate the angle difference of planet-star radiation signals, the angle difference of the light emitted by the first light through hole 13 and the angle difference of the light emitted by the small-hole diaphragm 110 entering the light splitting prism 111 is smaller than 1 arc second. The first plane mirror 16 and the second plane mirror 18 are used for turning the light path, so that the light enters the aperture diaphragm 110, and the included angle between the two parallel lights can be adjusted.
This light source provides the input for test system, and this input contains the very little two bunches of parallel light of contained angle, when adopting single subaperture formation of image, can't distinguish two bunches of parallel light, through synthetic aperture formation of image, the combination of a plurality of subapertures has promptly improved the angular resolution who forms images to distinguish two bunches of parallel light. In other words, the star-planet light source simulator 1 is an optical device essential for verifying synthetic aperture imaging. In addition, the star-planet light source simulator 1 of the invention can be used for simulating the light source of the out-of-system planet system, and can also be popularized to the detection of some existing optical instruments, such as different reticles are matched, and a micrometer lens or a microscope system is matched, so that the focal length, the discrimination rate and other imaging quality of a lens or a lens group can be measured, a plane reflector is placed on a workpiece which moves linearly, and the straightness of the workpiece is detected through a Gauss eyepiece on a collimator.
The controllable aperture array 2 is used for receiving the optical signal generated by the star-planet light source simulator 1 and comprises a plurality of individually controlled sub apertures; the controllable aperture array 2 receives a control instruction of the data processing module 5, sequentially enables different sub-aperture combinations to be in a working state, generates geometric arrangement of the different sub-aperture combinations, simulates the motion situation of the sub-apertures of the space satellite, and performs equivalence on motion.
The controllable aperture array 2 adopts a liquid crystal array, the liquid crystal array comprises a plurality of liquid crystal units 21, the sub apertures are the liquid crystal units 21, two electrodes of each liquid crystal unit 21 are powered on or powered off according to a control instruction received by the controllable aperture array 2, the electric field effect of liquid crystal molecule twisted nematic is caused by the driving of an electric field between two electrodes of each liquid crystal unit 21 so as to achieve the function of controlling the transmission or shielding of a light source, and when the two electrodes of the liquid crystal unit 21 are not powered, an optical signal from the star-planet light source simulator 1 forms a complete light ray penetrating path through the controllable aperture array 2; once the two electrodes of the liquid crystal cell 21 are powered on, the liquid crystal molecules are no longer arranged in a normal manner due to the influence of the external voltage, so that light cannot pass through the liquid crystal cell, and the on-off control of the incident light signal is realized.
The liquid crystal cells 21 in the liquid crystal array take a hexagonal or circular shape, as shown in fig. 3a-3 b; the hexagonal design is considered from the perspective of reducing the wasted area, the circular design is considered from the perspective of simple processing, the effective area of the controllable aperture array 2 is equal to the light collecting area (the area is recorded as a) of the focusing imaging module 3, in order to effectively simulate the sub-aperture movement, the area of each hexagonal unit or circular liquid crystal unit 21 in the crystal oscillator array should be selected to be a proper size, the size of the liquid crystal unit 21 which is too large enables the selectable aperture combinations to be few, the influence of the space coverage characteristic on the synthetic aperture imaging cannot be effectively verified, the size of the liquid crystal unit 21 which is too small can only cover a small part of space, the light ratio which is transmitted by each liquid crystal unit 21 is small, the leaked stray light can influence, and the synthetic aperture imaging is not facilitated. In summary, the areas of the liquid crystal cells 21 selected in the present invention are 1/1000 to 1/16 of the light collecting area a.
The focusing imaging module 3 is used for converging the optical signals output by the controllable aperture array 2 and sending the optical signals to the microscopic imaging module 4; the focusing imaging module 3 adopts a convex lens, the processing error requirement of the surface type is controlled within 1/10 wavelength to meet the requirement of the common phase interference condition, and the lenses for optical interference imaging need special polishing and are ensured by the processing precision.
In order to avoid extra errors caused by surface type difference in a multi-mirror system, only one group of focusing imaging modules is adopted, the system errors are effectively controlled under the condition of ensuring the surface shape precision, the extra errors caused by the surface type difference in the multi-mirror system are avoided, and sufficient allowance is left for other environment error simulation and interference imaging method verification. The system errors mainly include surface type processing errors, motion introduction errors and environmental factor introduction errors (such as expansion with heat and contraction with cold), and when the multi-group split focusing imaging module is adopted, because interference imaging needs to be controlled at 1/10 wavelength level, the multiple groups of lenses are required to have consistent processing precision (all the lenses need to be controlled at 1/10 wavelength level, the processing cost is extremely high, generally hundreds of thousands or even millions of lenses are unequal), great challenges are brought to phase difference control of the multi-group split focusing imaging module, and otherwise, the interference imaging cannot be realized because the phase difference is not uniform. The invention introduces the equivalent motion and only adopts a group of focusing imaging modules, so that when the optical lens is processed, only the surface type precision of a single lens is ensured, the technical cost and the economic cost of interference imaging are greatly reduced, the pressure of optical compensation is reduced, and enough margin can be provided for the simulation of environmental error and the verification of an interference imaging algorithm.
And the microscopic imaging module 4 is used for generating and amplifying the interference fringe signal and sending the interference fringe signal to the data processing module 5.
And the data processing module 5 is used for recording interference fringes each time and controlling the controllable aperture array 2 to execute on and off of next sub-aperture combination so as to simulate baseline change, and when the baseline change is enough to carry out imaging UV coverage, the data processing module 5 carries out imaging calculation according to the recorded interference fringes so as to reconstruct image information of the star-planet light source.
In spatial synthetic aperture optical interference imaging, it is required to change the geometrical arrangement of the sub-apertures, i.e. the change of the relative positions of the sub-apertures, given the number of sub-apertures, to achieve spatial frequency coverage and obtain better interference images. In order to realize optimal coverage, the data processing module 5 adopts an FPGA + DSP combined framework, stores geometric arrangements of different sub-aperture combinations to generate a control instruction, and sends the control instruction to the controllable aperture array 2 according to certain exposure time to control the on and off of the corresponding sub-aperture combination, wherein the exposure time is determined according to the detected brightness of a target source; an "on" liquid crystal cell 21 indicates that the corresponding sub-aperture is active, whereas an "off" liquid crystal cell 21 indicates that the corresponding sub-aperture is inactive. And generating corresponding sub-aperture geometric arrangement according to the above to realize equivalent sub-aperture spatial motion. According to the command on/off, each on/off may correspond to a different liquid crystal cell 21. The data processing module 5 adopts an FPGA + DSP combined framework as real-time information processing.
The controllable aperture array 2, the focusing imaging module 3 and the microscopic imaging module 4 are all installed in a vacuum optical darkroom 6, a vacuum sealing window 61 is arranged on the vacuum optical darkroom 6, an optical signal output by the fixed star-planet light source simulator 1 is allowed to penetrate and be transmitted to the controllable aperture array 2, the microscopic imaging module 4 is connected with the data processing module 5 through a second vacuum sealing joint 63, and the data processing module 5 is connected with the controllable aperture array 2 through a first vacuum sealing joint 62. The vacuum optical darkroom 6 is used for shielding the influence of external environment light; the star-planet light source simulator 1, the vacuum optical darkroom 6 and the data processing module 5 are all arranged on a vibration reduction table 7, and the vibration reduction table 7 is used for providing a uniform spatial reference for the whole system so as to eliminate errors introduced to measurement by different spatial references.
The working principle is as follows: the light source 11 generates ultraviolet light, visible light or infrared light, the ultraviolet light, the visible light or the infrared light is uniformly diffused and reflected by the integrating sphere 12, uniform light intensity distribution is formed on the spherical surface, the diffused and reflected light is respectively output through the first light through hole 13 and the second light through hole 14, the light output through the second light through hole 14 enters the small hole diaphragm 110 after being attenuated by the attenuator 15, emergent light is formed, the first plane mirror 16 and the second plane mirror 18 are fixed at the inner corner of the sleeve 17 and are used for turning the light path, so that the light is transmitted along the sleeve 17 and then enters the small hole diaphragm 110; the beam splitter prism 111 refracts the light output by the pinhole diaphragm 110 and the first light passing hole 13 to the plane reflector 112, and outputs two beams of parallel light with a certain included angle and different brightness after twice reflection by the plane reflector 112 and the off-axis parabolic mirror 113; two beams of parallel light are emitted to the controllable aperture array 2, the controllable aperture array 2 receives a control instruction of the data processing module 5, different sub-aperture combinations are sequentially in a working state, geometric arrangement of the different sub-aperture combinations is generated, the motion situation of the sub-apertures of the space satellite is simulated, and the motion is equivalent; the focusing imaging module 3 converges the optical signal output by the controllable aperture array 2 and sends the optical signal to the microscopic imaging module 4; the microscopic imaging module 4 generates and amplifies interference fringe signals and sends the interference fringe signals to the data processing module 5; the data processing module 5 records interference fringes and controls the controllable aperture array 2 to execute on and off of next sub-aperture combination so as to simulate baseline change, and when the baseline change is enough to carry out imaging UV coverage, the data processing module 5 carries out imaging calculation according to the recorded interference fringes.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (10)
1. An optical synthetic aperture imaging test system for extrasystematic planet detection is characterized by comprising
The star-planet light source simulator (1) is used for outputting two beams of parallel light with certain angle difference and different brightness and simulating light signals generated by the outer star and the planet;
a controllable aperture array (2) for receiving an optical signal generated by the star-planet light source simulator (1), comprising a plurality of individually controlled sub-apertures;
the focusing imaging module (3) is used for converging the optical signals output by the controllable aperture array (2) and sending the optical signals to the microscopic imaging module (4);
the microscopic imaging module (4) is used for generating and amplifying interference fringe signals and sending the interference fringe signals to the data processing module (5);
and the data processing module (5) is used for recording interference fringes and controlling the controllable aperture array (2) to execute on and off of next sub-aperture combination so as to simulate baseline change, and when the baseline change is enough for imaging UV coverage, imaging calculation is carried out according to the recorded interference fringes so as to reconstruct image information of the star-planet light source.
2. The optical synthetic aperture imaging test system for extrasystematic planetary exploration, as set forth in claim 1, characterized in that the data processing module (5) adopts an FPGA + DSP combined architecture, stores geometrical arrangements of different subaperture combinations in advance and generates a control command, and sends the control command to the controllable aperture array (2) according to a certain exposure time to control on and off of the corresponding subaperture combination; the exposure time is determined according to the detected brightness of the target source.
3. The optical synthetic aperture imaging test system for extrasystole detection according to claim 2, characterized in that the controllable aperture array (2) adopts a liquid crystal array, the liquid crystal array comprises a plurality of liquid crystal units (21), the sub-apertures are liquid crystal units (21), and two electrodes of each liquid crystal unit (21) are powered on or powered off according to a control command received by the controllable aperture array (2).
4. The SAR imaging test system for extra-system planetary detection as claimed in claim 3, wherein the liquid crystal cells (21) in the liquid crystal array are hexagonal or circular.
5. The optical synthetic aperture imaging test system for extrasystematic planet detection according to claim 1, wherein the star-planet light source simulator (1) comprises a light source (11), the light source (11) is arranged at the center of the integrating sphere (12), a first light through hole (13) and a second light through hole (14) which are perpendicular to each other are arranged on the spherical surface of the integrating sphere (12), the second light through hole (14) is connected with one end of a U-shaped sleeve (17), a small-hole diaphragm (110) is arranged at the other end of the sleeve (17), an attenuator (15) is arranged in the sleeve (17), a first plane mirror (16) and a second plane mirror (18) are sequentially arranged in the sleeve (17) at a bending position along the light path direction, a light splitting prism (111) is used for deflecting light output by the small-hole diaphragm (110) and the first light through hole (13) to the plane mirror (112), and the light is reflected twice by the plane mirror (112) and an off-axis parabolic mirror (113), two beams of parallel light with certain angle difference and different brightness are output.
6. The SAR imaging test system for extrasystole detection as claimed in claim 5, wherein the angle difference between the light from the first light passing hole (13) and the light from the aperture diaphragm (110) entering the beam splitter prism (111) is less than 1 second.
7. The SAR imaging test system for extra-planetary detection as claimed in claim 5, wherein the aperture diaphragm (110) is fixedly connected to the sleeve (17) by a locking lock (19).
8. The system of claim 1, wherein the effective area of the controllable aperture array (2) is equal to the collection area of the focusing imaging module (3), and the area of each sub-aperture is 1/1000 to 1/16 of the collection area.
9. The optical synthetic aperture imaging test system for extrasystole detection according to claim 1, characterized in that the focusing imaging module (3) uses convex lens, and the processing error of the surface shape is controlled within 1/10 wavelength.
10. The optical synthetic aperture imaging test system for extrasystematic planet detection according to any one of claims 1 to 9, wherein the controllable aperture array (2), the focusing imaging module (3) and the microscopic imaging module (4) are all installed in a vacuum optical darkroom (6), a vacuum sealed window (61) is arranged on the vacuum optical darkroom (6) to allow an optical signal output by the star-planet light source simulator (1) to transmit and emit to the controllable aperture array (2), the microscopic imaging module (4) is connected with the data processing module (5) through a second vacuum sealed joint (63), and the data processing module (5) is connected with the controllable aperture array (2) through a first vacuum sealed joint (62); the star-planet light source simulator (1), the vacuum optical darkroom (6) and the data processing module (5) are all arranged on the vibration reduction table (7).
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