CN107167998B - Space dual-waveband composite dynamic scene projection simulation system - Google Patents

Space dual-waveband composite dynamic scene projection simulation system Download PDF

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CN107167998B
CN107167998B CN201710517056.8A CN201710517056A CN107167998B CN 107167998 B CN107167998 B CN 107167998B CN 201710517056 A CN201710517056 A CN 201710517056A CN 107167998 B CN107167998 B CN 107167998B
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visible light
short
wave infrared
target
dmd
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CN107167998A (en
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夏鲁瑞
崔文楠
孙浩
李纪莲
张涛
张占月
杨雪榕
胡敏
肖龙龙
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Shanghai Institute of Technical Physics of CAS
PLA Equipment College
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Shanghai Institute of Technical Physics of CAS
PLA Equipment College
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    • G—PHYSICS
    • G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
    • G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
    • G03B21/00—Projectors or projection-type viewers; Accessories therefor
    • G03B21/14—Details
    • G03B21/20—Lamp housings
    • G03B21/208—Homogenising, shaping of the illumination light
    • G—PHYSICS
    • G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
    • G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
    • G03B21/00—Projectors or projection-type viewers; Accessories therefor
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects

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  • Engineering & Computer Science (AREA)
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  • Theoretical Computer Science (AREA)
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Abstract

The invention provides a space two-waveband composite dynamic scene projection simulation system, which comprises a visible light simulation unit, a short wave infrared simulation unit and a dichroic filter, wherein the visible light simulation unit comprises: the visible light simulation unit comprises a visible light source, a visible light DMD device and a visible light projection device which are arranged in sequence; the short-wave infrared simulation unit comprises a short-wave infrared light source, a short-wave infrared DMD device and a short-wave infrared projection device which are sequentially arranged, and the visible light DMD device and the short-wave infrared DMD device are connected with a driving device; the dichroic filter is arranged between the visible light projection device and the short wave infrared projection device. The invention can simulate the radiation and motion characteristics of satellites in different orbits and different postures observing a target, projects the optical load in a dynamic scene mode, is used for verifying the performance of the satellite load for detecting and tracking a space target on the ground, solves the problem of high cost of an on-orbit test, and improves the technical maturity of the satellite load.

Description

Space dual-waveband composite dynamic scene projection simulation system
Technical Field
The invention mainly relates to the technical field of semi-physical simulation of low-orbit satellite optical detection target scenes, in particular to a space two-waveband composite dynamic scene projection simulation system.
Background
In the prior art, in order to verify the functions of searching, capturing, tracking and measuring a target by a low-orbit satellite photoelectric detection load and test the function and partial performance of the photoelectric detection load, an outfield flight test is usually required, the resource consumption is high, the system development cycle is long, and the development cost is high.
Therefore, how to perform the optical detection semi-physical simulation test of the low-orbit satellite in a controlled environment in a laboratory, simulate various test environments and detection scenes, verify the technical scheme of the photoelectric detection tracking system, find design defects and hidden dangers of the system in time, make up for the deficiency of an outfield flight test, and are key problems to be solved urgently by technical personnel in the field.
Disclosure of Invention
In view of this, the present invention provides a spatial two-band composite dynamic scene projection simulation system, which can be used to evaluate the performance of a photoelectric detection tracking system and solve the defects of large resource consumption and long development cycle in the prior art.
The invention relates to a space two-waveband composite dynamic scene projection simulation system, which comprises a visible light simulation unit, a short wave infrared simulation unit and a dichroic filter, wherein:
the visible light simulation unit comprises a visible light source, a visible light DMD device and a visible light projection device which are sequentially arranged;
the short-wave infrared simulation unit comprises a short-wave infrared light source, a short-wave infrared DMD device and a short-wave infrared projection device which are sequentially arranged, and the visible light DMD device and the short-wave infrared DMD device are connected with a driving device;
the dichroic filter is disposed between the visible light projection device and the short wave infrared projection device.
Further, the simulation system further includes:
a visible light turning device disposed between the visible light source and the visible light DMD device;
the short wave infrared steering device is arranged between the short wave infrared light source and the short wave infrared DMD device.
Further, the simulation system further includes:
a first light unifying means disposed between the visible light source and the visible light turning means;
and the second dodging device is arranged between the short-wave infrared light source and the short-wave infrared steering device.
Furthermore, the first light homogenizing device and the second light homogenizing device both comprise an ellipsoid reflection bowl and an integral square rod, the corresponding light source is placed at a first focus in the ellipsoid reflection bowl, light emitted by the light source is converged at a second focus through reflection of the ellipsoid reflection bowl, and the integral square rod is arranged at the second focus.
Furthermore, the visible light source and the short-wave infrared light source both adopt short-arc xenon lamps.
Further, the dichroic filter is arranged such that it is reflective in the visible wavelength band and transmissive in the short wavelength infrared band.
Furthermore, the simulation system further comprises an FPGA control circuit board, the FPGA control circuit board is connected with an upper computer and a DDC4100 chip, the DDC4100 chip is connected with two DAD2000 chips, and the two DAD2000 chips are respectively used for controlling the visible light DMD device and the short wave infrared DMD device.
Further, the simulation system further comprises an FIFO chip and a DDR3 chip, the FIFO chip is used for buffering data issued by the upper computer, and the FPGA control circuit board reads the data in the FIFO chip and stores the data in the DDR3 chip.
Further, the upper computer establishes a simulation scene of visible light according to the earth background, the star background, the motion characteristic of the target and the reflection characteristic of the target in the field of view.
Further, the upper computer establishes a short-wave infrared simulation scene according to the earth background in the field of view, the motion characteristic of the target and the radiation characteristic of the target.
The space two-waveband composite dynamic scene projection simulation system establishes a visible light and short wave infrared simulation scene by utilizing input satellite orbit data and motion and radiation data of a target, converts a digital scene into optical scenes of different wavebands by utilizing visible light and short wave infrared simulation devices respectively, and converts the visible light and short wave infrared optical scenes into a composite scene containing information of two wavebands by utilizing a dichroic filter.
The invention can simulate the dynamic scene observed by the satellite loads with different orbits and different attitudes, can simulate the background characteristics of stars, earth and the like in a large field of view, can simulate the morphological characteristics, the motion characteristics and the relative radiation characteristics of multiple targets under the complex background condition, can simultaneously simulate the scene of the visible light and short wave infrared dual-band combination of the targets and the background, can simulate the relative attenuation characteristics of the atmosphere to the targets with different wave bands and different heights, is used for verifying the performance of the satellite loads for detecting and tracking the space targets on the ground, solves the problem of high cost of the on-orbit test, and improves the technical maturity of the satellite loads.
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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, and 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 these drawings without creative efforts.
FIG. 1 is a schematic diagram of a spatial two-band composite dynamic scene projection simulation system according to an embodiment of the present invention;
FIG. 2 is an optical path diagram of an optical system in accordance with an embodiment of the present invention;
FIG. 3 is a hardware block diagram of an electronic system according to an embodiment of the invention;
FIG. 4 is a flow chart of creating a simulation scenario according to an embodiment of the present invention.
Wherein the reference numerals are as follows:
1-visible light simulation unit 11-visible light source
12-visible light DMD device 13-visible light projection device
14-visible light steering gear 2-shortwave infrared simulation unit
21-shortwave infrared light source 22-shortwave infrared DMD device
24-shortwave infrared steering device of 23-shortwave infrared projection device
3-drive 4-dichroic filter
5-upper computer 6-projection screen
7-ellipsoidal reflecting bowl 8-integral square rod.
Detailed Description
The following provides a more detailed description of the present invention. The above and other objects, features and advantages of the present invention will be apparent to those skilled in the art from the detailed description of the present invention.
Fig. 1 is a schematic structural diagram of a spatial two-band composite dynamic scene projection simulation system according to an embodiment of the present invention, where the embodiment includes a visible light simulation unit 1, a short-wave infrared simulation unit 2, and a dichroic filter 4.
The visible light simulation unit 1 comprises a visible light source 11, a visible light DMD device 12 and a visible light projection device 13 which are sequentially arranged; the short-wave infrared simulation unit 2 comprises a short-wave infrared light source 21, a short-wave infrared DMD device 22 and a short-wave infrared projection device 23 which are sequentially arranged, and the visible light DMD device 12 and the short-wave infrared DMD device 22 are connected with the driving device 3; the dichroic filter 4 is disposed between the visible light projection device 13 and the short wave infrared projection device 23.
The visible light simulation wave band in the invention: 400-800 nm; short wave infrared analog band: 1-2.3 mu m; horizontal field angle: 20 ° ± 1 °; vertical field angle: 10 ° ± 1 °; working distance: 2.5m +/-0.2 m; optical distortion: less than or equal to 5 percent; illuminance nonuniformity: less than or equal to 10 percent; DMD pixel Scale: 1920 × 1080; DMD pixel size: 10.8 mu m; frame frequency: 200 plus or minus 10 Hz; gray scale: 256 stages; the optical composite precision of visible light simulation and infrared simulation at the central view field is less than or equal to 3 pixels; the continuous working time of the simulation system is not less than 5 hours.
The visible light DMD device 12 and the short wave infrared DMD device 22 can adopt a digital Micromirror device DMD (digital Micromirror device) of TI company, the scale of the devices is 1920 x 1080, and the pixel size is 10.8 mu m. The DMD display portion is composed of an array of micromirrors, each of which can independently control a respective deflection state.
The micromirrors of the DMD are statically in the "on" state and the "off" state, and the DMD displays a 1-bit binary image. To display an 8-bit gray scale image, the DMD is gray scale modulated. The basic principle of gray scale modulation is that the detectors have integration time, and the period of displaying the gray scale image by the DMD is controlled to be smaller than the integration time of the detectors, so that the detectors have the characteristic of 'visual persistence' on the gray scale image displayed by the DMD.
In addition, the preferred embodiment also includes a visible light redirecting device 14 and a short wave infrared redirecting device 24. The visible light turning device 14 is arranged between the visible light source 11 and the visible light DMD device 12; the short-wave infrared steering device 24 is arranged between the short-wave infrared light source 21 and the short-wave infrared DMD device 22, and can transmit light to the corresponding DMD device through the turning of the reflector.
Further, the space two-waveband composite dynamic scene projection simulation system further comprises a first light homogenizing device and a second light homogenizing device. The first dodging device is arranged between the visible light source 11 and the visible light turning device 14; the second dodging device is arranged between the short-wave infrared light source 21 and the short-wave infrared steering device 24, and therefore projection of the system is uniform.
The visible light source 11 and the short-wave infrared light source 21 can adopt short-arc xenon lamps. The short-arc xenon lamp emits light by utilizing the discharge between arcs of xenon and can emit continuous spectrum white light which is very close to natural light. The first light homogenizing device and the second light homogenizing device both comprise an ellipsoid reflection bowl 7 and an integral square rod 8, corresponding light sources are placed at a first focus in the ellipsoid reflection bowl 7, light emitted by the light sources is converged at a second focus through reflection of the ellipsoid reflection bowl 7, and the integral square rod 8 is arranged at the second focus. The square rod illumination system is simple in structure, low in manufacturing cost, and capable of converting a round light beam into a rectangular light beam efficiently and uniformly, so that light converged by the focus is guided out by the integrating square rod 8, and light emitted by the xenon lamp light source is uniformly distributed on the other end face of the integrating square rod 8.
The steering device can adopt a light path form similar to a double telecentric light path structure, the incident light principal ray of each view field is parallel to the axis of the integrating square rod 8, and the focal plane of the emergent light forms an angle of 24 degrees with the optical axis. The optical system ensures that the light beams of the emergent light principal rays perpendicularly incident to each field of view on the DMD reflector have the same incident angle, so that the chip surface has better illumination uniformity no matter in a bright state or a dark state. The factors such as the size of a light beam at the output end of the integrating square rod 8, the size of a DMD chip, the F number of a projection lens and the like are considered for the setting of the index of the steering device, and the phase difference of the system mainly controls the color difference, so that the phenomenon that the color of an image has large deviation when the transmission distance is large is avoided.
For the dichroic filter 4, the working wavelength (0.4-2.3 μm) covers the whole visible light and short wave infrared band, and the optical substrate materials selectable in the band comprise infrared quartz JGS-3, sapphire, calcium fluoride and the like. Since the size of the dichroic filter 4 reaches approximately 200mm x 200mm, JGS-3 is a reasonable choice considering the processing difficulty, the physical and chemical stability of the material, the material and the processing cost, and other factors.
In the visible and short wave infrared bands, the commonly used optical thin film materials are mainly metal and semiconductor oxides. For low refractive index materials, SiO2Are widely used due to their good optical properties and process stability; high refractive index material selected from TiO2，Nb2O5，Ta2O5Etc. TiO2Ta, which affects optical efficiency due to its greater absorption in the visible near-ultraviolet band2O5The film is not efficient because of the relatively low refractive index, and Nb2O5Is a better choice.
In addition, the dichroic filter 4 requires spectral separation of a visible light band (0.4 to 0.8 μm) and a short wave infrared band (1.0 to 2.3 μm), and the working angle of the dichroic filter 4 is 45 +/-10 degrees. According to the analysis of the wave band width and the transition region between the two wave bands, the visible light wave band reflection can be realized by 'reflecting visible light and transmitting infrared', and the scheme of the short wave infrared wave band transmission is more excellent.
The visible light projection device 13 and the short wave infrared projection device 23 adopt high-precision projection lenses. According to the technical index requirements, the field angle of the visible light and infrared projection lens is calculated to be 21 degrees multiplied by 11.7 degrees according to the projection ratio of 2.7 and the working distance of 3000mm, and the focal length is calculated to be f =56.58mm according to the specification of a DMD chip, 1920 multiplied by 1080 and the unit size of 10.8 μm. The projection lens is similar to a common photographic lens in terms of optical design method, optical structure and optical performance, and in terms of use, the position of an object image of the photographic lens is equivalently inverted, so that the image is enlarged and displayed.
When the projection lens is designed, the F number of the system is given by considering the DMD chip parameters and the modulation transfer function of the projection optical lens. According to the DMD chip in the on state of +12 degrees and the off state of-12 degrees, the F number of the projection device is calculated to be larger than 2.4, and if the F number is smaller than 2.4, the light of the light source in the flat state of 0 degree and the light of the light source in the off state of-12 degrees can still be transmitted to the projection screen 6 through the projection lens. According to the experience of the optoelectronic system for aerospace application, the overall optical transfer function value of the optoelectronic system is more than 0.2-0.3, so that the optical transfer function value of the optical system is ensured to be more than 0.4 during the design of the optical system. The F-numbers of the visible light projection device 13 and the short-wave infrared projection device 23 are set to F =4 in accordance with the relationship between the system F-number and the theoretical optical function limit of the system.
In addition, the design of the projection objective adopts an image space telecentric optical path, so that the uniformity of the illumination of the image surface of the system is ensured, meanwhile, the distortion requirement of the projection objective is very high, and the distortion of the system is generally within 2% in order to ensure that the deformation of the projected image is small. The projection lens can uniformly transmit the light of the light source reflected from the DMD chip to the screen by adopting the mode, so that a good image effect is formed.
Fig. 3 is a hardware block diagram of an electronic system according to an embodiment of the present invention, which includes an FPGA control circuit board, where the FPGA control circuit board is connected to the upper computer 5 and the DDC4100 chip, the DDC4100 chip is connected to two DAD2000 chips, and the two DAD2000 chips are respectively used to control the visible light DMD device 12 and the short wave infrared DMD device 22. In addition, the data transmission device further comprises an FIFO chip and a DDR3 chip, the FIFO chip is used for buffering data issued by the upper computer 5, and the FPGA control circuit board reads the data in the FIFO chip and stores the data in the DDR3 chip.
The FPGA control circuit board adopts a PCIE high-speed interface to realize high-speed data interaction with the upper computer 5, realizes control over the digital micromirror device through an LVDS interface, and is configured with DDR3 for high-speed storage of data information. The upper computer 5 transmits the control information and the image data to the FPGA control circuit board through the PCIE high-speed bus, the FPGA control circuit board receives and stores the data into the DDR3, and after the data are processed, DMD control and data signals are generated to further control the DMD to finish high-frame-frequency display of the image.
The FPGA selects a Xilinx Virtex-6 chip, is mainly responsible for hardware management work of a whole system circuit, and outputs DMD control and data information to a DDC4100 chip; the DDC4100 chip is responsible for generating initialization and control signals of the DAD2000 chip and the DMD, and loading data to the DMD through a high-speed LVDS interface; the 2 DAD2000 chips are used for realizing the power management and reset functions of the DMD.
The FPGA system management program mainly completes system hardware resource configuration and initialization, PCIE bus data receiving, DDR3 data reading and writing and DDC4100 control.
After the system is powered on/reset, the Virtex-6 FPGA is reset, a command is sent to the DDC4100, the DDC4100 is controlled to complete initialization operation, and the DMD is ensured to work in a normal state; after the system initialization is completed, sending a command to the upper computer 5, and then waiting for the upper computer 5 to download data to the FPGA; the FIFO is used for buffering data issued by the upper computer 5, the upper computer 5 sends image data to the FPGA at regular time, the FPGA receives and stores the image data to the FIFO, and meanwhile, the FPGA reads the data in the FIFO and stores the data in the DDR 3; after the upper computer 5 starts to send data, the control flow of the DMD is started, the FPGA displays a PWM modulation time sequence according to the designed high-frame-frequency DMD, and the DMD image is updated in a timing control mode.
The shortest time for loading a 1024 × 768-scale image by the DMD is 30.72 μ s, and the shortest time is used as the time base of PWM gray-scale modulation. In order to improve the system display frame frequency, the time base of the PWM needs to be reduced, and 8 μ s is taken as the base, so that the PWM method is improved, and the display frame frequency for displaying the 8-bit gray level image after improvement is 400 Hz.
The space dual-band composite dynamic scene projection simulation system of the embodiment of the invention can be arranged in a box body to form a box-type structure, and also can comprise a light absorption plate, a heat dissipation unit and the like.
The upper computer 5 can calculate the reflection characteristic of a visible light band target and the radiation characteristic of a short wave infrared band target. When calculating the characteristics of the stars, the characteristics of the stars comprise the movement of the stars, the spatial distribution of the stars, the stars of the stars and the like, and a characteristic model of the stars is established. The implementation process of the star simulation is as follows: the quantity of fixed stars to be simulated and the position and the gray level of each fixed star are solved through the input parameters, a background fixed star simulation scene is generated, and a visible light background fixed star scene to be simulated is projected by utilizing the DMD micro-mirror array. The establishment of the simulation scene is to simulate the three-dimensional dynamic scene by utilizing the OpenGL technology on the basis of the calculation results of the motion characteristic and the radiation characteristic of the target and combining the background star characteristic and the earth background characteristic.
The simulation system main program operation platform is an Window7 version operation system; the simulation system software is developed by adopting a version above VC 6.0. In addition, the hardware using environment of the simulation system is as follows: a power supply: 220V +/-10% AC, 50Hz and current of 10A; working temperature: the temperature is between +15 and +35 ℃; relative humidity: < 70% (20 ℃).
FIG. 4 is a flow chart illustrating the creation of a simulation scenario according to an embodiment of the present invention. After the start, necessary initialization configuration is carried out, and satellite orbit data, satellite attitude data and target ballistic data are received in real time. The direction of the optical axis of the detection system can be calculated according to the orbit data and the attitude data of the satellite, and further an earth scene and a fixed star distribution scene in a field of view can be calculated. Meanwhile, the surface reflection characteristic of the target and the incident angle of the sun can be used for calculating the visible light reflection characteristic of the target, and the equivalent blackbody temperature and the specific radiance of the target can be used for calculating the short-wave infrared radiation characteristic of the target. The relative motion characteristic of the target in the field of view can be calculated according to the orbit data of the satellite and the ballistic data of the target.
The upper computer 5 can establish a simulation scene of visible light according to the earth background, the star background, the motion characteristic of the target and the reflection characteristic of the target in the field of view. The upper computer 5 can establish a short-wave infrared simulation scene according to the earth background in the field of view, the motion characteristic of the target and the radiation characteristic of the target. And then, synchronously processing the visible light simulation scene and the short wave infrared simulation scene, and transmitting the data of the visible light simulation scene and the short wave infrared simulation scene to a DMD drive board through a high-speed interface.
The embodiment of the invention can simulate the dynamic scene observed by the satellite loads with different orbits and different attitudes on the projection screen 6, can simulate the background characteristics of stars, earth and the like in a large view field range, can simulate the morphological characteristics, the motion characteristics and the relative radiation characteristics of multiple targets under a complex background condition, can simultaneously simulate the scene of visible light and short wave infrared dual-band composite of the targets and the background, can simulate the relative attenuation characteristics of the atmosphere to the targets with different wave bands and different heights, is used for verifying the performance of the satellite loads for detecting and tracking the space targets on the ground, solves the problem of high cost of an on-orbit test, improves the technical maturity of the satellite loads, can make up the defects of an outfield flight test, shortens the research and development period and saves the development expenditure.
It should also be understood that although the present invention has been clearly illustrated by the above embodiments, it will be apparent to those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined in the appended claims.

Claims (7)

1. The utility model provides a compound dynamic scene projection simulation system of space dual waveband which characterized in that, includes visible light emulation unit, shortwave infrared emulation unit and dichroic filter, wherein:
the visible light simulation unit comprises a visible light source, a visible light DMD device and a visible light projection device which are sequentially arranged;
the short-wave infrared simulation unit comprises a short-wave infrared light source, a short-wave infrared DMD device and a short-wave infrared projection device which are sequentially arranged, and the visible light DMD device and the short-wave infrared DMD device are connected with a driving device;
the visible light DMD device and the short wave infrared DMD device respectively convert a digital scene into visible light and short wave infrared optical scenes with different wave bands;
the dichroic filter is arranged between the visible light projection device and the short wave infrared projection device and converts a visible light and short wave infrared optical scene into a composite scene containing information of two wave bands;
the space dual-waveband composite dynamic scene projection simulation system further comprises an FPGA control circuit board, the FPGA control circuit board is connected with an upper computer and a DDC4100 chip, the DDC4100 chip is connected with two DAD2000 chips, and the two DAD2000 chips are respectively used for controlling the visible light DMD device and the short wave infrared DMD device;
the upper computer establishes a simulation scene of visible light according to the earth background, the fixed star background, the motion characteristic of the target and the reflection characteristic of the target in the field of view;
the upper computer establishes a short-wave infrared simulation scene according to the earth background in the field of view, the motion characteristic of the target and the radiation characteristic of the target;
the earth background and the star background in the field of view are obtained by calculating the direction of the optical axis of the detection system according to the satellite orbit data and the attitude data;
the motion characteristic of the target is calculated according to the orbit data of the satellite and the ballistic data of the target;
the reflection characteristic of the target is calculated by utilizing the surface reflection characteristic of the target and the incident angle of the sun;
calculating the radiation characteristic of the target by using the equivalent blackbody temperature and the specific radiance of the target;
and the satellite orbit data, the attitude data and the ballistic data of the target are received in real time by the space two-waveband composite dynamic scene projection simulation system.
2. The spatial dual band composite dynamic scene projection simulation system of claim 1, further comprising:
a visible light turning device disposed between the visible light source and the visible light DMD device;
the short wave infrared steering device is arranged between the short wave infrared light source and the short wave infrared DMD device.
3. The spatial dual band composite dynamic scene projection simulation system of claim 2, further comprising:
a first light unifying means disposed between the visible light source and the visible light turning means;
and the second dodging device is arranged between the short-wave infrared light source and the short-wave infrared steering device.
4. The spatial dual-band composite dynamic scene projection simulation system of claim 3, wherein the first light evening device and the second light evening device each comprise an ellipsoid reflection bowl and an integral square rod, the corresponding light source is disposed at a first focus in the ellipsoid reflection bowl, light emitted by the light source is converged at a second focus through reflection of the ellipsoid reflection bowl, and the integral square rod is disposed at the second focus.
5. The spatial two-band composite dynamic scene projection simulation system of claim 4, wherein the visible light source and the short wave infrared light source both use short arc xenon lamps.
6. The spatial dual band composite dynamic scene projection simulation system of any of claims 1-5, wherein the dichroic filters are configured to be reflective in the visible band and transmissive in the short wave infrared band.
7. The spatial dual-band composite dynamic scene projection simulation system according to claim 6, further comprising a FIFO chip and a DDR3 chip, wherein the FIFO chip is used for buffering data issued by the upper computer, and the FPGA control circuit board reads the data in the FIFO chip and stores the data in the DDR3 chip.
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