CN111854696A - High-reliability step-by-step picture type staring three-dimensional imaging space camera and implementation method thereof - Google Patents

High-reliability step-by-step picture type staring three-dimensional imaging space camera and implementation method thereof Download PDF

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CN111854696A
CN111854696A CN202010627003.3A CN202010627003A CN111854696A CN 111854696 A CN111854696 A CN 111854696A CN 202010627003 A CN202010627003 A CN 202010627003A CN 111854696 A CN111854696 A CN 111854696A
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imaging sensor
color imaging
cmos color
camera
assembly
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余国彬
刘恩海
周向东
赵汝进
刘光林
周黎
陈元培
曾骏哲
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Institute of Optics and Electronics of CAS
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Institute of Optics and Electronics of CAS
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C11/00—Photogrammetry or videogrammetry, e.g. stereogrammetry; Photographic surveying
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C11/00—Photogrammetry or videogrammetry, e.g. stereogrammetry; Photographic surveying
    • G01C11/02—Picture taking arrangements specially adapted for photogrammetry or photographic surveying, e.g. controlling overlapping of pictures

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Abstract

The invention discloses a high-reliability step-by-step picture type staring three-dimensional imaging space camera and an implementation method thereof, wherein the high-reliability step-by-step picture type staring three-dimensional imaging space camera comprises an optical component, a reference component, a CMOS (complementary metal oxide semiconductor) color imaging sensor component, a camera control electronics component and a camera supporting component; the key point is that for a space camera using a CMOS color imaging sensor, a camera integrated modular design technology and a step-frame staring design technology are introduced, high-quality and high-reliability step-frame staring three-dimensional imaging of the space camera in deep space remote sensing detection is realized, and the method has the advantages of small distortion, easy control of exposure time, high imaging quality and strong environmental adaptability, and meets the requirements of deep space remote sensing detection on the three-dimensional imaging space camera.

Description

High-reliability step-by-step picture type staring three-dimensional imaging space camera and implementation method thereof
Technical Field
The invention belongs to the technical field of deep space remote sensing detection photoelectric detection, and relates to a high-quality high-reliability step-by-step picture type staring three-dimensional imaging space camera for deep space remote sensing detection and an implementation method thereof.
Background
With the development of deep space exploration technology and the demand of deep space exploration tasks, the development trend of a payload (space camera) which is necessary for deep space exploration is as follows: with the continuous progress of the technology, the performance of the space camera is higher and higher, the space camera plays an important role in deep space exploration, and the number of the space cameras carried by the deep space exploration is more and more; the scientific targets borne by the space camera range from single to diversified, simple to complex; the deep space exploration space camera tends to be integrated, miniaturized and multifunctional, high in quality and reliability, so that the quality is reduced, wood is reduced, fuel is saved, and the service life of the deep space exploration camera is prolonged. Therefore, the development technology of the high-quality high-reliability step-by-step picture type three-dimensional imaging space camera is one of the key technologies for the development of the deep space exploration technology.
Disclosure of Invention
In view of the above, the main objective of the present invention is to provide a high-quality high-reliability step-and-frame staring stereo imaging space camera for deep space remote sensing detection and an implementation method thereof.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the invention provides a high-quality high-reliability step-by-step picture type staring three-dimensional imaging space camera for deep space remote sensing detection, which comprises an optical component, a reference component, a CMOS (complementary metal oxide semiconductor) color imaging sensor component, a camera control electronics component and a camera supporting component, wherein the reference component is arranged on the upper surface of the optical component; wherein:
the optical component is used for imaging a deep space target to be imaged on the CMOS color imaging sensor;
the reference assembly provides an installation reference for the camera;
the CMOS color imaging sensor component is used for photoelectric conversion, and converts an optical image acquired by the optical component into a corresponding electric signal so as to obtain a digital image;
the camera control electronics assembly is used for generating bias voltage of the CMOS color imaging sensor, generating a driving time sequence signal of the CMOS color imaging sensor, communicating with the CMOS color imaging sensor through the SPI, configuring and reading parameters of the CMOS color imaging sensor, receiving an image signal output by the CMOS color imaging sensor, analyzing and caching an image, performing automatic exposure calculation according to the image, controlling exposure, outputting an image data stream and engineering parameters according to a specified format, receiving a control command and the parameters, and feeding back a working state;
The camera supporting assembly is used for fixing the optical assembly, the reference assembly, the CMOS color imaging sensor assembly and the camera control electronic assembly, and mechanical characteristics of the camera are guaranteed.
In the above scheme, the CMOS color imaging sensor assembly includes a CMOS color imaging sensor base, a CMOS color imaging sensor board, and a CMOS color imaging sensor adjustment pad; wherein the content of the first and second substances,
the CMOS color imaging sensor base is used for fixing the CMOS color imaging sensor plate;
the CMOS color imaging sensor board is used for ensuring the flatness and the straightness of an imaging surface of the CMOS color imaging sensor;
the CMOS color imaging sensor adjusting pad is used for ensuring that the imaging surface of the CMOS color imaging sensor is parallel to the flatness reference of the CMOS color imaging sensor base.
In the above scheme, the CMOS color imaging sensor board includes a CMOS color imaging sensor circuit board and a CMOS color imaging sensor reinforcing plate; wherein the content of the first and second substances,
the CMOS color imaging sensor circuit board is used for welding a CMOS color imaging sensor;
the CMOS color imaging sensor reinforcing plate is used for reinforcing and fixing the CMOS color imaging sensor circuit board.
In the above scheme, the number of pixels of the CMOS color imaging sensor assembly is 4096 × 3072, the number of pixels of the CMOS color imaging sensor is 4096 while being perpendicular to the flight direction, and the number of pixels of the CMOS color imaging sensor is 3072 while being parallel to the flight direction.
In the above scheme, the optical assembly and the CMOS color imaging sensor assembly are combined in a modular design, so that the optical axis of the optical assembly is perpendicular to the imaging surface of the CMOS color imaging sensor assembly and the relative position is fixed.
In the scheme, the optical assembly, the CMOS color imaging sensor assembly and the camera supporting assembly are combined in a modularized mode, so that the number of pixels of a CMOS color imaging sensor of the CMOS color imaging sensor assembly is 4096, the pixels are perpendicular to the mounting surface of the camera supporting assembly, the number of pixels of the CMOS color imaging sensor is 3072, and the pixels are parallel to the mounting surface of the camera supporting assembly; the optical axis of the optical assembly is made perpendicular to the Z-direction of the camera support assembly and parallel to the X-direction and the Y-direction.
In the above solution, the X-direction, the Y-direction, and the Z-direction of the reference assembly are respectively parallel to the X-direction, the Y-direction, and the Z-direction of the camera support assembly.
In the above scheme, the color of the space camera is a standard RGB color, the spectral range is 430nm to 690nm, and the focal length: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm by 160mm by 180 mm.
The invention provides a method for realizing a high-quality high-reliability step-by-step picture type staring three-dimensional imaging space camera for deep space remote sensing detection, which is characterized in that the space camera comprises an optical component, a reference component, a CMOS (complementary metal oxide semiconductor) color imaging sensor component, a camera control electronic component and a camera supporting component; the color of the space camera is standard RGB color, the spectral range is 430 nm-690 nm, and the focal length is as follows: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm × 160mm × 180 mm; the implementation method comprises the following steps:
1) high-quality and high-reliability implementation method of space camera
Firstly, the high quality and high reliability of the space camera are realized through the modular design of a CMOS color imaging sensor board;
The CMOS color imaging sensor which passes the upgrading screening and the quality assurance is welded on a CMOS color imaging sensor circuit board, and then the CMOS color imaging sensor circuit board is fixed on a CMOS color imaging sensor reinforcing plate, so that the mechanical characteristics of the CMOS color imaging sensor are reinforced.
Realizing high quality and high reliability of the space camera by modular design of a CMOS color imaging sensor assembly;
fixing the CMOS color imaging sensor board on the CMOS color imaging sensor board through the CMOS color imaging sensor adjusting pad; the imaging surface of the CMOS color imaging sensor is ensured to be parallel to the flatness reference of the CMOS color imaging sensor base through the modular design, and the imaging pixel of the CMOS color imaging sensor is ensured to be parallel to the straightness reference of the CMOS color imaging sensor base.
Realizing the high quality and high reliability of the space camera through a modular combination design of an optical component and a CMOS color imaging sensor component;
the optical assembly is fixed on the CMOS color imaging sensor assembly, the imaging surface of the CMOS color imaging sensor assembly is ensured to be on the focal plane of the optical assembly through modular design, the optical axis of the optical assembly is perpendicular to the imaging surface of the CMOS color imaging sensor assembly and the relative position is fixed, the number of pixels of the CMOS color imaging sensor assembly is 4096, the number of pixels of the CMOS color imaging sensor assembly is 3072, the pixels of the CMOS color imaging sensor assembly are parallel to the mounting surface of the camera support assembly, and the optical axis of the optical assembly is perpendicular to the Z direction of the camera support assembly and is parallel to the X direction and the Y direction.
The high quality and high reliability of the space camera are realized through the modular combination design of the reference component and the camera supporting component;
the reference assembly is fixed on the camera support assembly, and the X direction, the Y direction and the Z direction of the reference assembly are respectively parallel to the X direction, the Y direction and the Z direction of the camera support assembly through modular design.
2) Implementation method of step-by-step frame type staring imaging of space camera
Firstly, realizing stepping imaging of the space camera by optimizing the time interval between two frames of images;
the stepping imaging is realized by optimizing the time interval, the exposure control module of the camera control electronics component optimizes and designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, and the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%.
Secondly, step-by-step frame type staring imaging of the space camera is realized by selecting a CMOS color imaging sensor;
the CMOS color imaging sensor of CMOSIS has color (R, G, B), effective pixel number of 4096 × 3072, pixel size of 5.5 μm × 5.5 μm, sensitivity of 4.64V/lux · s, and well-filled charge of 13500e -The dynamic range is 60dB, QE FF is 50% @550 nm.
Step-by-step frame staring imaging of the space camera is realized through the optimization design of the maximum exposure time;
the staring imaging is realized by optimally designing the maximum exposure time, the maximum exposure time for realizing the staring imaging is optimally designed according to the focal length of the optical system of the optical component, the pixel size of a CMOS color imaging sensor of the CMOS color imaging sensor component, the maximum tangential speed of the deep space remote sensing detector and the track height corresponding to the maximum tangential speed of the deep space remote sensing detector, and the image shift amount generated on the image surface by the maximum exposure time is not more than one third of pixel.
Fourthly, realizing the step-by-step picture type staring imaging of the space camera through the optimization design of the optical system parameters
The gaze imaging is achieved by optimally designing optical system parameters, the optical system parameters of the optical assembly being determined by:
Figure BDA0002566892600000041
wherein S isimageFor accumulating the number of electrons, phi, in a single picture element0The number density of solar photons is shown, and rho is a diffuse reflection coefficient; τ is the optical system transmittance; thetasIs the angle between the normal vector of the imaging plane and the sun, thetaoIs the angle between the normal vector of the imaging plane and the observer, F is the F number of the camera, B sIs the area of a single pixel, eta is the quantum efficiency, kappa is the fill factor, and t is the exposure time;
the optical system parameters of the optical component are that the wave band range is 430 nm-700 nm, the visual field is 53.1 degrees multiplied by 41.1 degrees, the focal length is 22.5mm, the F number is 5, and the transfer function MTF is more than 0.45;
3) method for realizing three-dimensional imaging of space camera
The three-dimensional imaging is realized by optimally designing the image overlapping rate of two images, and the exposure control module of the camera control electronics component optimally designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, so that the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%.
Compared with the prior art, the invention has the advantages that: the problem of space camera in deep space remote sensing detection stereo imaging is solved by utilizing the mature technology in the existing aerospace field. The high-quality high-reliability step-by-step picture type staring stereo imaging of the space camera in deep space remote sensing detection is achieved through the camera integrated modular design and the step-by-step picture type design innovativeness, the relative position fixing between the CMOS color imaging sensor and the optical assembly is achieved, the verticality error between the optical axis of the optical system and the CMOS color imaging sensor is not larger than 0.008mm, the parallelism (verticality) error between the pixel of the CMOS color imaging sensor and the mounting surface is not larger than 0.005mm, and the space camera has the high-quality high-reliability picture type stereo imaging function in deep space remote sensing detection. The space camera has the advantages of small distortion, easy control of exposure time, high imaging quality and strong environmental adaptability.
Drawings
FIG. 1 is a system composition schematic of a space camera of the present invention;
the figures are marked as: 11-an optical component, 12-a reference component, 13-a CMOS color imaging sensor component, 14-a camera control electronics component, 15-a camera support component;
FIG. 2 is a schematic diagram of a CMOS color imaging sensor assembly of the space camera of the present invention;
the figures are marked as: the device comprises a 21-CMOS color imaging sensor base, a 22-CMOS color imaging sensor plate and a 23-CMOS color imaging sensor adjusting pad;
FIG. 3 is a schematic diagram of a CMOS color imaging sensor board of the space camera of the present invention;
the figures are marked as: 31-CMOS color imaging sensor circuit board, 32-CMOS color imaging sensor reinforcing plate;
FIG. 4 is a CMOS color imaging sensor package design reference schematic for a space camera of the present invention;
FIG. 5 is a schematic view of step-and-frame imaging of the space camera of the present invention;
FIG. 6 is a schematic diagram of the modular design of the CMOS color imaging sensor assembly and the optical assembly of the space camera of the present invention;
the figures are marked as: 13-CMOS color imaging sensor component, 11-optical component;
FIG. 7 is a schematic view of the modular design of the fiducial assembly and camera support assembly of the space camera of the present invention;
FIG. 8 is a specific embodiment of the space camera of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The specific implementation indexes of the space camera provided by the invention are as follows:
1) color: standard RGB colors;
2) spectral range: 430 nm-690 nm;
3) focal length: 22.5 mm;
4) relative pore diameter: f/5;
5) visual field: 53.1 ° × 41.1 °;
6) ground resolution: 98m @400 km;
7) imaging width: 400km @400 km;
8) the number of effective pixels: 4096 × 3072;
9) weight: 3.5 kg;
10) power consumption: 19.72W;
11) envelope size: 278mm by 160mm by 180 mm.
The invention provides a high-quality high-reliability step-by-step picture type staring stereo imaging space camera for deep space remote sensing detection, which comprises an optical component 11, a reference component 12, a CMOS (complementary metal oxide semiconductor) color imaging sensor component 13, a camera control electronic component 14 and a camera supporting component 15, as shown in figure 1; wherein:
the optical assembly 11 is used for imaging a deep space target to be imaged on the CMOS color imaging sensor;
a fiducial component 12 providing a mounting fiducial for the camera;
a CMOS color imaging sensor module 13 for photoelectric conversion, which converts the optical image acquired by the optical module 11 into a corresponding electrical signal, thereby obtaining a digital image;
The camera control electronics component 14 is used for generating bias voltage of the CMOS color imaging sensor, generating a driving time sequence signal of the CMOS color imaging sensor, communicating with the CMOS color imaging sensor through the SPI, configuring and reading parameters of the CMOS color imaging sensor, receiving an image signal output by the CMOS color imaging sensor, analyzing and caching an image, performing automatic exposure calculation according to the image, controlling exposure, outputting an image data stream and engineering parameters according to a specified format, receiving a control instruction and the parameters, and feeding back a working state;
and the camera supporting assembly 15 is used for fixing the optical assembly 11, the reference assembly 12, the CMOS color imaging sensor assembly 13 and the camera control electronics assembly 14 and ensuring the mechanical characteristics of the camera.
As shown in fig. 2 and 4, the CMOS color imaging sensor module 13 includes a CMOS color imaging sensor base 21, a CMOS color imaging sensor board 22, a CMOS color imaging sensor adjustment pad 23; wherein the content of the first and second substances,
a CMOS color imaging sensor base 21 for fixing a CMOS color imaging sensor board 22;
a CMOS color imaging sensor board 22 for ensuring flatness and straightness of an imaging plane of the CMOS color imaging sensor;
and a CMOS color imaging sensor adjustment pad 23 for ensuring that the CMOS color imaging sensor imaging plane is parallel to the flatness reference of the CMOS color imaging sensor base 21.
As shown in fig. 3, the CMOS color imaging sensor board 22 includes a CMOS color imaging sensor circuit board 31, a CMOS color imaging sensor reinforcing plate 32; wherein the content of the first and second substances,
a CMOS color imaging sensor circuit board 31 for soldering a CMOS color imaging sensor;
and a CMOS color imaging sensor reinforcing plate 32 for reinforcing and fixing the CMOS color imaging sensor circuit board 31.
As shown in fig. 5, the number of pixels of the CMOS color imaging sensor module 13 is 4096 × 3072, the number of pixels of the CMOS color imaging sensor is 4096 while being perpendicular to the flight direction, and the number of pixels of the CMOS color imaging sensor is 3072 while being parallel to the flight direction.
As shown in fig. 6, the optical assembly 11 and the CMOS color imaging sensor assembly 13 are designed by a modular combination, such that the optical axis of the optical assembly 11 is perpendicular to the imaging surface of the CMOS color imaging sensor assembly 13 and the relative position is fixed.
As shown in fig. 6 and 7, the optical assembly 11, the CMOS color imaging sensor assembly 13 and the camera supporting assembly 15 are designed by a modular combination, such that the number of pixels of the CMOS color imaging sensor assembly 13 is 4096, which is perpendicular to the mounting surface of the camera supporting assembly 15, and the number of pixels of the CMOS color imaging sensor is 3072, which is parallel to the mounting surface of the camera supporting assembly 15; the optical axis of the optical assembly 11 is made perpendicular to the Z direction of the camera support assembly 15 and parallel to the X and Y directions.
As shown in fig. 7, the X-direction, Y-direction, and Z-direction of the reference assembly 12 are parallel to the X-direction, Y-direction, and Z-direction of the camera support assembly 15, respectively.
The color of the space camera is standard RGB color, the spectral range is 430 nm-690 nm, and the focal length is as follows: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm by 160mm by 180 mm.
The invention provides a method for realizing a high-quality high-reliability step-by-step picture type staring three-dimensional imaging space camera for deep space remote sensing detection, which comprises an optical component 11, a reference component 12, a CMOS color imaging sensor component 13, a camera control electronics component 14 and a camera supporting component 15, wherein the reference component 12 is arranged on the upper surface of the optical component; the color of the space camera is standard RGB color, the spectral range is 430 nm-690 nm, and the focal length is as follows: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm × 160mm × 180 mm; the implementation method comprises the following steps:
1) High-quality and high-reliability implementation method of space camera
Firstly, the high quality and high reliability of the space camera are realized through the modular design of a CMOS color imaging sensor board 22;
as shown in fig. 3, the CMOS color imaging sensor that passes the upgrade screening and the quality assurance is soldered to the CMOS color imaging sensor circuit board 31, and then the CMOS color imaging sensor circuit board 31 is fixed to the CMOS color imaging sensor reinforcing plate 32, thereby reinforcing the mechanical characteristics of the CMOS color imaging sensor.
The high quality and high reliability of the space camera are realized through the modular design of the CMOS color imaging sensor assembly 13;
as shown in fig. 2 and 4, the CMOS color imaging sensor board 22 is fixed to the CMOS color imaging sensor board 22 by the CMOS color imaging sensor adjustment pad 23; the imaging surface of the CMOS color imaging sensor is ensured to be parallel to the flatness reference of the CMOS color imaging sensor base 21 through modular design, and the imaging pixel of the CMOS color imaging sensor is ensured to be parallel to the straightness reference of the CMOS color imaging sensor base 21.
The optical component 11 and the CMOS color imaging sensor component 13 are combined in a modularization mode to achieve high quality and high reliability of the space camera;
As shown in fig. 6 and 7, the optical assembly 11 is fixed on the CMOS color imaging sensor assembly 13, the imaging surface of the CMOS color imaging sensor assembly 13 is ensured to be on the focal plane of the optical assembly 11 by a modular design, the optical axis of the optical assembly 11 is perpendicular to the imaging surface of the CMOS color imaging sensor assembly 13 and the relative position is fixed, the number of pixels of the CMOS color imaging sensor assembly 13 is 4096, which is perpendicular to the mounting surface of the camera supporting assembly 15, the number of pixels of the CMOS color imaging sensor is 3072, which is parallel to the mounting surface of the camera supporting assembly 15, and the optical axis of the optical assembly 11 is perpendicular to the Z direction of the camera supporting assembly 15 and parallel to the X direction and the Y direction.
High-quality and high-reliability space camera is realized through modular combination design of the reference component 12 and the camera support component 15
As shown in fig. 7, the fiducial component 12 is fixed on the camera support component 15, and the X-direction, Y-direction and Z-direction of the fiducial component 12 are ensured to be parallel to the X-direction, Y-direction and Z-direction of the camera support component 15 respectively through a modular design.
2) Implementation method of step-by-step frame type staring imaging of space camera
Firstly, realizing stepping imaging of the space camera by optimizing the time interval between two frames of images;
the step imaging is realized by optimizing the design time interval, the exposure control module of the camera control electronics component 14 optimizes and designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, and the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%.
Secondly, step-by-step frame type staring imaging of the space camera is realized by selecting a CMOS color imaging sensor;
the CMOS color imaging sensor of CMOSIS has color (R, G, B), effective pixel number of 4096 × 3072, pixel size of 5.5 μm × 5.5 μm, sensitivity of 4.64V/lux · s, and well-filled charge of 13500e-The dynamic range is 60dB, QE FF is 50% @550 nm.
Step-by-step frame staring imaging of the space camera is realized through the optimization design of the maximum exposure time;
the staring imaging is realized by optimally designing the maximum exposure time, the maximum exposure time for realizing the staring imaging is optimally designed according to the focal length of the optical system of the optical component 11, the pixel size of the CMOS color imaging sensor component 13, the maximum tangential speed of the deep space remote sensing detector and the track height corresponding to the maximum tangential speed of the deep space remote sensing detector, and the image displacement generated on the image plane by the maximum exposure time is not more than one third of pixel.
Fourthly, realizing the step-by-step picture type staring imaging of the space camera through the optimization design of the optical system parameters
The gaze imaging is achieved by optimally designing optical system parameters, which are determined for the optical assembly 11 by:
Figure BDA0002566892600000091
wherein S isimageFor accumulating the number of electrons, phi, in a single picture element0The number density of solar photons is shown, and rho is a diffuse reflection coefficient; τ is the optical system transmittance; thetasIs the angle between the normal vector of the imaging plane and the sun, thetaoIs the angle between the normal vector of the imaging plane and the observer, F is the F number of the camera, BsIs the area of a single pixel, eta is the quantum efficiency, kappa is the fill factor, and t is the exposure time;
the optical system parameters of the optical component 11 are that the wave band range is 430 nm-700 nm, the visual field is 53.1 degrees multiplied by 41.1 degrees, the focal length is 22.5mm, the F number is 5, and the transfer function MTF is more than 0.45;
3) method for realizing three-dimensional imaging of space camera
The three-dimensional imaging is realized by optimally designing the image overlapping rate of two images, and the exposure control module of the camera control electronics assembly 14 optimally designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, so that the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%.

Claims (9)

1. A high reliability step-and-frame gaze stereo imaging space camera, characterized in that it comprises an optical component (11), a reference component (12), a CMOS color imaging sensor component (13), a camera control electronics component (14) and a camera support component (15); wherein:
the optical component (11) is used for imaging a deep space target to be imaged on the CMOS color imaging sensor;
the reference assembly (12) provides a mounting reference for the camera;
the CMOS color imaging sensor component (13) is used for photoelectric conversion, and converts an optical image acquired by the optical component (11) into a corresponding electric signal so as to obtain a digital image;
the camera control electronics assembly (14) is used for generating bias voltage of the CMOS color imaging sensor, generating a driving time sequence signal of the CMOS color imaging sensor, communicating with the CMOS color imaging sensor through the SPI, configuring and reading parameters of the CMOS color imaging sensor, receiving an image signal output by the CMOS color imaging sensor, analyzing and caching an image, performing automatic exposure calculation according to the image, controlling exposure, outputting an image data stream and engineering parameters according to a specified format, receiving a control command and the parameters, and feeding back a working state;
The camera supporting assembly (15) is used for fixing the optical assembly (11), the reference assembly (12), the CMOS color imaging sensor assembly (13) and the camera control electronic assembly (14), and mechanical characteristics of the camera are guaranteed.
2. The high reliability step-and-frame gaze stereo imaging space camera according to claim 1, characterized by the CMOS color imaging sensor assembly (13) comprising a CMOS color imaging sensor base (21), a CMOS color imaging sensor board (22), a CMOS color imaging sensor adjustment pad (23); wherein the content of the first and second substances,
the CMOS color imaging sensor base (21) is used for fixing a CMOS color imaging sensor plate (22);
the CMOS color imaging sensor plate (22) is used for ensuring the flatness and the straightness of an imaging surface of the CMOS color imaging sensor;
the CMOS color imaging sensor adjusting pad (23) is used for ensuring that the imaging surface of the CMOS color imaging sensor is parallel to the planeness reference of the CMOS color imaging sensor base (21).
3. The high reliability step-and-frame gaze stereoscopic imaging space camera according to claim 1, characterized by the CMOS color imaging sensor board (22) comprising a CMOS color imaging sensor circuit board (31), a CMOS color imaging sensor stiffener board (32); wherein the content of the first and second substances,
The CMOS color imaging sensor circuit board (31) is used for welding the CMOS color imaging sensor;
the CMOS color imaging sensor reinforcing plate (32) is used for reinforcing and fixing the CMOS color imaging sensor circuit board (31).
4. The high reliability step-by-step frame staring stereo imaging space camera according to claim 1, wherein the number of pixels of the CMOS color imaging sensor assembly (13) is 4096 x 3072, the number of pixels of the CMOS color imaging sensor is 4096 sides perpendicular to the flight direction, and the number of pixels of the CMOS color imaging sensor is 3072 sides parallel to the flight direction.
5. The high-reliability step-and-frame staring stereoscopic imaging space camera according to claim 1, wherein the optical assembly (11) and the CMOS color imaging sensor assembly (13) are designed by a modular combination such that the optical axis of the optical assembly (11) is perpendicular to the imaging plane of the CMOS color imaging sensor assembly (13) and the relative position is fixed.
6. The high-reliability step-by-step frame staring stereo imaging space camera according to claim 1, wherein the optical assembly (11), the CMOS color imaging sensor assembly (13) and the camera support assembly (15) are designed by modular combination, so that the number of pixels of the CMOS color imaging sensor assembly (13) is 4096, which is perpendicular to the mounting surface of the camera support assembly (15), and the number of pixels of the CMOS color imaging sensor is 3072, which is parallel to the mounting surface of the camera support assembly (15); the optical axis of the optical assembly (11) is perpendicular to the Z direction of the camera support assembly (15) and parallel to the X direction and the Y direction.
7. The high reliability step-and-frame gaze stereoscopic imaging space camera according to claim 1, characterized in that the X-, Y-, and Z-directions of the reference assembly (12) are parallel to the X-, Y-, and Z-directions of the camera support assembly (15), respectively.
8. The high reliability step-by-step frame staring stereo imaging space camera as claimed in claim 1, wherein the color of the space camera is standard RGB color, the spectral range is 430 nm-690 nm, the focal length: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm by 160mm by 180 mm.
9. A method for realizing a high-reliability step-and-frame staring stereo imaging space camera is characterized in that the space camera comprises an optical component (11), a reference component (12), a CMOS color imaging sensor component (13), a camera control electronics component (14) and a camera supporting component (15); the color of the space camera is standard RGB color, the spectral range is 430 nm-690 nm, and the focal length is as follows: 22.5mm, relative pore size: f/5, a field of view of 53.1 degrees multiplied by 41.1 degrees, a ground element resolution of 98m @400km, an imaging width of 400km @400km, an effective pixel number of 4096 multiplied by 3072, a weight of 3.5kg, a power consumption of 19.72W, and an envelope size of: 278mm × 160mm × 180 mm; the implementation method comprises the following steps:
1) High-quality and high-reliability implementation method of space camera
The space camera is high in quality and reliability through the modular design of a CMOS color imaging sensor board (22);
the CMOS color imaging sensor which passes the upgrading screening and the quality assurance is welded on a CMOS color imaging sensor circuit board (31), and then the CMOS color imaging sensor circuit board (31) is fixed on a CMOS color imaging sensor reinforcing plate (32) to reinforce the mechanical property of the CMOS color imaging sensor;
the high quality and high reliability of the space camera are realized through the modular design of a CMOS color imaging sensor assembly (13);
fixing the CMOS color imaging sensor plate (22) on the CMOS color imaging sensor plate (22) through the CMOS color imaging sensor adjusting pad (23); the imaging surface of the CMOS color imaging sensor is ensured to be parallel to the flatness reference of the CMOS color imaging sensor base (21) through modular design, and the imaging pixel of the CMOS color imaging sensor is ensured to be parallel to the straightness reference of the CMOS color imaging sensor base (21);
realizing high quality and high reliability of the space camera through a modular combination design by an optical component (11) and a CMOS color imaging sensor component (13);
Fixing an optical assembly (11) on a CMOS color imaging sensor assembly (13), ensuring that an imaging surface of a CMOS color imaging sensor of the CMOS color imaging sensor assembly (13) is on a focal plane of the optical assembly (11) through modular design, ensuring that an optical axis of the optical assembly (11) is perpendicular to the imaging surface of the CMOS color imaging sensor assembly (13) and the relative position is fixed, ensuring that the number of pixels of the CMOS color imaging sensor assembly (13) is 4096, the edges of the pixels are perpendicular to a mounting surface of a camera supporting assembly (15), the edges of the pixels of the CMOS color imaging sensor are 3072, the edges of the pixels are parallel to the mounting surface of the camera supporting assembly (15), and the optical axis of the optical assembly (11) is perpendicular to the Z direction of the camera supporting assembly (15) and is parallel to the X direction and the Y direction;
high-quality and high-reliability space camera is realized through modular combination design of the reference component (12) and the camera support component (15)
Fixing the reference component (12) on the camera support component (15), and ensuring that the X direction, the Y direction and the Z direction of the reference component (12) are respectively parallel to the X direction, the Y direction and the Z direction of the camera support component (15) through a modular design;
2) implementation method of step-by-step frame type staring imaging of space camera
Firstly, realizing stepping imaging of the space camera by optimizing the time interval between two frames of images;
step imaging is realized by optimizing the design time interval, the exposure control module of the camera control electronics component (14) optimizes and designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, and the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%;
secondly, step-by-step frame type staring imaging of the space camera is realized by selecting a CMOS color imaging sensor;
the CMOS color imaging sensor of CMOSIS has color (R, G, B), effective pixel number of 4096 × 3072, pixel size of 5.5 μm × 5.5 μm, sensitivity of 4.64V/lux · s, and well-filled charge of 13500e-The dynamic range is 60dB, QE is 50% @550 nm;
step-by-step frame staring imaging of the space camera is realized through the optimization design of the maximum exposure time;
the staring imaging is realized by optimally designing the maximum exposure time, the maximum exposure time for realizing the staring imaging is optimally designed according to the focal length of an optical system of the optical component (11), the pixel size of a CMOS color imaging sensor of the CMOS color imaging sensor component (13), the maximum tangential speed of the deep space remote sensing detector and the track height corresponding to the maximum tangential speed of the deep space remote sensing detector, and the image shift amount generated on an image plane by the maximum exposure time is not more than one third of pixel;
Fourthly, realizing the step-by-step picture type staring imaging of the space camera through the optimization design of the optical system parameters
Gaze imaging is achieved by optimally designing optical system parameters, the optical system parameters of the optical assembly (11) being determined by:
Figure FDA0002566892590000041
wherein S isimageFor accumulating the number of electrons, phi, in a single picture element0The number density of solar photons is shown, and rho is a diffuse reflection coefficient; τ is the optical system transmittance; thetasIs the angle between the normal vector of the imaging plane and the sun, thetaoIs the angle between the normal vector of the imaging plane and the observer, F is the F number of the camera, BsIs the area of a single pixel, eta is the quantum efficiency, kappa is the fill factor, and t is the exposure time;
the optical system parameters of the optical component (11) are that the wave band range is 430 nm-700 nm, the visual field is 53.1 degrees multiplied by 41.1 degrees, the focal length is 22.5mm, the F number is 5, and the transfer function MTF is more than 0.45;
3) method for realizing three-dimensional imaging of space camera
The three-dimensional imaging is realized by optimally designing the image overlapping rate of two images, and the exposure control module of the camera control electronics assembly (14) optimally designs the time interval between two frames of images according to the track height and the speed of the satellite points of the deep space remote sensing detector, so that the image overlapping rate of two adjacent images along the flight direction of the deep space remote sensing detector can be ensured to reach 60%.
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