CN115077700A - Hyper-spectrum aerospace optical imaging system - Google Patents
Hyper-spectrum aerospace optical imaging system Download PDFInfo
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- CN115077700A CN115077700A CN202210666694.7A CN202210666694A CN115077700A CN 115077700 A CN115077700 A CN 115077700A CN 202210666694 A CN202210666694 A CN 202210666694A CN 115077700 A CN115077700 A CN 115077700A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/28—Investigating the spectrum
- G01J3/2823—Imaging spectrometer
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/02—Details
- G01J3/0205—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows
Abstract
The invention discloses a hyper-spectral space optical imaging system, which comprises: the system comprises a grating main mirror, a spectrum focusing imaging system, a slit or a coding plate and a spectrum unfolding system; wherein the slit or the coding plate is arranged at a primary image surface of the spectral focusing imaging system; the incident light is diffracted by the grating primary mirror to generate +1 order or-1 order diffracted light, the parallel light forms a primary image on the slit or the coding plate through the spectrum focusing imaging system, and the primary image forms a secondary image on a secondary image surface of the spectrum spreading system through the spectrum spreading system. The invention meets the requirements of follow-up spaceflight on the optical imaging spectrometer with large caliber and ultra-large caliber.
Description
Technical Field
The invention belongs to the technical field of optical system design, and particularly relates to a hyper-spectral aerospace optical imaging system.
Background
With the increase of the application demand in the field of space remote sensing, new performance requirements are provided for the imaging spectrum system, with the continuous increase of the number of spectrums, the design difficulty of the optical system is improved, particularly, the traditional spectrometer system comprises a dispersion type spectrometer, a narrow-band tunable optical filter imaging spectrometer, an imaging Fourier transform spectrometer and a chromatography type imaging spectrometer, is limited and restricted by the limitation of an imaging system and a space emission space, and the factors such as the preparation of optical system materials, processing technology, carrying capacity and the like, and the requirement of follow-up space flight on a large-caliber and ultra-large-caliber optical imaging spectrometer can not be met by adopting the traditional imaging mode.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects in the prior art are overcome, the hyper-spectral aerospace optical imaging system is provided, and the requirements of follow-up aerospace on large-caliber and ultra-large-caliber optical imaging spectrometers are met.
The purpose of the invention is realized by the following technical scheme: a hyperspectral aerospace optical imaging system comprising: the device comprises a grating primary mirror, a spectrum focusing imaging system, a slit or coding plate and a spectrum unfolding system; wherein the slit or the coding plate is arranged at a primary image surface of the spectral focusing imaging system; the incident light is diffracted by the grating primary mirror to generate +1 order or-1 order diffracted light, the parallel light forms a primary image on the slit or the coding plate through the spectrum focusing imaging system, and the primary image forms a secondary image on a secondary image surface of the spectrum spreading system through the spectrum spreading system.
In the hyperspectral aerospace optical imaging system, the spectrum focusing imaging system comprises a second reflector, a third reflector and a fourth reflector; the + 1-order or-1-order diffracted light sequentially passes through the second reflector, the third reflector and the fourth reflector as parallel light to form a primary image on the slit or the coding plate.
In the hyperspectral space optical imaging system, the spectrum spreading system comprises a sixth reflector, a seventh reflective dispersion grating and an eighth reflector; and the primary image sequentially passes through the sixth reflector, the seventh reflective dispersion grating and the eighth reflector to form a secondary image.
In the hyperspectral aerospace optical imaging system, the radius of curvature of the third mirror is smaller than that of the second mirror, the radius of curvature of the fourth mirror is larger than that of the third mirror and the radius of curvature of the fourth mirror is smaller than that of the second mirror; the distance from the grating main mirror to the second mirror is larger than the distance from the second mirror to the third mirror; the distance from the second reflector to the third reflector is equal to the distance from the third reflector to the fourth reflector; the distance from the fourth reflector to the slit or the coding plate is larger than the distance from the second reflector to the third reflector.
In the hyperspectral aerospace optical imaging system, a curvature radius of the sixth reflector is greater than a curvature radius of the seventh reflector dispersion grating, the curvature radius of the seventh reflector dispersion grating is smaller than a curvature radius of the eighth reflector, and the curvature radius of the eighth reflector is smaller than the curvature radius of the sixth reflector; the distance from the sixth mirror to the seventh mirror dispersion grating is greater than the distance from the seventh mirror dispersion grating to the eighth mirror; and the distance from the eighth reflector to the secondary image surface of the spectrum spreading system is greater than the distance from the sixth reflector to the dispersion grating of the seventh reflector.
In the hyperspectral aerospace optical imaging system, the curvature radius of the grating primary mirror is infinite, the thickness of the grating primary mirror is 30mm, the linear density of the first grating primary mirror is 1740lp/mm, the distance from the grating primary mirror to the spectrum focusing imaging system is 11180mm, and the light-passing aperture of the first grating primary mirror is 3000 multiplied by 20000 mm.
In the hyperspectral aerospace optical imaging system, the curvature radius of the second reflector is-53700 mm, the distance from the second reflector to the third reflector is 1279.3mm, the clear aperture of the second reflector is 3000 multiplied by 3000mm, and the distance from the grating main mirror to the second reflector is 11180 mm.
In the hyperspectral aerospace optical imaging system, the radius of curvature of the third reflector is-13750 mm, the distance from the third reflector to the fourth reflector is 1279.3mm, and the light transmission aperture of the third reflector is 2600 multiplied by 2600 mm.
In the hyperspectral space optical imaging system, the curvature radius of the fourth reflector is-17470 mm, the distance from the fourth reflector to the slit or the coding plate is 2166.6mm, and the light transmission aperture of the third reflector is 3600 x 3600 mm.
In the hyperspectral aerospace optical imaging system, the curvature radius of the sixth reflector is 2120mm, the distance from the sixth reflector to the dispersion grating of the seventh reflector is 1023mm, and the clear aperture of the sixth reflector is 590 x 590 mm.
In the hyperspectral aerospace optical imaging system, the curvature radius of the seventh mirror dispersion grating is 1067.4mm, the linear density of the seventh mirror dispersion grating is 145lp/mm, the distance from the seventh mirror dispersion grating to the eighth mirror is 990.4mm, and the clear aperture of the seventh mirror dispersion grating is 192 × 192 mm.
In the hyperspectral aerospace optical imaging system, the curvature radius of the eighth reflector is 2086.5mm, the distance from the eighth reflector to the secondary image plane of the spectrum spreading system is 2113.3mm, and the light transmission aperture of the eighth reflector is 590 x 403 mm.
Compared with the prior art, the invention has the following beneficial effects:
(1) the whole hyper-spectral space optical imaging system meets the requirements of follow-up space flight on large-caliber and ultra-large-caliber optical imaging spectrometers;
(2) the invention effectively utilizes the advantages of the diffraction grating spectral imaging technology, simultaneously completes dispersion and imaging, is a unique axial dispersion spectrometer, perfectly combines high resolution and high spectral resolution, and can realize 0.05nm of ultra-spectral resolution, so that the finally obtained spectral resolution is superior to the traditional imaging spectral system.
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Various additional advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic diagram of a hyper-spectral aerospace optical imaging system provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of a diffraction optical path of a grating primary mirror of a hyper-spectral aerospace optical imaging system provided by an embodiment of the invention;
FIG. 3 is a schematic diagram of a spectrally focused imaging system provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of a spectrum spreading system provided by an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic diagram of a hyper-spectral aerospace optical imaging system provided by an embodiment of the invention. As shown in fig. 1, the system includes: the system comprises a grating main mirror 1, a spectrum focusing imaging system, a slit or coding plate 5 and a spectrum unfolding system; wherein the content of the first and second substances,
the slit or the coding plate 5 is arranged at a primary image surface of the spectrum focusing imaging system;
the incident light is diffracted by the grating primary mirror 1 to generate +1 order or-1 order diffraction light, the parallel light forms a primary image on the slit or the coding plate 5 through the spectrum focusing imaging system, and the primary image forms a secondary image on a secondary image surface of the spectrum spreading system through the spectrum spreading system.
As shown in fig. 3, the spectral focusing imaging system includes a second mirror 2, a third mirror 3, and a fourth mirror 4; the +1 order or-1 order diffracted light sequentially passes through the second reflector 2, the third reflector 3 and the fourth reflector 4 as parallel light to form a primary image on the slit or the encoding plate 5.
As shown in fig. 4, the spectrum spreading system includes a sixth mirror 6, a seventh reflective dispersion grating 7, and an eighth mirror 8; wherein, the primary image sequentially passes through the sixth reflector 6, the seventh reflective dispersion grating 7 and the eighth reflector 8 to form a secondary image.
As shown in fig. 2, the grating main mirror 1 is a plane grating, light is diffracted by the grating, and the generated +1 st order diffracted light is emitted as parallel light, and the emitting angle is 80 degrees, which is determined by the slit pitch of the grating. Because the diffraction emergent angle of the grating primary mirror 1 can realize 80-degree emergent, the axial size of the whole system is greatly compressed and reduced to 1/6 of the original system, the design of light and small optical imaging is facilitated, and the cost of the optical system is reduced.
The curvature radius of the grating main mirror 1 is infinite, the thickness of the grating main mirror 1 is 30mm, the linear density of the first grating main mirror 1 is 1740lp/mm, and the distance from the grating main mirror 1 to the second reflecting mirror 2 is 11180mm, and the light transmission aperture of the first grating main mirror 1 is 3000 multiplied by 20000 mm.
The radius of curvature of the second reflector 2 is-53700 mm, the distance from the second reflector 2 to the third reflector is 1279.3mm, and the clear aperture of the second reflector 2 is 3000 x 3000 mm.
The radius of curvature of the third reflector 3 is-13750 mm, the distance from the third reflector 3 to the fourth reflector is 1279.3mm, and the aperture of the third reflector 3 is 2600 mm.
The radius of curvature of the fourth mirror 4 is-17470 mm, the distance from the fourth mirror to the slit or the encoding plate 5 is 2166.6mm, and the aperture of the third mirror 4 is 3600X 3600 mm.
The slit or the encoding plate 5 is located at the primary real image; if slit push-broom spectral imaging is adopted, a slit is placed at the position of a primary real image, and the system is utilized to push-broom a target to realize spectral data acquisition; if the snapshot type calculation spectral imaging is adopted, an encoding plate is placed at the position of the primary real image, and the spectral data is obtained at one time by using a calculation and calculation mode.
Specifically, a snapshot-type spectral imaging calculation mode is utilized, a sparse reconstruction theory is used as a basis, an observation matrix irrelevant to a transformation basis is adopted, a high-dimensional signal is projected to a low-dimensional space, and an original high-dimensional signal is reconstructed and restored through optimization solution. In the implementation process, light rays perform amplitude modulation on three-dimensional data (1-dimensional spectrum + 2-dimensional space) through a coding plate (2-dimensional space), the three-dimensional data is dispersed and split by a grating and then received by a detector, the planar array detector obtains space-spectrum aliasing data, the space-spectrum aliasing data is resolved through priori information of the coding plate, and sparse reconstruction is performed on the three-dimensional aliasing data to obtain two-dimensional (1-dimensional spectrum + 2-dimensional space) data.
The radius of curvature of the sixth mirror 6 is 2120mm, the distance from the sixth mirror 6 to the seventh mirror dispersion grating is 1023mm, and the clear aperture of the sixth mirror 6 is 590 x 590 mm.
The curvature radius of the seventh mirror dispersion grating 7 is 1067.4mm, the linear density of the seventh mirror dispersion grating 7 is 145lp/mm, the distance from the seventh mirror dispersion grating 7 to the eighth mirror is 990.4mm, and the clear aperture of the seventh mirror dispersion grating 7 is 192 × 192 mm.
The curvature radius of the eighth reflector 8 is 2086.5mm, the distance from the eighth reflector 8 to the image plane is 2113.3mm, and the aperture of the eighth reflector 8 is 590 x 403 mm.
The working principle is as follows: the grating is used as a main mirror, spectral information and imaging information of the same ground feature information are detected at high precision according to different imaging positions of different fields of view by satellite push-broom or area array imaging, and the scene in the field of view is subjected to one-time hyperspectral imaging by simultaneous light splitting and imaging. Meanwhile, the principle of reverse grating diffraction is adopted, and 80-degree emergent can be realized by utilizing the +1/-1 diffraction emergent angle, so that the overall axial size of the system is greatly compressed, and the light and small design of optical imaging is facilitated.
After the light transmission grating main mirror, the light is transmitted among all the reflectors along a straight line, and the parameters of all the light elements are shown in the following table:
the working spectrum of the system is 450-850nm, the finite focal length is 13m, and the full field angle is 18.7 degrees multiplied by 1.6 degrees.
The embodiment provides the technical indexes that when the satellite orbit height is 500km, the ground resolution is 0.5m and the spectral resolution is 0.05nm by using the hyper-spectral space optical imaging system in the embodiment.
The photon shot noise of the spectrum signal is relatively small. Because this noise only comes from a few spectral channels adjacent to the measurement spectral band, in a conventional fourier transform imaging spectroscopy system, its entire spectral band will produce photon shot noise; compared with the conventional dispersive spectrometer, the invention has the advantages that the whole input aperture can collect light rays, the utilization rate of luminous flux is improved, and the luminous flux can be improved by more than 4 times when the fifth coding plate is adopted at the primary image position; the invention effectively utilizes the advantages of the diffraction grating spectral imaging technology, simultaneously completes dispersion and imaging, is a unique axial dispersion spectrometer, perfectly combines high resolution and high spectral resolution, and can realize 0.05nm of ultra-spectral resolution, so that the finally obtained spectral resolution is superior to the traditional imaging spectral system.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A hyperspectral aerospace optical imaging system, comprising: the system comprises a grating main mirror (1), a spectrum focusing imaging system, a slit or an encoding plate (5) and a spectrum unfolding system; wherein the content of the first and second substances,
the slit or the coding plate (5) is arranged at a primary image surface of the spectral focusing imaging system;
the incident light is diffracted by the grating primary mirror (1) to generate +1 order or-1 order diffracted light, and the parallel light forms a primary image on the slit or the coding plate (5) through the spectrum focusing imaging system, and the primary image forms a secondary image on a secondary image surface of the spectrum spreading system through the spectrum spreading system.
2. The hyperspectral aerospace optical imaging system of claim 1, wherein: the spectrum focusing imaging system comprises a second reflector (2), a third reflector (3) and a fourth reflector (4); wherein the content of the first and second substances,
the + 1-order or-1-order diffracted light rays sequentially pass through the second reflector (2), the third reflector (3) and the fourth reflector (4) as parallel light to form a primary image on a slit or an encoding plate (5).
3. The hyperspectral aerospace optical imaging system of claim 1, wherein: the spectrum spreading system comprises a sixth reflector (6), a seventh reflective dispersion grating (7) and an eighth reflector (8); wherein the content of the first and second substances,
the primary image sequentially passes through the sixth reflector (6), the seventh reflective dispersion grating (7) and the eighth reflector (8) to form a secondary image.
4. The hyperspectral aerospace optical imaging system of claim 2, wherein: the radius of curvature of the third mirror (3) is smaller than the radius of curvature of the second mirror (2), the radius of curvature of the fourth mirror (4) is larger than the radius of curvature of the third mirror (3) and the radius of curvature of the fourth mirror (4) is smaller than the radius of curvature of the second mirror (2);
the distance from the grating main mirror (1) to the second mirror (2) is greater than the distance from the second mirror (2) to the third mirror (3);
the distance from the second reflector (2) to the third reflector (3) is equal to the distance from the third reflector (3) to the fourth reflector (4);
the distance from the fourth mirror to the slit or the coding plate (5) is greater than the distance from the second mirror (2) to the third mirror (3).
5. The hyperspectral aerospace optical imaging system of claim 3, wherein: the radius of curvature of the sixth mirror (6) is greater than the radius of curvature of the seventh mirror dispersion grating, the radius of curvature of the seventh mirror dispersion grating is less than the radius of curvature of the eighth mirror (8), and the radius of curvature of the eighth mirror (8) is less than the radius of curvature of the sixth mirror (6);
the distance of the sixth mirror (6) to the seventh mirror dispersion grating (7) is greater than the distance of the seventh mirror dispersion grating (7) to the eighth mirror; the distance from the eighth reflector (8) to the secondary image surface of the spectrum spreading system is larger than the distance from the sixth reflector (6) to the seventh reflector dispersion grating (7).
6. The hyperspectral aerospace optical imaging system of claim 1, wherein: the curvature radius of grating primary mirror (1) is the infinity, the thickness of grating primary mirror (1) is 30mm, the linear density of first grating primary mirror (1) is 1740lp/mm, grating primary mirror (1) arrives spectral focusing imaging system's distance is 11180mm, the light aperture that leads to of first grating primary mirror (1) is 3000 x 20000 mm.
7. The hyperspectral aerospace optical imaging system of claim 2, wherein: the curvature radius of the second reflector (2) is-53700 mm, the distance from the second reflector (2) to the third reflector (3) is 1279.3mm, the clear aperture of the second reflector (2) is 3000 multiplied by 3000mm, and the distance from the grating main mirror (1) to the second reflector (2) is 11180 mm;
the curvature radius of the third reflector (3) is-13750 mm, the distance from the third reflector (3) to the fourth reflector (4) is 1279.3mm, and the light transmission aperture of the third reflector (3) is 2600mm by 2600 mm.
8. The hyperspectral aerospace optical imaging system of claim 2, wherein: the curvature radius of the fourth reflector (4) is-17470 mm, the distance between the fourth reflector and the slit or the encoding plate (5) is 2166.6mm, and the clear aperture of the third reflector (4) is 3600 x 3600 mm.
9. The hyperspectral aerospace optical imaging system of claim 3, wherein: the radius of curvature of the sixth mirror (6) is 2120mm, the distance from the sixth mirror (6) to the seventh mirror dispersion grating is 1023mm, and the clear aperture of the sixth mirror (6) is 590 x 590 mm.
10. The hyperspectral aerospace optical imaging system of claim 3, wherein: the curvature radius of the seventh mirror dispersion grating (7) is 1067.4mm, the linear density of the seventh mirror dispersion grating (7) is 145lp/mm, the distance from the seventh mirror dispersion grating (7) to the eighth mirror is 990.4mm, and the clear aperture of the seventh mirror dispersion grating (7) is 192 × 192 mm;
the curvature radius of the eighth reflector (8) is 2086.5mm, the distance from the eighth reflector (8) to the secondary image surface of the spectrum spreading system is 2113.3mm, and the light transmission aperture of the eighth reflector (8) is 590 x 403 mm.
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