A satellite-borne small and lightweight Dyson hyperspectral imaging system

Abstract

The present invention provides a satellite-borne small-sized and lightweight Dyson hyperspectral imaging system, which solves the problem that the existing Dyson prototype spectrometer is difficult to carry out structural layout and engineering development due to its overly compact structure. The system includes a box, a front telescope group, a Dyson prism group, a rear mirror assembly, an electronic focal plane assembly and a precision measuring mirror assembly; the incident light is incident through the front telescope group, passes through the Dyson prism group and the rear mirror assembly in sequence, and is reflected by the rear mirror assembly to achieve optical path multiplexing, and then passes through the rear mirror assembly and the Dyson prism assembly to form an image on the electronic focal plane assembly. The system can realize the separation of the object plane and the image plane, and is easy to realize structural layout and engineering development.

Description

Technical Field

[0001] The invention belongs to the field of satellite-borne hyperspectral imaging, and in particular relates to a satellite-borne small and lightweight Dyson hyperspectral imaging system. Background Art

[0002] Spectral imagers can realize spectral imaging and detect two-dimensional spatial information and one-dimensional spectral information at the same time. While performing timing and positioning measurements, they have the functions of qualitative measurement and quantitative analysis, so they can be used in many fields such as material detection, target identification, component analysis, and process monitoring. Compared with ground-based spectrometers and airborne spectrometers, satellite-borne hyperspectral imagers can realize normalized, wide-bandwidth, and high-revisit rate detection, and are widely used in military, agriculture, oceanography, geography, and other fields.

[0003] With the continuous development of space platforms such as cubic satellites and micro-nano satellites, the volume and weight of the optical payloads carried are required to be smaller and smaller, so miniaturized and high-performance hyperspectral imaging technology is urgently needed. Since the optical path of the Dyson spectrometer goes back and forth in the system, it has the efficiency of repeated use, so the system structure is compact, small in size, and light in weight, which is easy to miniaturize. In addition, the Dyson spectrometer still maintains good concentricity as a whole, so it has good aberration characteristics, is easy to achieve a large field of view and a large relative aperture, and can achieve higher detection sensitivity, so it has significant advantages in the technical system of miniaturized, lightweight, and high-performance satellite-borne spectrometers.

[0004] However, the prototype of the spectrometer based on the Dyson structure is composed of a plano-convex lens, a concave grating, an incident slit and a detector. The incident slit and the detector receiving surface are both located on the plane of the plano-convex lens. In the engineering implementation, the prototype of the Dyson structure spectrometer is too compact in system structure, making it difficult to layout the spectrometer with slit components, front telescope group, detector and optical elements, and interference is very likely to occur. Summary of the invention

[0005] The purpose of the present invention is to solve the problem that the existing Dyson prototype spectrometer is too compact and difficult to carry out structural layout and engineering research and development, and to provide a satellite-borne small and lightweight Dyson hyperspectral imager system, which can separate the object plane and the image plane and is easy to implement structural layout and engineering research and development.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A satellite-borne small and lightweight Dyson hyperspectral imaging system comprises a housing, a front telescope group, a Dyson prism group, a rear mirror assembly, an electronic focal plane assembly and a precision measuring mirror assembly; incident light is incident through the front telescope group, passes through the Dyson prism group and the rear mirror assembly in sequence, is reflected by the rear mirror assembly to realize optical path multiplexing, and then is imaged to the electronic focal plane assembly through the rear mirror assembly and the Dyson prism group; the front telescope group is arranged at the front end of the housing, and comprises a front lens barrel, a front light shield and a plurality of front lens groups; The front shading hood is arranged at the front end of the front lens barrel to block external stray light and improve the imaging quality of the spectrometer; multiple groups of front lens groups are arranged in the front lens barrel, wherein the last group of front lens groups includes a glass slit and a protective glass, the glass slit is used to form an optical slit to facilitate system imaging, and the protective glass is used to achieve slit cleanliness; the Dyson prism lens group is arranged in the box, including a Dyson prism, a Dyson prism mounting seat and a Dyson prism mounting seat trimming pad; the Dyson prism is arranged in the Dyson prism The Dyson prism mount is arranged in the box through the Dyson prism mount trimming pad; the Dyson prism includes an incident surface, an exit surface, a transmission surface and a reflection surface, the incident surface and the exit surface are arranged vertically, the reflection surface is arranged at 45 degrees to the incident surface and the exit surface, and the transmission surface is a curved surface; the incident light is emitted through the incident surface and the transmission surface, and after being reflected by the rear mirror assembly, the light path is multiplexed and then it is incident to the reflection surface again through the transmission surface, and then reflected to the exit surface through the reflection surface, and finally an image is formed. The invention relates to an electronic focal plane component; the rear mirror component is arranged at the rear end of the housing, and comprises a rear lens barrel, a concave grating component and a plurality of rear mirror groups; the plurality of rear mirror groups are arranged in the rear lens barrel, the concave grating component is connected to the rear lens barrel through a concave grating trimming pad, and the concave grating trimming pad is used to adjust the spatial position of the concave grating component; the precision measuring mirror component comprises a precision measuring mirror and a precision measuring mirror bonding seat, the precision measuring mirror is arranged at the front end of the housing through the precision measuring mirror bonding seat, and is used to adjust the pitch angle and rotation angle of the Dyson prism during system integration.

[0008] Furthermore, the electronic focal plane assembly is arranged in a housing, including a focal plane panel, a processing board, a connector, an electronic board frame, an electronic rear cover, a focal plane trimming pad and a connector pressure plate; the focal plane panel is arranged on one side of the electronic board frame for arranging the CCD target surface; the processing board is arranged on the other side of the electronic board frame for electronic signal control and transmission; the connector is arranged on the processing board for connecting the digital transmission and electrical signal cables; the connector pressure plate is arranged on the electronic board frame for fixing the position of the connector; the electronic rear cover is arranged on one side of the processing board; the focal plane trimming pad is arranged between the electronic assembly and the housing for adjusting the position of the CCD.

[0009] Furthermore, a glue injection hole is provided on the front lens barrel for fixing the front lens group.

[0010] Furthermore, an exhaust groove is provided on the front lens barrel to facilitate the exhaust of internal gas of the front telescope group when it is used in a vacuum.

[0011] Furthermore, the multiple front lens groups include front lens group one, front lens group two, front lens group three, front lens group four, front lens group five, front lens group six, front lens group seven, front lens group eight and front lens group nine, which are arranged in sequence; spacers are arranged between the front lens groups, and the intervals between the front lens groups are ensured by adjusting the thickness of the spacers, and the front lens groups are pressed tightly in the front lens barrel by the front left outer pressure ring and the front right outer pressure ring. At the same time, the lenses in each front lens group are fixed in the frame by the pressure ring after glue is applied on the circumference.

[0012] Furthermore, the front lens group is provided with a flange mounting hole for connecting the front lens group to the box.

[0013] Furthermore, the Dyson prism mounting base is provided with a plurality of process holes for ensuring the bonding position accuracy of the Dyson prism.

[0014] Furthermore, the Dyson prism mounting seat is provided with a glue overflow groove for collecting the overflow of epoxy glue.

[0015] Furthermore, the box body includes a box body main body, a box body cover plate and a box body side plate; the box body cover plate is arranged on the top of the box body, and the box body side plate is arranged on the side of the box body; the front telescope group is installed on the front end face flange of the box body through a trimming pad; the precision measuring mirror assembly is installed on the front end face boss of the box body through a trimming pad; the Dyson prism assembly is installed on the bottom mounting surface of the box body; the rear mirror assembly is installed on the rear end face of the box body through a trimming pad; and the electronic focal plane assembly is installed on the side panel mounting surface of the box body.

[0016] Furthermore, the distance between the glass slit and the front end face of the Dyson prism is 17.66 mm, and the distance between the system image plane position and the exit end face of the Dyson prism is 6 mm.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The Dyson spectrometer optical system of the present invention can realize object plane-image plane separation, overcoming the difficulty of structural layout and engineering development of the Dyson prototype spectrometer due to its overly compact structure.

[0019] 2. The spectrometer system of the present invention is designed with a front telescopic objective lens, which has high-resolution imaging performance. The idea of ​​using an optical slit to transmit light, a metal structural part to block, and a protective glass to seal and protect is first proposed in the front mirror group slit assembly, which reduces the difficulty of processing and designing the slit assembly. In addition, the structural design of the front mirror group can easily realize the vacuum image plane prefabrication and one-time image plane position, ensuring high-quality imaging performance on track.

[0020] 3. Each component of the satellite-borne small and lightweight Dyson hyperspectral imaging system of the present invention adopts a modular design concept, and each component can be assembled separately and then integrated on the box.

[0021] 4. When assembling and adjusting the components of the satellite-borne small and lightweight Dyson hyperspectral imager system of the present invention, each component is provided with a number of adjustable links, which can realize the spatial position adjustment of each optical component, achieve high-quality imaging, and can be effectively applied to engineering applications.

[0022] 5. The satellite-borne small and lightweight Dyson hyperspectral imaging system of the present invention has a reasonable structural layout, compact size and low weight. This spectrometer is suitable for the visible spectrum, with a focal length of 55mm, a relative aperture of not less than 1 / 2.2, an effective field of view angle ≥11.42°, a ground resolution of 100m, and a total weight of no more than 2.5Kg. The first-order mode of the whole machine is greater than 600Hz, and has good mechanical stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A three-dimensional schematic diagram of a satellite-borne small and lightweight Dyson hyperspectral imager system of the present invention;

[0024] Figure 2 The three-dimensional schematic diagram of the hyperspectral imaging system of the present invention (without the box cover);

[0025] Figure 3 Schematic diagram of the optical system of the Dyson hyperspectral imager of the present invention;

[0026] Figure 4 It is a structural schematic diagram of the front telescope assembly of the present invention;

[0027] Figure 5 is a schematic structural diagram of the front lens group nine of the present invention;

[0028] Figure 6 It is a structural schematic diagram of the front lens barrel of the present invention;

[0029] Figure 7 It is a schematic diagram of the structure of the Dyson prism assembly of the present invention;

[0030] Figure 8 It is a structural schematic diagram of a rear mirror assembly of the present invention;

[0031] Fig. 9 It is a structural schematic diagram of the electronic focal plane assembly of the present invention;

[0032] Fig.10 It is a structural schematic diagram of the box body of the present invention;

[0033] Fig.11 It is a structural schematic diagram of the box body of the present invention;

[0034] Fig.12 It is a schematic diagram of the structure of the Dyson prism of the present invention.

[0035] Figure numerals: 1-front telescope group, 2-Dyson prism group, 3-rear mirror assembly, 4-electronic focal plane assembly, 5-box, 6-precision measuring mirror assembly, 101-front mirror group one, 102-front mirror group two, 103-front mirror group three, 104-front mirror group four, 105-front mirror group five, 106-front mirror group six, 107-front mirror group seven, 108-front mirror group eight, 109-front mirror group nine, 110-front lens barrel, 111-front right outer pressure ring, 112-front shading Cover, 113-front left outer pressure ring, 114-front spacer two, 115-front spacer three, 116-front spacer four, 117-front spacer five, 118-front spacer six, 119-front spacer seven, 120-front spacer eight, 121-front spacer nine, 1091-glass slit, 1092-protective glass, 1093-lens group nine frame, 1094-slit protection device, 1095-lens group nine pressure ring, 1101-glue injection hole, 1102-exhaust groove, 1103-flange mounting hole, 21-Dyson prism, 22-Dyson prism mount, 23-Dyson prism mount trimming pad, 211-incident surface, 212-exit surface, 213-transmission surface, 214-reflection surface, 221-process hole, 222-overflow groove, 301-rear mirror group 1, 302-rear mirror group 2, 303-rear mirror group 3, 304-concave grating assembly, 305-rear lens barrel, 306-rear mirror assembly pressure ring, 307-rear spacer ring 1, 308-rear spacer ring 2, 309 -concave grating trimming pad, 310-rear end cover, 41-focus panel, 42-processing board, 43-connector, 44-electronics board frame, 45-electronics rear cover, 46-focus surface trimming pad, 47-connector pressure plate, 51-box body, 52-box cover, 53-box side plate, 511-front end face flange, 512-front end face boss, 513-mounting lug, 514-rear end face, 515-bottom mounting surface, 516-box side mounting surface, 517-upper end face, 518-side panel mounting surface. DETAILED DESCRIPTION

[0036] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0037] The present invention provides a satellite-borne small-sized and lightweight Dyson hyperspectral imager system. The system realizes the separation of the object plane and the image plane of the optical system through the optical optimization design of the Dyson prism and the rear mirror assembly, avoids the disadvantage that the layout of the optical support structure is difficult due to the overlap of the object plane and the image plane, and is easy for engineering research and development.

[0038] like Figure 1 and Figure 2 As shown, the satellite-borne small and lightweight Dyson hyperspectral imaging system of the present invention comprises a front telescope assembly 1, a Dyson prism assembly 2, a rear mirror assembly 3, an electronic focal plane assembly 4, a box 5 and a precision measuring mirror assembly 6. Figure 3 As shown, the working principle of the optical system of the satellite-borne small and lightweight Dyson hyperspectral imager of the present invention is: the incident light enters the spectrometer system through the front telescope group 1, and then passes through the Dyson prism group 2 and the rear mirror assembly 3 in sequence, and is reflected by the last concave grating of the rear mirror assembly 3 to achieve optical path multiplexing, and then passes through the rear mirror assembly 3 and the Dyson prism group 2 to form an image on the electronic focal plane assembly 4.

[0039] like Figure 4As shown, the front telescope group 1 of the present invention is arranged at the front end of the box body 5, including a front lens barrel 110, a front light shield 112 and multiple groups of front lens groups; the front light shield 112 is arranged at the front end of the front lens barrel 110, and is used to block external stray light and improve the imaging quality of the spectrometer; multiple groups of front lens groups are arranged in the front lens barrel 110, wherein the last group of front lens groups includes a glass slit 1091 and a protective glass 1092, the glass slit 1091 is used to form an optical slit to facilitate system imaging, and the protective glass 1092 is used to achieve slit cleanliness to prevent dust and excess objects from falling on the slit and affecting imaging. Specifically, the front telescope group 1 of the present invention comprises nine lens groups, namely, front lens group 1 101, front lens group 2 102, front lens group 3 103, front lens group 4 104, front lens group 5 105, front lens group 6 106, front lens group 7 107, front lens group 8 108 and front lens group 9 109. When the lenses of each front lens group are installed in each lens assembly frame, it is necessary to apply XM-31 glue on the circumference of the lens, and then screw in each lens assembly pressure ring for fixing. Each lens assembly is processed by centering to ensure that each optical element coincides with the axis of each lens assembly frame. Spacers are provided between each lens assembly, and the thickness of the spacers is repaired to ensure the spacing of each optical element. During installation, front lens group eight 108, front spacer eight 120, front lens group seven 107, front spacer seven 119, front lens group six 106, front spacer six 118, front lens group five 105, front spacer five 117, front lens group four 104, front spacer four 116, front lens group three 103, front spacer three 115, front lens group two 102, front spacer two 114, front lens group one 101 are sequentially loaded into the front lens barrel 110, and the front left outer pressure ring 113 is installed to press and fix the above lens groups, and then the front spacer nine 121 and the front lens group nine 109 are installed into the front lens barrel 110 from the right side, and they are pressed and fixed by tightening the front right outer pressure ring 111.

[0040] like Figure 5 As shown, the front lens group nine 109 is the last front lens group, which specifically includes a glass slit 1091, a protective glass 1092, a lens group nine frame 1093, a slit protection device 1094 and a lens group nine pressure ring 1095. The glass slit 1091 is installed in the lens group nine frame 1093, and then the slit protection device 1094 is installed, and then the protective glass 1092 is installed, and then the lens group nine pressure ring 1095 is tightened to press and fix the parts. The slit protection device 1094 is a window with a size larger than the optical slit opened on the structural member, which plays a role in preventing stray light and preventing dust from falling into the slit.

[0041] like Figure 6As shown, the front lens barrel 110 is provided with a glue injection hole 1101 for fixing each lens group. The front lens barrel 110 is also provided with an exhaust groove 1102 to facilitate the exhaust of the internal gas of the front lens group during vacuum use. The front lens group is provided with a flange mounting hole 1103 for connecting the front lens group with the box 5. Because the Dyson spectrometer needs to perform vacuum image plane prefabrication to determine the image plane position of the front lens group 101, after the front lens group is installed, XM-31 glue is injected into the position of the front lens group 101 to the front lens group 8 108 on the glue injection hole 1101 of the front lens barrel 110 for fixing. The front lens group 9 109 needs a vacuum image plane prefabrication test, and the front spacer ring 9 121 is repaired and then glue is injected for fixing. Vacuum image plane preparation means that when the mirror group is tested in the air and in space, the optical transmission medium changes, resulting in a change in the optical path, so the image plane position of the mirror group needs to be adjusted. Specifically, the difference between the image plane position distance tested in a vacuum environment and the image plane position measured in the air is used to determine the size of the trimming pad between the mirror groups.

[0042] like Figure 7 As shown, the Dyson prism 21 assembly includes a Dyson prism 21, a Dyson prism mount 22 and a Dyson prism mount trimming pad 23; the Dyson prism is fixed to the Dyson prism mount 22 by epoxy adhesive bonding. The Dyson prism mount 22 is provided with three process holes 221 to ensure the bonding position accuracy of the Dyson prism 21. Standard pins are installed in the process holes 221, and the circumferential surface of the standard pins is used as the supporting surface of the Dyson prism 21 during bonding, thereby ensuring the azimuth angle of the Dyson prism 21 during bonding. The Dyson prism mount 22 is provided with an overflow groove 222 for bonding the overflow of epoxy adhesive.

[0043] like Fig.12 As shown, the Dyson prism 21 of the present invention may specifically include an incident surface 211, an exit surface 212, a transmission surface 213 and a reflection surface 214. The incident surface 211 and the exit surface 212 are vertically arranged, and the reflection surface 214 is arranged at 45 degrees to the incident surface 211 and the exit surface 212, and the transmission surface 213 is a curved surface; the incident light is emitted through the incident surface 211 and the transmission surface 213, and after being reflected by the rear mirror component 3 to achieve optical path multiplexing, it is incident on the reflection surface 214 again through the transmission surface 213, and then reflected by the reflection surface 214 to the exit surface 212, and finally imaged on the electronic focal plane component 4.

[0044] The specific design process of Dyson prism 21 is as follows: 1) Based on the prototype of Dyson hyperspectral imager, the image plane and object plane of the spectrometer are forcibly pulled out of the plane-convex lens surface, and the aberration caused by the meniscus lens correction is added; 2) The object plane and image plane are forced to separate the design, and then the aberration is corrected by the overall optimization of the meniscus lens and the Dyson structure, where the separation distance between the image plane and the object plane is determined by the aperture when the incident light reaches the convex surface of the Dyson prism 21; 3) A 45° reflection surface is added to the plane-convex lens to make the outgoing light perpendicular to the optical axis of the incident light. The Dyson prism exit surface is also perpendicular to the incident surface, and the separation distance between the object plane and the image plane in the second step is guaranteed. After the light is refracted, the exit surface is lower than the bottom of the aperture on the convex surface of the plane-convex lens, thereby solving the disadvantage that the optical support structure is difficult to layout and is easy to engineer. After the above three steps of design, the final Dyson lens form is the appearance of the system including three planes and one convex surface. The difference between the Dyson prism 21 proposed by the present invention and the existing prism is that the reflective surface maintains a standard angle of 45° with the incident surface 211 and the exit surface 212, which is easy to process and test. The overall flatness, smoothness and angle between the planes are also easy to ensure; the commonly used aerospace fixing method for prisms is adhesive bonding. This Dyson prism 21 has two surfaces perpendicular to each other, which makes it easy to ensure the prism's orientation angle during bonding, which can reduce the difficulty of installation and adjustment.

[0045] like Figure 8 As shown, the rear mirror assembly 3 includes a rear mirror group 1 301, a rear mirror group 2 302, a rear mirror group 3 303 and a concave grating assembly 304 which are arranged in sequence; when each lens is installed in each lens assembly frame, XM-31 glue needs to be applied on the circumference of the lens, and then the pressing ring of each lens assembly needs to be screwed in to fix it. Each lens assembly is processed by centering to ensure that each optical element is aligned with the axis of each lens assembly frame. Spacers are provided between each lens assembly, and the thickness of the spacers is adjusted to ensure the spacing of each optical element. During installation, the rear mirror group 3 303, the rear spacer 2 308, the rear mirror group 2 302, the rear spacer 1 307, and the rear mirror group 1 301 are sequentially installed in the rear lens barrel 305, and then the rear mirror assembly pressing ring 306 is installed and tightened to fix it. In order to facilitate the adjustment of the spatial position of the concave grating, it is used as a separate component. The concave grating component 304 is connected to the rear lens barrel 305 through the concave grating trimming pad 309 by screws, and the rear end is connected to the rear end cover 310 by threads to protect the optical element. The spatial position of the concave grating component 304 is adjusted by the concave grating trimming pad 309 and the screw through-hole amount.

[0046] The front telescope assembly 1 of the present invention includes a total of 10 optical lenses, with a maximum optical aperture of 32 mm. The ninth lens in the front lens assembly is an optical slit, and the distance between the optical slit and the front end face of the Dyson prism 21 is 17.66 mm. The distance between the system image plane position and the exit end face of the Dyson prism 21 is 6 mm. The rear mirror assembly 3 includes a total of 3 optical lenses and 1 concave grating, wherein the 3 lenses are all concave-convex lenses, and the maximum optical aperture of the rear mirror assembly 3 is 60 mm. The maximum outer envelope of the entire optical system is X291mm.

[0047] like Fig. 9 As shown, the electronic focus plane assembly 4 includes a focus panel 41, a processing board 42, a connector 43, an electronic board frame 44, an electronic back cover 45, a focus plane trimming pad 46 and a connector pressure plate 47; the focus panel 41 is arranged on one side of the electronic board frame 44 for arranging the CCD target surface; the processing board 42 is arranged on the other side of the electronic board frame 44 for electronic signal control and transmission; during specific installation, the focus panel 41 is loaded into the electronic board frame 44 from the top, and the processing board 42 is loaded into the electronic board frame 44 from the bottom, and both are fixed with screws. The connector 43 is arranged on the processing board 42 for connecting the data transmission and the electrical signal cable; the connector pressure plate 47 is arranged on the electronic board frame 44 for fixing the position of the connector 43; the electronic rear cover plate 45 is arranged on one side of the processing board 42 and is fixed to the electronic board frame 44 with screws; the focal plane trimming pad 46 is arranged between the electronic component and the box 5 for adjusting the position of the CCD and for trimming the spatial position of the electronic focal plane component 4.

[0048] like Fig.10 and Fig.11 As shown, the box 5 includes a box body 51, a box cover 52 and a box side panel 53; the front telescope group 1 is installed at the front end face flange 511 of the box body 51 through a trimming pad. The precision measuring mirror assembly 6 is installed at the front end face boss 512 of the box body 51 through a trimming pad. The box cover 52 is installed at the upper end face 517 of the box body. The Dyson prism 21 assembly is installed at the bottom mounting surface 515 of the box body 51. The rear mirror assembly 3 is installed at the rear end face 514 of the box body 51 through a trimming pad. The electronic focal plane assembly 4 is installed at the side panel mounting surface of the box 5. Each component is connected to the box 5 by screws, and a mounting lug 513 is provided at the bottom of the box body 51 for connecting with external equipment.

[0049] The precision measuring mirror assembly 6 includes a precision measuring mirror and a precision measuring mirror adhesive seat. The precision measuring mirror is arranged at the front end of the box body 5 through the precision measuring mirror adhesive seat, and is used to adjust the pitch angle and rotation angle of the Dyson prism 21 during system integration. The precision measuring mirror is used to monitor the pitch and azimuth angles of the Dyson prism 21 during system integration, which is convenient for adjustment. It can also be used to adjust the azimuth angle and pitch angle of the spectrometer when the spectrometer is installed on the satellite cabin board to ensure that the slit direction is perpendicular to the satellite flight direction.

Claims

1. A satellite-borne small and lightweight Dyson hyperspectral imaging system, characterized by: It comprises a box body (5), a front telescope assembly (1), a Dyson prism assembly (2), a rear mirror assembly (3), an electronic focal plane assembly (4) and a precision measuring mirror assembly (6); The incident light enters through the front telescope assembly (1), passes through the Dyson prism assembly (2) and the rear mirror assembly (3) in sequence, realizes optical path multiplexing after being reflected by the rear mirror assembly (3), and then forms an image on the electronic focal plane assembly (4) through the rear mirror assembly (3) and the Dyson prism assembly (2); The front telescope group (1) is arranged at the front end of the box (5), and comprises a front lens barrel (110), a front light shield (112), and a plurality of front lens groups; the front light shield (112) is arranged at the front end of the front lens barrel (110) and is used to shield external stray light and improve the imaging quality of the spectrometer; the plurality of front lens groups are arranged in the front lens barrel (110), wherein the last front lens group comprises a glass slit (1091) and a protective glass (1092); the glass slit (1091) is used to form an optical slit to facilitate system imaging, and the protective glass (1092) is used to achieve slit cleanliness; The Dyson prism assembly (2) is arranged in a housing (5), and comprises a Dyson prism (21), a Dyson prism mounting seat (22), and a Dyson prism mounting seat trimming pad (23); the Dyson prism (21) is arranged on the Dyson prism mounting seat (22), and the Dyson prism mounting seat (22) is arranged in the housing (5) via the Dyson prism mounting seat trimming pad (23); the Dyson prism (21) comprises an incident surface (211), an exit surface (212), a transmission surface (213), and A reflection surface (214), the incident surface (211) and the exit surface (212) are arranged vertically, the reflection surface (214) is arranged at 45 degrees to the incident surface (211) and the exit surface (212), and the transmission surface (213) is a curved surface; the incident light is emitted through the incident surface (211) and the transmission surface (213), and after being reflected by the rear mirror component (3) to achieve optical path multiplexing, it is incident on the reflection surface (214) again through the transmission surface (213), and then reflected by the reflection surface (214) to the exit surface (212), and finally imaged on the electronic focal plane component (4); The rear mirror assembly (3) is arranged at the rear end of the box (5), and comprises a rear mirror barrel (305), a concave grating assembly (304) and a plurality of rear mirror groups; the plurality of rear mirror groups are arranged in the rear mirror barrel (305), the concave grating assembly (304) is connected to the rear mirror barrel (305) via a concave grating trimming pad (309), and the concave grating trimming pad (309) is used to adjust the spatial position of the concave grating assembly (304); The precision measuring mirror assembly (6) comprises a precision measuring mirror and a precision measuring mirror bonding seat, wherein the precision measuring mirror is arranged at the front end of the box (5) via the precision measuring mirror bonding seat and is used to adjust the pitch angle and rotation angle of the Dyson prism (21) during system integration.

2. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 1, characterized in that: The electronic focal plane assembly (4) is arranged in a housing (5), and comprises a focal plane panel (41), a processing board (42), a connector (43), an electronic board frame (44), an electronic rear cover (45), a focal plane trimming pad (46) and a connector pressure plate (47); the focal plane panel (41) is arranged on one side of the electronic board frame (44) for arranging a CCD target surface; the processing board (42) is arranged on the other side of the electronic board frame (44) for electronic signal control and transmission; the connector (43) is arranged on the processing board (42) for connecting a data transmission cable with an electrical signal cable; the connector pressure plate (47) is arranged on the electronic board frame (44) for fixing the position of the connector (43); the electronic rear cover (45) is arranged on one side of the processing board (42); the focal plane trimming pad (46) is arranged between the electronic board frame (44) and the housing (5) for adjusting the position of the CCD.

3. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 2 is characterized in that: The front lens barrel (110) is provided with a glue injection hole (1101) for fixing the front lens group.

4. The satellite-borne small and lightweight Dyson hyperspectral imager system according to claim 1, 2 or 3, characterized in that: The front lens barrel (110) is provided with an exhaust groove (1102) to facilitate the exhaust of internal gas of the front telescope assembly (1) when it is used in a vacuum.

5. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 4, characterized in that: The plurality of front lens groups include a front lens group one (101), a front lens group two (102), a front lens group three (103), a front lens group four (104), a front lens group five (105), a front lens group six (106), a front lens group seven (107), a front lens group eight (108) and a front lens group nine (109) which are arranged in sequence; a spacer is arranged between each front lens group, and the spacing between each front lens group is ensured by adjusting the thickness of the spacer, and each front lens group is pressed tightly in a front lens barrel (110) by a front left outer pressure ring (113) and a front right outer pressure ring (111); at the same time, the lens in each front lens group is fixed in a lens frame after glue is applied on the circumference.

6. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 5, characterized in that: The front lens group is provided with a flange mounting hole (1103) for connecting the front lens group to the box (5).

7. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 6, characterized in that: The Dyson prism mounting seat (22) is provided with a plurality of process holes (221) for ensuring the bonding position accuracy of the Dyson prism (21).

8. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 7, characterized in that: The Dyson prism mounting seat (22) is provided with a glue overflow groove (222) for collecting overflow of epoxy glue.

9. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 8, characterized in that: The box body (5) comprises a box body main body (51), a box body cover plate (52) and a box body side plate (53); the box body cover plate (52) is arranged above the box body main body (51), and the box body side plate (53) is arranged on the side of the box body main body (51); The front telescope assembly (1) is mounted on the front face flange (511) of the box body (51) through a trimming pad; the precision measuring mirror assembly (6) is mounted on the front face boss (512) of the box body (51) through a trimming pad; the Dyson prism (21) assembly is mounted on the bottom mounting surface (515) of the box body (51); the rear mirror assembly (3) is mounted on the rear face (514) of the box body (51) through a trimming pad; and the electronic focal plane assembly (4) is mounted on the side panel mounting surface (518) of the box body (5).

10. The satellite-borne small and lightweight Dyson hyperspectral imaging system according to claim 9, characterized in that: The distance between the glass slit (1091) and the front end face of the Dyson prism (21) is 17.66 mm, and the distance between the system image plane position and the emission end face of the Dyson prism (21) is 6 mm.

Images