CN113155285A - Satellite-borne small-sized lightweight Dyson hyperspectral imager system - Google Patents

Abstract

The invention provides a satellite-borne small-sized lightweight Dyson hyperspectral imager system, which solves the problem that the conventional Dyson prototype spectrometer is difficult to carry out structural layout and engineering development due to excessively compact structure. The system comprises a box body, a front telescope group, a Dyson prism group, a rear mirror assembly, an electronic focal plane assembly and a precision measurement mirror assembly; incident light enters through the front telescope group, sequentially passes through the Dyson prism lens group and the rear mirror group, is reflected by the rear mirror group to realize light path multiplexing, and is imaged on the electronic focal plane assembly through the rear mirror group and the Dyson prism lens group. The system can realize the separation of the object plane and the image plane, and is easy to realize the structural layout and the engineering development.

Description

Satellite-borne small-sized lightweight Dyson hyperspectral imager system

Technical Field

The invention belongs to the field of satellite-borne hyperspectral imaging, and particularly relates to a satellite-borne small and light Dyson hyperspectral imager system.

Background

The spectral imager can realize spectral imaging, can detect two-dimensional space information and one-dimensional spectral information simultaneously, has the functions of qualitative measurement and quantitative analysis while performing timing and positioning measurement, and can be applied to the fields of material detection, target identification, component analysis, process monitoring and the like. Compared with a ground spectrometer and an airborne spectrometer, the spaceborne hyperspectral imager can realize normalized, large-breadth and high-revisitation rate detection, and is widely applied to the fields of military affairs, agriculture, oceanography, geography and the like.

With the continuous development of the aerospace platform cubstar and the micro-nano star, the requirements on the volume and the weight of the carried optical load are smaller and smaller, so that the technology of a miniaturized and high-performance hyperspectral imager is urgently needed. The Dyson spectrometer has the advantage of recycling because the light path returns in the system, so that the system has compact structure, small volume and light weight and is convenient to realize miniaturization. In addition, the Dyson spectrometer still keeps good concentricity as a whole, has good aberration characteristics, is easy to realize large field of view and large relative aperture, and can realize higher detection sensitivity, so the Dyson spectrometer has obvious advantages in the technical system of the satellite-borne spectrometer with miniaturization, light weight and high performance.

However, the prototype of the spectrometer based on the Dyson structure consists of a plano-convex lens, a concave grating, an incident slit and a detector. Wherein the entrance slit and the detector receiving surface are both located on the plane of the plano-convex lens. In the engineering realization of the spectrometer prototype with the Dyosn structure, due to the excessively compact system structure, the space of the spectrometer with the slit assembly, the front telescope group, the detector and the optical element is difficult to arrange and is easy to interfere.

Disclosure of Invention

The invention aims to solve the problem that the conventional Dyson prototype spectrometer is too compact in structure and difficult to perform structural layout and engineering development, and provides a satellite-borne small-size light-weight Dyson hyperspectral imager system which can realize separation of an object plane and an image plane and is easy to realize structural layout and engineering development.

In order to achieve the purpose, the invention adopts the following technical scheme:

a satellite-borne small-sized lightweight Dyson hyperspectral imager system comprises a box body, a front telescope group, a Dyson prism group, a rear mirror assembly, an electronic focal plane assembly and a precision measurement mirror assembly; incident light is incident through the front telescope group, sequentially passes through the Dyson prism lens group and the rear mirror group, is reflected by the rear mirror group to realize light path multiplexing, and is imaged on the electronic focal plane component through the rear mirror group and the Dyson prism lens group; the front telescope group is arranged at the front end of the box body and comprises a front lens cone, a front lens hood and a plurality of groups of front telescope groups; the front lens hood is arranged at the front end of the front lens barrel and used for shielding external stray light and improving the imaging quality of the spectrometer; the multiple groups of front lens groups are arranged in the front lens cone, wherein the last group of front lens groups comprises a glass slit and protective glass, the glass slit is used for forming an optical slit, system imaging is facilitated, and the protective glass is used for realizing slit cleanliness; the Dyson prism lens group is arranged in the box body and comprises a Dyson prism, a Dyson prism mounting seat and a Dyson prism mounting seat trimming pad; the Dyson prism is arranged on the Dyson prism mounting seat, and the Dyson prism mounting seat is arranged in the box body through a trimming pad of the Dyson prism mounting seat; the Dyson prism comprises an incident surface, an emergent surface, a transmission surface and a reflection surface, wherein the incident surface and the emergent surface are vertically arranged, the reflection surface is arranged at an angle of 45 degrees with the incident surface and the emergent surface, and the transmission surface is a curved surface; the incident light is emitted through the incident surface and the transmission surface, the light path multiplexing is realized after the reflection of the rear mirror assembly, the incident light is emitted to the reflection surface through the transmission surface again, then the incident light is reflected to the emitting surface through the reflection surface, and finally the image is formed on the electronic focal plane assembly; the rear lens assembly is arranged at the rear end of the box body and comprises a rear lens cone, a concave grating assembly and a plurality of groups of rear lens groups; the plurality of groups of rear lens groups are arranged in the rear lens cone, the concave grating component is connected with the rear lens cone through a concave grating trimming pad, and the concave grating trimming pad is used for adjusting the spatial position of the concave grating component; the accurate measurement mirror assembly comprises an accurate measurement mirror and an accurate measurement mirror bonding seat, wherein the accurate measurement mirror is arranged at the front end of the box body through the accurate measurement mirror bonding seat and used for adjusting the pitching angle and the rotating angle of the Dyson prism during system integration.

Furthermore, the electronic focal plane assembly is arranged in the box body and comprises a focal plane plate, a processing plate, a connector, an electronic plate frame, an electronic rear cover plate, a focal plane trimming pad and a connector pressing plate; the focal plane is arranged on one side of the electronics plate frame and used for arranging the CCD target surface; the processing board is arranged on the other side of the electronic board frame and is used for controlling and transmitting electronic signals; the connector is arranged on the processing board and used for connecting a data transmission cable with an electric signal cable; the connector pressing plate is arranged on the frame of the electronics plate and used for fixing the position of the connector; the electronic rear cover plate is arranged on one side of the processing plate; the focal plane trimming pad is arranged between the electronic component and the box body and used for adjusting the position of the CCD.

Furthermore, the front lens cone is provided with a glue injection hole for fixing the front lens group.

Furthermore, an exhaust groove is formed in the front lens cone, so that internal gas of the front telescope group can be conveniently exhausted in vacuum use.

Further, the multiple groups of front lens groups comprise a first front lens group, a second front lens group, a third front lens group, a fourth front lens group, a fifth front lens group, a sixth front lens group, a seventh front lens group, an eighth front lens group and a ninth front lens group which are sequentially arranged; and a spacing ring is arranged between the front lens groups, the spacing of the front lens groups is ensured by repairing and grinding the thickness of the spacing ring, the front lens groups are tightly pressed in the front lens cone through a front left outer pressing ring and a front right outer pressing ring, and simultaneously, lenses in the front lens groups are fixed in the lens cone through the pressing rings after glue is coated on the circumference.

Furthermore, the front lens group is provided with a flange mounting hole for connecting the front lens group with the box body.

Furthermore, a plurality of process holes are formed in the Dyson prism mounting base and used for guaranteeing the bonding position accuracy of the Dyson prism.

Furthermore, an overflow groove is arranged on the Dyson prism mounting base and used for adhering overflow of epoxy glue.

Further, the box body comprises a box body main body, a box body cover plate and a box body side plate; the box body cover plate is arranged above the box body main body, and the box body side plate is arranged on the side surface of the box body main body; the front telescope group is arranged at a flange on the front end surface of the box body through a trimming pad; the precision measuring mirror assembly is arranged at a boss on the front end face of the box body through a trimming pad; the Dyson prism assembly is arranged on a bottom mounting surface of the box body; the rear mirror assembly is arranged on the rear end face of the box body main body through a trimming pad; the electronic focal plane assembly is arranged on the side plate mounting surface of the box body.

Further, the distance between the glass slit and the front end face of the Dyson prism is 17.66mm, and the distance between the position of a system image plane and the emergent end face of the Dyson prism is 6 mm.

Compared with the prior art, the invention has the following beneficial effects:

1. the optical system of the Dyson spectrometer can realize object plane-image plane separation, and overcomes the difficulty that the Dyson prototype spectrometer is difficult to carry out structural layout and engineering development due to over compact structure.

2. The spectrometer system of the invention designs the front telescope objective and has high resolution imaging performance. The idea of adopting optical slit light transmission, metal structural member shielding and protective glass sealing protection is firstly proposed in the front lens group slit component, so that the processing and design difficulty of the slit component is reduced. In addition, the structural design of the front lens group can easily realize the prefabrication and the grinding of the vacuum image surface at one-time image surface position, and the on-orbit high-quality imaging performance is ensured.

3. According to the satellite-borne small-sized lightweight Dyson hyperspectral imager system, each component adopts a modular design idea, and each component can be independently assembled and then integrated on the box body.

4. When all components of the satellite-borne small-sized lightweight Dyson hyperspectral imager system are assembled and adjusted, all the components are provided with a plurality of adjustable links, the spatial position of all the optical components can be adjusted, high-quality imaging is realized, and the satellite-borne small-sized lightweight Dyson hyperspectral imager system can be effectively applied to engineering application.

5. The satellite-borne small-sized light-weight Dyson hyperspectral imager system is reasonable in structural layout, compact in size and low in weight. The spectrometer is suitable for visible spectrum, the focal length is 55mm, the relative aperture is not less than 1/2.2, the effective field angle is not less than 11.42 degrees, the ground resolution is 100m, and the weight of the whole spectrometer is not more than 2.5 Kg. The first-order mode of the whole machine is larger than 600Hz, and the mechanical stability is good.

Drawings

FIG. 1 is a three-dimensional schematic diagram of a satellite-borne small-sized lightweight Dyson hyperspectral imager system of the invention;

FIG. 2 is a three-dimensional schematic view of a hyperspectral imager system of the invention (with the cover plate of the box removed);

FIG. 3 is a schematic view of the optical system of the Dyson hyperspectral imager of the invention;

FIG. 4 is a schematic structural diagram of a front telescope group according to the present invention;

FIG. 5 is a schematic structural diagram of a front lens group nine according to the present invention;

FIG. 6 is a schematic structural diagram of a front lens barrel according to the present invention;

fig. 7 is a schematic structural view of a Dyson prism assembly of the present invention;

FIG. 8 is a schematic view of the rear mirror assembly of the present invention;

FIG. 9 is a schematic view of the electronic focal plane assembly of the present invention;

FIG. 10 is a schematic structural view of the case of the present invention;

FIG. 11 is a schematic structural view of the main body of the container of the present invention;

fig. 12 is a schematic structural view of a Dyson prism of the present invention.

Reference numerals: 1-front telescope group, 2-Dyson prism group, 3-rear mirror group, 4-electronic focal plane group, 5-box, 6-precision mirror group, 101-front mirror group I, 102-front mirror group II, 103-front mirror group III, 104-front mirror group IV, 105-front mirror group V, 106-front mirror group VI, 107-front mirror group VII, 108-front mirror group VIII, 109-front mirror group VII, 110-front lens cone, 111-front right outer pressing ring, 112-front light shield, 113-front left outer pressing ring, 114-front spacer ring II, 115-front spacer ring III, 116-front spacer ring IV, 117-front spacer ring V, 118-front spacer ring VI, 119-front spacer ring VII, 120-front spacer ring VIII, 121-a front diaphragm ring nine, 1091-a glass slit, 1092-protective glass, 1093-a mirror frame with a mirror assembly nine, 1094-a slit protective device, 1095-a pressing ring with a mirror assembly nine, 1101-a glue injection hole, 1102-an exhaust groove, 1103-a flange mounting hole, 21-a Dyson prism, 22-a Dyson prism mounting seat, 23-a Dyson prism mounting seat trimming pad, 211-an incident surface, 212-an emergent surface, 213-a transmission surface, 214-a reflection surface, 221-a process hole, 222-a glue overflow groove, 301-a rear mirror assembly one, 302-a rear mirror assembly two, 303-a rear mirror assembly three, 304-a concave grating assembly, 305-a rear lens barrel, 306-a rear mirror assembly pressing ring, 307-a rear diaphragm ring one, 308-a rear diaphragm ring two, 309-a concave grating trimming pad, 310-rear end cover, 41-focal plane plate, 42-processing plate, 43-connector, 44-electronics plate frame, 45-electronics rear cover plate, 46-focal plane trimming pad, 47-connector pressing plate, 51-box body, 52-box cover plate, 53-box side plate, 511-front end flange, 512-front end boss, 513-mounting lug, 514-rear end face, 515-bottom mounting face, 516-box side mounting face, 517-upper end face and 518-side plate mounting face.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

The invention provides a satellite-borne small-size light-weight Dyson hyperspectral imager system, which realizes the separation of an object plane and an image plane of an optical system through the optical optimization design of a Dyson prism and a rear mirror assembly, avoids the defect that an optical support structure is difficult to arrange due to the coincidence of the object plane and the image plane, and is easy for engineering development.

As shown in fig. 1 and 2, the satellite-borne small-sized and light-weight Dyson hyperspectral imager system comprises afront telescope group 1, a Dyson prism group 2, a rear mirror assembly 3, an electronicfocal plane assembly 4, abox body 5 and a precision mirror assembly 6. As shown in fig. 3, the working principle of the optical system of the satellite-borne small and light Dyson hyperspectral imager of the invention is as follows: incident light enters the spectrometer system through thefront telescope group 1, then sequentially passes through the Dyson prism lens group 2 and the rear mirror group 3, is reflected by the last concave grating of the rear mirror group 3 to realize light path multiplexing, and then is imaged on the electronicfocal plane component 4 through the rear mirror group 3 and the Dyson prism lens group 2.

As shown in fig. 4, thefront telescope group 1 of the present invention is disposed at the front end of thebox 5, and includes afront lens cone 110, afront lens hood 112 and a plurality of front telescope groups; thefront light shield 112 is arranged at the front end of thefront lens barrel 110 and used for shielding external stray light and improving the imaging quality of the spectrometer; the multiple groups of front lens sets are arranged in thefront lens barrel 110, wherein the last group of front lens sets comprises aglass slit 1091 and aprotective glass 1092, theglass slit 1091 is used for forming an optical slit, which is convenient for imaging the system, and theprotective glass 1092 is used for realizing the cleanliness of the slit and preventing dust falling at the slit from causing redundancy and influencing imaging. Specifically, the fronttelescopic mirror group 1 of the present invention includes nine mirror groups, which are a front mirror group one 101, a front mirror group two 102, a front mirror group three 103, a front mirror group four 104, a front mirror group five 105, a front mirror group six 106, a front mirror group seven 107, a front mirror group eight 108, and a front mirror group nine 109. When the lens of each preposed lens group is arranged in each lens component frame, XM-31 glue is needed to be coated on the circumference of the lens, and then each lens component pressing ring is screwed in for fixing. And each lens component ensures that the axes of each optical element and each lens group and each lens frame are superposed through centering processing. And space rings are arranged among the lens assemblies, and the space between the optical elements is ensured by repairing and grinding the thickness of the space rings. When the lens is installed, a front lens group eight 108, a front spacer ring eight 120, a front lens group seven 107, a front spacer ring seven 119, a front lens group six 106, a front spacer ring six 118, a front lens group five 105, a front spacer ring five 117, a front lens group four 104, a front spacer ring four 116, a front lens group three 103, a front spacer ring three 115, a front lens group two 102, a front spacer ring two 114 and a front lens group one 101 are sequentially arranged in thefront lens cone 110, a front left outerpressing ring 113 is arranged to tightly press and fix the lens groups, a front spacer ring nine 121 and a front lens group nine 109 are arranged in thefront lens cone 110 from the right side, and the front right outerpressing ring 111 is tightly pressed and fixed.

As shown in fig. 5, the front lens group nine 109 is the last front lens group, and specifically includes aglass slit 1091, aprotection glass 1092, a lens group nineframe 1093, aslit protection device 1094, and a lens group ninepress ring 1095. Theglass slit 1091 is placed in the mirror assembly nine-lens frame 1093, and then theslit protector 1094, and then theprotective glass 1092, and then the mirror assembly nine-pressingring 1095 is tightened to press and fix the components. Theslit protector 1094 is a window with a size larger than that of the optical slit, and is used for preventing stray light and slit dust.

As shown in fig. 6, thefront lens barrel 110 is provided with a glue injection hole 1101 for fixing each lens group. Thefront lens barrel 110 is further provided with anexhaust groove 1102 for exhausting internal gas of the front lens group during vacuum use. The front lens group is provided with aflange mounting hole 1103 for connecting the front lens group with thebox body 5. Because the Dyson spectrometer needs to perform vacuum image plane prefabrication and determines the image plane position of the front lens group for the first time and the second time, after the front lens group is installed, XM-31 glue is injected into the positions from the firstfront lens group 101 to the eighthfront lens group 108 on the glue injection hole 1101 of thefront lens cone 110 for fixing. The front lens group nine 109 needs vacuum image surface prefabrication test, and the front space ring nine 121 is repaired and ground and then glue injection fixation is carried out. The vacuum image plane prefabrication refers to that when the lens group is tested in air and in space, the optical transmission medium changes, so that the optical path changes, the position of the image plane of the lens group needs to be adjusted, and the size of a trimming pad between the lens groups is determined by testing the difference between the distance of the image plane position and the position of the image plane measured in air in a vacuum environment.

As shown in fig. 7, theDyson prism 21 assembly includes aDyson prism 21, aDyson prism mount 22, and a Dyson prismmount trimming pad 23; the Dyson prism is fixed to the Dyson prism mount 22 by means of epoxy adhesive. The Dysonprism mounting base 22 is provided with threeprocess holes 221 for ensuring the accuracy of the bonding position of theDyson prism 21, and standard pins are mounted on the process holes 221, and the circumferential surfaces of the standard pins are used as the leaning surfaces of theDyson prism 21 during bonding, so that the azimuth angle of theDyson prism 21 during bonding is ensured. TheDyson prism mount 22 is provided with anoverflow groove 222 for the overflow of the bonding epoxy glue.

As shown in fig. 12, theDyson prism 21 of the present invention may specifically include anincident surface 211, anexit surface 212, atransmission surface 213, and areflection surface 214, where theincident surface 211 and theexit surface 212 are vertically disposed, thereflection surface 214 is disposed at 45 degrees with respect to theincident surface 211 and theexit surface 212, and thetransmission surface 213 is a curved surface; the incident light is emitted through theincident surface 211 and thetransmission surface 213, reflected by the rear mirror assembly 3, and then is reflected to thereflection surface 214 through thetransmission surface 213 after the optical path multiplexing is realized, and then is reflected to theemission surface 212 through thereflection surface 214, and finally is imaged on the electronicfocal plane assembly 4.

The specific design process of theDyson prism 21 is as follows: 1) on the basis of a Dyson hyperspectral imager prototype, an image surface and an object surface of a spectrometer are forcibly pulled out of the surface of a plano-convex lens, and meanwhile, a meniscus lens is added to correct the aberration; 2) the separation design of an object plane and an image plane is forced, aberration is corrected through the meniscus lens and the Dyson structure in an overall optimization mode, wherein the separation distance between the image plane and the object plane is determined by the light transmission caliber when incident light reaches the convex surface of theDyson prism 21; 3) a45-degree reflecting surface is added on the plano-convex lens, so that the emergent light is vertical to the optical axis of the incident light. The exit surface and the entrance surface of the Dyson prism are also vertical, and the separation distance between the object plane and the image plane in the second step is ensured. After the light is converted, the emergent surface is lower than the bottom end of the light-transmitting aperture on the convex surface of the plano-convex lens, so that the defect that an optical supporting structure is difficult to arrange is overcome, and engineering development is easy. After the design of the three steps, the final form of the Dyson lens is that the external shape in the system comprises three planes and a convex surface. The difference between theDyson prism 21 provided by the invention and the existing prism is as follows: the reflecting surface keeps a standard angle of 45 degrees with theincident surface 211 and theemergent surface 212, and is easy to process and test. The integral flatness, the integral smoothness and the included angle between planes are easy to ensure; the aerospace common fixing mode of the prism is glue bonding, theDyson prism 21 has two surfaces which are perpendicular to each other, the azimuth angle of the prism is easy to guarantee during bonding, and the difficulty of assembly and adjustment can be reduced.

As shown in fig. 8, the rear mirror assembly 3 includes a firstrear mirror group 301, a secondrear mirror group 302, a thirdrear mirror group 303 and a concavegrating assembly 304, which are sequentially disposed; when each lens is arranged in each lens component frame, XM-31 glue is needed to be coated on the circumference of the lens, and then each lens component clamping ring is screwed for fixing. And each lens component ensures that the axes of each optical element and each lens frame of each lens group are reset through centering processing. And space rings are arranged among the lens assemblies, and the space between the optical elements is ensured by repairing and grinding the thickness of the space rings. When the lens is installed, the rear lens group three 303, the rear spacer ring two 308, the rear lens group two 302, the rear spacer ring one 307 and the rear lens group one 301 are sequentially installed in therear lens barrel 305, and then the rear lensassembly pressing ring 306 is installed and screwed down for fixing. In order to adjust the spatial position of the concave grating, the concavegrating assembly 304 is used as a separate assembly, and is connected with therear lens barrel 305 through the concavegrating trimming pad 309 by screws, and the rear end is connected with therear end cap 310 by threads for protecting the optical elements. The concavegrating assembly 304 adjusts its spatial position by the amount of concavegrating trim pads 309 and screw through holes.

Thefront telescope group 1 of the invention totally comprises 10 optical lenses, the maximum optical aperture is 32mm, the ninth lens in the front telescope group is an optical slit, the distance from the optical slit to the front end face of aDyson prism 21 is 17.66mm, the distance from the system image surface position to the emergent end face of theDyson prism 21 is 6mm, the rear telescope group 3 totally comprises 3 optical lenses and 1 concave grating, wherein 3 lenses are concave-convex lenses, and the maximum optical aperture of the rear telescope group 3 is 60 mm. The maximum outer envelope of the entire optical system is

X291mm。

As shown in fig. 9, the electronicsfocal plane assembly 4 includes afocal plane plate 41, aprocessing plate 42, aconnector 43, anelectronics frame 44, an electronicsback cover plate 45, a focalplane trim pad 46, and a connector hold downplate 47; thefocal plane plate 41 is arranged on one side of theelectronics plate frame 44 and is used for arranging the CCD target surface; theprocessing board 42 is arranged on the other side of theelectronics board frame 44 and is used for controlling and transmitting electronic signals; specifically, thefocal plane 41 is mounted on theframe 44 from above, and theprocessing plate 42 is mounted on theframe 44 from below, both of which are fixed by screws. Theconnector 43 is arranged on theprocessing board 42 and is used for connecting a data transmission cable with an electric signal cable; theconnector pressing plate 47 is arranged on theframe 44 of the electronics board and used for fixing the position of theconnector 43; the electronicrear cover plate 45 is arranged on one side of theprocessing plate 42 and is fixedly connected with theelectronic plate frame 44 by screws; the focalplane trimming pad 46 is disposed between the electronic component and thehousing 5 for adjusting the position of the CCD and for trimming the spatial position of the electronicfocal plane component 4.

As shown in fig. 10 and 11, thecase 5 includes a casemain body 51, acase cover 52, and acase side plate 53; thefront telescope group 1 is mounted on afront end flange 511 of thebox body 51 via a trimming pad. The precision mirror assembly 6 is mounted on aboss 512 on the front end face of thebox body 51 through a trimming pad. The case cover 52 is mounted at theupper end surface 517 of the case body. TheDyson prism 21 assembly is mounted at thebottom mounting surface 515 of the cabinetmain body 51. The rear mirror assembly 3 is mounted at therear end surface 514 of the cabinetmain body 51 via a trimming pad. The electronicfocal plane assembly 4 is mounted at a side plate mounting surface of thecabinet 5. The components are connected with thebox body 5 by screws, and the bottom of thebox body 51 is provided with a mountinglug 513 for connecting with external equipment.

The accurate measurement mirror assembly 6 comprises an accurate measurement mirror and an accurate measurement mirror bonding seat, wherein the accurate measurement mirror is arranged at the front end of thebox body 5 through the accurate measurement mirror bonding seat and used for adjusting the pitching angle and the rotating angle of theDyson prism 21 during system integration. The accurate measurement mirror is used for monitoring the pitching and azimuth angles of theDyson prism 21 during system integration, is convenient to adjust, and can be used for adjusting the azimuth angle and the pitching angle of the whole spectrometer when the spectrometer is installed on a satellite cabin plate, so that the slit direction is perpendicular to the satellite flight direction.

Claims (10)

Translated fromChinese

1.一种星载小型轻量化Dyson高光谱成像仪系统，其特征在于：包括箱体(5)、前置望远镜组(1)、Dyson棱镜镜组(2)、后置镜组件(3)、电子学焦面组件(4)和精测镜组件(6)；1. A space-borne small and lightweight Dyson hyperspectral imager system, characterized in that: comprising a box (5), a front telescope group (1), a Dyson prism group (2), a rear mirror assembly (3) , an electronic focal plane assembly (4) and a precision measuring mirror assembly (6);入射光经前置望远镜组(1)入射，依次通过Dyson棱镜镜组(2)和后置镜组件(3)，经后置镜组件(3)反射后实现光路复用，再通过后置镜组件(3)和Dyson棱镜镜组(2)成像于电子学焦面组件(4)；The incident light is incident through the front telescope group (1), passes through the Dyson prism group (2) and the rear mirror assembly (3) in turn, is reflected by the rear mirror assembly (3) to realize optical path multiplexing, and then passes through the rear mirror The component (3) and the Dyson prism group (2) are imaged on the electronic focal plane component (4);所述前置望远镜组(1)设置在箱体(5)的前端，包括前置镜筒(110)、前部遮光罩(112)和多组前置镜组；所述前部遮光罩(112)设置在前置镜筒(110)前端，用于遮挡外部杂散光，提高光谱仪成像质量；多组前置镜组设置在前置镜筒(110)内，其中最后一组前置镜组包括玻璃狭缝(1091)和保护玻璃(1092)，玻璃狭缝(1091)用于形成光学狭缝，便于系统成像，保护玻璃(1092)用于实现狭缝清洁度；The front telescope group (1) is arranged at the front end of the box body (5), and includes a front lens barrel (110), a front hood (112) and multiple groups of front mirror groups; the front hood (112) 112) is arranged at the front end of the front lens barrel (110) 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 Including 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;所述Dyson棱镜镜组(2)设置在箱体(5)内，包括Dyson棱镜(21)、Dyson棱镜安装座(22)和Dyson棱镜安装座修切垫(23)；所述Dyson棱镜(21)设置在Dyson棱镜安装座(22)上，所述Dyson棱镜安装座(22)通过Dyson棱镜安装座修切垫(23)设置在箱体(5)内；所述Dyson棱镜(21)包括入射面(211)、出射面(212)、透射面(213)和反射面(214)，所述入射面(211)、出射面(212)垂直设置，所述反射面(214)均与入射面(211)、出射面(212)呈45度设置，所述透射面(213)为曲面；入射光通过入射面(211)、透射面(213)出射，经后置镜组件(3)反射后实现光路复用后再次通过透射面(213)入射至反射面(214)，然后通过反射面(214)反射至出射面(212)，最后成像于电子学焦面组件(4)；The Dyson prism group (2) is arranged in the box body (5) and includes 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 box body (5) through the Dyson prism mounting seat trimming pad (23); the Dyson prism (21) includes an incident surface (211), exit surface (212), transmission surface (213) and reflection surface (214), the entrance surface (211) and exit surface (212) are vertically arranged, and the reflecting surface (214) is both connected to the entrance surface (211), the exit surface (212) is set at 45 degrees, and the transmission surface (213) is a curved surface; the incident light exits through the incident surface (211) and the transmission surface (213), and is reflected by the rear mirror assembly (3) After realizing the optical circuit multiplexing, it is incident on the reflection surface (214) through the transmission surface (213) again, and then reflected to the exit surface (212) through the reflection surface (214), and finally imaged on the electronic focal plane assembly (4);所述后置镜组件(3)设置在箱体(5)的后端，包括后置镜筒(305)、凹面光栅组件(304)和多组后置镜组；多组后置镜组设置在后置镜筒(305)内，所述凹面光栅组件(304)通过凹面光栅修切垫(309)与后置镜筒(305)连接，凹面光栅修切垫(309)用于调节凹面光栅组件(304)的空间位置；The rear mirror assembly (3) is arranged at the rear end of the box body (5), and includes a rear lens barrel (305), a concave grating assembly (304) and multiple groups of rear mirrors; the multiple groups of rear mirrors are arranged In the rear lens barrel (305), the concave grating assembly (304) is connected to the rear lens barrel (305) through a concave grating trimming pad (309), and the concave grating trimming pad (309) is used to adjust the concave grating the spatial location of the component (304);所述精测镜组件(6)包括精测镜和精测镜粘接座，所述精测镜通过精测镜粘接座设置在箱体(5)的前端，用于系统集成时调整Dyson棱镜(21)的俯仰角度与旋转角度。The fine-measuring mirror assembly (6) includes a fine-gauge mirror and a fine-gauge mirror bonding seat, and the fine-gauge mirror is arranged on the front end of the box body (5) through the fine-gauge mirror bonding seat, and is used for adjusting the Dyson during system integration. The pitch angle and rotation angle of the prism (21).2.根据权利要求1所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述电子学焦面组件(4)设置在箱体(5)内，包括焦面板(41)、处理板(42)、接插件(43)、电子学板框(44)、电子学后盖板(45)、焦面修切垫(46)和接插件压板(47)；所述焦面板(41)设置在电子学板框(44)的一侧，用于布置CCD靶面；所述处理板(42)设置在电子学板框(44)的另一侧，用于电子学信号控制与传输；所述接插件(43)设置在处理板(42)上，用于数传与电信号线缆的接通；所述接插件压板(47)设置在电子学板框(44)上，用于接插件(43)位置的固定；所述电子学后盖板(45)设置在处理板(42)的一侧；所述焦面修切垫(46)设置在电子学板框(44)与箱体(5)间，用于调整CCD的位置。2. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 1, wherein the electronic focal plane assembly (4) is arranged in the box (5) and includes a focal plane (41) , a processing board (42), a connector (43), an electronics board frame (44), an electronics rear cover (45), a focal plane trimming pad (46) and a connector pressing plate (47); the focal panel (41) is arranged on one side of the electronics board frame (44) for arranging the CCD target surface; the processing board (42) is arranged on the other side of the electronics board frame (44) for electronic signal control and transmission; the connector (43) is arranged on the processing board (42) for connecting data transmission and electrical signal cables; the connector pressing plate (47) is arranged on the electronics board frame (44) , used for fixing the position of the connector (43); the electronics rear cover plate (45) is arranged on one side of the processing board (42); the focal plane trimming pad (46) is arranged on the electronics board frame (46). 44) and the box (5), used to adjust the position of the CCD.3.根据权利要求2所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述前置镜筒(110)上设置有注胶孔(1101)，用于固定前置镜组。3. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 2, wherein the front lens barrel (110) is provided with a glue injection hole (1101) for fixing the front lens Group.4.根据权利要求1或2或3所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述前置镜筒(110)上设置有排气槽(1102)，便于前置望远镜组(1)在真空使用中内部气体的排出。4. The spaceborne 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), which is convenient for the front lens barrel (110). Set the exhaust of the internal gas of the telescope group (1) in vacuum use.5.根据权利要求4所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：多组前置镜组包括依次设置的前置镜组一(101)、前置镜组二(102)、前置镜组三(103)、前置镜组四(104)、前置镜组五(105)、前置镜组六(106)、前置镜组七(107)、前置镜组八(108)和前置镜组九(109)；各前置镜组之间设置有隔圈，通过修研隔圈厚度保证各前置镜组的间隔，且各前置镜组通过前置左外压圈(113)和前置右外压圈(111)压紧在前置镜筒(110)内，同时，各前置镜组中的透镜在圆周涂抹胶后再固定在镜框内。5. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 4, wherein the multiple groups of front mirror groups comprise a front mirror group one (101) and a front mirror group two (101) arranged in sequence. 102), front mirror group three (103), front mirror group four (104), front mirror group five (105), front mirror group six (106), front mirror group seven (107), front mirror group Mirror group eight (108) and front mirror group nine (109); spacers are arranged between each front mirror group, and the thickness of the spacer ring is repaired to ensure the interval of each front mirror group, and each front mirror group passes through The front left outer pressure ring (113) and the front right outer pressure ring (111) are pressed in the front lens barrel (110). At the same time, the lenses in each front lens group are glued on the circumference and then fixed on the frame Inside.6.根据权利要求5所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述前置镜组设置有法兰安装孔(1103)，用于前置镜组与箱体(5)连接。6. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 5, wherein the front mirror group is provided with a flange mounting hole (1103) for the front mirror group and the box body (5) Connection.7.根据权利要求6所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述Dyson棱镜安装座(22)上设置有多个工艺孔(221)，用于保证Dyson棱镜(21)的粘接位置精度。7. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 6, characterized in that: the Dyson prism mount (22) is provided with a plurality of process holes (221) for ensuring the Dyson prism (21) The bonding position accuracy.8.根据权利要求7所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述Dyson棱镜安装座(22)上设置有溢胶槽(222)，用于粘接环氧胶的溢出。8. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 7, characterized in that: the Dyson prism mount (22) is provided with an overflow groove (222) for bonding epoxy resin Glue spillage.9.根据权利要求8所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述箱体(5)包括箱体主体(51)、箱体盖板(52)和箱体侧板(53)；所述箱体盖板(52)设置在箱体主体(51)的上方，所述箱体侧板(53)设置在箱体主体(51)的侧面；9 . The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 8 , wherein the box body ( 5 ) comprises a box body body ( 51 ), a box body cover plate ( 52 ) and a box body a side plate (53); the box cover plate (52) is arranged above the box body (51), and the box body side plate (53) is arranged on the side surface of the box body (51);所述前置望远镜组(1)通过修切垫安装于箱体主体(51)的前端面法兰(511)处；所述精测镜组件(6)通过修切垫安装于箱体主体(51)的前端面凸台(512)处；所述Dyson棱镜(21)组件安装于箱体主体(51)的底部安装面(515)上；所述后置镜组件(3)通过修切垫安装于箱体主体(51)的后端面(514)上；所述电子学焦面组件(4)安装于箱体(5)的侧板安装面(518)上。The front telescope group (1) is mounted on the front-end face flange (511) of the box body (51) through a trimming pad; the precision measuring mirror assembly (6) is mounted on the box body (511) through a trimming pad. 51) at the front boss (512); the Dyson prism (21) assembly is mounted on the bottom mounting surface (515) of the box body (51); the rear mirror assembly (3) passes through the trim pad The electronic focal plane assembly (4) is mounted on the side plate mounting surface (518) of the box body (5).10.根据权利要求9所述的星载小型轻量化Dyson高光谱成像仪系统，其特征在于：所述玻璃狭缝(1091)距离Dyson棱镜(21)前端面距离为17.66mm，系统像面位置距离Dyson棱镜(21)出射端面距离为6mm。10. The spaceborne small and lightweight Dyson hyperspectral imager system according to claim 9, wherein the distance between the glass slit (1091) and the front end surface of the Dyson prism (21) is 17.66mm, and the system image plane position The distance from the exit end face of the Dyson prism (21) is 6 mm.

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