CN111025612B - Low-cost and small-sized space remote sensing camera - Google Patents
Low-cost and small-sized space remote sensing camera Download PDFInfo
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- CN111025612B CN111025612B CN201911122351.9A CN201911122351A CN111025612B CN 111025612 B CN111025612 B CN 111025612B CN 201911122351 A CN201911122351 A CN 201911122351A CN 111025612 B CN111025612 B CN 111025612B
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/02—Catoptric systems, e.g. image erecting and reversing system
- G02B17/06—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror
- G02B17/0626—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror using three curved mirrors
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- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
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Abstract
The invention provides a low-cost and miniaturized space remote sensing camera, which adopts an off-axis three-mirror optical system with a compact structure, effectively reduces the volume of the space remote sensing camera, and realizes low cost and miniaturization by improving the structure and materials of the space remote sensing camera. This remote space sensing camera includes: a camera frame, a diaphragm, a focal plane structure, and an optical system; the camera frame is used for supporting the optical system and the focal plane structure; the optical system is used for reflecting the shot object image in the focal plane structure; the method comprises the following steps: an off-axis three-mirror optical system and a mirror, the off-axis three-mirror optical system comprising: a primary mirror, a secondary mirror, and a tertiary mirror; the primary mirror and the secondary mirror adopt aspheric mirrors, and the third mirror adopts a spherical mirror; the light incident to the primary mirror is reflected by the primary mirror, the secondary mirror, the third mirror and the reflector in sequence, and then the shot target image is reflected in the focal plane structure; the focal plane structure is used for image acquisition, photoelectric conversion and signal bearing and transmission.
Description
Technical Field
The invention relates to a space remote sensing camera, in particular to a miniaturized space remote sensing camera, and belongs to the technical field of space remote sensing.
Background
With the increasing demand for detecting ground objects in daily life, geological exploration and rescue and relief work, space cameras are also receiving more attention as ground detection equipment in the civil commercial field, but the requirements for the space cameras are higher due to the complexity of terrain and the variability of conditions. The space camera is more convenient, flexible and accurate, and the design of the space camera gradually tends to miniaturization due to the fact that the target ground object in a wide range is accurately surveyed by timeliness. The light and small space camera is more and more greatly concerned in the fields of aerospace and space exploration due to the characteristics of short research and development period, light weight, convenience in design, small size, low research and development cost and the like. The civil commercial field has severe requirements on the production cost, the research and development period and the volume quality of the space camera.
The research and development cost of the space camera is in direct proportion to the mass and the volume of the space camera, and the light and small design of the space camera has very important significance in reducing the research and development cost of the space camera and shortening the research and development period of the space camera. Therefore, the optimal design of the optical system and the structural components of the space camera in the design of the space camera is an important means for shortening the manufacturing period of the camera and reducing the production cost of the camera.
Disclosure of Invention
In view of the above, the present invention provides a low-cost and small-sized space remote sensing camera, which is designed to achieve low cost and small-sized space remote sensing camera.
The low-cost and miniaturized space remote sensing camera comprises: a camera frame, a diaphragm, a focal plane structure, and an optical system;
the camera frame is used for supporting an optical system and a focal plane structure;
the optical system is used for reflecting the shot object image in the focal plane structure; the optical system includes: an off-axis three-mirror optical system and a mirror, the off-axis three-mirror optical system comprising: a primary mirror, a secondary mirror, and a tertiary mirror; the primary mirror and the secondary mirror adopt aspheric mirrors, and the third mirror adopts a spherical mirror; the primary mirror and the tertiary mirror are positioned on the same side, and the secondary mirror and the reflecting mirror are positioned on the opposite sides of the primary mirror and the tertiary mirror; the light incident to the primary mirror is further reflected by the reflector after being reflected by the primary mirror, the secondary mirror and the third mirror in sequence, and the shot target image is emitted out from between the primary mirror and the third mirror and is received by a focal plane structure positioned behind the primary mirror and the third mirror.
As a preferred embodiment of the present invention: the camera frame is provided with a front side plate for mounting the secondary mirror and the reflecting mirror, and a rear side plate opposite to the front side plate; the secondary mirror and the reflecting mirror are fixedly arranged on the outer end face of the front side plate of the camera frame, and the mirror faces of the reflecting mirror and the secondary mirror face the inside of the camera frame;
the main mirror and the three mirrors are fixedly arranged on a substrate inside the camera frame; an opening used for enabling light to enter is formed in the position, opposite to the main mirror, of the front side plate of the camera frame and serves as an entrance port;
an opening for emitting light is arranged on the rear side plate of the camera frame and between the main mirror and the third mirror to serve as an emitting port; the focal plane structure is fixedly arranged on the rear side plate of the camera frame and corresponds to the position of the emergent port.
As a preferred embodiment of the present invention: and a diaphragm extends outwards below the incident port.
As a preferred embodiment of the present invention: the diaphragm is made of nylon glass fibers by adopting a 3D laser powder printing technology.
As a preferred embodiment of the present invention: the camera frame is made of invar steel.
Has the advantages that:
(1) the optical system is additionally provided with a reflector in the off-axis three-mirror optical system, and light rays reflected by the reflector are emitted out between the primary mirror and the three mirrors and are received by a focal plane structure positioned behind the primary mirror and the three mirrors; from this change the position of the relative off-axis three-mirror optical system of focal plane structure, and can make the focal plane structure lie in the envelope scope of primary mirror and three mirrors in the direction of height, and adopt the great focal plane structure of single target surface size (in traditional optical system, for satisfying the operation requirement, need a plurality of focal plane structures concatenation uses, lead to optical system size great), compare in traditional off-axis three-mirror optical system, the structure is more compact, for realizing that space remote sensing camera overall structure is miniaturized provides the basis.
(2) In the off-axis three-mirror optical system, only the primary mirror and the secondary mirror adopt aspheric reflectors, the three mirrors adopt spherical reflectors, fewer aspheric reflectors are used, the spherical reflectors are easy to process and manufacture, and the processing cost of the aspheric surface is far higher than that of the spherical reflectors; compared with the traditional off-axis three-mirror optical system, the production cost of about 1/3 can be reduced.
(3) The camera frame is made of invar steel materials, can adapt to a severe space environment only by a passive thermal control means, and can reduce the complexity and the processing cost of the space remote sensing camera. Compared with high-volume aluminum-based silicon carbide, titanium alloy and other materials, the invar steel material has lower response sensitivity to the warm heat of the working environment, and by utilizing the characteristic that the invar steel material is insensitive to the warm environment, the problem of thermal control of the micro-nano camera can be solved, and the production cost of the space camera frame can be reduced.
(4) The diaphragm uses nylon glass fiber as the material, adopts 3D laser powder printing technique to make, compares in the tradition and adopts carbon fiber material, adopts mould curing manufacturing process to make the diaphragm, has low in production cost, advantages such as manufacturing cycle is short.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the remote space sensing camera;
FIG. 2 is a schematic diagram of an optical system of the remote space sensing camera;
FIG. 3 is a schematic view of a focal plane structure;
fig. 4 is a schematic structural diagram of the space remote sensing camera frame.
Wherein: 1-diaphragm, 2-primary mirror, 3-secondary mirror, 4-tertiary mirror, 5-reflector, 6-focal plane structure, 7-camera frame
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a compact-structure low-cost and miniaturized space remote sensing camera suitable for a micro-nano satellite, the compact-structure off-axis three-mirror optical system is adopted, the size of the space remote sensing camera is effectively reduced, and the low cost and the miniaturization are realized through the improvement of the structure and materials of the space remote sensing camera.
As shown in fig. 1, the remote space sensing camera includes: camera frame 7, diaphragm 1, focal plane structure 6 and optical system. Wherein the camera frame 7 is used for carrying the diaphragm 1, the optical system and the focal plane structure 6; the optical system is used for reflecting a shot object image in the focal plane structure 6, and the focal plane structure 6 is used for image acquisition, photoelectric conversion and signal bearing and transmission.
As shown in fig. 2, the optical system includes: an off-axis three-mirror optical system and a mirror 5, the off-axis three-mirror optical system comprising: a primary mirror 2, a secondary mirror 3, and a tertiary mirror 4; the primary mirror 2 and the secondary mirror 3 are aspheric mirrors, and the three mirrors 4 are spherical mirrors, namely, only two aspheric mirrors are arranged in the off-axis three-mirror optical system. Wherein the primary mirror 2 and the tertiary mirror 4 are positioned at the same side, and the secondary mirror 3 and the reflecting mirror 5 are positioned at the opposite sides; the light incident to the primary mirror 2 is reflected by the primary mirror 2, the secondary mirror 3 and the tertiary mirror 4 in sequence, then reflected to the reflecting mirror 5, and finally reflected to a focal plane structure 6 by the reflecting mirror 5; the optical system can adjust the position of the focal plane structure 6 by additionally arranging the reflector 5 to change a reflection line, so that the optical system has a compact structure. In the scheme, the light reflected by the reflector 5 is emitted out through the space between the main mirror 2 and the three mirrors 4 and is received by the focal plane structure 6 positioned behind the main mirror 2 and the three mirrors 4.
The camera frame 7 is made of invar steel, and although the large-caliber space camera has good thermal control performance compared with a micro-nano camera, the thermal control system is high in cost. The camera frame is made of invar steel materials, the characteristic that the invar steel materials are insensitive to a warm environment can be well utilized, the problem of thermal control of the micro-nano camera is solved, and meanwhile, the production cost of the camera frame is reduced.
In this example, the camera frame 7 is configured as shown in fig. 4, the optical system is supported on the camera frame 7, and in order to adapt to the structure of the micro-nano satellite, the camera frame 7 adopts a rectangular parallelepiped frame mechanism having a front side plate for mounting the secondary mirror 3 and the reflecting mirror 5, and a rear side plate opposite to the front side plate, the secondary mirror 3 and the reflecting mirror 5 are fixedly mounted on the outer end surface of the front side plate of the camera frame 7, and the reflecting mirror 5 is located above the secondary mirror 3, and the mirror surfaces of the reflecting mirror 5 and the secondary mirror 3 face the inside of the camera frame 7. The main mirror 2 and the three mirrors 4 are fixedly arranged on a substrate inside the camera frame 7, and the substrate is fixedly arranged on the inner end face of the rear side plate of the camera frame 7, so that the main mirror 2 and the three mirrors 4 share the substrate, and the space remote sensing camera is ensured to be compact in structure. Wherein the three mirrors 4 are located above the primary mirror 2. An opening for allowing light to enter is provided in a position facing the main mirror 2 on the front side plate of the camera frame 7, and this opening is an entrance port. An opening for emitting light is provided in a position between the main mirror 2 and the three mirrors 4 on the rear side plate of the camera frame 7, and this opening is made to be an exit port.
A diaphragm 2 extends outwards below the entrance port, and the diaphragm 2 is used for filtering stray light outside a required shooting visual field. Diaphragm 2 uses nylon glass fiber as the material, adopts 3D laser powder printing technique to make, compares in the tradition and adopts carbon fiber as the material, adopts mould curing manufacturing process to make the diaphragm, has low in production cost, advantages such as manufacturing cycle is short.
The single focal plane structure 6 is fixedly arranged on the outer end face of the rear side plate of the camera frame 7, corresponds to the emergent port and receives a target image shot by the optical system; and the height and width of the focal plane structure 6 are not larger than those of the camera frame 7 (let the front-rear direction of the camera frame 7 be the length direction).
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A low-cost, miniaturized space remote sensing camera; it is characterized by comprising: a camera frame (7), a diaphragm (1), a focal plane structure (6) and an optical system;
the camera frame (7) is used for supporting an optical system and a focal plane structure (6);
the optical system is used for reflecting a shot object image in a focal plane structure (6); the optical system includes: an off-axis three-mirror optical system and a mirror (5), the off-axis three-mirror optical system comprising: a primary mirror (2), a secondary mirror (3) and a tertiary mirror (4); the primary mirror (2) and the secondary mirror (3) adopt aspheric mirrors, and the three mirrors (4) adopt spherical mirrors; the primary mirror (2) and the tertiary mirror (4) are positioned on the same side, and the secondary mirror (3) and the reflecting mirror (5) are positioned on the opposite sides of the primary mirror (2) and the tertiary mirror (4); the light incident to the primary mirror (2) is further reflected by the reflecting mirror (5) after being reflected by the primary mirror (2), the secondary mirror (3) and the tertiary mirror (4) in sequence, a shot target image is emitted from between the primary mirror (2) and the tertiary mirror (4), and is received by a focal plane structure (6) positioned behind the primary mirror (2) and the tertiary mirror (4);
the focal plane structure is positioned in the envelope range of the primary mirror (2) and the three mirrors (4) in the height direction;
the camera frame (7) is a cuboid frame mechanism and is provided with a front side plate for mounting the secondary mirror (3) and the reflecting mirror (5) and a rear side plate opposite to the front side plate; the secondary mirror (3) and the reflecting mirror (5) are fixedly arranged on the outer end face of the front side plate of the camera frame (7), and the mirror faces of the reflecting mirror (5) and the secondary mirror (3) face the inside of the camera frame (7);
the main mirror (2) and the three mirrors (4) are fixedly arranged on a substrate inside a camera frame (7), so that the main mirror (2) and the three mirrors (4) share the substrate; an opening for allowing light to enter is formed in the position, opposite to the main mirror (2), on the front side plate of the camera frame (7) and serves as an entrance port;
an opening for emitting light is arranged on the rear side plate of the camera frame (7) and between the main mirror (2) and the three mirrors (4) to serve as an emitting port; the focal plane structure (6) is fixedly arranged on the rear side plate of the camera frame (7) and corresponds to the position of the emergent port.
2. A low-cost, miniaturized space remote sensing camera according to claim 1, characterized in that: and a diaphragm (2) extends outwards below the entrance port.
3. A low-cost, miniaturized space remote sensing camera according to claim 2, characterized in that: the diaphragm (2) is made of nylon glass fibers by adopting a 3D laser powder printing technology.
4. A low-cost, miniaturized space remote sensing camera according to claim 1 or 2, characterized in that: the camera frame (7) is made of invar steel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911122351.9A CN111025612B (en) | 2019-11-15 | 2019-11-15 | Low-cost and small-sized space remote sensing camera |
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| CN201911122351.9A CN111025612B (en) | 2019-11-15 | 2019-11-15 | Low-cost and small-sized space remote sensing camera |
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| CN111025612A CN111025612A (en) | 2020-04-17 |
| CN111025612B true CN111025612B (en) | 2021-05-14 |
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| CN111999873B (en) * | 2020-08-10 | 2022-07-29 | 北京空间机电研究所 | Linear array push-broom type three-reflector off-axis camera stray light suppression structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303449A (en) * | 2008-07-10 | 2008-11-12 | 北京空间机电研究所 | Double-view-field off-axis three-mirror integrated optical system sharing primary and secondary mirrors |
| CN105607216A (en) * | 2015-12-30 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | Large-size and high specific stiffness truss off-axis three-reflection optical system main support structure |
| CN105842953A (en) * | 2016-05-31 | 2016-08-10 | 中国科学院长春光学精密机械与物理研究所 | Long-focus off-axis three-mirror space camera system for suppressing full-path stray light |
| CN106324816A (en) * | 2016-10-21 | 2017-01-11 | 北京空间机电研究所 | Small 100-million pixel high resolution space camera |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303449A (en) * | 2008-07-10 | 2008-11-12 | 北京空间机电研究所 | Double-view-field off-axis three-mirror integrated optical system sharing primary and secondary mirrors |
| CN105607216A (en) * | 2015-12-30 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | Large-size and high specific stiffness truss off-axis three-reflection optical system main support structure |
| CN105842953A (en) * | 2016-05-31 | 2016-08-10 | 中国科学院长春光学精密机械与物理研究所 | Long-focus off-axis three-mirror space camera system for suppressing full-path stray light |
| CN106324816A (en) * | 2016-10-21 | 2017-01-11 | 北京空间机电研究所 | Small 100-million pixel high resolution space camera |
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