CN116047840A - Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera - Google Patents
Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera Download PDFInfo
- Publication number
- CN116047840A CN116047840A CN202310165302.3A CN202310165302A CN116047840A CN 116047840 A CN116047840 A CN 116047840A CN 202310165302 A CN202310165302 A CN 202310165302A CN 116047840 A CN116047840 A CN 116047840A
- Authority
- CN
- China
- Prior art keywords
- main mirror
- fixedly connected
- wall
- oxygen
- silicon carbide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- G03B17/02—Bodies
- G03B17/12—Bodies with means for supporting objectives, supplementary lenses, filters, masks, or turrets
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Telescopes (AREA)
Abstract
The invention discloses a large-caliber silicon carbide main mirror supporting component suitable for a coaxial space camera, which relates to the technical field of space optics and comprises a back plate, wherein a main mirror and the back plate are made of silicon carbide materials, the mechanical property and the thermal property of the materials are excellent, the thermal expansion coefficient is matched with that of a flexible hinge, the influence of temperature change on the main mirror component is reduced, a traditional mirror body back three-point support is designed to be a flange three-point support, the force transmission path is changed, the influence of assembly stress and thermal stress of a supporting structure on the mirror surface shape precision of a reflecting mirror is reduced, the stability of the main mirror structure is improved, the main mirror surface shape precision is always in a stable state in operation, the processing and manufacturing manufacturability is good, the assembly and adjustment are convenient, the space camera development period is shortened, the manufacturing cost is reduced, the shock absorption capability is improved due to the arrangement of a composite supporting plate, the main mirror can be reinforced and fixed when the main mirror is impacted by sundries, and the influence of external force on the main mirror precision is reduced.
Description
Technical Field
The invention relates to the technical field of space optics, in particular to a large-caliber silicon carbide main mirror supporting component suitable for a coaxial space camera.
Background
With the rapid development of space-to-ground observation technology, the space resolution of a space remote sensing camera is increasingly required, and the ground pixel resolution is generally improved by increasing the focal length and the caliber of a main mirror of a coaxial three-mirror optical system. The large-caliber main mirror is used as a key optical element in an optical system, and is influenced by complex factors such as gravity, temperature change and vibration under the conditions of processing and adjustment, environment test, carrying emission, on-orbit working and the like, so that the surface shape precision and the position precision of the main mirror are changed, the optical axis direction of the optical system of the space remote sensing camera is deviated, and the spatial resolution of the camera is reduced, therefore, the main mirror of the space camera and a supporting component thereof have an important effect on the imaging quality.
The SiC material has the excellent performances of small self gravity influence deformation, high strength, high reflectivity and the like, and is an ideal material for manufacturing the reflecting mirror. The reflector with the caliber of phi 500-phi 800mm is also called a large-caliber reflector, and the supporting mode of the reflector is usually a center support, a three-point support at the back of the reflector body or an integrated support of the reflector body and a backboard. The center support is typically used for small caliber main mirror support. When the main mirror assembly is subjected to external force, temperature change or vibration, the back three-point support directly acts on the mirror body, so that the accuracy of the surface shape of the main mirror surface is reduced. And adopts a structure of integrating a main mirror and a back plate, such as a silicon carbide reflecting mirror CN111308644A. In general, an electric box, a three-mirror, a turning mirror, a detector assembly and the like are required to be installed on a main mirror back plate of a coaxial three-mirror space camera, particularly, the electric box, an electronic element heats to easily cause the back plate to deform, and then internal stress is directly transmitted to a mirror body of the reflecting mirror, so that the mirror surface is deformed, and the surface shape precision is reduced.
In order to solve the problems in the prior art, a large-caliber (diameter 520 mm) silicon carbide main mirror supporting component suitable for a coaxial space camera is provided. When this main mirror subassembly has avoided usually back three-point to support, external force direct action mirror body easily causes the mirror surface to warp, through main mirror flange and flexible hinged joint, when having overcome mirror body and backplate integration, the backplate warp and drive the main mirror and take place to warp because of environmental change such as being heated, vibrations, does not have flexible transition between main mirror and the backplate, and the internal stress can't release, causes main mirror surface precision to drop. The main mirror assembly meets the requirements of the coaxial three-mirror space camera on high surface shape precision and high light weight of the main mirror.
Disclosure of Invention
In order to solve the technical problems, the invention provides a large-caliber silicon carbide main mirror supporting component suitable for a coaxial space camera, which comprises a back plate, wherein the bottom of the back plate is fixedly connected with a bearing plate, the periphery of the bottom of the bearing plate is fixedly connected with three supporting plates, the top center shaft of the back plate is fixedly connected with a flange, the large-caliber silicon carbide main mirror supporting component further comprises a stable precision mechanism, the stable precision mechanism comprises a stable main mirror mechanism fixedly connected inside the back plate, the top of the flange is movably connected with an auxiliary stable main mirror mechanism, an anti-collision supporting structure comprises an oxygen storage mechanism fixedly connected with the center shafts on the left side and the right side of the supporting plates, the center shaft of the left wall of the oxygen storage mechanism is slidingly connected with an oxygen conveying mechanism, the left end of the oxygen conveying mechanism is rotationally connected with a buffering mechanism, the left end of the buffering mechanism is rotationally connected with a supporting and damping mechanism, and the top of the supporting and damping mechanism is fixedly connected with an auxiliary buffering mechanism.
Further, the stable main mirror mechanism comprises a supporting rib fixedly connected inside the back plate, three flexible hinges are fixedly connected to the periphery of a top central shaft of the supporting rib, and the outer wall of the top end of each flexible hinge is fixedly connected with the bottom end of a flange.
Further, the auxiliary stabilizing main mirror mechanism comprises a triangular rib fixedly connected to the top of the flange, the bottom end of the triangular rib is fixedly connected with an annular rib, and the top of the triangular rib is fixedly connected with a main mirror.
Further, the oxygen storage mechanism comprises an oxygen bottle fixedly connected to the middle shafts at the left side and the right side of the supporting plate, an oxygen delivery tube is fixedly connected to the middle shaft at the front side of the right end of the oxygen bottle, and an air bag is fixedly connected to one end, far away from the oxygen bottle, of the oxygen delivery tube.
Further, the oxygen conveying mechanism comprises a compression rod which is slidably connected to the center shaft of the left wall of the oxygen cylinder, a compression sheet is fixedly connected to the outer wall of the bottom end of the compression rod, the outer wall of the compression sheet is slidably connected to the inner wall of the upper end of the oxygen cylinder, and a fixing rod I is fixedly connected to the inner wall of the top of the compression rod.
Further, the buffer mechanism comprises a first connecting plate which is rotationally connected with the outer wall of the first fixing rod, one end, far away from the first fixing rod, of the first connecting plate is rotationally connected with a second fixing rod, the outer wall of the top end of the second fixing rod is rotationally connected with a second connecting plate, and the bottom of the left end of the second connecting plate is hinged with the upper side of the bottom end of the first connecting plate.
Further, support damper includes the connecting rod one of fixed connection at connecting plate one middle-end inner wall, connecting rod one's outer wall rotates and is connected with damper plate one, connecting plate two's middle-end inner wall fixedly connected with connecting rod two, connecting rod two's outer wall rotates and is connected with damper plate two, damper plate two keeps away from connecting rod two's one end and rotates and be connected with the limit pole, limit pole top's outer wall rotates and connects the inner wall at damper plate right-hand member, limit pole front end fixedly connected with links the carrier block, link the front end axis department fixedly connected with compound backup pad of carrier block, compound backup pad keeps away from the one end fixedly connected with of linking the carrier block around the primary mirror.
Further, the auxiliary buffer mechanism comprises a circular rib fixedly connected to the top of the composite supporting plate, the inner wall of the circular rib is movably connected to the outer wall of the air bag, and a plurality of triangular ribs are fixedly connected to the center shaft of the top of the circular rib.
Compared with the prior art, the invention has the beneficial effects that:
(1) The large-caliber silicon carbide main mirror supporting component suitable for the coaxial space camera has the advantages that the main mirror and the backboard are made of silicon carbide materials, the mechanical property and the thermal property of the materials are good, the thermal expansion coefficient is matched with that of a flexible hinge, the influence of temperature change on the main mirror component is reduced, the traditional three-point support at the back of the mirror body is designed into the three-point support on the flange, the force transmission path is changed, the influence of the assembly stress of the supporting structure and the thermal stress on the surface shape precision of the mirror surface of the mirror is reduced, the stability of the structure of the main mirror is improved, the surface shape precision of the main mirror is always in a stable state in working, the processing and manufacturing manufacturability is good, the adjustment is convenient, the development period of the space camera is shortened, and the manufacturing cost is reduced.
(2) The large-caliber silicon carbide main mirror supporting component suitable for the coaxial space camera has the advantages that the influence on the surface shape accuracy of the main mirror when the main mirror is subjected to temperature, external force or vibration is effectively eliminated by the flexible hinge of the main mirror. The main mirror is connected with the back plate through the flexible hinge screw, so that the influence of deformation of the integrated back plate of the main mirror and the back plate on the surface shape precision of the main mirror is reduced, the flexible joint is connected and fastened with the screw of the main mirror, the defect that the cementing of the traditional main mirror and the taper sleeve is unstable is overcome, the traditional complex flexible hinge taper sleeve structure is avoided, the structural form is simplified, and the connection rigidity is improved.
(3) This heavy-calibre carborundum principal mirror supporting component suitable for coaxial space camera, when being located space during operation, by debris striking easily, when being struck, auxiliary buffer gear can give and support damper and give a power, makes it carry out the extrusion to the oxygen cylinder, and the gas in the oxygen cylinder gets into to the gasbag along the oxygen therapy pipe, and the gasbag swell is bounced debris, makes it can not hinder the work of principal mirror, again because the elasticity to debris leads to the gasbag to flow back, means that the consumption rate of gas has been slowed down to the efficiency of work has been strengthened.
(4) This heavy-calibre carborundum main mirror supporting component suitable for coaxial space camera because the material of ring muscle and triangle muscle is rubber nature, can not cause the influence to the work of main mirror, again because the setting of angle has improved the absorbing ability, because the setting of compound backup pad, when being impacted by debris, can strengthen fixedly to the main mirror to external force has reduced the influence to the main mirror precision.
Drawings
FIG. 1 is a schematic front view of the overall structure of the present invention;
FIG. 2 is a schematic view of the bottom surface of the overall structure of the present invention;
FIG. 3 is a schematic front view of a stable precision structure of the present invention;
FIG. 4 is a schematic cross-sectional view of the underside of the crash support structure of the invention;
FIG. 5 is a schematic front view of an impact support structure of the present invention;
FIG. 6 is a schematic front cross-sectional view of a stable precision structure of the present invention;
fig. 7 is an enlarged view of a of fig. 4 according to the present invention.
In the figure: 1. a back plate; 2. a flange; 3. a carrying plate; 5. an oxygen therapy tube; 6. an air bag; 13. a support plate; 201. a stable precision mechanism; 203. stabilizing the primary mirror mechanism; 202. auxiliary stabilization of the primary mirror mechanism; 501. an anti-collision supporting mechanism; 604. an oxygen storage mechanism; 601. an oxygen delivery mechanism; 602. a buffer mechanism; 603. supporting a damping mechanism; 101. an auxiliary buffer mechanism; 41. a support rib; 42. a flexible hinge; 12. triangular ribs; 23. annular ribs; 21. a primary mirror; 14. an oxygen cylinder; 76. a compression rod; 77. a compression sheet; 71. a first fixed rod; 68. a first connecting plate; 79. a second fixing rod; 67. a second connecting plate; 78. a first connecting rod; 62. a damping plate I; 61. a second connecting rod; 75. a second damping plate; 72. a limiting rod; 74. a carrier block; 73. a composite support plate; 51. a circular rib; 52. triangular ribs.
Detailed Description
The invention will be described in further detail with reference to the drawings and the detailed description. The embodiments of the invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
In the case of example 1,
referring to fig. 1-5, the device comprises a back plate 1, a bearing plate 3 is fixedly connected to the bottom of the back plate 1, three supporting plates 13 are fixedly connected to the periphery of the bottom of the bearing plate 3, the purpose of the arrangement is to install an oxygen bottle 14, a flange 2 is fixedly connected to a center shaft of the top of the back plate 1, the purpose of the arrangement is to provide a high-precision machining reference for precision manufacturing, and the device further comprises;
the stable precision mechanism 201, the stable precision mechanism 201 comprises a stable main mirror mechanism 203 fixedly connected inside the backboard 1, and the top of the flange 2 is movably connected with an auxiliary stable main mirror mechanism 202;
the anti-collision supporting structure 501 comprises an oxygen storage mechanism 604 fixedly connected to the middle shafts on the left side and the right side of the supporting plate 13, an oxygen conveying mechanism 601 is slidably connected to the middle shaft on the left wall of the oxygen storage mechanism 604, a buffer mechanism 602 is rotatably connected to the left end of the oxygen conveying mechanism 601, a supporting shock absorbing mechanism 603 is rotatably connected to the left end of the buffer mechanism 602, and an auxiliary buffer mechanism 101 is fixedly connected to the top of the supporting shock absorbing mechanism 603.
In the case of example 2,
the distinguishing features from example 1 are that,
as shown in figures 1-7 of the drawings,
the stabilizing main mirror mechanism 203 comprises a supporting rib 41 fixedly connected inside the back plate 1, the purpose of the arrangement supports the flexible hinge 42, three flexible hinges 42 are fixedly connected to the periphery of a top central shaft of the supporting rib 41, and the purpose of the arrangement is that the thermal expansion coefficient of the material is adjustable, and the outer wall of the top end of the flexible hinge 42 is fixedly connected to the bottom end of the flange 2.
The auxiliary stabilizing main mirror mechanism 202 comprises the triangular rib 12 fixedly connected to the top of the flange 2, so that the set purpose structure is better in stability, the annular rib 23 is fixedly connected to the bottom end of the triangular rib 12, the set purpose changes the force transmission path, the support structure assembly stress is reduced, the main mirror 21 is fixedly connected to the top of the triangular rib 12, and the set purpose is to observe the ground surface.
The oxygen storage mechanism 604 comprises an oxygen bottle 14 fixedly connected to the middle shafts on the left side and the right side of the supporting plate 13, the purpose of the arrangement is to store gas, an oxygen therapy tube 5 is fixedly connected to the middle shaft on the front side of the right end of the oxygen bottle 14, the purpose of the arrangement is to conduct limited planning on the oxygen conveying path, an air bag 6 is fixedly connected to one end, far away from the oxygen bottle 14, of the oxygen therapy tube 5, and the purpose of the arrangement is to hinder sundries.
The oxygen delivery mechanism 601 includes the compression pole 76 of sliding connection in the left wall axis department of oxygen cylinder 14, and the purpose of setting like this extrudees inside gas, and compression pole 76's bottom outer wall fixedly connected with compression piece 77, and the purpose of setting like this is more comprehensive the displacement to inside gas, and compression piece 77's outer wall sliding connection is at the inner wall of oxygen cylinder 14 upper end, and compression pole 76's top inner wall fixedly connected with dead lever one 71, and the purpose of setting like this is connected with connecting plate one 68.
The buffer mechanism 602 comprises a first connecting plate 68 which is rotationally connected with the outer wall of the first fixing rod 71, the purpose of the arrangement is hinged with a second connecting plate 67, one end, away from the first fixing rod 71, of the first connecting plate 68 is rotationally connected with a second fixing rod 79, the purpose of the arrangement is to connect the first connecting plate 68 with the second connecting plate 67, the outer wall of the top end of the second fixing rod 79 is rotationally connected with the second connecting plate 67, and the bottom of the left end of the second connecting plate 67 is hinged with the upper side of the bottom end of the first connecting plate 68.
The supporting and damping mechanism 603 comprises a first connecting rod 78 fixedly connected to the inner wall of the middle end of the first connecting rod 68, a first damping plate 62 is rotatably connected to the outer wall of the first connecting rod 78, a second connecting rod 61 is fixedly connected to the inner wall of the middle end of the second connecting rod 67, a second damping plate 75 is rotatably connected to the outer wall of the second connecting rod 61, the purpose of the arrangement can be to reciprocate the composite supporting plate 73, a limiting rod 72 is rotatably connected to one end, far away from the second connecting rod 61, of the second damping plate 75, and the outer wall at the top end of the limiting rod 72 is rotatably connected to the inner wall at the right end of the first damping plate 62;
the limiting rod 72 is fixedly connected with the connecting carrier block 74 at the front end, so that the purpose of the arrangement is to connect the composite support plate 73, the composite support plate 73 is fixedly connected to the central shaft of the front end of the connecting carrier block 74, one end, away from the connecting carrier block 74, of the composite support plate 73 is fixedly connected to the periphery of the main mirror 21, and the purpose of the arrangement is to strengthen and fix the main mirror 21.
The auxiliary buffer mechanism 101 comprises a circular rib 51 fixedly connected to the top of the composite supporting plate 73, the purpose of the arrangement is to reduce kinetic energy of impact force, the inner wall of the circular rib 51 is movably connected to the outer wall of the air bag 6, the purpose of the arrangement is to fix the air bag 6, a plurality of triangular ribs 52 are fixedly connected to the center shaft of the top of the circular rib 51, and the purpose of the arrangement is to strengthen the force of impact reduction.
One specific application of this embodiment is;
the main mirror 21 and the backboard 1 are made of silicon carbide materials, the mechanical property and the thermal property of the materials are excellent, the thermal expansion coefficient is matched with the flexible hinge 42, the influence of temperature change on the main mirror 21 assembly is reduced, the traditional three-point support at the back of the mirror body is designed to be the three-point support on the flange 2, the force transmission path is changed, the influence of the assembly stress and the thermal stress of the support structure on the surface shape precision of the mirror surface of the mirror is reduced, the stability of the structure of the main mirror 21 is improved, the surface shape precision of the main mirror 21 is always in a stable state in working, the processing and manufacturing manufacturability is good, the assembly and the adjustment are convenient, the development period of the space camera is shortened, and the manufacturing cost is reduced.
The flexible hinge 42 of the main mirror 21 effectively eliminates the influence on the surface shape accuracy of the main mirror 21 when in temperature, external force or vibration. The main mirror 21 is connected with the back plate 1 through the flexible hinge 42 screw, so that the influence of deformation of the main mirror 21 and the back plate 1 integrated back plate 1 on the surface shape precision of the main mirror 21 is reduced, the flexible joint is connected and fastened with the screw of the main mirror 21, the defect of weak cementation of the traditional main mirror 21 and the taper sleeve is overcome, the traditional complex flexible hinge 42 taper sleeve structure is avoided, the structural form is simplified, and the connection rigidity is improved.
When the device is positioned in space and works, the device is easy to be impacted by sundries, when the device is impacted, the auxiliary buffer mechanism 101 can give power to the supporting shock absorbing mechanism 603 to enable the supporting shock absorbing mechanism 603 to squeeze the oxygen bottle 14, gas in the oxygen bottle 14 enters the air bag 6 along the oxygen delivery pipe 5, the air bag 6 bulges to rebound the sundries, the main mirror 21 cannot be hindered, and the air bag 6 flows back due to elasticity of the sundries, so that the consumption rate of the gas is slowed down, and the working efficiency is enhanced.
Because the material of ring muscle 51 and triangle muscle 52 is the rubber nature, can not cause the influence to the work of main mirror 21, again because the setting of angle, improved the absorbing capacity, because the setting of compound backup pad 73, when being impacted by debris, can strengthen fixedly to main mirror 21 to the influence of external force to main mirror 21 precision has been reduced.
It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art and which are included in the embodiments of the present invention without the inventive step, are intended to be within the scope of the present invention. Structures, devices and methods of operation not specifically described and illustrated herein, unless otherwise indicated and limited, are implemented according to conventional means in the art.
Claims (8)
1. The utility model provides a heavy-calibre carborundum main mirror supporting component suitable for coaxial space camera, includes backplate (1), the bottom fixedly connected with loading board (3) of backplate (1), the bottom fixedly connected with three backup pad (13) all around of loading board (3), the top axis department fixedly connected with flange (2) of backplate (1), its characterized in that still includes;
the stable precision mechanism (201), the stable precision mechanism (201) comprises a stable main mirror mechanism (203) fixedly connected inside the backboard (1), and the top of the flange (2) is movably connected with an auxiliary stable main mirror mechanism (202);
anti-collision supporting structure (501), anti-collision supporting structure (501) are including oxygen storage mechanism (604) of fixed connection in backup pad (13) left and right sides axis department, the left wall axis department sliding connection of oxygen storage mechanism (604) has oxygen conveying mechanism (601), the left end of oxygen conveying mechanism (601) rotates and is connected with buffer gear (602), the left end of buffer gear (602) rotates and is connected with and supports damper (603), the top fixedly connected with auxiliary buffer mechanism (101) of supporting damper (603).
2. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 1, wherein: the stable main mirror mechanism (203) comprises a supporting rib (41) fixedly connected inside the backboard (1), three flexible hinges (42) are fixedly connected to the periphery of a top central shaft of the supporting rib (41), and the bottom end of a flange (2) is fixedly connected to the outer wall of the top end of each flexible hinge (42).
3. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 2, wherein: the auxiliary stabilizing main mirror mechanism (202) comprises a triangular rib (12) fixedly connected to the top of the flange (2), an annular rib (23) is fixedly connected to the bottom end of the triangular rib (12), and a main mirror (21) is fixedly connected to the top of the triangular rib (12).
4. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 3, wherein: the oxygen storage mechanism (604) comprises an oxygen bottle (14) fixedly connected to the middle shafts on the left side and the right side of the supporting plate (13), an oxygen delivery tube (5) is fixedly connected to the middle shaft on the front side of the right end of the oxygen bottle (14), and an air bag (6) is fixedly connected to one end, far away from the oxygen bottle (14), of the oxygen delivery tube (5).
5. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 4, wherein: the oxygen conveying mechanism (601) comprises a compression rod (76) which is slidably connected to the center shaft of the left wall of the oxygen cylinder (14), a compression sheet (77) is fixedly connected to the outer wall of the bottom end of the compression rod (76), the outer wall of the compression sheet (77) is slidably connected to the inner wall of the upper end of the oxygen cylinder (14), and a fixing rod I (71) is fixedly connected to the inner wall of the top of the compression rod (76).
6. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 5, wherein: the buffering mechanism (602) comprises a first connecting plate (68) which is rotationally connected with the outer wall of a first fixed rod (71), one end, away from the first fixed rod (71), of the first connecting plate (68) is rotationally connected with a second fixed rod (79), the outer wall of the top end of the second fixed rod (79) is rotationally connected with a second connecting plate (67), and the bottom of the left end of the second connecting plate (67) is hinged with the upper side of the bottom end of the first connecting plate (68).
7. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 6, wherein: the supporting damping mechanism (603) comprises a first connecting rod (78) fixedly connected to the inner wall of the middle end of a first connecting plate (68), a first damping plate (62) is rotationally connected to the outer wall of the first connecting rod (78), a second connecting rod (61) is fixedly connected to the inner wall of the middle end of a second connecting plate (67), a second damping plate (75) is rotationally connected to the outer wall of the second connecting rod (61), a limiting rod (72) is rotationally connected to one end, far away from the second connecting rod (61), of the second damping plate (75), and the outer wall at the top end of the limiting rod (72) is rotationally connected to the inner wall of the right end of the first damping plate (62);
the limiting rod (72) is fixedly connected with a connecting carrier block (74), a composite supporting plate (73) is fixedly connected to the center shaft of the front end of the connecting carrier block (74), and one end, far away from the connecting carrier block (74), of the composite supporting plate (73) is fixedly connected to the periphery of the main mirror (21).
8. A large caliber silicon carbide main mirror support assembly for a coaxial space camera as claimed in claim 7, wherein: the auxiliary buffer mechanism (101) comprises a circular rib (51) fixedly connected to the top of the composite supporting plate (73), the inner wall of the circular rib (51) is movably connected to the outer wall of the air bag (6), and a plurality of triangular ribs (52) are fixedly connected to the middle shaft of the top of the circular rib (51).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310165302.3A CN116047840A (en) | 2023-02-27 | 2023-02-27 | Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310165302.3A CN116047840A (en) | 2023-02-27 | 2023-02-27 | Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116047840A true CN116047840A (en) | 2023-05-02 |
Family
ID=86122260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310165302.3A Pending CN116047840A (en) | 2023-02-27 | 2023-02-27 | Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116047840A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117724218A (en) * | 2024-02-18 | 2024-03-19 | 中国科学院长春光学精密机械与物理研究所 | Thermally stable camera structure |
-
2023
- 2023-02-27 CN CN202310165302.3A patent/CN116047840A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117724218A (en) * | 2024-02-18 | 2024-03-19 | 中国科学院长春光学精密机械与物理研究所 | Thermally stable camera structure |
| CN117724218B (en) * | 2024-02-18 | 2024-04-26 | 中国科学院长春光学精密机械与物理研究所 | Thermally stable camera structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116047840A (en) | Large-caliber silicon carbide main mirror supporting assembly suitable for coaxial space camera | |
| JP6214773B2 (en) | Optimal kinematic mount for large mirrors | |
| CN103969788B (en) | A kind of side flexible support structure of space optical remote sensor circular reflector | |
| JP2018529992A (en) | High rigidity structure for large aperture telescope | |
| US11913755B2 (en) | Method for shock attenuation device using a pivot mechanism | |
| Tapos et al. | High bandwidth fast steering mirror | |
| CN104570320A (en) | Axial main lens support mechanism for vehicle-mounted self-adapting optical imaging telescope | |
| CN109387997A (en) | A kind of high rigidity lightweight space camera lens barrel and its vibrostability test method | |
| CN109027430A (en) | A kind of spring support hanging frame | |
| Lake et al. | Deployable primary mirror for space telescopes | |
| CN110735987A (en) | Pipeline vibration absorber and air conditioning unit | |
| CN101135771B (en) | Telescopic lens cone | |
| CN108870034A (en) | A kind of robotization panorama camera turntable adapting to lunar surface environment | |
| CN106291866A (en) | A kind of applicable moon base mechanics and the mirror support mechanism of the temperature difference | |
| CN217382293U (en) | Lens detector support | |
| CN219257733U (en) | Zoom double-light integrated stability-enhancing cradle head nacelle with built-in shock absorption | |
| CN210660483U (en) | Air condition compressor vibration damping mount | |
| CN219035454U (en) | Damping vibration attenuation device and blade | |
| CN210294673U (en) | Azimuth axis safety braking protection structure for large-caliber telescope assembly equipment | |
| CN109596293A (en) | A kind of cooling device reducing exciting rod temperature in hot modal test | |
| CN110778396B (en) | Hoisting type mounting device for piston engine of helicopter | |
| CN214790148U (en) | Light high strength carbon fiber camera supporting structure | |
| CN221446367U (en) | Telescope embedded type variable truss structure | |
| CN218063235U (en) | Damping arm | |
| KR101516598B1 (en) | optical structure with high-precision focus mechanism for space deployable |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |