CN112731618A - Light-duty multi-functional secondary mirror bearing structure of integration suitable for space camera - Google Patents
Light-duty multi-functional secondary mirror bearing structure of integration suitable for space camera Download PDFInfo
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- CN112731618A CN112731618A CN202110057977.7A CN202110057977A CN112731618A CN 112731618 A CN112731618 A CN 112731618A CN 202110057977 A CN202110057977 A CN 202110057977A CN 112731618 A CN112731618 A CN 112731618A
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- 230000010354 integration Effects 0.000 title claims description 3
- 239000000463 material Substances 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 4
- 239000003973 paint Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 6
- 230000008569 process Effects 0.000 abstract description 5
- 238000013461 design Methods 0.000 abstract description 4
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 2
- 239000000956 alloy Substances 0.000 abstract description 2
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000010923 batch production Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002966 varnish Substances 0.000 description 1
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- 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
-
- 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
- G02B7/183—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy, or solar concentrators
-
- 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
- G02B7/198—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors with means for adjusting the mirror relative to its support
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- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Astronomy & Astrophysics (AREA)
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Abstract
The invention provides a light integrated multifunctional secondary mirror supporting structure suitable for a space camera, which comprises a support ring, support arms, a thin-walled cylinder, a front frame ring, a rear frame ring and a diaphragm assembly, wherein the front frame ring is fixed at the top end of the thin-walled cylinder, the rear frame ring is fixed at the bottom end of the thin-walled cylinder, the diaphragm assembly comprises a plurality of diaphragms which are arranged in the thin-walled cylinder in parallel from top to bottom, the support ring is arranged in the thin-walled cylinder and is fixedly connected with the thin-walled cylinder through the three support arms, the support rings and the thin-walled cylinder are arranged coaxially, and the three support arms are uniformly arranged between the support ring and the thin-walled cylinder; the lower surface of the support ring provides a mounting surface for the secondary mirror assembly, and the lower surface of the rear frame ring provides a mounting surface for the camera platform. The invention adopts a plane assembly form, has simple assembly process and reduces assembly difficulty, simultaneously adopts the metal titanium alloy material to be integrally cast and molded, has the advantages of high specific rigidity and high stability, and is widely applied to the design of the main support structure of the space camera.
Description
Technical Field
The invention belongs to the technical field of space cameras, and particularly relates to a light integrated multifunctional secondary mirror supporting structure suitable for a space camera.
Background
In the prior art, most of space small and medium-sized coaxial two-mirror remote sensing cameras adopt a truss rod type secondary mirror supporting structure or a force bearing cylinder type secondary mirror supporting structure. The truss rod type has overlarge size envelope, no stray light eliminating performance and difficult assembly technology, and is not beneficial to batch development; the existing force-bearing cylinder type secondary mirror supporting structure is a force-bearing cylinder type carbon fiber integrally formed secondary mirror supporting structure, is complex in structural form, high in development difficulty, low in machining efficiency, difficult in assembly technology and not beneficial to batch production; in the process of developing the existing space camera, the contradiction exists between the performance of the camera and the mass production, so that a light integrated multifunctional secondary mirror supporting structure which has compact size envelope, stray light eliminating performance and simple assembly process and is suitable for the space camera is needed to be designed.
Disclosure of Invention
In view of the above, the invention aims to provide a light integrated multifunctional secondary mirror support structure and a force bearing cylinder type secondary mirror support structure suitable for a space camera, which adopt a plane assembly form, have simple assembly process and reduce assembly difficulty, and simultaneously adopt a metal titanium alloy material to be integrally cast and formed, have the advantages of high specific rigidity, high stability and the like, and are widely applied to the design of a main support structure of the space camera.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a light-duty integrated multifunctional secondary mirror supporting structure suitable for a space camera comprises a support ring, support arms, a thin-walled cylinder, a front frame ring, a rear frame ring and a diaphragm assembly, wherein the front frame ring is fixed at the top end of the thin-walled cylinder, the rear frame ring is fixed at the bottom end of the thin-walled cylinder, the diaphragm assembly comprises a plurality of diaphragms which are arranged in the thin-walled cylinder in parallel from top to bottom, the support ring is arranged in the thin-walled cylinder and is fixedly connected with the thin-walled cylinder through the three support arms, the support ring and the thin-walled cylinder are coaxially arranged, and the three support arms are uniformly arranged between the support ring and the thin-walled cylinder;
the support arm is of a plate-shaped structure, the length of a connecting wire at one end connected with the support ring is the length of a bus of the support ring, the length of a connecting wire at one end connected with the thin-walled cylinder is the distance between the front frame ring and the uppermost diaphragm, the upper surface of the support arm at one end connected with the thin-walled cylinder is fixedly connected with the front frame ring, and the lower surface of the support arm is fixedly connected with the uppermost diaphragm;
the lower surface of the support ring and the lower surface of the rear frame ring are both planes, the lower surface of the support ring provides a mounting surface for the secondary mirror assembly, and the lower surface of the rear frame ring provides a mounting surface for the camera platform.
Further, the thin-wall cylinder is a cylindrical cylinder structure with the wall thickness of 1.2mm and the inner diameter of 470.6 mm.
Furthermore, the support ring is a space envelope solid structure with an inner diameter of 45mm, an outer diameter of 65mm and a height of 41 mm.
Further, the support arm is of a trapezoidal plate-shaped structure with the thickness of 6 mm.
Further, the thickness of the front frame ring is 2mm, the inner diameter is 470.6mm, and the outer diameter is 503 mm; the thickness of back frame ring is 7mm, and the internal diameter is 446mm, and the external diameter is 471 mm.
Furthermore, the support ring, the support wall, the thin-wall cylinder, the front frame ring, the rear frame ring and the diaphragm assembly are made of TC4 materials and are formed by one-step casting.
Further, an upper surface of the carrier ring is disposed flush with the front frame ring.
Furthermore, the thin-wall cylinder is of a variable-thickness cylinder structure, and the wall thickness of the cylinder is 1-2 mm.
Further, the thin-wall cylinder is a conical cylinder.
Further, uniformly spraying impurity-removing varnish on the inner wall of the thin-walled cylinder.
Compared with the prior art, the light integrated multifunctional secondary mirror supporting structure applicable to the space camera has the following advantages:
1. the force-bearing cylinder type secondary mirror supporting structure is integrally formed by casting TC4 material at one time, so that the processing and production efficiency is greatly improved.
2. The bearing cylinder type secondary mirror supporting structure integrates the functions of secondary mirror supporting, shading, stray light eliminating and the like, greatly reduces the assembly difficulty of the optical camera, and greatly reduces the production period and the manufacturing cost.
3. The main bearing cylinder of the invention adopts a cylinder wall structure with optimal thickness, greatly reduces the mass of the secondary mirror support on the premise of meeting the requirements of integral structure rigidity and strength, and meets the requirement of light weight of a camera.
4. The thin-wall cylinder inner wall is sprayed with the stray light eliminating paint, and the stray light eliminating effect is greatly improved by combining the space position design of the diaphragm.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a top view of a lightweight integrated multifunctional secondary mirror support structure for use in a space camera, according to an embodiment of the present invention;
FIG. 2 is a schematic perspective view of a support structure of a light-weight integrated multifunctional secondary mirror for a space camera in a forward tilting state according to an embodiment of the present invention;
FIG. 3 is a schematic perspective view of a support structure of a lightweight integrated multifunctional secondary mirror for a space camera in a reverse tilt state according to an embodiment of the present invention;
fig. 4 is a bottom view of a light-weight integrated multifunctional secondary mirror support structure for a space camera according to an embodiment of the present invention.
Description of reference numerals:
1. the support comprises a support ring, 2, a support wall, 3, a thin-wall cylinder, 4, a diaphragm, 5, a front frame ring, 6, a rear frame ring, 7, the lower surface of the support ring and 8, the lower surface of the rear frame ring.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-4, a light-duty integrated multifunctional secondary mirror supporting structure suitable for a space camera comprises a support ring 1, support arms 2, a thin-wall barrel 3, a front frame ring 5, a rear frame ring 6 and a diaphragm assembly, wherein the front frame ring 5 is fixed at the top end of the thin-wall barrel 3, the rear frame ring 6 is fixed at the bottom end of the thin-wall barrel 3, the diaphragm assembly comprises a plurality of diaphragms 4 which are arranged in the thin-wall barrel in parallel from top to bottom, the support ring is arranged in the thin-wall barrel 3 and is fixedly connected with the thin-wall barrel through the three support arms 2, the support ring and the thin-wall barrel are coaxially arranged, and the three support arms are uniformly arranged between the support ring and the thin-wall barrel; the upper surface of the bracket ring 1 is arranged flush with the front frame ring 5;
the support arm 2 is of a trapezoidal plate-shaped structure, and has the beneficial effects that: the bearing effect of the bracket ring 1 in any direction in space is improved, and meanwhile, the structural quality of the bracket arm 2 is optimized. The length of a connecting wire at one end of the bracket arm 2 connected with the bracket ring 1 is the length of a bus of the bracket ring 1, so that stress concentration is reduced; the length of a connecting wire at one end connected with the thin-walled cylinder 3 is the vertical distance between the front frame ring 5 and the diaphragm 4 positioned at the top, the upper surface of the support arm 2 at one end connected with the thin-walled cylinder 3 is fixedly connected with the front frame ring 5, and the lower surface of the support arm 2 is fixedly connected with the diaphragm positioned at the top, so that the connecting strength can be increased to the maximum extent, and the safety margin is improved;
the lower surface 7 of the support ring and the lower surface 8 of the rear frame ring are both planes, the lower surface 7 of the support ring provides a mounting surface for the secondary mirror assembly, and the lower surface 8 of the rear frame ring provides a mounting surface for the camera platform.
The thin-wall barrel 3 is of a cylindrical barrel structure with the wall thickness of 1.2mm and the inner diameter of 470.6mm, the support ring 1 is of a space envelope solid structure with the inner diameter of 45mm, the outer diameter of 65mm and the height of 41mm, the support arm 2 is of a trapezoidal plate structure with the thickness of 6mm, the front frame ring 5 is of the thickness of 2mm, the inner diameter of 470.6mm and the outer diameter of 503 mm; the thickness of back frame ring 6 is 7mm, and the internal diameter is 446mm, and the external diameter is 471 mm. The invention adopts a three-point secondary mirror supporting mode, the secondary mirror is in a statically determinate state, the influence of precision imbalance caused by mutual coupling of force paths in a four-point supporting hyperstatic structure is optimized, and the supporting precision of the spatial position of the secondary mirror is greatly improved.
The support ring 1, the support wall 2, the thin-wall barrel 3, the front frame ring 5, the rear frame ring 6 and the diaphragm assembly are made of TC4 materials and are formed by one-step casting. Compared with the structure instability caused by the air release of the carbon fiber material in the rail, the structure thermal stability is better, the method is suitable for mass production, and the performance of the product is stable.
The thin-wall barrel 3 can also be of a variable-thickness barrel structure, and the wall thickness of the barrel is 1mm-2 mm. The thin-walled cylinder 3 is not limited to a cylindrical cylinder, and may be a tapered cylinder.
The inner wall of the thin-wall cylinder 3 is uniformly sprayed with the stray light eliminating paint, and the stray light eliminating effect is greatly improved by combining the space position design of the diaphragm.
The light shading device has the advantages of being compact in structure, simple to process, high in stability, specific rigidity, shading, high in efficiency, capable of eliminating stray light and the like.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. The utility model provides a multi-functional secondary mirror bearing structure of light-duty integration suitable for space camera which characterized in that: the diaphragm type diaphragm plate support comprises a support ring (1), support arms (2), a thin-walled cylinder (3), a front frame ring (5), a rear frame ring (6) and diaphragm components, wherein the front frame ring (5) is fixed at the top end of the thin-walled cylinder (3), the rear frame ring (6) is fixed at the bottom end of the thin-walled cylinder (3), the diaphragm components comprise a plurality of diaphragms (4) which are arranged in the thin-walled cylinder in parallel from top to bottom, the support ring is arranged in the thin-walled cylinder (3) and is fixedly connected with the thin-walled cylinder through three support arms (2), the support ring and the thin-walled cylinder are coaxially arranged, and the three support arms are uniformly arranged between the support ring and the thin-walled cylinder;
the support arm (2) is of a plate-shaped structure, the length of a connecting wire at one end connected with the support ring (1) is the length of a bus of the support ring (1), the length of a connecting wire at one end connected with the thin-walled cylinder (3) is the distance between the front frame ring (5) and the diaphragm (4) positioned at the top, the upper surface of the support arm (2) at one end connected with the thin-walled cylinder (3) is fixedly connected with the front frame ring (5), and the lower surface of the support arm (2) is fixedly connected with the diaphragm positioned at the top;
the lower surface (7) of the support ring and the lower surface (8) of the rear frame ring are both planes, the lower surface (7) of the support ring provides a mounting surface for the secondary mirror assembly, and the lower surface (8) of the rear frame ring provides a mounting surface for the camera platform.
2. The lightweight integrated multifunctional secondary mirror support structure for a space camera as claimed in claim 1, wherein: the thin-wall barrel (3) is a cylindrical barrel structure with the wall thickness of 1.2mm and the inner diameter of 470.6 mm.
3. The lightweight integrated multifunctional secondary mirror support structure for space camera as claimed in claim 2, wherein: the support ring (1) is a space envelope solid structure with the inner diameter of 45mm, the outer diameter of 65mm and the height of 41 mm.
4. The lightweight integrated multifunctional secondary mirror support structure for space camera as claimed in claim 3, wherein: the support arm (2) is of a trapezoidal plate-shaped structure with the thickness of 6 mm.
5. The lightweight integrated multifunctional secondary mirror support structure for space camera as claimed in claim 4, wherein: the thickness of the front frame ring (5) is 2mm, the inner diameter is 470.6mm, and the outer diameter is 503 mm; the thickness of the rear frame ring (6) is 7mm, the inner diameter is 446mm, and the outer diameter is 471 mm.
6. The lightweight integrated multifunctional secondary mirror support structure for space camera as claimed in claim 5, wherein: the support ring (1), the support wall (2), the thin-wall barrel (3), the front frame ring (5), the rear frame ring (6) and the diaphragm assembly are made of TC4 materials and are formed by one-step casting.
7. The lightweight integrated multifunctional secondary mirror support structure for a space camera as claimed in claim 1, wherein: the upper surface of the bracket ring (1) is arranged flush with the front frame ring (5).
8. The lightweight integrated multifunctional secondary mirror support structure for a space camera as claimed in claim 1, wherein: the thin-wall barrel (3) is of a variable-thickness barrel structure, and the wall thickness of the barrel is 1-2 mm.
9. The lightweight integrated multifunctional secondary mirror support structure for a space camera as claimed in claim 1, wherein: the thin-wall cylinder (3) is a conical cylinder.
10. A lightweight, integrated, multi-function secondary mirror support structure for use in a space camera, as claimed in any one of claims 1-9, wherein: and uniformly spraying impurity-removing gloss paint on the inner wall of the thin-walled cylinder (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110057977.7A CN112731618A (en) | 2021-01-15 | 2021-01-15 | Light-duty multi-functional secondary mirror bearing structure of integration suitable for space camera |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110057977.7A CN112731618A (en) | 2021-01-15 | 2021-01-15 | Light-duty multi-functional secondary mirror bearing structure of integration suitable for space camera |
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| CN112731618A true CN112731618A (en) | 2021-04-30 |
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| CN202110057977.7A Pending CN112731618A (en) | 2021-01-15 | 2021-01-15 | Light-duty multi-functional secondary mirror bearing structure of integration suitable for space camera |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101799580A (en) * | 2010-04-12 | 2010-08-11 | 中国科学院西安光学精密机械研究所 | Moisture absorption expansion compensation fixed length structure and telescope secondary mirror fixed length strutting arrangement |
| CN104570265A (en) * | 2014-12-18 | 2015-04-29 | 中国科学院西安光学精密机械研究所 | Lightweight, simplified and high-stability primary and secondary lens component of coaxial camera and mounting method |
| CN107577028A (en) * | 2017-09-20 | 2018-01-12 | 长春理工大学 | A kind of multi-purpose laser communication optics antenna system |
| CN108241198A (en) * | 2018-02-07 | 2018-07-03 | 中国科学院光电研究院 | The main secondary mirror supporting structure of coaxial spaces camera |
| CN108646380A (en) * | 2018-04-10 | 2018-10-12 | 长光卫星技术有限公司 | A kind of secondary mirror supporting structure of space optical remote camera |
| CN109387997A (en) * | 2017-08-04 | 2019-02-26 | 北京空间机电研究所 | A kind of high rigidity lightweight space camera lens barrel and its vibrostability test method |
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-
2021
- 2021-01-15 CN CN202110057977.7A patent/CN112731618A/en active Pending
Patent Citations (8)
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| CN104570265A (en) * | 2014-12-18 | 2015-04-29 | 中国科学院西安光学精密机械研究所 | Lightweight, simplified and high-stability primary and secondary lens component of coaxial camera and mounting method |
| CN109387997A (en) * | 2017-08-04 | 2019-02-26 | 北京空间机电研究所 | A kind of high rigidity lightweight space camera lens barrel and its vibrostability test method |
| CN107577028A (en) * | 2017-09-20 | 2018-01-12 | 长春理工大学 | A kind of multi-purpose laser communication optics antenna system |
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| CN108646380A (en) * | 2018-04-10 | 2018-10-12 | 长光卫星技术有限公司 | A kind of secondary mirror supporting structure of space optical remote camera |
| CN110596991A (en) * | 2019-09-27 | 2019-12-20 | 长光卫星技术有限公司 | Ultra-light stray light eliminating assembly suitable for coaxial micro-nano remote sensing camera |
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