CN111694128A - Supporting assembly for space large-caliber reflecting mirror - Google Patents
Supporting assembly for space large-caliber reflecting mirror Download PDFInfo
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- CN111694128A CN111694128A CN202010625094.7A CN202010625094A CN111694128A CN 111694128 A CN111694128 A CN 111694128A CN 202010625094 A CN202010625094 A CN 202010625094A CN 111694128 A CN111694128 A CN 111694128A
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- reflector
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- support
- locking nut
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- 230000008093 supporting effect Effects 0.000 title claims abstract description 50
- 239000000463 material Substances 0.000 claims description 6
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 4
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004429 Calibre Substances 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 15
- 230000003287 optical effect Effects 0.000 abstract description 14
- 230000008859 change Effects 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 6
- 238000009434 installation Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 abstract description 3
- 238000001514 detection method Methods 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 239000012790 adhesive layer Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 239000013585 weight reducing agent 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
- 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
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- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Astronomy & Astrophysics (AREA)
- Sustainable Development (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Telescopes (AREA)
Abstract
The invention discloses a support assembly for a space large-caliber reflector. The supporting component consists of a reflector supporting back plate, a reflector supporting cylinder, a locking nut and a flexible gasket. The axial positioning of the reflector is fixed on the reflector supporting back plate through a locking nut and a front end screw column of the reflector supporting cylinder, and the locking nut and the reflector are isolated by a flexible gasket and used for uniformly applying locking pressure. The invention has the advantages that: the reflector support assembly solves the problems of complex design and higher assembly process requirement of a reflector support structure in the original large-caliber off-axis three-mirror optical system and the like; meanwhile, the problem of additional stress on the reflector body caused by cantilever support, temperature field change and installation and detection modes of the traditional large-caliber support structure is solved. The influence of the support on the optical surface type can be effectively reduced. The invention has simple structure and easy realization, and has practical engineering significance for light weight of space large-caliber optical load.
Description
Technical Field
The invention belongs to the field of spaceflight, relates to a support assembly for a space large-caliber reflector, and particularly aims to solve the problem of stress-free support of the large-caliber reflector in the field of spaceflight. The design can effectively simplify the design difficulty of the large-caliber reflector support and the difficulty of engineering realization; the assembly and calibration efficiency of the large-aperture reflector can be effectively improved; the influence of the assembly stress of the large-caliber reflector on the surface type can be effectively reduced. Has great practical engineering application value and economic benefit.
Technical Field
With the continuous development of aerospace industry in China, the ground resolution requirement of a space optical remote sensing instrument is higher and higher; meanwhile, the requirements on detection field (width) and detection sensitivity are higher and higher; the three-mirror optical system becomes a trend for solving the current problems, and the development of a decimeter-level visible light and a meter-level infrared remote sensing instrument is started at present. With the improvement of ground resolution, the demand on optical caliber is more and more increased, the caliber is developed from the original 200mm caliber to the caliber of 1m, and a reflector with the caliber of more than 2m is developed at present; meanwhile, the improvement of the optical image quality has higher and higher requirements on the surface type of the optical component.
The reflector is a key component of a reflective optical system, and the reflector supporting technology is one of the most key technologies in the engineering application of the large-aperture reflector. As the aperture of the mirror increases, it is necessary to design the mirror to be light in weight so as to reduce the influence of the self-weight distortion. After the main mirror is reduced in weight, the sensitivity of the mirror to supporting stress is rapidly increased because the specific stiffness is improved as the weight reduction ratio is increased, but the absolute stiffness of the structure is decreased. Meanwhile, the change of the space environment temperature easily causes the surface shape change of the reflector through the supporting structure. After entering the space orbit, the mirror surface shape of the main mirror which meets the engineering use requirement on the ground is easy to change due to the disappearance of the dead weight and the complicated change of the external temperature, deviates from the requirements of design and processing, and directly influences the imaging effect of the space camera.
The design requirements of the support system are different according to different working conditions, materials, processing conditions, use conditions and the like of the primary mirror. In a space optical system, the support design of the primary mirror mainly considers the influence of gravity, temperature and impact vibration. Thus, the loads on the support system are gravitational, thermodynamic and kinetic loads.
The support of the primary mirror is to effectively position the primary mirror and unload the dead weight of the primary mirror, so as to reduce the deformation of the dead weight and bear the influence of temperature and impact. The existing supporting schemes are that position limitation and force action are applied to the main mirror at certain positions of the main mirror through a mechanical structure, supporting force and mirror body gravity are balanced, and the influence of gravity on mirror surface deformation can be partially eliminated. For the large-aperture primary mirror, the following support systems are used.
1) Center support
For the reflector with the middle and small caliber, the central shaft can be used for realizing positioning and constraint independently; for the reflector with a larger aperture, the mirror surface deformation is larger when the reflector is used alone, and the predetermined supporting effect can be met only by matching with other supporting modes. At this time, the central shaft only plays a role of positioning and restraining, and has small load.
2) Multi-point support system
Typical multi-point support systems include Grubb systems, Hinddle systems, Lassell systems, and pneumatic (hydraulic) support systems.
(1) Grubb braced system
This system uses a hinge bracket structure that uses the mutual balancing of the own weights of the mirror parts. The structure is equivalent to a lever mechanism, and the extending part of the lever and the corresponding mirror body supporting part are balanced by virtue of space, and the rigidity of the supporting member does not influence the supporting effect.
(2) Hinddle support system
The system applies a lever mechanism to the Grubb system, which is equivalent to connecting two Grubb systems with a balance lever, and one degree of freedom is increased. The number of the supporting points is expanded, and the problem of over-constraint cannot occur.
(3) Lassell supporting system
The Lassell supporting system is essentially a lever structure, and the gravity of the balancing weight is changed into supporting force for the mirror body through the lever. The supporting points and the distribution of the system are not affected mutually, and the deformation of the local area can be changed by adjusting a single supporting point according to the requirement. Are commonly used as side supports.
(4) Air or hydraulic support system
The system adopts air pressure or hydraulic pressure to replace mechanical acting force, generates surface acting force on the surface of the air (liquid) bag, realizes the restraint and the positioning of the mirror body, and can correct the local deformation of the mirror surface to a certain degree.
(5) Edge support
The edge support of the large-aperture reflector has heavy weight, and the temperature influence is difficult to eliminate.
The back multi-point support is a main way for solving the problem of supporting a large-aperture reflector of an off-axis reflective optical system at present, and designers in the field develop a large amount of work in the aspects of cementing transition sleeves, decoupling design with fixed degree of freedom and the like and obtain remarkable achievement. But the difficulty in the aspects of the processing technology of the reflector support hole, the assembly technology of the support structure and the like is greatly increased. Meanwhile, the machining precision, the assembling process and the steps of the parts directly influence the final assembling quality of the reflector.
The method is used for eliminating the influence of external heat flow change generated by satellite orbit change on the temperature level of a reflector of a remote sensing instrument, so that temperature stress causes the shape of the reflector to change. In addition to the high-precision temperature control measures adopted by the instrument, materials with matched linear expansion coefficients are often adopted in the design to manufacture the reflector supporting barrel and the reflector supporting back plate. Common mirror support cylinder materials include: 4J32 or 4J36 alloy. The reflector supporting back plate is usually made of aluminum-based silicon carbide which is the same as or higher than the reflector supporting cylinder.
Disclosure of Invention
In order to solve the problem of stress-free support of the large-caliber reflector. The invention provides a design idea for a space large-caliber reflector supporting assembly, and aims to solve the practical problem in the large-caliber reflector assembling and correcting process in the current aerospace engineering.
A support assembly for a large aperture spatial reflector comprising: the reflecting mirror support back plate 1, the reflecting mirror support barrel 2, the locking nut 3 and the flexible gasket 4. The axial positioning of the reflector is fixed on the reflector supporting back plate 1 through a locking nut 3 and a stud at the front end of the reflector supporting cylinder 2, and the locking nut 3 is isolated from the reflector through a flexible gasket 4 and used for uniformly locking pressure. The concrete structure is shown in figure 1.
The reflector supporting cylinder 2 is made of 4J32 or 4J36 alloy with the same expansion coefficient.
The reflector back plate 1 is made of the same material of a reflector supporting cylinder or high-component aluminum-based silicon carbide.
The invention is an extension of the central support structure, and seeks a balance between the requirements of optical light-blocking rate and optical reflector type precision. Although a certain light blocking area is increased, the supporting difficulty of the reflector can be effectively reduced; the accuracy of the assembled rear surface of the reflector is effectively improved. And meanwhile, the reliability of the whole assembly is improved to a certain extent.
The working principle is as follows: the traditional cementing structure is replaced by a mechanical limiting mode. The problem of additional force generated by the adhesive layer to the mirror body due to different expansion coefficients when the adhesive additional stress and the temperature of the adhesive layer are changed is solved. Meanwhile, the reliability of the whole assembly in a resistance mechanical environment test is improved to a certain extent by the traditional mechanical limit. The design is connected to the taper sleeve for the speculum supports and speculum inner bore area of contact increases, and the weight of speculum can the equipartition on the bigger area that supports. The generation of concentrated stress is favorably reduced. The taper sleeve and the reflector body are not glued, so that the whole structure can be conveniently disassembled and assembled in the assembling and correcting process.
The reflector support assembly of the present invention has the following advantages:
1. the invention has simple structure and high reliability, and meets the requirement of environment application with harsh space;
2. the invention effectively simplifies the design of the supporting piece, fully utilizes the space and improves the utilization rate;
3. the method has simple implementation steps and is easy to ensure the processing precision.
The reflector support assembly of the present invention has the disadvantage of reducing the effective clear area due to the presence of the axial locking nut. But the area is controllable, and the caliber can be increased properly to solve the problem. The selection of the supporting scheme and the requirement of the optical remote sensing instrument on the image quality are determined. The invention mainly aims at the large-caliber reflector and designs the reflector supporting component with higher requirements on imaging image quality.
Drawings
FIG. 1 is a three-dimensional view of a particular design for a spatial large aperture mirror support assembly;
figure 2 is a cross-sectional view of a specific design for a space heavy caliber mirror support assembly.
Detailed Description
The following detailed description is provided in conjunction with fig. 1 to better illustrate the structural and functional features of the present invention, without limiting the scope of the invention.
The large-caliber reflector support assembly adopts a matched taper sleeve (reflector support cylinder 2) and a locking nut 3 is axially locked. The large-aperture reflector adopts a silicon carbide material, and the back part adopts a three-point supporting mode. 3 mounting holes of the reflector are in butt-grinding with the reflector supporting cylinder 2, the reflector mounting holes are preassembled with the reflector supporting cylinder 2, and the reflector supporting cylinder 2 is repaired and ground, so that 3 supporting surfaces are coplanar, and the coplanarity is required to be within 2 mu m. The flatness of the mirror support backplate 1 and the mirror support mounting surface is required to be within 2 μm. When the reflector is installed, the supporting cylinder 2 is installed in the reflector installation hole, and the locking nut 3 is locked. And then installing the back plate, tightening the installation screw, loosening the locking nut 3, and fixing the back plate installation screw by adopting a fixed-torque wrench. And finally, the locking nut 3 is screwed.
Claims (3)
1. The utility model provides a be used for space heavy-calibre speculum supporting component, is including supporting backplate (1), a speculum supporting cylinder (2), lock nut (3), flexible gasket (4), its characterized in that:
the axial positioning of the reflector is fixed on the reflector supporting back plate (1) through a locking nut (3) and a front end screw column of the reflector supporting cylinder (2), and the locking nut and the reflector are isolated by a flexible gasket (4) and used for uniformly applying locking pressure.
2. A support assembly for a large aperture mirror for a space according to claim 1, wherein: the reflector supporting cylinder (2) is made of 4J32 or 4J36 alloy with the same expansion coefficient.
3. A support assembly for a large aperture mirror for a space according to claim 1, wherein: the reflector back plate (1) is made of the same material of a reflector supporting cylinder or high-component aluminum-based silicon carbide.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911125184.3A CN110780416A (en) | 2019-11-18 | 2019-11-18 | Supporting assembly for space large-caliber reflecting mirror |
| CN2019111251843 | 2019-11-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111694128A true CN111694128A (en) | 2020-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911125184.3A Pending CN110780416A (en) | 2019-11-18 | 2019-11-18 | Supporting assembly for space large-caliber reflecting mirror |
| CN202021257429.6U Active CN212933116U (en) | 2019-11-18 | 2020-07-01 | Support assembly for space large-aperture reflector |
| CN202010625094.7A Pending CN111694128A (en) | 2019-11-18 | 2020-07-01 | Supporting assembly for space large-caliber reflecting mirror |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911125184.3A Pending CN110780416A (en) | 2019-11-18 | 2019-11-18 | Supporting assembly for space large-caliber reflecting mirror |
| CN202021257429.6U Active CN212933116U (en) | 2019-11-18 | 2020-07-01 | Support assembly for space large-aperture reflector |
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| CN (3) | CN110780416A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114089585A (en) * | 2021-11-30 | 2022-02-25 | 中国科学院长春光学精密机械与物理研究所 | Hot implementation device for large-caliber reflector |
| CN114988907A (en) * | 2022-05-31 | 2022-09-02 | 华中科技大学 | High-specific-component gradient aluminum-based silicon carbide composite material reflector and preparation method thereof |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110780416A (en) * | 2019-11-18 | 2020-02-11 | 中国科学院上海技术物理研究所 | Supporting assembly for space large-caliber reflecting mirror |
| CN111999847B (en) * | 2020-08-04 | 2022-07-29 | 北京空间机电研究所 | High-stability supporting structure applied to strip-shaped space reflector |
| CN113253415B (en) * | 2021-06-01 | 2022-02-11 | 中国科学院长春光学精密机械与物理研究所 | Main mirror lateral support structure and assembling and adjusting method |
| CN114047593B (en) * | 2022-01-14 | 2022-04-08 | 中国人民解放军63921部队 | Light-weight SiC primary mirror supporting mechanism of optical measuring equipment |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204188863U (en) * | 2014-10-23 | 2015-03-04 | 中国工程物理研究院总体工程研究所 | A kind of large caliber reflecting mirror back support device |
| CN106526784A (en) * | 2016-11-30 | 2017-03-22 | 中国科学院长春光学精密机械与物理研究所 | Flexible supporting mechanism for plane mirror |
| CN212933116U (en) * | 2019-11-18 | 2021-04-09 | 中国科学院上海技术物理研究所 | Support assembly for space large-aperture reflector |
-
2019
- 2019-11-18 CN CN201911125184.3A patent/CN110780416A/en active Pending
-
2020
- 2020-07-01 CN CN202021257429.6U patent/CN212933116U/en active Active
- 2020-07-01 CN CN202010625094.7A patent/CN111694128A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204188863U (en) * | 2014-10-23 | 2015-03-04 | 中国工程物理研究院总体工程研究所 | A kind of large caliber reflecting mirror back support device |
| CN106526784A (en) * | 2016-11-30 | 2017-03-22 | 中国科学院长春光学精密机械与物理研究所 | Flexible supporting mechanism for plane mirror |
| CN212933116U (en) * | 2019-11-18 | 2021-04-09 | 中国科学院上海技术物理研究所 | Support assembly for space large-aperture reflector |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114089585A (en) * | 2021-11-30 | 2022-02-25 | 中国科学院长春光学精密机械与物理研究所 | Hot implementation device for large-caliber reflector |
| CN114089585B (en) * | 2021-11-30 | 2022-09-06 | 中国科学院长春光学精密机械与物理研究所 | Hot implementation device for large-caliber reflector |
| CN114988907A (en) * | 2022-05-31 | 2022-09-02 | 华中科技大学 | High-specific-component gradient aluminum-based silicon carbide composite material reflector and preparation method thereof |
| CN114988907B (en) * | 2022-05-31 | 2023-01-06 | 华中科技大学 | High-specific-component gradient aluminum-based silicon carbide composite material reflector and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110780416A (en) | 2020-02-11 |
| CN212933116U (en) | 2021-04-09 |
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Application publication date: 20200922 |