CN106405785B - A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount - Google Patents
A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount Download PDFInfo
- Publication number
- CN106405785B CN106405785B CN201610875871.7A CN201610875871A CN106405785B CN 106405785 B CN106405785 B CN 106405785B CN 201610875871 A CN201610875871 A CN 201610875871A CN 106405785 B CN106405785 B CN 106405785B
- Authority
- CN
- China
- Prior art keywords
- thermal compensation
- reflecting mirror
- connecting plate
- plate
- support structure
- 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.)
- Active
Links
Classifications
-
- 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
- G02B7/181—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors with means for compensating for changes in temperature or for controlling the temperature; thermal stabilisation
Abstract
A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount, including main force support structure (2), the programmable load-carrying construction of heat distortion amount (3).The programmable large caliber reflecting mirror component load-carrying construction of the heat distortion amount is used to solve space large caliber reflecting mirror and its support construction linear expansion coefficient mismatches and the thermal stress issues of introducing.The programmable load-carrying construction of heat distortion amount (3) includes: damping glue (33), thermal compensation plate (32), connecting plate (31).Damping glue (33) is filled in the rectangular channel that thermal compensation plate (32) upper and lower end face opens up.When environment temperature changes, utilize the different feature in main force support structure (2), thermal compensation plate (32), connecting plate (31) thermal deformation direction, realize that mirror assembly support construction (1) holds radial heat distortion to match with main force support structure (2) radial heat distortion by design thermal compensation plate (32) and the size of connecting plate (31), to eliminate influence of the radial thermal stress to reflecting mirror surface precision.
Description
Technical field
The invention belongs to space optics field, it is related in high resolution space optical system (such as space telescope) crucial group
The thermally matched design of part and camera main force support structure, especially meets the needs of space industry.
Background technique
In order to realize Space Optical System high resolution observations and meet high s/n ratio requirement, the big mouth of long-focus is generally used
Diameter reflective optical system.Thus many problems are brought, on the one hand as the increase of mirror size and mirror surface are close
Spend it is smaller and smaller, reflecting mirror flexibility it is increasing, reflecting mirror rigidity is lower and lower, the reflection of supporting form discrete for back
Mirror assembly, the decline of reflecting mirror rigidity will lead to the mirror surface heat that reflecting mirror is generated by variation of ambient temperature and mirror body temperature gradient
Deformation increases, and influences remote sensor image quality.
After satellier injection, principal reflection mirror component and load-carrying construction can be because the variation of temperature be biggish along primary mirror radial direction generation
Thermal deformation, due to material therefor difference, the heat distortion amount of principal reflection mirror component and load-carrying construction is also different, therefore can produce to primary mirror
The raw thermal stress for influencing surface figure accuracy, to reduce the image quality of camera.Therefore using the programmable support knot of heat distortion amount
Structure makes the heat distortion amount of support construction match with principal reflection mirror radial heat distortion amount, avoids principal reflection mirror because of structure thermal change
Shape mismatches the thermal stress generated.
Summary of the invention
Technology of the invention solves the problems, such as: overcome the deficiencies in the prior art, for main mirror assembly and camera load knot
A set of plate type support structure is devised between structure.The support construction has heat distortion amount designability, within the scope of larger temperature
The radial heat distortion and load-carrying construction radial heat distortion that may insure heavy caliber principal reflection mirror component match, it ensure that space
Support construction will not generate thermal stress and then the face shape essence to reflecting mirror because of temperature change during optical system operation on orbit
Degree has an impact.
The technical solution of the invention is as follows: a kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount,
Including main force support structure (2), the programmable load-carrying construction of heat distortion amount (3)；
The programmable load-carrying construction of heat distortion amount (3) includes: damping glue (33), thermal compensation plate (32), connecting plate (31)；Heat
The cross section of compensating plate (32) is H-type；Connecting plate (31) is plate；
Thermal compensation plate (32) lower end surface is connect with main force support structure (2), the upper surface of thermal compensation plate (32) and connecting plate
(31) lower end surface connection, connecting plate (31) upper surface is connect with external mirror modular support structure (1)；The external reflection
Mirror assembly support construction (1) includes reflecting mirror and bipod support construction；
When the reflecting mirror line that main force support structure (2) linear expansion coefficient is greater than external mirror modular support structure (1) expands
When coefficient, thermal compensation plate (32) material is aluminium alloy or titanium alloy, and connecting plate (31) material is indium steel；
When the reflecting mirror line that main force support structure (2) linear expansion coefficient is less than external mirror modular support structure (1) expands
When coefficient, thermal compensation plate (32) material is indium steel, and connecting plate (31) material is aluminium alloy or titanium alloy.
A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount, it is characterised in that: primary load bearing
Structure (2) and thermal compensation plate (32) connection type are flanged joint or threaded connection；Thermal compensation plate (32) and connecting plate (31) are even
Connecing mode is flanged joint or threaded connection；Connecting plate (31) and external mirror modular support structure (1) connection type are method
Orchid connection.
Fixing screws internal thread hole is arranged in connecting plate (31) upper surface, is also equipped in bipod support construction and connecting plate
(31) the corresponding fixation hole of the internal thread hole of upper surface, connecting plate (31) can be with external mirror modular support structure (1)
Bipod support construction be connected by screw to fixation.
It is main force support structure (2) radial dimension, thermal compensation plate (32) radial dimension, connecting plate (31) radial dimension, anti-
Mirror installation site is penetrated to reflecting mirror axial dimension, as shown in Figure 1, meeting following relationship:
α1L1+α3L3-α2L2=αmLm (1)
L2=L3 (2)
In formula:
L1--- main force support structure radial dimension；Main force support structure can be circle；
L2--- thermal compensation plate radial dimension；Thermal compensation plate can be circle；
L3--- connecting plate radial dimension；Connecting plate can be circle；
Lm--- reflecting mirror installation site to reflecting mirror axial dimension；
α1--- main force support structure linear expansion coefficient；
α2--- the thermal compensation printed line coefficient of expansion；
α3--- connecting plate linear expansion coefficient.
αm--- reflecting mirror linear expansion coefficient.
The thermal compensation plate (32) has certain thickness, and the upper surface of thermal compensation plate (32) offers rectangular recess, vulcanizes
The lower end surface for repaying plate (32) offers rectangular recess, depth h；The lower end surface of thermal compensation plate (32) offers and upper surface depth
Identical rectangular recess, thermal compensation plate (32) thickness h1, connecting plate (31) thickness h2, thermal compensation plate (32), connecting plate (31) width
Equal is b, and mirror assembly gross mass is m, as shown in Figure 3.To ensure that the large caliber reflecting mirror component ground experiment stage can answer
Identical performance when now with operation on orbit, the relationship that should meet are as follows:
mgμ2s≤α2E2ΔT(h1-2h)b (3)
mgμ3s≤α3E3ΔT h2b (4)
In formula:
M --- mirror assembly gross mass；
G --- acceleration of gravity；
μ2s--- coefficient of friction between thermal compensation plate and main force support structure；
μ3s--- connecting plate and thermal compensation interleaf friction coefficient；
α2--- the thermal compensation printed line coefficient of expansion；
α3--- connecting plate linear expansion coefficient；
E2--- thermal compensation plate elasticity modulus；
E3--- connecting plate elasticity modulus；
Δ T --- range of temperature, Δ T≤5 DEG C；
h1--- thermal compensation plate thickness, h1≤15mm；
h2--- connection plate thickness, h2≤15mm；
The rectangular recess depth that h --- thermal compensation plate opens up, h=(1/3~1/4) h1；
B --- thermal compensation plate, connection board width；Thermal compensation plate, connecting plate can be rectangle, and width is bond length；
Damping glue (33) are filled in the rectangular recess of the upper surface of the thermal compensation plate (32), the lower end of thermal compensation plate (32)
The rectangular recess in face fills damping glue (33), and the damping characteristic of damping glue (33) is determined by specific damping requirements.
The advantages of the present invention over the prior art are that:
(1) it is mainly released at present by the deformation of flexible link under the in-orbit environment of large-aperture optical remote sensing camera both domestic and external
Principal reflection mirror component and the unmatched problem of load-carrying construction thermal deformation are put, however as the increase of principal reflection mirror bore, reflecting mirror
Surface precision is higher and higher to the sensitivity of thermal stress, simple to can no longer meet high-resolution by plastic deformation release thermal deformation
The requirement of rate camera large caliber reflecting mirror surface precision, the present invention are excellent compared with the existing technology for discharging thermal stress by plastic deformation
Point is: the programmable support construction of heat distortion amount can be realized principal reflection mirror component and load-carrying construction in certain temperature range
Between radial heat distortion exactly match, will not to mirror assembly generate thermal stress, guarantee the in-orbit imaging process of reflecting mirror in face
Type precision.The present invention can apply in 2 meters of bore or more circles or rectangular space light-weighted mirror.
(2) main force support structure (2) of the present invention and thermal compensation plate (32) connection type are flanged joint or threaded connection；It vulcanizes
It repays plate (32) and connecting plate (31) connection type is flanged joint or threaded connection；Connecting plate (31) and external reflection mirror assembly branch
Support structure (1) connection type is flanged joint.This kind is connected and fixed mode high reliablity and can be entirely limited between each part
Six-freedom degree, it is ensured that large caliber reflecting mirror component position precision with higher.
(3) the programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount of the present invention according to master the advantage is that: hold
Power structure (2), the difference of reflecting mirror material therefor are according to formula (1), (2), (3), (4) to the programmable load knot of heat distortion amount
Structure (3) carry out thermal deformation design, realize satellier injection after under the conditions of biggish temperature change mirror assembly support construction (1)
It is exactly matched with main force support structure (2) radial heat distortion, causes mirror surface type accuracy decline to big to eliminate thermal stress
The influence of the in-orbit image quality of bore reflecting mirror remote sensing satellite.
(4) the programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount of the present invention is the advantage is that: ground test
Stage, there are the influences of gravity, and the in-orbit imaging of satellite is state of weightlessness, to guarantee that large caliber reflecting mirror assembly property is real
Existing world consistency, is designed the programmable load-carrying construction of heat distortion amount (3) according to formula (3), (4), can eliminate big
Bore mirror assembly is in ground test, temperature change by the frictional force introducing of gravity generation to large caliber reflecting mirror
The adverse effect that assembly property generates.Guarantee the consistency of large caliber reflecting mirror component on-orbit performance and ground test performance.
(5) damping glue (33) are filled in the rectangular recess of the upper surface of thermal compensation plate (32) of the present invention, thermal compensation plate (32)
Lower end surface rectangular recess fill damping glue (33), utilize damping glue damping property guarantee large caliber reflecting mirror remote sensing satellite
Pass through emission process mechanics vibration environment.The damping characteristic of damping glue (33) is determined by specific vibration damping condition.
Detailed description of the invention
Fig. 1 is the programmable large caliber reflecting mirror component load-carrying construction overall construction drawing of heat distortion amount；
Fig. 2 is the programmable large caliber reflecting mirror modular support structure schematic diagram of heat distortion amount；
Fig. 3 is the programmable large caliber reflecting mirror modular support structure sectional view of heat distortion amount.
Specific embodiment
Basic ideas of the invention are as follows: a kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount, including
Main force support structure (2), the programmable load-carrying construction of heat distortion amount (3).The programmable large caliber reflecting mirror component of the heat distortion amount
Load-carrying construction is used to solve the thermal stress that space large caliber reflecting mirror is mismatched and introduced with its support construction linear expansion coefficient and asks
Topic.The programmable load-carrying construction of heat distortion amount (3) includes: damping glue (33), thermal compensation plate (32), connecting plate (31).Damping glue
(33) it is filled in the rectangular channel that thermal compensation plate (32) upper and lower end face opens up.Thermal compensation plate (32) lower end surface and main force support structure
(2) it connects, the upper surface of thermal compensation plate (32) is connect with the lower end surface of connecting plate (31), connecting plate (31) upper surface and outer counter
Penetrate mirror assembly support construction (1) connection.When main force support structure (2) linear expansion coefficient is greater than external mirror modular support structure
(1) when reflecting mirror linear expansion coefficient, thermal compensation plate (32) material is aluminium alloy or titanium alloy, and connecting plate (31) material is indium
Steel；When main force support structure (2) linear expansion coefficient is less than the reflecting mirror linear expansion coefficient of external mirror modular support structure (1)
When, thermal compensation plate (32) material is indium steel, and connecting plate (31) material is aluminium alloy or titanium alloy.When environment temperature changes
When, using the different feature in main force support structure (2), thermal compensation plate (32), connecting plate (31) thermal deformation direction, vulcanized by design
The size for repaying plate (32) and connecting plate (31) realizes mirror assembly support construction (1) end radial heat distortion and main force support structure
(2) radial heat distortion matches, to eliminate influence of the radial thermal stress to reflecting mirror surface precision.
A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount of the present invention, including main force support structure (2),
The programmable load-carrying construction of heat distortion amount (3).The support construction is used to solve space large caliber mirror assembly to support knot with it
Structure linear expansion coefficient mismatches and the thermal stress issues of introducing.The programmable load-carrying construction of heat distortion amount (3) includes: damping glue
(33), thermal compensation plate (32), connecting plate (31).Thermal compensation plate (32) lower end surface is connect with main force support structure (2), thermal compensation plate
(32) upper surface is connect with the lower end surface of connecting plate (31), connecting plate (31) upper surface and external mirror modular support structure
(1) it connects.When the reflecting mirror line that main force support structure (2) linear expansion coefficient is greater than external mirror modular support structure (1) expands
When coefficient, thermal compensation plate (32) material is aluminium alloy or titanium alloy, and connecting plate (31) material is indium steel；When main force support structure (2)
When linear expansion coefficient is less than the reflecting mirror linear expansion coefficient of external mirror modular support structure (1), thermal compensation plate (32) material
For indium steel, connecting plate (31) material is aluminium alloy or titanium alloy.When environment temperature changes, using main force support structure (2),
The different feature in thermal compensation plate (32), connecting plate (31) thermal deformation direction passes through design thermal compensation plate (32) and connecting plate (31)
Size realize mirror assembly support construction end radial heat distortion match with main force support structure (2) radial heat distortion, thus
Eliminate adverse effect of the radial thermal stress to reflecting mirror surface precision, it is ensured that the in-orbit image quality of large-aperture optical remote sensor is excellent
It is good.
The present invention will be described in the following with reference to the drawings and specific embodiments.
The programmable large caliber reflecting mirror modular support structure schematic diagram of heat distortion amount is as shown in Figure 2.Structure is by damping glue
(33), thermal compensation plate (32), connecting plate (31) composition.Thermal compensation plate (32) lower end surface is connect with main force support structure (2), thermal compensation
The upper surface of plate (32) is connect with the lower end surface of connecting plate (31), connecting plate (31) upper surface and external mirror modular support knot
Structure (1) connection；
When the reflecting mirror line that main force support structure (2) linear expansion coefficient is greater than external mirror modular support structure (1) expands
When coefficient, thermal compensation plate (32) material is aluminium alloy or titanium alloy, and connecting plate (31) material is indium steel；
When the reflecting mirror line that main force support structure (2) linear expansion coefficient is less than external mirror modular support structure (1) expands
When coefficient, thermal compensation plate (32) material is indium steel, and connecting plate (31) material is aluminium alloy or titanium alloy.
When operation on orbit, when main force support structure (2) expanded by heating, the heat of thermal compensation plate (32) and main force support structure (2)
Deformation direction is on the contrary, connecting plate (31) is identical as main force support structure (2) thermal deformation direction, when environment temperature changes, benefit
With the different feature in main force support structure (2), thermal compensation plate (32), connecting plate (31) thermal deformation direction, pass through design thermal compensation plate
(32) and the size of connecting plate (31) realizes synthesis thermal change of connecting plate (31) free end relative to main force support structure (2) reference edge
Shape amount is target thermal deformation magnitude, and target heat distortion amount had both been deflection of the reflecting mirror installation site to reflecting mirror axis.
As shown in Figure 1, can design support construction principle according to above-mentioned heat distortion amount can be obtained following formula:
α1L1+α3L3-α2L2=αmLm (1)
L2=L3 (2)
In formula:
L1--- main force support structure radial dimension；
L2--- thermal compensation plate radial dimension；
L3--- connecting plate radial dimension；
Lm--- reflecting mirror installation site to reflecting mirror axial dimension；
α1--- main force support structure linear expansion coefficient；
α2--- the thermal compensation printed line coefficient of expansion；
α3--- connecting plate linear expansion coefficient.
αm--- reflecting mirror linear expansion coefficient.
It is available according to reflecting mirror, the physical parameter of main force support structure (2) material therefor under formula (1), (2) and actual conditions
The radial ruler of thermal compensation plate (32) and connecting plate (31) needed for reflecting mirror installation site to reflecting mirror axial dimension free wxpansion
It is very little.
Preferred embodiment are as follows: forThe mirror assembly of bore, when main force support structure material is titanium alloy, reflecting mirror
Material is SiC, to repay plate material be aluminium alloy, connection plate material when being invar to heat, L1It is preferred according to mirror assembly support construction
Range be 1.9m~2.1m, Lm obtained according to the structure type optimization design of reflecting mirror, rule of thumb formula be preferably 1.5m~
1.6m.Take L1=2m, Lm=1.6m then obtains L according to formula (1), (2)2=L3=0.645m.
According to the above results, in preferably 20 DEG C of ± 5 DEG C of range of temperature, the surface precision RMS of reflecting mirror is 1/38 λ
(λ=632.8nm) can design the mirror surface under the conditions of large caliber reflecting mirror component load-carrying construction compared to no heat distortion amount
Type precision RMS=1/5.2 λ (λ=632.8nm) performance improves 7.3 times, the results showed that the programmable heavy caliber of heat distortion amount is anti-
Influence of the thermal stress to surface precision can be eliminated by penetrating mirror assembly load-carrying construction, make boreAbove optical element compared with
There is good surface precision in big range of temperature, solve the in-orbit imaging of high-resolution large-aperture optical remote sensing satellite
The key technology that thermal stress influences surface precision in the process.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (5)
1. a kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount, it is characterised in that: include: main force support structure
(2), the programmable load-carrying construction of heat distortion amount (3)；
The programmable load-carrying construction of heat distortion amount (3) includes: damping glue (33), thermal compensation plate (32), connecting plate (31)；Thermal compensation
The cross section of plate (32) is H-type；Connecting plate (31) is plate；
Thermal compensation plate (32) lower end surface is connect with main force support structure (2), upper surface and connecting plate (31) of thermal compensation plate (32)
Lower end surface connection, connecting plate (31) upper surface is connect with external mirror modular support structure (1)；The external reflection mirror assembly
Support construction (1) includes reflecting mirror and bipod support construction；
When main force support structure (2) linear expansion coefficient is greater than the reflecting mirror linear expansion coefficient of external mirror modular support structure (1)
When, thermal compensation plate (32) material is aluminium alloy or titanium alloy, and connecting plate (31) material is indium steel；
When main force support structure (2) linear expansion coefficient is less than the reflecting mirror linear expansion coefficient of external mirror modular support structure (1)
When, thermal compensation plate (32) material is indium steel, and connecting plate (31) material is aluminium alloy or titanium alloy；
Main force support structure (2) radial dimension, thermal compensation plate (32) radial dimension, connecting plate (31) radial dimension, reflecting mirror
Installation site meets following relationship to reflecting mirror axial dimension:
α1L1+α3L3-α2L2=αmLm (1)
L2=L3 (2)
In formula:
L1--- main force support structure radial dimension；
L2--- thermal compensation plate radial dimension；
L3--- connecting plate radial dimension；
Lm--- reflecting mirror installation site to reflecting mirror axial dimension；
α1--- main force support structure linear expansion coefficient；
α2--- the thermal compensation printed line coefficient of expansion；
α3--- connecting plate linear expansion coefficient；
αm--- reflecting mirror linear expansion coefficient.
2. the programmable large caliber reflecting mirror component load-carrying construction of a kind of heat distortion amount according to claim 1, feature
It is: a kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount, it is characterised in that: main force support structure
(2) and thermal compensation plate (32) connection type is flanged joint or threaded connection；Thermal compensation plate (32) and connecting plate (31) connection side
Formula is flanged joint or threaded connection；Connecting plate (31) and external mirror modular support structure (1) connection type are flange company
It connects.
3. the programmable large caliber reflecting mirror component load-carrying construction of a kind of heat distortion amount according to claim 1, feature
Be: fixing screws internal thread hole is arranged in connecting plate (31) upper surface, is also equipped in bipod support construction and connecting plate (31)
The corresponding fixation hole of the internal thread hole of upper surface, connecting plate (31) can be with external mirror modular support structures (1)
Bipod support construction is connected by screw to fixation.
4. the programmable large caliber reflecting mirror component load-carrying construction of a kind of heat distortion amount according to claim 1, feature
Be: the thermal compensation plate (32) has certain thickness, and the upper surface of thermal compensation plate (32) offers rectangular recess, thermal compensation plate
(32) lower end surface offers rectangular recess, depth h；The lower end surface of thermal compensation plate (32) offers identical with upper surface depth
Rectangular recess, thermal compensation plate (32) thickness h1, connecting plate (31) thickness h2, thermal compensation plate (32), connecting plate (31) width are equal
For b, mirror assembly gross mass is m, when to ensure that the large caliber reflecting mirror component ground experiment stage can reappear with operation on orbit
Identical performance, the relationship that should meet are as follows:
mgμ2s≤α2E2ΔT(h1-2h)b (3)
mgμ3s≤α3E3ΔT h2b (4)
In formula:
M --- mirror assembly gross mass；
G --- acceleration of gravity；
μ2s--- coefficient of friction between thermal compensation plate and main force support structure；
μ3s--- connecting plate and thermal compensation interleaf friction coefficient；
α2--- the thermal compensation printed line coefficient of expansion；
α3--- connecting plate linear expansion coefficient；
E2--- thermal compensation plate elasticity modulus；
E3--- connecting plate elasticity modulus；
Δ T --- range of temperature, Δ T≤5 DEG C；
h1--- thermal compensation plate thickness, h1≤15mm；
h2--- connection plate thickness, h2≤15mm；
The rectangular recess depth that h --- thermal compensation plate opens up, h=(1/3~1/4) h1；
B --- thermal compensation plate, connection board width.
5. the programmable large caliber reflecting mirror component load-carrying construction of a kind of heat distortion amount according to claim 4, feature
It is: fills damping glue (33) in the rectangular recess of the upper surface of the thermal compensation plate (32), the lower end surface of thermal compensation plate (32)
Rectangular recess fill damping glue (33), the damping characteristic of damping glue (33) determines by specific damping requirements.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610875871.7A CN106405785B (en) | 2016-09-30 | 2016-09-30 | A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610875871.7A CN106405785B (en) | 2016-09-30 | 2016-09-30 | A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106405785A CN106405785A (en) | 2017-02-15 |
| CN106405785B true CN106405785B (en) | 2019-09-06 |
Family
ID=59228729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610875871.7A Active CN106405785B (en) | 2016-09-30 | 2016-09-30 | A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106405785B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109669253A (en) * | 2019-01-31 | 2019-04-23 | 中国科学院西安光学精密机械研究所 | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly |
| CN110703407B (en) * | 2019-10-17 | 2020-10-30 | 中国科学院长春光学精密机械与物理研究所 | High-precision spliced reflector supporting and driving structure |
| CN111610584A (en) * | 2020-05-25 | 2020-09-01 | 中国科学院长春光学精密机械与物理研究所 | Modified layer based on aluminum alloy matrix reflector and processing method thereof |
| CN112612136B (en) * | 2020-12-11 | 2022-08-05 | 杭州电子科技大学 | Deformable mirror unit with deformation compensation function and discrete deformable mirror system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4826303A (en) * | 1987-04-04 | 1989-05-02 | Carl-Zeiss-Stiftung | Arrangement for connecting bodies wherein thermally-related constraining forces on the bodies are minimized |
| US6293682B1 (en) * | 2000-04-13 | 2001-09-25 | Mitsubishi Denki Kabushiki Kaisha | Reflecting panel adjusting mechanism |
| CN103472566A (en) * | 2013-09-12 | 2013-12-25 | 北京空间机电研究所 | Zero-expansion flexible damping supporting device of space reflector |
| CN104280858A (en) * | 2014-10-23 | 2015-01-14 | 中国工程物理研究院总体工程研究所 | Flexible back supporting device for large-caliber reflector |
| CN104914550A (en) * | 2015-05-28 | 2015-09-16 | 北京空间机电研究所 | Reflector support structure capable of eliminating thermal stress |
-
2016
- 2016-09-30 CN CN201610875871.7A patent/CN106405785B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4826303A (en) * | 1987-04-04 | 1989-05-02 | Carl-Zeiss-Stiftung | Arrangement for connecting bodies wherein thermally-related constraining forces on the bodies are minimized |
| US6293682B1 (en) * | 2000-04-13 | 2001-09-25 | Mitsubishi Denki Kabushiki Kaisha | Reflecting panel adjusting mechanism |
| CN103472566A (en) * | 2013-09-12 | 2013-12-25 | 北京空间机电研究所 | Zero-expansion flexible damping supporting device of space reflector |
| CN104280858A (en) * | 2014-10-23 | 2015-01-14 | 中国工程物理研究院总体工程研究所 | Flexible back supporting device for large-caliber reflector |
| CN104914550A (en) * | 2015-05-28 | 2015-09-16 | 北京空间机电研究所 | Reflector support structure capable of eliminating thermal stress |
Non-Patent Citations (1)
| Title |
|---|
| 大口径反射镜结构参数优化设计;杨佳文等;《中国空间科学技术》;20110825(第4期);第77-82页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106405785A (en) | 2017-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106405785B (en) | A kind of programmable large caliber reflecting mirror component load-carrying construction of heat distortion amount | |
| CN108594396A (en) | A kind of quasi- zero thermal expansion space optical remote sensor support construction and method | |
| CN106291864B (en) | Reflecting mirror support structure, mirror assembly and optical remote sensing camera | |
| CN208270826U (en) | A kind of quasi- zero thermal expansion space optical remote sensor support construction | |
| CN108508570A (en) | Multiaxis flexible supporting device of the aspect than rectangular mirror | |
| CN110231689A (en) | Push away the ultralight carbon fiber lattice supporting framework of solidifying integrated high-resolution space optics load | |
| CN104482874A (en) | On-orbit measurement system used for pointing relative deformation of satellite load | |
| Tandy et al. | MOIRE gossamer space telescope-structural challenges and solutions | |
| Srivastava et al. | Piezo-deformable mirrors for active mode matching in advanced LIGO | |
| Smith et al. | Performance testing of the LMT/GTM primary surface actuators | |
| CN104743138B (en) | High-precision micro-deformation attitude control instrument installing structure for spaceflight | |
| Hull | GMT primary mirror support | |
| Lucarelli et al. | The breadboard model of the LISA telescope assembly | |
| CN107656367B (en) | Scanning mirror assembly for satellite-borne scanning mechanism | |
| Wang et al. | Stability metering method for high-resolution space telescope with large F-number based on combination optimization | |
| Xu et al. | Design and analysis of a star simulator suitable for confined space | |
| Neill et al. | Active tangent link system for transverse support of large thin meniscus mirrors | |
| Edeson et al. | Dimensional stability testing on a space optical bench structure | |
| Wang et al. | Study on assembly technology of primary and secondary mirror system based on truss structure | |
| Zeiders | Design rules and scaling for solar sails | |
| Arters et al. | Preliminary design of piezo-activated composite sandwich fins for projectile maneuverability | |
| CN117781851B (en) | Multistage correction method for closed-loop piezoelectric driving phase shifter | |
| CN113280025B (en) | Line expansion compensation gasket for image sensor | |
| CN108286639B (en) | Coaxial optical dual-camera splicing structure | |
| Chen et al. | Design and optimization of 1.2-m primary mirror supporting systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |