CN106443959A - Split type bi-material flexible mechanism of space-based large-calibre high-facial-contour-precision reflector assembly - Google Patents
Split type bi-material flexible mechanism of space-based large-calibre high-facial-contour-precision reflector assembly Download PDFInfo
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- CN106443959A CN106443959A CN201611114961.0A CN201611114961A CN106443959A CN 106443959 A CN106443959 A CN 106443959A CN 201611114961 A CN201611114961 A CN 201611114961A CN 106443959 A CN106443959 A CN 106443959A
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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
- G02B7/185—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors with means for adjusting the shape of the mirror surface
Abstract
The invention, which belongs to the technical field of spatial remote sensing, relates to a split type bi-material flexible mechanism of a space-based large-calibre high-facial-contour-precision reflector assembly. The provided flexible mechanism is formed by an invar flange plate and a titanium-alloy flexible link. Flatness of a twenty-first flange surface and a twentieth flange surface of the invar flange plate is higher than 0.005mm and depths of parallelism of the twenty-first flange surface and the twentieth flange surface of the invar flange plate are not lower than 0.008mm. The titanium-alloy flexible link has a structure with three claws distributed around the periphery uniformly at 120 degrees; three radial flexible grooves and two axial flexible grooves are formed in each claw; flatness of a thirteenth flange plane and a nineteenth flange plane of the titanium-alloy flexible link is higher than -.005mm and depths of parallelism of the thirteenth plane and the nineteenth plane of the titanium-alloy flexible link are not lower than 0.008mm; and the thirteenth flange plane is formed by three small planes. The invar flange plate and the titanium-alloy flexible link are connected by connection of the thirteenth flange plane and the twenty-first flange surface with twelve bolts six cylindrical pins, thereby forming the flexible mechanism. According to the flexible mechanism provided by the invention, the influence on the facial contour precision by a thermal load and an assembling error is reduced substantially; and the anti-facial-contour-changing performance under a gravitational load is optimized.
Description
Technical field
The invention belongs to space remote sensing technical field, and in particular to a kind of space-based for being applied to the passive support in 3 points of back is big
The soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of bore.
Background technology
Space Remote Sensors are used for generally investigating the earth and space resources and detailed survey, lead in observation, deep space probing etc. over the ground
The application in domain has important science and economic implications.It is whole light that optical element in remote sensor is particularly large caliber reflecting mirror
Most important part in system, its surface figure accuracy height is directly connected to the quality of whole remote sensor image quality.
The surface figure accuracy error of reflecting mirror mainly includes the face shape that the residual processing error of mirror surface, gravity release are brought
Several aspects such as the face shape error that error, temperature loading bring and the face shape error that build-up tolerance brings.Except residual processing
Error is only relevant with mirror body specific stiffness, remaining error and the specific stiffness of mirror body and supporting construction good and bad related.With reflecting mirror
Bore increase, the sensitivity of the surface figure accuracy error relative gravity load, temperature loading and build-up tolerance of reflecting mirror is gradually
Increase.With the raising that the increase of mirror assembly bore, surface figure accuracy are required, the error that above-mentioned several factors are brought is in total face
Proportion in shape error is slightly changed.
For space-based large caliber reflecting mirror component, it is weight that state and the main distinction of operation on orbit state are debug in ground
Can there is the change of a gravity release during being and not being, i.e. operation on orbit of power load, this gravity release will introduce face shape
The change of error, this factor is an importance for needing consideration during the design of space-based mirror assembly, and gravity release brings
Face deformationization can be by lifting the matching of mirror body rigidity and soft section flexibility reducing；The residual processing error of mirror surface
And mirror body rigidity relevant with the working ability of optical manufacturing is relevant, by mirror body processing staff and Machine Design personnel come common
Ensure, the processed personnel of mirror body are by lifting mirror shape rigidity using advanced processing technique, and Machine Design personnel design is closed
The mirror structure of reason is obtaining the high specific stiffness of mirror body；Build-up tolerance is produced in assembling mainly due to the mismachining tolerance of part
Erection stress causes the change of mirror body face shape, and this needs to protect by the machining accuracy of machine components and appropriate design frame for movement
Card, improves machining accuracy during machine components processing as far as possible, and Machine Design personnel flexible structure reasonable in design is alleviating dress
Join impact of the error to mirror shape；Mirror assembly operation on orbit and ground are debug state and all there is temperature loading, work as mirror body
When thermal characteristicss between material and main supporting structure are inconsistent, temperature rise load can bring face deformation, and this will depend on thermal control design people
Member and Machine Design personnel are ensureing, thermal control design personnel are supplied to the ring of one steady temperature of mirror assembly as far as possible
Border, makes mirror assembly temperature fluctuation range in the course of the work as little as possible, and Machine Design personnel will reasonably design machine
Tool structure, makes mirror assembly insensitive to the fluctuation of thermal temperature.
As the being and not being that main difference is that gravitational load of state and operation on orbit state is debug on mirror assembly ground,
Guarantee that state supporting construction is debug on ground during design supporting construction insensitive to the change of gravitational load, passive support extensively
Using a kind of supporting form be back supported at three point, this form can be with optical axis horizontal positioned, such as Fig. 1, and mirror body is in radial direction
Rigidity is very big, and face deformation is insensitive to gravitational load, and therefore, back supported at three point form can be used for 0.4m-2m or even big
The support of the reflecting mirror that debugs in the optical axis horizontality of 2m bore.The structure composition of back supported at three point is as shown in Fig. 2 bag
Include：Mirror body 1, backboard 2, tapered sleeve 3 and soft section 4.In the supported at three point of back, soft section 4 and tapered sleeve 3 have three sets, and concyclic 120 ° are distributed in
Mirror body back.
In the past, as seen in figures 3-6, soft section 4 is by for the soft section 4 that the mirror assembly of back supported at three point is adopted for the present invention
Seven flanges 7 are linked together with tapered sleeve 3, are linked together with backboard by eight therapeutic methods blue 8.Have on soft section 4 vertically arranged
5th soft groove 5 and the 6th soft groove 6.5th soft groove 5 is a pair, symmetrical around soft 180 ° of 4 axis of section；6th soft groove 6 is also one
Right, symmetrical around soft 180 ° of 4 axis of section；5th soft groove 5 and the 6th soft groove 6 are arranged up and down along 4 axis of soft section, and around soft section 4
Axis is arranged vertically.This soft section 4 useful effect be weaken when there is temperature loading mirror body with the connection of backboard and backboard
The inconsistent thermal stress that brings of the thermal coefficient of expansion of structure, weakens backboard, the deformation of backboard attachment structure and parts assembly tolerance
The erection stress that brings.
The shortcoming of the structure is：(1), the 5th soft groove 5 and the 6th soft groove 6 are arranged vertically, and the stiffness characteristics of soft section 4 are not
Symmetrical around 4 circumference of soft section, for guaranteeing uniformly to weaken thermal stress and erection stress, three soft sections 4 are around the light of primary mirror
Axle 120 is in a rotationally symmetrical arrangement, so when optical axis horizontality bears gravitational load three soft section 4 gravity direction rigidity not
Unanimously, deformation, three soft sections bear the cause not of uniform size of mirror body gravity, will cause the internal stress of mirror body, cause anti-
Penetrate that the face shape error that mirror assembly brought by gravitational load is larger, this impact is not very big certainly, but will for high-precision surface shape
For the large caliber reflecting mirror component that asks, then obvious；(2), during mirror assembly bearing temperature load, soft section 4 weakens mirror
Body is with the inconsistent thermal stress that brings of thermal coefficient of expansion of backboard and the attachment structure of backboard, but the weakening of this soft section 4
The ability of thermal stress is limited, and this is when mirror assembly surface figure accuracy is less demanding, and soft section 4 meets use demand,
But for the mirror assembly of high surface figure accuracy demand, the residual thermal stress after this soft section 4 weakens can not be ignored, especially
Which is for large caliber reflecting mirror component.For weakening invar material of the thermal stress tapered sleeve 3 using scalable thermal coefficient of expansion, will
Its coefficient of expansion be adjusted to consistent with mirror body thermal coefficient of expansion, soft section 4 general employing stable performances titanium alloy material, on soft section 4
The 7th flange 7 adopt multiple mode connects for screws with 3 joint face of tapered sleeve, when soft section 4 and 3 volume ratio of tapered sleeve are larger, the 7th flange 7
Also increase accordingly with the contact surface of tapered sleeve 3, when there is temperature loading, this contact surface can have larger thermal stress, the position
Closely mirror body is put, the surface figure accuracy impact on minute surface is very big, for the mirror assembly that high surface figure accuracy is required, this portion
The face shape error that point thermal stress is brought is a larger component of total face shape error.
Content of the invention
The purpose of the present invention is：Shape below a kind of, antigravity load all insensitive to temperature loading and build-up tolerance is provided
Split type pair of material of change is more excellent, to be applied to 3 points of the back passive high surface figure accuracy mirror assembly of the space-based heavy caliber for supporting
Expect soft section.
To achieve these goals, technical scheme is specific as follows：
A kind of soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber, by invar ring flange and titanium
Alloy flexibility link two parts composition；
Upper and lower 21st flange face of the invar ring flange, the flatness of the 20th flange face are better than
0.005mm, the depth of parallelism must not be less than 0.008mm；
Titanium alloy flexibility link is circumferentially 120 ° of uniform three-jaw structures, including the of three radial directions on each pawl
14 soft grooves, the 16th soft groove and the 17th soft groove, the 15th soft groove of two axial directions and the 18th soft groove；
Titanium alloy flexibility the 13rd flange face of link and the flatness of the 19th flange face are better than 0.005mm,
The depth of parallelism must not be less than 0.008mm, and wherein the 13rd flange face is made up of three facets；
The invar ring flange and titanium alloy flexibility link use 12 by the 13rd flange face and the 21st flange face
Individual screw and 6 straight pins link together, and constitute soft section.
In technique scheme, the 14th soft groove, the 16th soft groove, the 17th soft groove, the 15th soft groove and
18 soft grooves are using slow wire feeding and the grinding technics processing of wire cutting so as to which the roughness of inwall is better than 1.6.
In technique scheme, the 13rd flange face is needed first by titanium alloy by the way of Combined machining
After being fixed together by screw and straight pin with invar ring flange, recombinant process three radial directions the 14th soft groove, the tenth
Six soft grooves and the 17th soft groove, the 15th soft groove of two axial directions, the 18th soft groove.
The invention has the beneficial effects as follows：
The split of the high surface figure accuracy mirror assembly of the space-based heavy caliber for being applied to back supported at three point that the present invention is provided
The soft section of formula bi-material layers, three soft sections are used in groups.There are three groups of soft grooves on the soft section, be circumferentially 120 ° of uniform three-jaw structures,
Three soft sections are uniform around 120 ° of primary mirror optical axis, and during mirror assembly optical axis level, three soft sections of this form are in gravity direction
Rigidity identical, respectively undertake the weight of mirror body 1/3rd, compatibility of deformation is good, using this soft section reflecting mirror gravity carry
Face shape error change under lotus is much smaller than the face shape error change using existing soft section under gravitational load；The soft section meets uniform
Release thermal stress and the requirement of erection stress, meanwhile, in order to the face shape for reducing the mirror body that temperature loading brings to greatest extent is missed
The change of difference, the soft section is disintegrated design, make split type, a part be the ring flange that is connected with tapered sleeve using and tapered sleeve material
Consistent invar, another part flexibility link adopts titanium alloy material.
The soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber that the present invention is provided can be very
The face shape error change that mirror assembly is brought under temperature loading is effectively reduced as material thermal characteristicss are inconsistent；Can have
The mirror assembly that reduces of effect changes as gravitational load changes the face shape error for bringing；Can effectively reduce due to speculum group
The change of the face shape error that part rigging error is brought.
Description of the drawings
With reference to the accompanying drawings and detailed description the present invention is described in further detail.
Fig. 1 is the mirror assembly structure composition schematic diagram of existing back supported at three point；
Fig. 2 is the mirror assembly schematic diagram of back supported at three point in Fig. 1；
Fig. 3 is the front view of soft section in Fig. 2；
Fig. 4 is the C-C cross section structure diagram of soft section shown in Fig. 3；
Fig. 5 is the overlooking the structure diagram of soft section shown in Fig. 2；
Fig. 6 is the present invention looks up structural representation of soft section shown in Fig. 2；
Fig. 7 is the three-dimensional of the soft section of split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber of the present invention
Axle geodesic structure schematic diagram；
Fig. 8 is facing for the soft section of split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber of the present invention
Structural representation；
Fig. 9 is looking up for the soft section of split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber of the present invention
Structural representation；
Figure 10 is the positive structure diagram of titanium alloy flexibility link in the present invention；
Figure 11 is the positive structure diagram of invar ring flange in the present invention；
Figure 12 is the Combined machining structural representation of soft groove in the present invention.
Reference in Fig. 1-6 is expressed as：
1- mirror body, 2- backboard, 3- tapered sleeve, the soft section of 4-, the 5th soft groove of 5-, the 6th soft groove of 6-, the 7th flange of 7-, 8- eight therapeutic methods
Blue；
Reference in Fig. 7-12 is expressed as：
9- invar ring flange, 10- titanium alloy flexibility link, 11- screw, 12- straight pin, the 13rd flange face of 13-, 14-
14th soft groove, the 15th soft groove of 15-, the 16th soft groove of 16-, the 17th soft groove of 17-, the 18th soft groove of 18-, 19- the 19th
Flange face, the 20th flange face of 20-, the 21st flange face of 21-, 22- titanium alloy.
Specific embodiment
The invention thought of the present invention is：
The present invention proposes temperature is carried on a kind of space-based large caliber reflecting mirror for being applied to the passive support in 3 points of back
Lotus and build-up tolerance are all insensitive, the soft section of the more excellent high-performance of deformationization below antigravity load.For overcoming prior art to exist
Defect, by newly soft section be designed to circumferentially 120 ° of uniform three-jaw structures, it is ensured that the real circumference of soft section performance is symmetrical.Three
Process the soft groove of three radial directions on individual claw respectively to weaken the erection stress that rigging error is brought；Processed on three claws respectively
Two are opened the soft groove in axial direction to slacken the stress that backboard and backboard installation frame bring with reflecting mirror thermal characteristicss mismatch, are further
Weaken the subtle effects that thermal characteristicss mismatch is brought, the flange of the soft upper and tapered sleeve connection end of section and soft section are disintegrated, is adopted and cone
The consistent material of set (can be consistent with mirror body thermal characteristicss by adjusting material proportion).This soft section greatly weaken thermal force and
Impact of the rigging error to surface figure accuracy, while the performance of deformation is more excellent below antigravity load.
For the passive supporting construction in 3 points of back using three soft sections, 120 ° of uniform features, it is the circle for ensureing three soft sections
All symmetrical performances-effectively uniformly discharge thermal stress, effectively release erection stress, it is ensured that mirror assembly is in optical axis level
The rigidity of state gravity direction is consistent, devises into 120 ° of symmetrical three-jaw structures in each titanium alloy flexibility link,
Respectively there is the soft groove of three radial directions on each pawl, the soft groove in two axial directions, when mirror body and backboard and backboard attachment structure as temperature is carried
When lotus has radial stress, the soft groove deformation energy absorption in two axial directions weakens stress, when there is erection stress and backing plate outer knot
During the axial deformation that structure is introduced, the soft groove change energy absorption of three radial directions weakens stress.Large reflective mirror group to high surface figure accuracy
For part, the face shape error that thermal force is brought is a main aspect of mirror assembly face shape, by the soft groove of three radial directions and
The soft groove in two axial directions weakens significantly, but the flange face of soft section bottom is with tapered sleeve contact area than larger, bi-material line
Expansion factor is inconsistent to bring larger thermal stress, so soft section has been designed to split type by here, is divided into invar ring flange and titanium
Alloy flexibility link two parts, invar ring flange is identical with tapered sleeve material, and its line expansion factor can be made by adjusting material mixture ratio
Consistent with mirror body, further reduce the impact of thermal stress.When mirror assembly is in optical axis horizontality, three soft sections exist
The rigidity in gravitational load direction is identical, and three respectively bears the weight of mirror body 1/3rd, compatibility of deformation, and mirror body will not be because of three
Rigidity is inconsistent to produce extra internal stress, substantially reduces the face deformation of gravitational load state.This soft section to gravitational load,
Erection stress and temperature loading have more preferable adaptability.
Below in conjunction with the accompanying drawings the present invention is described in detail.
The split of the high surface figure accuracy mirror assembly of the space-based heavy caliber for being applied to back supported at three point that the present invention is provided
The soft section of formula bi-material layers, three soft sections are used in groups.The soft section is a kind of soft section of split type bi-material layers, by 9 He of invar ring flange
Titanium alloy flexibility link 10 two parts composition, wherein invar ring flange 9 is employed and tapered sleeve identical invar material, and titanium alloy is soft
Property link 10 employ the titanium alloy material of stable performance, the structure as shown in Fig. 7-Figure 12 is implemented.
The all parts of thoroughly cleaning before assembling, it is ensured that free from admixture, assembly environment will cleaning.Upper and lower the second of invar ring flange 9
The flatness of 11 flange faces 21 and the 20th flange face 20 is better than 0.005mm, and the depth of parallelism must not be less than 0.008mm；Described
Titanium alloy flexibility link 10 is circumferentially 120 ° of uniform three-jaw structures, on each pawl including three radial directions the 14th soft groove
14th, the 16th soft groove 16 and the 17th soft groove 17, the 15th soft groove 15 of two axial directions and the 18th soft groove 18；Titanium alloy flexibility
The flatness of the 13rd flange face 13 of link 10 and the 19th flange face 19 is better than 0.005mm, and the depth of parallelism must not be less than
0.008mm, wherein the 13rd flange face 13 are made up of three facets.Invar ring flange 9 and titanium alloy flexibility link 10
Connected using the screw 11 of 12 M5 and the straight pin 12 of 6 Ф 4 by the 13rd flange face 13 and the 21st flange face 21
Together, constitute soft section.
20th flange face 20 of the soft section is fixed together by screw and straight pin with tapered sleeve, and tapered sleeve is adopted with mirror body
Bonded together with epoxide-resin glue；19th flange face 19 of the soft section other end is solid with backboard by screw and straight pin
It is scheduled on together, constitutes mirror assembly.
Three soft sections are arranged symmetrically for 120 ° around mirror optical axis circumference, and the pawl in the three-jaw of each soft section will be along mirror body
Radial arrangement.
For ensureing the performance of soft section, the flange face of invar ring flange 9 and titanium alloy flexibility link 10 must assure that 0.005mm
Flatness and 0.008mm the depth of parallelism.Wherein, titanium alloy flexibility link 10 the 13rd flange face 13 be by three facets
Composition, and respectively there are the 14th soft groove 14 of three radial directions, the 16th soft groove 16, the 17th soft groove 17 in each faceted rear end
The 15th soft groove 15, the 18th soft groove 18 with two axial directions, it is difficult to ensure that high-precision flatness and the depth of parallelism.Therefore, need
To implement according to the Combined machining figure shown in Figure 12.Will 22 (the titanium alloy flexibility link of undressed soft groove of titanium alloy
10), it is fixed together by screw 11 and straight pin 12 with invar ring flange 9, (now titanium alloy 22 and invar ring flange 9
The flatness and the depth of parallelism of the flange face at upper two ends meets use requirement all through processing and grinding), three footpaths of Combined machining
To the 14th soft groove 14, the 16th soft groove 16 and the 17th soft groove 17, the 15th soft groove 15 of two axial directions, the 18th soft groove
18.The flatness of ten three flange face 13 titanium alloy flexibility link 10 in and the depth of parallelism so just can ensure that.
14th soft groove 14, the 16th soft groove 16, the 17th soft groove 17, the 15th soft groove 15 and the 18th soft groove 18 plus
Work operation adopts wire cutting, and adopts slow wire feeding technique, and will make pestle after machining is carried out to the inwall of each soft groove
Grinding, it is ensured that the roughness of each soft groove is better than 1.6.
Obviously, above-described embodiment is only intended to clearly illustrate example, and the not restriction to embodiment.Right
For those of ordinary skill in the art, can also make on the basis of the above description other multi-forms change or
Change.There is no need to be exhaustive to all of embodiment.And the obvious change thus extended out or
Change among still in the protection domain of the invention.
Claims (3)
1. the soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of a kind of space-based heavy caliber, it is characterised in that by invar
Ring flange (9) and titanium alloy flexibility link (10) two parts composition；
Upper and lower 21st flange face (21) of invar ring flange (9), the flatness of the 20th flange face (20) are better than
0.005mm, the depth of parallelism must not be less than 0.008mm；
Titanium alloy flexibility link (10) is circumferentially 120 ° of uniform three-jaw structures, including the of three radial directions on each pawl
14 soft groove (14), the 16th soft groove (16) and the 17th soft groove (17), the 15th soft groove (15) of two axial directions and the 18th
Soft groove (18)；
13rd flange face (13) of titanium alloy flexibility link (10) and the flatness of the 19th flange face (19) are better than
0.005mm, the depth of parallelism must not be less than 0.008mm, and wherein the 13rd flange face (13) is made up of three facets；
Invar ring flange (9) and titanium alloy flexibility link (10) are by the 13rd flange face (13) and the 21st flange face
(21) linked together using 12 screws (11) and 6 straight pins (12), constitute soft section.
2. the soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber according to claim 1, its
It is characterised by, the 14th soft groove (14), the 16th soft groove (16), the 17th soft groove (17), the 15th soft groove (15) and
18 soft groove (18) are using slow wire feeding and the grinding technics processing of wire cutting so as to which the roughness of inwall is better than 1.6.
3. the soft section of the split type bi-material layers of the high surface figure accuracy mirror assembly of space-based heavy caliber according to claim 1, its
It is characterised by, the 13rd flange face (13) is needed first by titanium alloy (22) and invar method by the way of Combined machining
After blue disk (9) are fixed together by screw (11) and straight pin (12), recombinant processes the 14th soft groove of three radial directions
(14), the 16th soft groove (16) and the 17th soft groove (17), the 15th soft groove (15) of two axial directions, the 18th soft groove (18).
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| CN201611114961.0A CN106443959A (en) | 2016-12-07 | 2016-12-07 | Split type bi-material flexible mechanism of space-based large-calibre high-facial-contour-precision reflector assembly |
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| CN108594399A (en) * | 2018-06-08 | 2018-09-28 | 中国科学院西安光学精密机械研究所 | A kind of support construction and support component of large caliber reflecting mirror |
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| CN111175928A (en) * | 2020-01-08 | 2020-05-19 | 合肥瑞利光学仪器有限公司 | Device structure of large-caliber inverted standard plane mirror |
| CN112130277A (en) * | 2020-09-28 | 2020-12-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
| CN112432004A (en) * | 2020-10-27 | 2021-03-02 | 北京控制工程研究所 | Flexible support structure for vibration suppression and heat dissipation support of spatial pointing measurement instrument |
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| CN114326013A (en) * | 2021-12-30 | 2022-04-12 | 中国科学院长春光学精密机械与物理研究所 | Primary mirror assembly for tilt measurement camera |
| CN114578505A (en) * | 2022-03-11 | 2022-06-03 | 中国科学院长春光学精密机械与物理研究所 | Back three-point supporting structure of space large-diameter reflector |
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| CN109932804B (en) * | 2019-03-04 | 2021-06-01 | 杭州电子科技大学 | Flexible memory alloy supporting device of small-caliber light reflector |
| CN109932804A (en) * | 2019-03-04 | 2019-06-25 | 杭州电子科技大学 | A kind of flexible memory alloy support device of small-bore lightweight mirror |
| CN109932805B (en) * | 2019-03-04 | 2021-06-01 | 杭州电子科技大学 | Adaptive supporting method for large-aperture reflector |
| CN111175928A (en) * | 2020-01-08 | 2020-05-19 | 合肥瑞利光学仪器有限公司 | Device structure of large-caliber inverted standard plane mirror |
| CN112130277A (en) * | 2020-09-28 | 2020-12-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
| CN112130277B (en) * | 2020-09-28 | 2021-06-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
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| CN112731612B (en) * | 2020-10-27 | 2022-07-29 | 北京控制工程研究所 | Flexible heat-dissipation vibration-reduction supporting structure for optical lens of space direction measuring instrument |
| CN112432004A (en) * | 2020-10-27 | 2021-03-02 | 北京控制工程研究所 | Flexible support structure for vibration suppression and heat dissipation support of spatial pointing measurement instrument |
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Application publication date: 20170222 |