CN102073123B - Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor - Google Patents
Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor Download PDFInfo
- Publication number
- CN102073123B CN102073123B CN2010106073455A CN201010607345A CN102073123B CN 102073123 B CN102073123 B CN 102073123B CN 2010106073455 A CN2010106073455 A CN 2010106073455A CN 201010607345 A CN201010607345 A CN 201010607345A CN 102073123 B CN102073123 B CN 102073123B
- Authority
- CN
- China
- Prior art keywords
- spron
- remote sensor
- small
- space optical
- optical remote
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Optical Transform (AREA)
Abstract
The invention discloses a single-point supporting flexible section for a small-aperture reflecting mirror of a space optical remote sensor, which belongs to the field of mechanical supporting. The supporting flexible section comprises a supporting mandrel body, three radial unloading troughs formed on the supporting mandrel body, three circumferential unloading troughs, three pasteboards and three clearances formed on the supporting mandrel body, wherein the pasteboards are arranged between the radial unloading troughs and the clearances; and the circumferential unloading troughs are formed in the pasteboards. The single-point supporting flexible section has small size and the maximum diameter of the single-point supporting flexible section is smaller than one third of the aperture of the reflecting mirror, so the single-point supporting flexible section can be processed and assembled conveniently and flexibly, and the installation space is saved; the reflecting mirror in which the single-point supporting flexible section is taken as a key supporting part is high in temperature adaptability, so when the external thermal deformation is transferred to the reflecting mirror through a mandrel, the deformation can be absorbed by the unloading troughs formed in two directions, which is equivalent to the process for shielding the reflecting mirror, so that the reflecting mirror is protected; and when the bonding working procedure is performed, the deformation energy produced by an adhesive layer during the solidification can be absorbed by the unloading troughs in two directions, so that the reflecting mirror is protected.
Description
Technical field
The present invention relates to the mechanical support field, particularly a kind of space optical remote sensor small-bore catoptron single-point supports gentle joint.
Background technology
In a kind of space optical remote sensor; The secondary mirror of participating in imaging is often small-sized; Secondary mirror generally all is set at the most significant end of remote sensor; Therefore installation site and space all receive very big limit extremely, and because the restriction of remote sensor thermal control, the working temperature of secondary mirror always fluctuates in the scope of broad.Because the influence of these factors is for guaranteeing the image quality of remote sensor, to the higher requirement of supporting construction proposition of secondary mirror.Supporting way commonly used at present mainly contains lateral support and mandrel rigid support, and these two kinds of methods have big limitation, are mainly reflected in: 1) perimeter support: complex structure, and bearing accuracy is poor, and assembly difficulty is big, and vibration resistance is relatively poor; 2) mandrel rigid support: catoptron is poor to the variation of temperature working environment adaptability; Simultaneously, the rigidity of small-bore catoptron is low, when carrying out bonding process, because bonding stress is bigger, can cause expendable distortion to catoptron, influences the image quality of catoptron.Therefore, developing novel space optical remote sensor, to support gentle joint imperative.
Summary of the invention
To above-mentioned situation; In order to address the deficiencies of the prior art, the object of the invention just is to provide a kind of space optical remote sensor small-bore catoptron single-point to support gentle joint, can effectively solve complex structure, bearing accuracy is poor; Assembly difficulty is big, and to the problem of thermal adaptability difference.
The technical scheme that technical solution problem of the present invention adopts is; A kind of space optical remote sensor small-bore catoptron single-point supports gentle joint; Comprise that support mandrel body, three are located at the radially spron on the back shaft body, three circumferential sprons, three pasting boards and three empty cuttves of opening on the back shaft body; Said pasting boards is located at radially between the spron and empty cutter, and said circumferential spron is opened in pasting boards.。
The present invention since single-point to support gentle joint size little, its maximum gauge is less than 1/3rd of the mirror aperture, process and assemble very convenient, flexible, so installing space can be saved greatly; It is high as the mirror temperature adaptability of critical support part to adopt single-point to support gentle joint; When extraneous thermal deformation through mandrel when catoptron transmits; Deformation energy can be absorbed by the spron of both direction fully, be equivalent to the process of catoptron conductively-closed, so catoptron is protected; When carrying out bonding process, the deformation energy that glue-line produces in solidification process can be absorbed by the spron of both direction equally, catoptron thereby be protected.
Description of drawings
Fig. 1 is the front view that a kind of space optical remote sensor of the present invention small-bore catoptron single-point supports gentle joint.
Fig. 2 is the cut-open view that a kind of space optical remote sensor of the present invention small-bore catoptron single-point supports gentle joint.
Among the figure, 1, the support mandrel body, 2, spron radially, 3, circumferential spron, 4, pasting boards, 5, empty cutter, 6, coupling shaft, 7, the unloading axle, 8, pin-and-hole, 9, screw hole, 10, first through hole, 11, second through hole.
Embodiment
Elaborate below in conjunction with the accompanying drawing specific embodiments of the invention.
By Fig. 1, shown in 2; A kind of space optical remote sensor small-bore catoptron single-point supports gentle joint; It is characterized in that; Comprise that support mandrel body 1, three are located at the circumferential spron of radially spron 2 on the back shaft body 1, three 3, three pasting boards 4 and three empty cuttves of opening on back shaft body 15, said pasting boards 4 is located at radially between the spron 2 and empty cutter 5, and said circumferential spron 3 is opened in pasting boards 4.
By shown in Figure 1, said pasting boards 4 is curved, and circumferentially spron 3 is curved.
The axis conllinear of the axis of said circumferential spron 3 and support mandrel body 1.
Said circumferential spron 3 communicates with spron 2 radially, and with radially spron 2 is vertical.
Said three radially spron 2 be rotation symmetry, three circumferential sprons 3 are the rotation symmetry, three empty cuttves 5 are the rotation symmetry.
Said adjacent circumferential spron 3, radially the arc angle that constitutes of spron 2 and empty cutter 5 is 120 °.
By shown in Figure 2; Said support mandrel body 1 comprises coupling shaft 6 and unloading axle 7, and both are integral structure, and the diameter of coupling shaft 6 is less than the diameter of unloading axle 7; Have first through hole 10 on the unloading axle 7; Coupling shaft 6 has second through hole, 11, the first through holes 10 and second through hole 11 communicates, and the diameter of first through hole 10 is greater than the diameter of second through hole 11.
By Fig. 1, shown in 2, said circumferential spron 3, radially spron 2 and pasting boards 4 all are located on the unloading axle 7, circumferentially spron 3 unloading axle 7 axially on connect; Have screw hole 9 and pin-and-hole 8 on the unloading axle 7.
Said three radially spron 2 be rotation symmetry, the longitudinal center line of per two adjacent radial sprons 2 differs 120 °; Said three circumferential sprons 3 are the rotation symmetry, and the longitudinal center line of per two adjacent radial sprons 2 differs 120 °; Said three empty cuttves 5 are the rotation symmetry, and the longitudinal center line of per two adjacent vacant cuttves 5 differs 120 °.
Integral body of the present invention all adopts titanium alloy material, and radially spron 2 and circumferential spron 3 all adopt the high precision silk thread cutting technique processing of being careful; Single-point supports the installed surface facing-up processing of gentle joint bonding plane and catoptron.
When the present invention installs, links to each other with catoptron above supporting gentle joint, links to each other with carrier below, adhesive sheet 4 will with the pilot hole coplane of catoptron, coaxial; In the time of installation, the size of empty cutter 5 is greater than the thickness of bonding glue-line; Installed surface is vertical with back shaft.
The present invention since single-point to support gentle joint size little, its maximum gauge is less than 1/3rd of the mirror aperture, process and assemble very convenient, flexible, so installing space can be saved greatly; It is high as the mirror temperature adaptability of critical support part to adopt single-point to support gentle joint; When extraneous thermal deformation through mandrel when catoptron transmits; Deformation energy can be absorbed by the spron of both direction fully, be equivalent to the process of catoptron conductively-closed, so catoptron is protected; When carrying out bonding process; The deformation energy that glue-line produces in solidification process; Can be absorbed equally by the spron of both direction, catoptron thereby be protected, thereby be specially adapted to that installing space is little, operating ambient temperature changes wide, launching phase vibration a kind of space optical remote sensor greatly.
Claims (8)
1. a space optical remote sensor small-bore catoptron single-point supports gentle joint; It is characterized in that; Comprise support mandrel body (1), three radially spron (2), three circumferential sprons (3), three pasting boards (4) and three empty cuttves of opening on back shaft body (1) (5) that are located on the back shaft body (1); Said pasting boards (4) is located at radially between the spron (2) and empty cutter (5), and said circumferential spron (3) is opened in pasting boards (4).
2. a kind of space optical remote sensor according to claim 1 small-bore catoptron single-point supports gentle joint, it is characterized in that said pasting boards (4) is curved, and circumferentially spron (3) is curved.
3. a kind of space optical remote sensor according to claim 1 and 2 small-bore catoptron single-point supports gentle joint, it is characterized in that the axis conllinear of the axis of said circumferential spron (3) and support mandrel body (1).
4. a kind of space optical remote sensor according to claim 1 small-bore catoptron single-point supports gentle joint, it is characterized in that, said circumferential spron (3) communicates with spron (2) radially, and with radially spron (2) is vertical.
5. support gentle joint according to claim 1 or 4 described a kind of space optical remote sensor small-bore catoptron single-points; It is characterized in that; Said three radially spron (2) be rotation symmetry, three circumferential sprons (3) are the rotation symmetry, three empty cuttves (5) are the rotation symmetry.
6. support gentle joint according to claim 1 or 4 described a kind of space optical remote sensor small-bore catoptron single-points, it is characterized in that, said adjacent circumferential spron (3), radially spron (2) is 120 ° with the arc angle of empty cutter (5) formation.
7. a kind of space optical remote sensor according to claim 1 small-bore catoptron single-point supports gentle joint; It is characterized in that; Said support mandrel body (1) comprises coupling shaft (6) and unloading axle (7), and both are integral structure, and the diameter of coupling shaft (6) is less than the diameter of unloading axle (7); Have first through hole (10) on the unloading axle (7); Coupling shaft (6) has second through hole (11), and first through hole (10) and second through hole (11) communicate, and the diameter of first through hole (10) is greater than the diameter of second through hole (11).
8. support gentle joint according to claim 1 or 7 described a kind of space optical remote sensor small-bore catoptron single-points; It is characterized in that; Said circumferential spron (3), radially spron (2) and pasting boards (4) all are located on the unloading axle (7), and circumferentially spron (3) connects axially going up of unloading axle (7); Have screw hole (9) and pin-and-hole (8) on the unloading axle (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106073455A CN102073123B (en) | 2010-12-27 | 2010-12-27 | Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106073455A CN102073123B (en) | 2010-12-27 | 2010-12-27 | Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102073123A CN102073123A (en) | 2011-05-25 |
| CN102073123B true CN102073123B (en) | 2012-07-25 |
Family
ID=44031730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010106073455A Expired - Fee Related CN102073123B (en) | 2010-12-27 | 2010-12-27 | Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102073123B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200623B (en) * | 2011-06-20 | 2012-08-22 | 北京空间机电研究所 | Micro-stress assembly flexible supporting method of small-calibre micro-crystal glass material reflector |
| CN102508348B (en) * | 2011-11-09 | 2014-03-12 | 中国科学院长春光学精密机械与物理研究所 | Spatial flexible filter supporting mechanism and method for mounting filter |
| CN102705657B (en) * | 2012-06-15 | 2014-10-15 | 中国科学院长春光学精密机械与物理研究所 | Flexible support frame for small high-stability multifunctional optical reflector |
| CN103792645B (en) * | 2014-01-24 | 2016-11-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of small mirrors superelevation power heat endurance supporting construction |
| CN106291864B (en) * | 2016-08-25 | 2019-04-02 | 中国科学院长春光学精密机械与物理研究所 | Reflecting mirror support structure, mirror assembly and optical remote sensing camera |
| CN106526784B (en) * | 2016-11-30 | 2019-01-08 | 中国科学院长春光学精密机械与物理研究所 | Plane mirror flexible support mechanism |
| CN109799594A (en) * | 2019-03-21 | 2019-05-24 | 长光卫星技术有限公司 | A kind of flexible mandrel for eliminating large caliber reflecting mirror adhesive stress |
| CN110764219A (en) * | 2019-11-08 | 2020-02-07 | 南昌航空大学 | Reflector bonding structure for reducing thermal stress |
| CN112255755B (en) * | 2020-11-17 | 2022-06-21 | 中国科学院长春光学精密机械与物理研究所 | Field diaphragm installation device and installation method thereof |
| CN112596198B (en) * | 2020-12-28 | 2022-06-21 | 中国科学院长春光学精密机械与物理研究所 | Curvature error adjusting device and method for large-caliber spliced reflector |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1243262A (en) * | 1999-06-18 | 2000-02-02 | 中国科学院上海技术物理研究所 | Support device for large-aperture optical main mirror for space use |
| CN101566718A (en) * | 2009-06-05 | 2009-10-28 | 中国科学院长春光学精密机械与物理研究所 | Flexible supporting structure for the back of reflecting mirror |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58211112A (en) * | 1982-06-02 | 1983-12-08 | Hitachi Ltd | Attitude adjusting device |
| JPH11308174A (en) * | 1998-04-20 | 1999-11-05 | Sony Corp | Mirror holding body and optical axis correction device using the body |
-
2010
- 2010-12-27 CN CN2010106073455A patent/CN102073123B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1243262A (en) * | 1999-06-18 | 2000-02-02 | 中国科学院上海技术物理研究所 | Support device for large-aperture optical main mirror for space use |
| CN101566718A (en) * | 2009-06-05 | 2009-10-28 | 中国科学院长春光学精密机械与物理研究所 | Flexible supporting structure for the back of reflecting mirror |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102073123A (en) | 2011-05-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102073123B (en) | Single-point supporting flexible section for small-aperture reflecting mirror of space optical remote sensor | |
| CN103792645B (en) | A kind of small mirrors superelevation power heat endurance supporting construction | |
| US9364933B2 (en) | Jig for Winston cone baffle machining | |
| CN102069109B (en) | Correction device and correction method for inner ring of engine crankcase | |
| CN101566718A (en) | Flexible supporting structure for the back of reflecting mirror | |
| US9989141B2 (en) | Fastening structure for fastening driven member to strain wave gearing device unit, and strain wave gearing device unit | |
| US9102135B2 (en) | Plate attachment device and method for attaching/detaching printing plate | |
| CN106526784A (en) | Flexible supporting mechanism for plane mirror | |
| WO2008156134A1 (en) | Lens unit, method of producing lens unit, and imaging device | |
| JP2010071705A (en) | Coupling centering tool | |
| CN201000386Y (en) | Dynamic balance device of axle coupler | |
| CN111308644A (en) | Silicon carbide reflector | |
| CN102096172B (en) | Back flexible supporting structure for reflecting mirror of space remote sensor | |
| EP3136566A1 (en) | Direct drive motor, conveyancing device, inspection device, and machine tool | |
| CN105911670A (en) | Planar mirror optical pointing assembly used for space | |
| CN204086654U (en) | A kind of ray machine integration silicon carbide mirror and system | |
| CN103472566B (en) | Zero-expansion flexible damping supporting device of space reflector | |
| US9358610B2 (en) | Device for supporting molten metal container | |
| CN105182501B (en) | A kind of large caliber reflecting mirror elastic connection expansion set | |
| CN104199171A (en) | Bare engine integrated silicon carbide reflecting mirror and preparation method thereof | |
| CN211083412U (en) | Temperature influence eliminating mechanism for pitching shafting of incubator turntable | |
| KR20130010816A (en) | Tool holder and spindle apparatus | |
| CN104350163B (en) | For the horizontal supporting portion of tipping converter with for the method transforming tipping converter | |
| CN103066800B (en) | Cold shrinkage-compensating and positioning superconducting motor | |
| CN207255790U (en) | A kind of machining center high-precision main shaft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120725 Termination date: 20131227 |