CN102081227A - Radial support mechanism for primary mirror of large-caliber telescope for eliminating temperature stress - Google Patents
Radial support mechanism for primary mirror of large-caliber telescope for eliminating temperature stress Download PDFInfo
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- CN102081227A CN102081227A CN2010105827370A CN201010582737A CN102081227A CN 102081227 A CN102081227 A CN 102081227A CN 2010105827370 A CN2010105827370 A CN 2010105827370A CN 201010582737 A CN201010582737 A CN 201010582737A CN 102081227 A CN102081227 A CN 102081227A
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- lever
- radial support
- primary mirror
- support seat
- indium steel
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- 229910000831 Steel Inorganic materials 0.000 claims abstract description 24
- 229910052738 indium Inorganic materials 0.000 claims abstract description 24
- 239000010959 steel Substances 0.000 claims abstract description 24
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical compound [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 claims abstract description 23
- 238000005096 rolling process Methods 0.000 claims abstract description 10
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 5
- 239000000741 silica gel Substances 0.000 claims abstract description 5
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 12
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 claims description 5
- 230000008030 elimination Effects 0.000 claims 3
- 238000003379 elimination reaction Methods 0.000 claims 3
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 2
- 229910052753 mercury Inorganic materials 0.000 description 2
- 230000005693 optoelectronics Effects 0.000 description 2
- 230000036760 body temperature Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
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Abstract
The invention provides a large-aperture telescope primary mirror radial supporting mechanism for eliminating temperature stress, which consists of a radial supporting seat, a lever bracket, a balancing weight, a lever, a low-pair sliding rod, a rolling bearing and an indium steel sleeve. The indium steel sleeve is sleeved on the radial support seat, the radial support seat is positioned in the middle of the indium steel sleeve, and silica gel is dotted at the clearance fit position of the indium steel sleeve and the radial support seat, so that the indium steel sleeve is fixed on the radial support seat; the lever is connected to the radial support seat through two mounting screws; the fulcrum end of the lever is connected to the lever bracket through two rolling bearings by a low pair of sliding rods; the balancing weight is screwed at the lower end part of the lever, and the balancing weight and the lever are in threaded connection; the two bearing cover plates cover the bearing holes of the lever bracket. When the main mirror radial supporting mechanism works, the lever support is fixedly connected onto a main mirror base by two mounting screws, and the radial supporting base extends into a radial supporting hole of a main mirror to be mounted.
Description
Technical field
The invention belongs to technical fields such as space exploration, astronomical sight, relate to a kind of heavy caliber telescopical primary mirror radial support mechanism and method for supporting.
Background technology
In technical fields such as space exploration, astronomical sights, be the implementation space long-range target acquisition, the exploration of the universe secret, the bore that needs to increase photoelectric detection equipment improves the resolution of system and collects more target energy, thus easier discovery and recognition objective.Heavy caliber primary mirror in these optoelectronic devices is the key component of entire equipment, and it not only had been subjected to the influence of external environment but also had been subjected to the effect of support system, and the primary mirror surface face deformations that these effects produce will cause the decline of the optics picture element of entire equipment.The support of heavy caliber primary mirror need be satisfied the requirement of support accuracy, and the structure dimension of supporting mechanism also can influence the one-piece construction performance of photoelectric detection equipment in addition; Streamlining organizations and satisfying the support accuracy requirement is the technical matters that large photoelectric equipment needs are considered.Therefore need to improve supporting mechanism and method for supporting and reduce the influence of the external world and supporting mechanism itself primary mirror and whole optoelectronic device.
At present, the normal flexible support that is supported on the mercury band of the external side of mirror or is installed in the side that adopts of heavy caliber primary mirror radial support both domestic and external, these method for supporting have not only increased the radial dimension of mechanism, and have influenced the radial support precision of big relative aperture primary mirror.
Summary of the invention
For the support accuracy problem of the inconsistent problem of the thermal expansivity that solves prior art primary mirror material and propping material, object lens of large relative aperture primary mirror, big physical dimension influences the problem of one-piece construction performance, the objective of the invention is will a kind of heavy caliber telescope primary mirror radial support mechanism of eliminating temperature stress.
In order to realize purpose of the present invention, the invention provides the heavy caliber telescope primary mirror radial support mechanism of eliminating temperature stress, solve the technical scheme that its technical matters adopts and comprise: radial support seat, lever dolly, balancing weight, lever, lower pair slide bar, bearing cover, mounting screw, rolling bearing and indium steel bushing; Wherein the indium steel bushing is placed on the radial support seat, and the radial support seat is positioned at the middle part of indium steel bushing, and at they clearance fit place's point silica gel, the indium steel bushing is fixed on the radial support seat; Lever is connected on the radial support seat by two mounting screws; The support end of lever is connected on the lever dolly by two rolling bearings by the lower pair slide bar; Balancing weight is threaded onto the bottom of lever, between them for being threaded; Two bearing covers are placed on the dead eye of lever dolly; When this primary mirror radial support mechanism works, be connected on the primary mirror seat by two mounting screws by lever dolly, the radial support seat stretches in the radial support hole of primary mirror to be installed.
Between described lower pair slide bar and the lever is clearance fit; Tolerance on fit is 0.01mm～0.03mm; The profile arithmetic average error of roughness height parameter that will make matching surface simultaneously is less than 0.8 μ m.
Relative translation and the radial support seat distortion of lever when the rotation of lower pair slide bar jointly eliminate temperature variation primary mirror and primary mirror radial support mechanism inconsistent of this primary mirror radial support mechanism by described lower pair slide bar and lever.
Except that the indium steel bushing, the material of remaining parts is general ferrous materials in this primary mirror radial support mechanism.
The present invention compared with prior art has following advantage:
Be the size of restriction primary mirror support system radial direction, improve the support accuracy of radial direction, the present invention proposes to realize radial support in primary mirror mirror body, can reduce the radial dimension of equipment greatly.When the ambient temperature variation caused primary mirror mirror body to produce internal stress, this primary mirror radial support mechanism can be converted to internal stress the lever displacement of two vertical direction, and primary mirror mirror body temperature inside stress is just eliminated.Adopt lever balance theory, by selecting and adjusting balancing weight and realize primary mirror support radially.This primary mirror radial support mechanism embeds primary mirror inside, and its strong point has reduced the lateral dimension that primary mirror mirror body supports in primary mirror mirror body, be convenient to improve the overall performance of heavy caliber telescope equipment like this.When causing the indium steel bushing of primary mirror mirror body radial deformation and primary mirror radial support mechanism, temperature variation is out of shape when inconsistent, this primary mirror radial support mechanism can be converted to radial deformation the displacement of two vertical direction in the sagittal plane, has avoided because the primary mirror minute surface distortion that temperature stress caused.This primary mirror radial support mechanism has very high support accuracy, can be used for large telescope equipment primary mirror and supports, and relates to technical fields such as photodetection, astronomical sight.
1, the primary mirror supporting seat needn't adopt and the approaching material of primary mirror line of material expansion coefficient, adopts general ferrous materials to get final product, and the influence of temperature stress to primary mirror can be eliminated by this primary mirror radial support mechanism under this state; Temperature variation only produces the variation of defocusing amount, can eliminate at interval by adjusting the primary and secondary mirror.
2, primary mirror radial support mechanism is embedded in primary mirror inside, has reduced the radial support space of primary mirror greatly, has simplified system architecture, has improved the mobility of the mirror device of looking in the distance.
3, compare with mercury band radial support form, the primary mirror radial support mechanism that the present invention proposes can improve the radial support precision greatly, and especially for the support of big relative aperture primary mirror, effect is more obvious.
Description of drawings
Fig. 1 eliminates the structure diagram of the heavy caliber telescope primary mirror radial support mechanism of temperature stress for what the present invention proposed based on lever balance theory.
Part description among Fig. 1:
The 1-primary mirror, 2-radial support seat,
3-primary mirror seat, the 4-lever dolly,
The 5-balancing weight, the 6-lever,
7-lower pair slide bar, the 8-bearing cover,
9, the 10-mounting screw, the 11-rolling bearing,
12-indium steel bushing, 13-radial support hole,
The bearing seat of 14-lever dolly 4, the threaded interior hole of 15-balancing weight 5,
The external thread of 16-lever 6.
Embodiment
For making the purpose, technical solutions and advantages of the present invention clearer, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
The present invention utilize lever balance theory propose to eliminate temperature stress heavy caliber telescope primary mirror radial support mechanism structure diagram as shown in Figure 1, comprise: radial support seat 2, primary mirror seat 3, lever dolly 4, balancing weight 5, lever 6, lower pair slide bar 7, bearing cover 8, mounting screw 9,10, rolling bearing 11, indium steel bushing 12; Wherein indium steel bushing 12 is placed on the radial support seat 2, and radial support seat 2 is positioned at the middle part of indium steel bushing 12, and at they clearance fit place's point silica gel, indium steel bushing 12 is fixed on the radial support seat 2; Lever 6 is connected on the radial support seat 2 by two mounting screws 10; The support end of lever 6 is connected on the lever dolly 4 by two rolling bearings 11 by lower pair slide bar 7; Balancing weight 5 is threaded onto the bottom of lever 6, between them for being threaded; Two bearing covers 8 are placed on the dead eye of lever dolly 4; When this primary mirror radial support mechanism works, be connected on the primary mirror seat 3 by two mounting screws 9 by lever dolly 4; Radial support seat 2 stretches in the radial support hole 13 of primary mirror 1 to be installed.
This primary mirror radial support mechanism by lower pair slide bar 7 and lever 6 relative translation and lever 6 that the radial support seat 2 of mirror body and supporting mechanism is out of shape when the rotation of lower pair slide bar 7 is eliminated temperature variation jointly is inconsistent.
Its concrete enforcement is as follows:
The first step: provide the structure diagram of primary mirror radial support of the present invention mechanism according to Fig. 1, design is satisfied heavy caliber telescope primary mirror and is supported the primary mirror radial support mechanism that requires; Wherein radial support seat 2 outer ledges need be used the bonding indium steel bushing 12 of elastic silica gel, in order to avoid the radial support seat 2 of general ferrous materials directly contacts with primary mirror 1, damage primary mirror 1; Between the radial support hole 13 of indium steel bushing 12 and primary mirror 1 is clearance fit, and tolerance on fit is chosen to be between 0.03～0.05mm, makes the primary mirror 1 radial support seat 2 of packing into smoothly; Also to guarantee simultaneously when temperature variation, can the surface figure accuracy of primary mirror 1 not to be exerted an influence; Radial support seat 2 is connected on the lever 6 by two mounting screws 10; The through hole of lever 6 center sections is used for installing lower pair slide bar 7; The upside of lever dolly 4 is two bearing seats 14; Accuracy requirement designs balancing weight 5 according to actual support, the threaded interior hole of threaded interior hole 15 for matching with the external thread 16 of lever 6 lower ends of balancing weight 5; The each part mentioned above part is except that indium steel bushing 12, and material all is general ferrous materials.
Second step: as shown in Figure 1, lower pair slide bar 7 being passed lever 6, and lower pair slide bar 7 is connected on the lever dolly 4 by rolling bearing 11, is clearance fit between lower pair slide bar 7 and the lever 6; Tolerance on fit is elected 0.01～0.03mm as, avoids because tolerance makes lever 6 stuck in sliding process too greatly, perhaps because tolerance is too for a short time lever 6 slips is had some setbacks; The roughness height parameter profile arithmetic average error that will make matching surface simultaneously is less than 0.8 μ m, to guarantee that lever 6 is free to slide on slide bar; Requiring weight according to the actual support of heavy caliber telescope primary mirror is the bottom that the balancing weight 5 of m=ML/nl is threaded onto lever 6.Wherein M represents the quality of primary mirror 1, the primary mirror barycenter was to the distance between the fulcrum of lever 6 when L represented primary mirror 1 vertical the placement, n represents the quantity (optional 3 of primary mirror radial support mechanism, 9,27), l represents the distance between the fulcrum of balancing weight 5 and lever 6, and this distance can freely be selected (guaranteeing that balancing weight 5 is in external thread 16 scopes of lever 6), and wherein the fulcrum of lever 6 is at lower pair slide bar 7 places.
The 3rd step; As shown in Figure 1, lever dolly 4 is connected in by two mounting screws 9 on the bottom surface of primary mirror seat 3 of horizontal positioned; Radial support seat 2 is in the mirror body at this moment, and according to the weight and the actual support requirement of primary mirror 1, turn balancing weight 5 is to correct position, and when this position can guarantee that primary mirror is vertically placed, lever 6 was in horizontality.Particular location is determined by formula ML=nml, M represents the quality of primary mirror 1 in the formula, the primary mirror barycenter was to the distance between the fulcrum of lever 6 when L represented primary mirror 1 vertical the placement, wherein the fulcrum of lever 6 is at lower pair slide bar 7 places, n represents the quantity of primary mirror radial support mechanism, m represents the quality of balancing weight 5, and l represents the distance between the fulcrum of balancing weight 5 and lever 6.
Above-described embodiment only limits to explain the present invention, and protection scope of the present invention should comprise the full content of claim, and promptly can realize the full content of claim of the present invention by the embodiment person skilled in art.
Claims (4)
1. heavy caliber telescope primary mirror radial support mechanism of eliminating temperature stress, it is characterized in that comprising: radial support seat (2), lever dolly (4), balancing weight (5), lever (6), lower pair slide bar (7), bearing cover (8), mounting screw (9,10), rolling bearing (11) and indium steel bushing (12); Wherein indium steel bushing (12) is placed on the radial support seat (2), and radial support seat (2) is positioned at the middle part of indium steel bushing (12), and at they clearance fit place's point silica gel, indium steel bushing (12) is fixed on the radial support seat (2); Lever (6) is connected on the radial support seat (2) by two mounting screws (10); The support end of lever (6) is connected on the lever dolly (4) by two rolling bearings (11) by lower pair slide bar (7); Balancing weight (5) is threaded onto the bottom of lever (6), between them for being threaded; Two bearing covers (8) are placed on the dead eye of lever dolly (4); When this primary mirror radial support mechanism works, be connected on the primary mirror seat (3) by two mounting screws (9) by lever dolly (4); Radial support seat (2) stretches in the radial support hole (13) of primary mirror to be installed (1).
2. the heavy caliber telescope primary mirror radial support mechanism of elimination temperature stress according to claim 1, it is characterized in that: between described lower pair slide bar (7) and the lever (6) is clearance fit; Tolerance on fit is 0.01mm～0.03mm; The profile arithmetic average error of roughness height parameter that will make matching surface simultaneously is less than 0.8 μ m.
3. the heavy caliber telescope primary mirror radial support mechanism of elimination temperature stress according to claim 1 is characterized in that: this primary mirror radial support mechanism by lower pair slide bar (7) and lever (6) relative translation and lever (6) that the radial support seat (2) of mirror body and supporting mechanism is out of shape when the rotation of lower pair slide bar (7) is eliminated temperature variation jointly is inconsistent.
4. the heavy caliber telescope primary mirror radial support mechanism of elimination temperature stress according to claim 1, it is characterized in that: except that the indium steel bushing, the material of remaining parts is general ferrous materials in this primary mirror radial support mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010582737 CN102081227B (en) | 2010-12-06 | 2010-12-06 | Radial support mechanism for primary mirror of large-caliber telescope for eliminating temperature stress |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010582737 CN102081227B (en) | 2010-12-06 | 2010-12-06 | Radial support mechanism for primary mirror of large-caliber telescope for eliminating temperature stress |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102081227A true CN102081227A (en) | 2011-06-01 |
| CN102081227B CN102081227B (en) | 2012-12-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010582737 Active CN102081227B (en) | 2010-12-06 | 2010-12-06 | Radial support mechanism for primary mirror of large-caliber telescope for eliminating temperature stress |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103412400A (en) * | 2013-07-20 | 2013-11-27 | 中国科学院光电技术研究所 | Heat diaphragm adjustable type segmented supporting device for coaxial solar telescope |
| CN107422453A (en) * | 2017-06-09 | 2017-12-01 | 中国科学院长春光学精密机械与物理研究所 | Lever torque compensation mechanism for large caliber reflecting mirror |
| CN109960030A (en) * | 2017-12-14 | 2019-07-02 | 哈尔滨新光光电科技有限公司 | It is a kind of big temperature range work heavy-caliber optical system without thermalization method |
| CN114035310A (en) * | 2021-11-23 | 2022-02-11 | 四川中科朗星光电科技有限公司 | Hyperboloid secondary mirror using free-form surface to replace RC optical system |
| CN114047593A (en) * | 2022-01-14 | 2022-02-15 | 中国人民解放军63921部队 | Light-weight SiC primary mirror supporting mechanism of optical measuring equipment |
Citations (3)
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| US6478434B1 (en) * | 1999-11-09 | 2002-11-12 | Ball Aerospace & Technologies Corp. | Cryo micropositioner |
| CN101059595A (en) * | 2007-06-05 | 2007-10-24 | 中国科学院国家天文台南京天文光学技术研究所 | Elastic element based three freedom degree precision movement support device |
| CN101621151A (en) * | 2009-08-12 | 2010-01-06 | 中国科学院国家天文台南京天文光学技术研究所 | Frame structure of reflecting surface of prestressing light antenna and preparation method thereof |
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2010
- 2010-12-06 CN CN 201010582737 patent/CN102081227B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6478434B1 (en) * | 1999-11-09 | 2002-11-12 | Ball Aerospace & Technologies Corp. | Cryo micropositioner |
| CN101059595A (en) * | 2007-06-05 | 2007-10-24 | 中国科学院国家天文台南京天文光学技术研究所 | Elastic element based three freedom degree precision movement support device |
| CN101621151A (en) * | 2009-08-12 | 2010-01-06 | 中国科学院国家天文台南京天文光学技术研究所 | Frame structure of reflecting surface of prestressing light antenna and preparation method thereof |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103412400A (en) * | 2013-07-20 | 2013-11-27 | 中国科学院光电技术研究所 | Heat diaphragm adjustable type segmented supporting device for coaxial solar telescope |
| CN103412400B (en) * | 2013-07-20 | 2015-12-02 | 中国科学院光电技术研究所 | Heat diaphragm adjustable type segmented supporting device for coaxial solar telescope |
| CN107422453A (en) * | 2017-06-09 | 2017-12-01 | 中国科学院长春光学精密机械与物理研究所 | Lever torque compensation mechanism for large caliber reflecting mirror |
| CN109960030A (en) * | 2017-12-14 | 2019-07-02 | 哈尔滨新光光电科技有限公司 | It is a kind of big temperature range work heavy-caliber optical system without thermalization method |
| CN114035310A (en) * | 2021-11-23 | 2022-02-11 | 四川中科朗星光电科技有限公司 | Hyperboloid secondary mirror using free-form surface to replace RC optical system |
| CN114047593A (en) * | 2022-01-14 | 2022-02-15 | 中国人民解放军63921部队 | Light-weight SiC primary mirror supporting mechanism of optical measuring equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102081227B (en) | 2012-12-19 |
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