CN102324625A - Active reflector structure of radio telescope - Google Patents
Active reflector structure of radio telescope Download PDFInfo
- Publication number
- CN102324625A CN102324625A CN201110151707A CN201110151707A CN102324625A CN 102324625 A CN102324625 A CN 102324625A CN 201110151707 A CN201110151707 A CN 201110151707A CN 201110151707 A CN201110151707 A CN 201110151707A CN 102324625 A CN102324625 A CN 102324625A
- Authority
- CN
- China
- Prior art keywords
- panel
- active
- node
- radio telescope
- reflector
- 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.)
- Granted
Links
Images
Landscapes
- Aerials With Secondary Devices (AREA)
Abstract
The invention relates to an active reflector structure of a radio telescope. A panel active adjusting mechanism is arranged on a panel supporting back rack, and a reflective panel unit is arranged on the panel active adjusting mechanism. The active reflector structure of the radio telescope is characterized in that the reflective panel unit consists of an active reflective panel and a passive reflective panel, wherein the active reflective panel is connected with the panel active adjusting mechanism; the passive reflective panel is connected with the active reflective panel through a panel connecting node mechanism; and the passive reflective panel is supported and driven by the active reflective panel through three angular points to realize passive displacement. The invention proposes the active reflector structure of the radio telescope with innovative active and passive conception, which is different from a high-cost mode that each piece of mirror unit needs a set of independent multiple-degree-of-freedom adjusting mechanism and is also different from the mode with the defect that a panel is easy to be subjected to restraint stress due to the fixed connection between a flexible connecting rod of an actuator and an adjacent panel. According to the active reflector structure of the radio telescope, the complexity level of a supporting mechanism is reduced, and the excessive restraint stress among panels is avoided.
Description
Technical field
The invention belongs to the astronomical telescope field, relate to the technology of radio telescope active reflecting plane, be specifically related to a kind of radio telescope active reflecting plane structure.
Background technology
Modern radio telescope bore is increasing, and the observation wave band often requires shorter and shorter again, for overcoming gravity deformation and thermal deformation; Revise the face shape of reflecting surface; Improve antenna efficiency, guarantee telescopical service behaviour, initiatively adjustment technology of panel is extensively adopted in the development of radio telescope.Structure as shown in Figure 1 adds initiatively adjusting mechanism B of panel between panel support back of the body frame C and Reflector Panel unit A, carry on the back the reflection face shape error that factors such as frame gravity deformation and thermal deformation cause with correction, or realize the face shape of certain requirement of reflecting surface.
At present; The still fan anchor ring plates that adopt of the radio telescope of using the active surface plate technique more; And in most of the cases, the angle point of adjacent panels (be generally 4 adjacent panels adjacent four jiaos) be linked together, and drive (being referred to as " sharing the displacement actuator design ") at this by a displacement actuator; With the normal direction displacement of adjustment panel and the inclination of both direction, common three degree of freedom.The distribution of displacement actuator is as shown in Figure 2, and average like this each piece panel needs a cover displacement actuator adjusting mechanism.
The above-mentioned shared displacement actuator method that generally all adopts radio telescope designs its initiatively panel system, promptly adjacent panel angle point by a shared displacement driver be linked together and realize displacement drive.From the viewpoint of theory of mechanisms, this panel support system is hyperstatic, and promptly when displacement actuator is worked, panel will suffer restraint stress, and this stress will cause the distortion of high accuracy panel.Share this shortcoming that the actuator design brings for alleviating, the supporting member that panel links to each other with displacement actuator generally must design to such an extent that have certain lateral flexibility to alleviate the unpredictable restraint stress of crossing.
Summary of the invention
In order to overcome the defective and the deficiency of radio telescope active reflecting plane technology in the prior art; The purpose of this invention is to provide a kind of radio telescope active reflecting plane structure; The outstanding feature of this structure is all to carry out active adjustment or passive adjustment to the six-freedom degree of every panel, makes that the face shape of radio telescope reflecting surface is more accurate; For the telescope of same Reflector Panel quantity, can significantly reduce the quantity of adjusting mechanism, make telescopical Electromechanical Control complexity reduce, manufacturing cost descends, and operational reliability improves.
The scheme of accomplishing the foregoing invention task is, a kind of radio telescope active reflecting plane structure, and the splicing panel unit is installed in panel initiatively on the adjusting mechanism, and initiatively adjusting mechanism is installed on the back frame structure.It is characterized in that; Described Reflector Panel cellular zone is divided into initiatively Reflector Panel and (or is called " the active Reflector Panel that is connected with the active adjusting mechanism "; Be called for short active plate or main panel) (or be called " the passive Reflector Panel that is not connected " with driven Reflector Panel with the active adjusting mechanism; Be called for short passive plate or from panel), active Reflector Panel wherein and panel initiatively adjusting mechanism are connected, accept panel initiatively the displacement of adjusting mechanism control; Described driven Reflector Panel is coupled to each other with Reflector Panel initiatively through panel connected node mechanism (or be called the bindiny mechanism between the adjacent panels, or be called for short the panel joint mechanism, or node); Driven Reflector Panel by the support/drive of active Reflector Panel, carries out passive displacement through three angle points.
The set-up mode of described joint mechanism is: initiatively Reflector Panel and driven Reflector Panel are provided with at interval, and guarantee to be connected with at least on the every driven Reflector Panel three panel connected node mechanisms.
In the above scheme, described " driven Reflector Panel is coupled to each other with the active Reflector Panel through panel connected node mechanism ", its mode has following several kinds:
1, substrate, swing arm connected mode: on a substrate, rotation is provided with some swing arms symmetrically, and (for the hexagon panel, be on a substrate, rotation is provided with 3 swing arms symmetrically; For triangular panels, then be on a substrate, rotation is provided with 6 swing arms symmetrically); Swing arm is hinged in the node substrate through post, and the other end of swing arm links to each other with each panel through ball pivot.Like this, every panel is supported and the location by 3 groups of oscillating arm mechanisms, and 3 groups of oscillating arm mechanisms that support same panel are installed and connected in respectively on 3 panel connected nodes.
2, two power bar simply-support panel node and supporting mechanism modes: rotation installs symmetrically that some (for the hexagon panel, be on a substrate, rotation is provided with 3 swing arms symmetrically to two power linkages in each panel connected node mechanism; For triangular panels, then be on a substrate, rotation is provided with 6 swing arms symmetrically); One end of every pair two power bar links to each other with the node substrate through 2 Hooke's hinges respectively, and the other end of every pair two power bar links to each other with the angle point of panel through 1 common ball pivot.Like this, every panel carries out freely-supported and location through 3 pairs two power linkages; And 3 couple, the two power linkages that support same panel are installed and connected in respectively on 3 panel connected nodes.
3, elasticity chip panel support mechanism mode: rotation is installed some thin flexure strips symmetrically (for the hexagon panel, 3 thin flexure strips is installed in rotation symmetrically on each panel node in each panel connected node mechanism; For triangular panels, then 6 thin flexure strips are installed in rotation symmetrically on each panel node; The drift angle of this flexure strip is got 55-65 degree); The base of every thin flexure strip and node substrate are connected, and the summit of every thin flexure strip and the angle point of panel are connected.That is, replace two power linkages in second kind of scheme with thin flexure strip mechanism.Good rigidity and the good flexibility of normal direction realizes the freely-supported characteristic that two power linkages provide in the face of the thin shell fragment of utilization.This elasticity chip support scheme, structure and technology are more succinct.But the thickness of flexure strip need suitably be chosen through designing and calculating.
In other words, the technical scheme that adopted of technical solution problem of the present invention is: the active reflecting surface organization plan that at first proposes a kind of MS master-slave notion.Shown in Fig. 3 (face plate configuration is a triangle) and Fig. 4 (face plate configuration is a hexagon), wherein " main panel " promptly is the active Reflector Panel, can carry out the six-freedom degree displacement; Around it " from panel " is installed, promptly driven Reflector Panel, or claim passive panel; Be coupled to each other through custom-designed panel connected node mechanism between the MS master-slave panel, and must be able to discharge panel and cross restraint stress.Like this; Pass through three angle points by main panel support/drive from panel; Thereby the rigid motion that has satisfied a rigid body (promptly from panel) is learned the mechanics principle that just depends on 3 points (three angle points of its three adjacent main panels); That is,, can reach correct position by nature from panel when main panel is initiatively adjusted to correct position by certain mechanism in six degree of freedom.The active panel of MS master-slave notion has tangible advantage, like the displacement error on all six-freedom degrees of recoverable panel, avoids panel to cross problems such as constraint, and is expected to reduce cost.
Then, the present invention proposes 3 kinds of panel bindiny mechanisms and panel support mechanism scheme.Panel bindiny mechanism, hereinafter referred to as " node " is used for connecting and locating passive panel, and transmits the motion between the panel.Fig. 5, Fig. 6 and shown in Figure 7ly propose swing arm panel connected node mechanism and panel support mechanism scheme for the present invention.With the hexagon panel is example, and on a substrate, rotation is provided with 3 swing arms (for triangular panels, then being 6 swing arms) symmetrically, and the length of swing arm and pivot angle size are confirmed by concrete designing requirement.Swing arm is hinged in the node substrate through post, and the other end of swing arm links to each other in panel through ball pivot.Like this, every panel is supported and the location by 3 groups of oscillating arm mechanisms, and 3 groups of oscillating arm mechanisms that support same panel are installed and connected in respectively on 3 panel connected nodes.
Second kind of panel connected node mechanism that Fig. 8 and shown in Figure 9 proposes for the present invention and panel support mechanism scheme are referred to as two power bar simply-support panel node and supporting mechanism schemes.With the hexagon panel is example, and 3 pairs two power linkages (for triangular panels, then being 6 pairs two power bars) are installed in rotation symmetrically on each panel node.Corner dimension between the length of two power bars and the every pair two power bar (generally getting 55-65 degree) is confirmed by concrete designing requirement.Every pair two power bar links to each other in the node substrate through 2 Hooke's hinges respectively in an end, and the other end links to each other with the angle point of panel through 1 common ball pivot.Like this, every panel carries out freely-supported and location through 3 pairs two power linkages; And 3 couple, the two power linkages that support same panel are installed and connected in respectively on 3 panel connected nodes.
Figure 10 is referred to as elasticity chip panel support mechanism scheme for the third panel connected node and panel support mechanism scheme that the present invention proposes.That is, replace two power linkages in second kind of scheme with thin flexure strip mechanism.Good rigidity and the good flexibility of normal direction realizes the freely-supported characteristic that two power linkages provide in the face of the thin shell fragment of utilization.This elasticity chip support scheme, structure and technology are more succinct.But the thickness of flexure strip need suitably be chosen through designing and calculating.
Above-mentioned three kinds of panel nodes and supported design scheme all have following characteristics and advantage:
⑴. clear principle is clear, symmetrical configuration is compact;
⑵. satisfy normal direction and the support of side direction and the requirement of location of counter plate;
⑶. when main panel is subjected to displacement; Or when causing the panel connected node to be subjected to displacement because of factors such as thermal expansion, gravity and wind carry; All can compensate, and can not produce additional load by counter plate, thereby can not destroy the face shape of panel or destruction panel by the passive movement of panel support mechanism;
⑷. only be connected in panel by 3 ball pivot or elastic steel sheets with 3 rotary freedoms; Thereby allow any distortion of panel itself; And distortion that panel itself is inner and stress also obtain discharging; Thereby do not have Stress Transfer to panel connected node, this means the initiatively working stress and the state of reflecting surface active movement adjusting mechanism of not influencing.
Characteristic of the present invention is with the innovation part: proposed the radio telescope active reflecting plane panel construction of the MS master-slave notion of innovation, the every sub-mirror unit that is different from optical telescope all will have the expensive pattern of the independent multiple degrees of freedom adjusting mechanism of a cover; The flexible coupling bar of actuator and the adjacent panels that also are different from the active reflecting surface technology of prior art are fixedly connected and make panel subject to the defective of restraint stress.The active reflection surface system of MS master-slave notion is in the complexity that reduces supporting mechanism and avoid having novelty and pioneering on the mistake restraint stress between the panel.
Description of drawings
Fig. 1 is the radio telescope active reflecting plane structural representation;
Fig. 2 is the radio telescope panel and the supporting construction sketch map thereof of prior art;
Fig. 3 is the MS master-slave notion active surface plate structure sketch map of triangle for panel of the present invention;
Fig. 4 is hexagonal MS master-slave notion active surface plate structure sketch map for panel of the present invention;
Fig. 5 is swing arm panel node and supporting mechanism sketch map one;
Fig. 6 is a swing arm panel support mechanism sketch map two;
Fig. 7 is swing arm panel node and supporting mechanism sketch map three;
Fig. 8 is two power bar simply-support panel support mechanism sketch mapes one;
Fig. 9 is two power bar simply-support panel node and supporting mechanism sketch mapes two;
Figure 10 is an elasticity chip panel support mechanism sketch map;
Figure 11 is for using 30 meters bores active reflecting surface examples of MS master-slave panel notion;
Figure 12 is a swing arm panel support applying examples.
Embodiment
As an example, this MS master-slave panel notion is applied to the design of a 30m bore radio telescope.Adopted the angle to be of a size of the hexagon panel of 1.5 m to the angle, had 438 panels, wherein 162 is main panel, and 276 is from panel.
With reference to Figure 11 and Figure 12: hexagon main panel 1 is driven by the active adjusting mechanism, drives panel connected node mechanism 2.In panel connected node mechanism 2, panel support swing arm 5 one ends are installed and connected in the panel connected node mechanism 2 through post hinge 4, and panel support swing arm 5 other ends connect through ball pivot 6 and support hexagon from panel 3.
Relatively: in this case, classical active reflecting surface radio telescope will need 438x3=1314 accurate displacement actuator to accomplish the displacement drive of 1 normal direction translation and 2 inclinations.And the active reflecting surface structure of MS master-slave notion, even the displacement on all 6 degrees of freedom of every panel of needs driving also only needs 162 mechanism in six degree of freedom, i.e. 162x6=972 displacement actuator.And if also only need accomplish the displacement drive of 1 normal direction translation and 2 inclinations; Then only need 486 displacement accuracy displacement actuators; Be equivalent to 37% of tradition active reflecting surface, this significant funds saving beyond doubt, and; Displacement on all 6 degrees of freedom of the active reflecting surface structure permission driving panel of MS master-slave notion, this is that traditional active reflecting surface can't be realized.
Claims (9)
1. radio telescope active reflecting plane structure; On panel support back of the body frame, be provided with initiatively adjusting mechanism of panel; This panel initiatively adjusting mechanism is provided with the Reflector Panel unit, it is characterized in that described Reflector Panel unit is made up of active Reflector Panel and driven Reflector Panel; Active Reflector Panel wherein is connected with panel active adjusting mechanism, accepts the initiatively displacement control of adjusting mechanism of panel; Described driven Reflector Panel is coupled to each other with the active Reflector Panel through panel connected node mechanism; Driven Reflector Panel by the support/drive of active Reflector Panel, carries out passive displacement through three angle points.
2. radio telescope active reflecting plane structure according to claim 1; It is characterized in that; The set-up mode of said panel connected node mechanism is: initiatively Reflector Panel and driven Reflector Panel are provided with at interval, and guarantee to be connected with at least on the every leg-of-mutton driven Reflector Panel three panel connected node mechanisms.
3. radio telescope active reflecting plane structure according to claim 1; It is characterized in that; Described " driven Reflector Panel is coupled to each other with the active Reflector Panel through panel connected node mechanism "; Its mode is to adopt substrate, swing arm connected mode: on a substrate, rotation is provided with some swing arms symmetrically; Swing arm is hinged in the node substrate through post; The other end of swing arm links to each other with each panel through ball pivot: every panel is supported by 3 groups of oscillating arm mechanisms and locatees, and 3 groups of oscillating arm mechanisms that support same panel are installed and connected in respectively on 3 panel connected node mechanisms.
4. radio telescope active reflecting plane structure according to claim 3 is characterized in that, and is described on a substrate, and rotation is provided with some swing arms symmetrically, is meant: for the hexagon panel, be on a substrate, rotation is provided with 3 swing arms symmetrically; For triangular panels, then be on a substrate, rotation is provided with 6 swing arms symmetrically.
5. radio telescope active reflecting plane structure according to claim 1; It is characterized in that; Described " driven Reflector Panel is coupled to each other with the active Reflector Panel through panel connected node mechanism ", its mode is to adopt two power bar simply-support panel node and supporting mechanism modes: rotation is installed some to two power linkages symmetrically on each panel joint mechanism; One end of every pair two power bar links to each other with the node substrate through 2 Hooke's hinges respectively, and the other end of every pair two power bar links to each other with the angle point of panel through 1 common ball pivot.
6. radio telescope active reflecting plane structure according to claim 5; It is characterized in that; Rotation is installed symmetrically and some two power linkages is meant on described each panel joint mechanism: for the hexagon panel, 3 pairs two power linkages are installed in rotation symmetrically on each panel node; For triangular panels, then 6 pairs two power bars are installed in rotation symmetrically on each panel node; Angle between this every pair two power bar is got 55-65 degree.
7. the radio telescope active reflecting plane structure of six-freedom degree displacement according to claim 1; It is characterized in that; Described " driven Reflector Panel is coupled to each other with the active Reflector Panel through panel connected node mechanism ", its mode is to adopt elasticity chip panel support mechanism mode: some thin flexure strips are installed in rotation symmetrically on each panel joint mechanism; The base of every thin flexure strip and node substrate are connected, and the summit of every thin flexure strip and the angle point of panel are connected.
8. the radio telescope active reflecting plane structure of six-freedom degree displacement according to claim 7; It is characterized in that; Rotation is installed some thin flexure strips symmetrically and is meant on described each panel joint mechanism: for the hexagon panel, 3 thin flexure strips are installed in rotation symmetrically on each panel node; For triangular panels, then 6 thin flexure strips are installed in rotation symmetrically on each panel node; The angle of this every thin flexure strip is got 55-65 degree.
9. according to the described radio telescope active reflecting plane structure of one of claim 1 ~ 8; It is characterized in that; Described active Reflector Panel and driven Reflector Panel all adopt the angle to be of a size of the hexagon panel of 1.5 m to the angle; Be provided with 438 panels altogether, wherein 162 is the active Reflector Panel, and 276 is driven Reflector Panel; Active Reflector Panel (1) is wherein driven by the active adjusting mechanism, drives panel connected node mechanism (2); In panel connected node mechanism (2), panel support swing arm (5) one ends are installed and connected in the panel connected node mechanism (2) through post hinge (4), and panel support swing arm (5) other end connects through ball pivot (6) and supports driven Reflector Panel (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110151707 CN102324625B (en) | 2011-06-08 | 2011-06-08 | Active reflector structure of radio telescope |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110151707 CN102324625B (en) | 2011-06-08 | 2011-06-08 | Active reflector structure of radio telescope |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102324625A true CN102324625A (en) | 2012-01-18 |
| CN102324625B CN102324625B (en) | 2013-08-07 |
Family
ID=45452325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110151707 Expired - Fee Related CN102324625B (en) | 2011-06-08 | 2011-06-08 | Active reflector structure of radio telescope |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102324625B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104638381A (en) * | 2014-11-27 | 2015-05-20 | 中国科学院国家天文台 | Spatial five-equal partition reflecting face unit of FAST (five-hundred-meter aperture spherical radio telescope) |
| CN104701632A (en) * | 2014-11-21 | 2015-06-10 | 贵州贵航飞机设计研究所 | Assembly adjusting method and device of panel sub-unit of radio telescope reflective face unit |
| CN104779440A (en) * | 2015-04-17 | 2015-07-15 | 北京航空航天大学 | Intelligent three-dimensional programmable antenna reflecting surface |
| CN104979640A (en) * | 2015-07-09 | 2015-10-14 | 中国科学院国家天文台 | Radio telescope center compression actuator and support device thereof |
| CN105958210A (en) * | 2016-05-06 | 2016-09-21 | 中国科学院国家天文台 | FAST telescope perforated reflective surface unit and perforating method |
| CN109301493A (en) * | 2018-10-23 | 2019-02-01 | 中国科学院国家天文台 | A kind of giant telescope reflecting surface structure for supporting optics and radio observation |
| CN109969430A (en) * | 2019-04-04 | 2019-07-05 | 北京航空航天大学 | A kind of hinge implementation method of Flasher development agency |
| CN111478054A (en) * | 2020-05-18 | 2020-07-31 | 中国科学院国家天文台 | FAST reflecting surface unit self-adaptive connecting mechanism and layout method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1892281A (en) * | 2006-05-19 | 2007-01-10 | 中国科学院国家天文台 | Large radio astronomical telescope common-drive parallel connected array mechanism |
| CN101179157A (en) * | 2007-11-14 | 2008-05-14 | 清华大学 | Large-scale radio telescope active reflecting plane common drive parallel mechanism array |
| CN101320844A (en) * | 2008-07-11 | 2008-12-10 | 中国科学院国家天文台南京天文光学技术研究所 | Light reflection surface panel support mechanism of radio astronomical telescope |
-
2011
- 2011-06-08 CN CN 201110151707 patent/CN102324625B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1892281A (en) * | 2006-05-19 | 2007-01-10 | 中国科学院国家天文台 | Large radio astronomical telescope common-drive parallel connected array mechanism |
| CN101179157A (en) * | 2007-11-14 | 2008-05-14 | 清华大学 | Large-scale radio telescope active reflecting plane common drive parallel mechanism array |
| CN101320844A (en) * | 2008-07-11 | 2008-12-10 | 中国科学院国家天文台南京天文光学技术研究所 | Light reflection surface panel support mechanism of radio astronomical telescope |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104701632A (en) * | 2014-11-21 | 2015-06-10 | 贵州贵航飞机设计研究所 | Assembly adjusting method and device of panel sub-unit of radio telescope reflective face unit |
| CN104701632B (en) * | 2014-11-21 | 2017-08-11 | 贵州贵航飞机设计研究所 | The assembled method of adjustment and device of radio telescope unit panel of reflecting surface subelement |
| CN104638381A (en) * | 2014-11-27 | 2015-05-20 | 中国科学院国家天文台 | Spatial five-equal partition reflecting face unit of FAST (five-hundred-meter aperture spherical radio telescope) |
| CN104638381B (en) * | 2014-11-27 | 2017-12-08 | 中国科学院国家天文台 | The decile reflecting surface unit of FAST radio telescopes space five |
| CN104779440B (en) * | 2015-04-17 | 2017-09-12 | 北京航空航天大学 | A kind of intelligent three-dimensional programmable antenna reflecting surface |
| CN104779440A (en) * | 2015-04-17 | 2015-07-15 | 北京航空航天大学 | Intelligent three-dimensional programmable antenna reflecting surface |
| CN104979640A (en) * | 2015-07-09 | 2015-10-14 | 中国科学院国家天文台 | Radio telescope center compression actuator and support device thereof |
| CN104979640B (en) * | 2015-07-09 | 2018-02-13 | 中国科学院国家天文台 | Radio telescope center deformation drive device |
| CN105958210A (en) * | 2016-05-06 | 2016-09-21 | 中国科学院国家天文台 | FAST telescope perforated reflective surface unit and perforating method |
| CN105958210B (en) * | 2016-05-06 | 2018-10-30 | 中国科学院国家天文台 | FAST telescope open-cell reflecting surface units and its boring method |
| CN109301493A (en) * | 2018-10-23 | 2019-02-01 | 中国科学院国家天文台 | A kind of giant telescope reflecting surface structure for supporting optics and radio observation |
| CN109301493B (en) * | 2018-10-23 | 2023-10-17 | 中国科学院国家天文台 | Giant telescope reflecting surface structure supporting optical and radio observation |
| CN109969430A (en) * | 2019-04-04 | 2019-07-05 | 北京航空航天大学 | A kind of hinge implementation method of Flasher development agency |
| CN111478054A (en) * | 2020-05-18 | 2020-07-31 | 中国科学院国家天文台 | FAST reflecting surface unit self-adaptive connecting mechanism and layout method |
| CN111478054B (en) * | 2020-05-18 | 2024-03-05 | 中国科学院国家天文台 | FAST reflecting surface unit self-adaptive connection mechanism and layout method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102324625B (en) | 2013-08-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102324625B (en) | Active reflector structure of radio telescope | |
| ES2758188T3 (en) | Solar tracker with free space reducing device | |
| US9733470B2 (en) | Device comprising a vibratably suspended optical element | |
| US9274306B2 (en) | Method for manufacturing a reflector, preferably for the solar energy field | |
| ES2715305T3 (en) | Procedure for the manufacture of a reflector element | |
| WO2011014690A2 (en) | Solar energy collection system | |
| CN102549468B (en) | Holding arrangement for an optical element | |
| CN104280858A (en) | Flexible back supporting device for large-caliber reflector | |
| EP2639618B1 (en) | Primary mirror support structure and telescope unit | |
| WO2013032729A1 (en) | Solar assembly structure | |
| CN102540398A (en) | Full-compliant two-spindle rotating and reflecting mirror with low cross coupling | |
| CN102840704B (en) | Mirror panel supporting device of solar trough type power generation system | |
| WO2015025065A1 (en) | Dual axis solar tracker | |
| US8757544B2 (en) | Aircraft control surface drive mechanism | |
| US6984049B2 (en) | Hinged substrate for large-aperture, lightweight, deformable mirrors | |
| WO2014118395A1 (en) | Actuation mechanism for a solar tracking system | |
| JP4375400B2 (en) | Reflector support mechanism | |
| JP3816490B2 (en) | Reflector support structure and adjustment method thereof | |
| RU2313046C2 (en) | Autonomous system for tracking movement of the sun across the dome of the sky | |
| CN204830522U (en) | Slot type solar concentrator based on non -uniform beam | |
| CN110202547A (en) | Six-degree-of-freedom parallel connection mechanism | |
| CN115943279A (en) | Heliostat mirror bracket, heliostat and heliostat field | |
| WO2014156725A1 (en) | Sunlight collection device | |
| CN204166185U (en) | For the flexible Hooke's hinge supporting mechanism of space remote sensing camera catoptron | |
| EP3190353A1 (en) | Solar collector |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130807 Termination date: 20140608 |
|
| EXPY | Termination of patent right or utility model |