CN102788234A - Satellite-borne precision sun pointing mechanism - Google Patents
Satellite-borne precision sun pointing mechanism Download PDFInfo
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- CN102788234A CN102788234A CN2012102788833A CN201210278883A CN102788234A CN 102788234 A CN102788234 A CN 102788234A CN 2012102788833 A CN2012102788833 A CN 2012102788833A CN 201210278883 A CN201210278883 A CN 201210278883A CN 102788234 A CN102788234 A CN 102788234A
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Abstract
The invention discloses a satellite-borne precision sun pointing mechanism and relates to the technical field of precision machinery tracking measurement. The invention aims to solve the problem that the mechanism can be easily damaged because a traditional ground sun tracking rotating table is not provided with a locking mechanism. The satellite-borne precision sun pointing mechanism comprises a mechanism base, support frames, an azimuth rotating component, a pitching rotating component and a load, wherein the support frames are connected with the mechanism base by through holes; the azimuth rotating component is fixedly connected with the support frames; the pitching rotating component is fixedly connected with the azimuth rotating component; and the load is movably connected onto the pitching rotating component. The load can rotate along an azimuth axis and a pitching axis. The satellite-borne precision sun pointing mechanism also comprises a locking mechanism. An expansion bolt or a built-in metal pin is adopted by the locking mechanism; the expansion bolt is arranged in the locking mechanism; and the metal pin is arranged in the locking mechanism and can stretch out or retract from the outside of the locking mechanism. An axial impact force borne by the satellite-borne precision sun pointing mechanism disclosed by the invention is reduced during a launching process, therefore, the service life of a bearing is prolonged, and the performance of the satellite-borne precision sun pointing mechanism is improved. The locking mechanism can be locked in two directions at the same time, thus, the reliability of the satellite-borne precision sun pointing mechanism is enhanced.
Description
Technical field
The present invention relates to precision optical machinery tracking measurement technical field, be specifically related to a kind of spaceborne accurate sun directing mechanism.
Background technique
Sun directing mechanism is used for the real-time tracking observation to solar radiation, can confirm the exact position of target, is widely used in meteorology and climatic prediction, Aero-Space and solar energy and utilizes many aspects.
At present, ground generally is made up of with the two-dimentional rotating machinery that the rotation axis system that is parallel to ground is used the rotation axis system perpendicular to ground with sun directing mechanism.With the most approaching existing technology of the present invention be that the solar tracking turntable is used on the ground of Changchun Inst. of Optics and Fine Mechanics, Chinese Academy of Sciences, as shown in Figure 1, this turntable comprises turret base 1; With turret base 1 be fixedly linked first the dimension rotatable parts 2; Be connected the supporting part 3 on the first dimension rotatable parts 2; The second dimension rotatable parts 4 that through hole through supporting part 3 is attached thereto; With second load 5 that is fixedly linked of dimension rotatable parts 4; Under the effect of the first dimension rotatable parts 2; Supporting part 3 rotates around the central axis of turret base 1; The second dimension rotatable parts 4 can freely rotate in the through hole of supporting part 3, and under the drive of the second dimension rotatable parts 4, load 5 is rotated around the horizontal axis of supporting part 3.Be applied to spaceborne condition following time, because supporting part 3 rotates around the central axis of turret base 1, load 5 is rotated around the horizontal axis of supporting part 3; Can not realize self rotating of load 5; The suffered axial impact force of turntable is excessive, shortened the working life and the performance of bearing, and this turntable does not have locking mechanism; Can receive severe impairment in emission process intermediate station integral body, its reliability also reduces greatly.
Summary of the invention
Excessive and be prone to make the problem of mechanism's infringement in order to solve axial impact force that existing ground receives with the solar tracking turntable, the present invention provides a kind of spaceborne accurate sun directing mechanism.
The technological scheme that the present invention is adopted for the technical solution problem is following:
A kind of spaceborne accurate sun directing mechanism comprises:
Mechanism base;
The supporting frame that links to each other with said mechanism base through through hole;
The azimuth rotation parts that are fixedly linked with support frame as described above;
The pitch rotation parts that are fixedly linked with said azimuth rotation parts;
Be movably connected in the load on the said pitch rotation parts.
Axial direction along said azimuth rotation parts is an azimuth axis, and said load can be rotated along azimuth axis.
Axial direction along said pitch rotation parts is an elevation axis, and said load can be rotated along elevation axis.
This mechanism also comprises locking mechanism, and said locking mechanism one end is fixed on the said mechanism base, and the other end links to each other with said load.
Said locking mechanism adopts EXPANSION ANCHOR BOLTS;
It is inner that said EXPANSION ANCHOR BOLTS is installed in said locking mechanism, and an end is fixed on the said mechanism base, and the other end links to each other with said load.
Said locking mechanism can also adopt the built-in metal pin;
It is inner that said metallic pin is built in said locking mechanism, and the said locking mechanism that can stretch out or withdraw is outside.
Said pitch rotation parts become cylindrical, and said load is actively set on the pitch rotation parts.
Said azimuth rotation parts mainly are formed by connecting on two groups of parallel frames, and said pitch rotation parts two ends are fixedly connected with one group of parallel frame of said azimuth rotation parts respectively.
The invention has the beneficial effects as follows: spaceborne accurate sun directing mechanism of the present invention owing to adopted the cooperation of azimuth rotation parts and two structures of pitch rotation parts, makes load rotate along azimuth axis and elevation axis; Realized the rotation of load self, changed the axial impact force direction that mechanism receives simultaneously, mechanism's axial impact force that rotatable parts bore in emission process is reduced; Prolonged the working life of bearing; And improved the performance of entire mechanism, and the present invention has simultaneously also increased locking mechanism, and locking mechanism can be locked both direction simultaneously; Be that load is rotated along azimuth axis and elevation axis two directions through azimuth rotation parts and pitch rotation parts respectively; The design of a locking mechanism locking of this usefulness both direction has not only strengthened the reliability of mechanism, and has made mechanism more compact.
Description of drawings
Fig. 1 is the structural representation of existing ground with the solar tracking turntable;
Fig. 2 is the structural representation of a kind of spaceborne accurate sun directing mechanism of the present invention;
Fig. 3 is the schematic representation that EXPANSION ANCHOR BOLTS is connected with mechanism base with load respectively;
Fig. 4 is built in the inner schematic representation of locking mechanism for metallic pin.
Among the figure: 1, turret base, 2, the first dimension rotatable parts, 3, supporting part, 4, the second dimension rotatable parts; 5, load, 6, mechanism base, 7, supporting frame, 8, the azimuth rotation parts; 9, pitch rotation parts, 10, locking mechanism, 11, EXPANSION ANCHOR BOLTS, 12, metallic pin.
Embodiment
Below in conjunction with accompanying drawing the present invention is done further explain.
As shown in Figure 2, spaceborne accurate sun directing mechanism of the present invention mainly comprises: mechanism base 6, supporting frame 7, azimuth rotation parts 8 and pitch rotation parts 9, mechanism base 6 concavities; Its spill two ends have cylindrical hole, and two 7 one-tenth of supporting frames are cylindrical, and each supporting frame 7 passes its corresponding cylindrical hole and links to each other with mechanism base 6; 8 one-tenth square frame shapes of azimuth rotation parts are formed by connecting on two groups of parallel frames, and pitch rotation parts 9 are fixedly connected on one group of parallel square frame of azimuth rotation parts 8; And two supporting frames 7 are fixedly connected with other one group of parallel frame respectively; 9 one-tenth of pitch rotation parts are cylindrical, and load 5 is actively set on the pitch rotation parts 9, are azimuth axis along the axial direction of azimuth rotation parts 8; Load 5 can be rotated along azimuth axis; Axial direction along pitch rotation parts 9 is an elevation axis, and load 5 can be rotated along elevation axis, has realized that promptly the two dimension of load 5 is rotated.
Spaceborne accurate sun directing mechanism of the present invention also comprises locking mechanism 10, and locking mechanism 10 1 ends are fixed on the mechanism base 6, and the other end links to each other with load 5; Be used to lock load 5; As shown in Figure 3, the locking mechanism 10 main EXPANSION ANCHOR BOLTSs 11 that adopt among the present invention, EXPANSION ANCHOR BOLTS 11 is installed in locking mechanism 10 inside; EXPANSION ANCHOR BOLTS 11 1 ends are fixed on the said mechanism base 6, and the other end links to each other with said load 5; Before emission, need be with load 5 lockings, at this moment, EXPANSION ANCHOR BOLTS 11 is with load 5 lockings, and anti-locking mechanism integral body suffers damage, and simultaneously, pitch rotation parts 9 play the effect that disperses axial impact force, and axial impact force is dwindled; In the course of normal operation after emission is accomplished, load 5 can be rotated along azimuth axis and elevation axis both direction, has realized that the two dimension of load 5 is rotated, and locking mechanism 10 utilizes EXPANSION ANCHOR BOLTS 11 can realize the locking effect on load 5 both directions.
As shown in Figure 4, above-mentioned locking mechanism 10 can also adopt built-in metal pin 12, and metallic pin 12 is built in locking mechanism 10 inside, locking mechanism 10 outsides of can stretching out or withdraw; Before emission, need be with load 5 lockings, at this moment; Metallic pin 12 stretches out locking mechanism 10 up to withstanding load 5; Entire mechanism all can not be rotated like this, reaches the purpose that locking and anti-locking mechanism integral body suffer damage, simultaneously; Pitch rotation parts 9 play the effect that disperses axial impact force, and axial impact force is dwindled; In the course of normal operation after emission is accomplished; Load 5 can be rotated along azimuth axis and elevation axis both direction; Realized the two dimension rotation of load 5, locking mechanism 10 utilizes EXPANSION ANCHOR BOLTS 11 can realize the locking effect on load 5 both directions, when load 5 needs to rotate; Locking mechanism 10 is regained metallic pin 12 automatically, and the 2DOF of entire mechanism can recover.
Above-mentioned locking mechanism 10 is inner corresponding with locking mechanism 10 outsides, and the outside is meant the outer surface that links to each other with load 5, and inside is meant not the internal structure space that links to each other with mechanism base 6 with load 5.
The total quality of spaceborne accurate sun directing mechanism of the present invention and structure are all axisymmetric with azimuth axis and pitching.
Claims (8)
1. a spaceborne accurate sun directing mechanism is characterized in that, comprising:
Mechanism base (6);
The supporting frame (7) that links to each other with said mechanism base (6) through through hole;
The azimuth rotation parts (8) that are fixedly linked with support frame as described above (7);
The pitch rotation parts (9) that are fixedly linked with said azimuth rotation parts (8);
Be movably connected in the load (5) on the said pitch rotation parts (9).
2. spaceborne accurate sun directing mechanism according to claim 1 is characterized in that, is azimuth axis along the axial direction of said azimuth rotation parts (8), and said load (5) can be rotated along azimuth axis.
3. spaceborne accurate sun directing mechanism according to claim 1 is characterized in that, is elevation axis along the axial direction of said pitch rotation parts (9), and said load (5) can be rotated along elevation axis.
4. spaceborne accurate sun directing mechanism according to claim 1 is characterized in that this mechanism also comprises locking mechanism (10), and said locking mechanism (10) one ends are fixed on the said mechanism base (6), and the other end links to each other with said load (5).
5. spaceborne accurate sun directing mechanism according to claim 4 is characterized in that, said locking mechanism (10) adopts EXPANSION ANCHOR BOLTS (11);
Said EXPANSION ANCHOR BOLTS (11) is installed in said locking mechanism (10) inside, and an end is fixed on the said mechanism base (6), and the other end links to each other with said load (5).
6. spaceborne accurate sun directing mechanism according to claim 4 is characterized in that said locking mechanism (10) can also adopt built-in metal pin (12);
Said metallic pin (12) is built in said locking mechanism (10) inside, said locking mechanism (10) outside of can stretching out or withdraw.
7. spaceborne accurate sun directing mechanism according to claim 1 is characterized in that, it is cylindrical that said pitch rotation parts (9) become, and said load (5) is actively set on the pitch rotation parts (9).
8. spaceborne accurate sun directing mechanism according to claim 7; It is characterized in that; Said azimuth rotation parts (8) mainly are formed by connecting on two groups of parallel frames, and said pitch rotation parts (9) two ends are fixedly connected with one group of parallel frame of said azimuth rotation parts (8) respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012102788833A CN102788234A (en) | 2012-08-07 | 2012-08-07 | Satellite-borne precision sun pointing mechanism |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012102788833A CN102788234A (en) | 2012-08-07 | 2012-08-07 | Satellite-borne precision sun pointing mechanism |
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| CN102788234A true CN102788234A (en) | 2012-11-21 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103470925A (en) * | 2013-09-04 | 2013-12-25 | 中国科学院深圳先进技术研究院 | Automatic-control spatial rotating device |
| CN106774443A (en) * | 2016-08-31 | 2017-05-31 | 北京空间机电研究所 | A kind of spaceborne novel high-precision high stability two-dimensional pointing mechanism |
| CN111504285A (en) * | 2020-05-14 | 2020-08-07 | 北京控制工程研究所 | Theodolite type laser coarse pointing mechanism |
| CN112730247A (en) * | 2020-12-28 | 2021-04-30 | 中国科学院合肥物质科学研究院 | Special calibration rotary table for spectrometer |
| CN115072010A (en) * | 2022-08-22 | 2022-09-20 | 中国科学院西安光学精密机械研究所 | Space satellite-borne deployable turntable mechanism and method for testing delay time thereof |
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| DE10233950A1 (en) * | 2002-07-25 | 2004-02-19 | Siemens Ag | Positioning unit for an optical measurement system is configured so that a test-piece support can be rotated and pivoted about vertical and horizontal axes that pass through the focal point of the measurement system |
| CN101109581A (en) * | 2006-07-20 | 2008-01-23 | 中国科学院长春光学精密机械与物理研究所 | Earth axis type solar furnace optical collector |
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| DE10233950A1 (en) * | 2002-07-25 | 2004-02-19 | Siemens Ag | Positioning unit for an optical measurement system is configured so that a test-piece support can be rotated and pivoted about vertical and horizontal axes that pass through the focal point of the measurement system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103470925A (en) * | 2013-09-04 | 2013-12-25 | 中国科学院深圳先进技术研究院 | Automatic-control spatial rotating device |
| CN103470925B (en) * | 2013-09-04 | 2015-07-08 | 中国科学院深圳先进技术研究院 | Automatic-control spatial rotating device |
| CN106774443A (en) * | 2016-08-31 | 2017-05-31 | 北京空间机电研究所 | A kind of spaceborne novel high-precision high stability two-dimensional pointing mechanism |
| CN111504285A (en) * | 2020-05-14 | 2020-08-07 | 北京控制工程研究所 | Theodolite type laser coarse pointing mechanism |
| CN112730247A (en) * | 2020-12-28 | 2021-04-30 | 中国科学院合肥物质科学研究院 | Special calibration rotary table for spectrometer |
| CN115072010A (en) * | 2022-08-22 | 2022-09-20 | 中国科学院西安光学精密机械研究所 | Space satellite-borne deployable turntable mechanism and method for testing delay time thereof |
| CN115072010B (en) * | 2022-08-22 | 2022-12-23 | 中国科学院西安光学精密机械研究所 | Space satellite-borne extensible turntable mechanism and method for testing delay time thereof |
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Application publication date: 20121121 |