CN104319455B - Satellite-borne movable antenna single-point locking system - Google Patents
Satellite-borne movable antenna single-point locking system Download PDFInfo
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- CN104319455B CN104319455B CN201410513732.0A CN201410513732A CN104319455B CN 104319455 B CN104319455 B CN 104319455B CN 201410513732 A CN201410513732 A CN 201410513732A CN 104319455 B CN104319455 B CN 104319455B
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Abstract
The invention provides a satellite-borne movable antenna single-point locking system. The satellite-borne movable antenna single-point locking system includes a locking releasing device, a first angle sheet, a second angle sheet, an X-axis support, a Y-axis support, an X-axis rotating unit, a fixing support and a Y-axis rotating unit. According to the satellite-borne movable antenna single-point locking system of the invention, a plurality of rotating components inside an antenna are connected in series and then are fixed in a single-point locking manner; after single-point locking is performed, only one locking point exists, corresponding initiating explosive devices can be decreased to one initiating explosive device; based on reasonable layout, the single-point locking can meet requirements for strength and stiffness; and therefore, the reliability of the unlocking of the antenna can be improved, an impact of the initiating explosive device on the antenna and the body of a satellite can be decreased, the envelope of the structure of the antenna is smaller, and the light weight and miniaturization of the antenna can be realized. The satellite-borne movable antenna single-point locking system has high applicability and popularization application value.
Description
Technical field
A kind of the invention belongs to space flight aerospace flight technology field, in particular it relates to single-point lock of spaceborne movable antenna
Clamping system, is particularly well-suited to antenna reflector bore no more than 0.6m, (orientation, pitching are equal for large rotation
± 110 ° can be reached), fundamental frequency is not higher than the spaceborne movable antenna of 60hz.
Background technology
With the continuous development of space technology, the continuous improvement of satellite resolution, camera therewith overstriking, lengthening,
Increase, lead to that spaceborne movable antenna must realize lightweight and miniaturization could meet envelope and weight demands.
The reliability of spacecraft is particularly important, and therefore its each stand-alone device must possess high reliability, spaceborne
The reliability of movable antenna depends primarily on its priming system whether normal release, and the reliability of priming system unblock is straight
Connect decision successful launch or failure, priming system quantity is more, just unlocks the impact to antenna and spacecraft simultaneously
Bigger, do not unlock if there are one, may result in satellite launch failure.
At present, spaceborne movable antenna (containing launching one-level) priming system quantity is substantially all more than 2.Cause
This, the technical problem that those skilled in the art are badly in need of solving is to reduce the priming system of spaceborne steerable antenna as far as possible
Quantity, to realize lightweight and miniaturization.
Content of the invention
The technical problem to be solved in the present invention is, for the deficiencies in the prior art, provides a kind of spaceborne movable sky
Line single-point fastening system, reduces priming system quantity will pass through, and reduces its impact to antenna and whole star for the unblock,
The reliability of raising system, realizes miniaturization and the lightweight of antenna simultaneously.
For solving above-mentioned technical problem, the technical solution used in the present invention includes:
A kind of spaceborne movable antenna single-point fastening system it is characterised in that include locking releasing device, first
Gusset plate, the second gusset plate, x-axis support, y-axis support, x-axis rotating unit, fixed support and y-axis turn
Moving cell, wherein, locking releasing device includes priming system sickle, check lock lever, spring assembly, locking bed,
Wherein, priming system sickle is arranged on locking bed；Check lock lever passes through the leading truck on locking bed to extend vertically,
The first end of check lock lever is associated with priming system sickle, and the second end is provided with spring assembly；X-axis support,
It is sleeved on check lock lever the first end sequence from low to uper part of the first end of the first gusset plate and the second gusset plate,
And it is located between leading truck and spring assembly；The first end of x-axis support is set in the defeated of x-axis rotating unit
On shaft；X-axis rotating unit is fixed on fixed support；Fixed support is fixed on the expansion arm of antenna；y
Axle rotating unit is fixed to the second end of x-axis support；The first end of y-axis support is set in y-axis rotating unit
Output shaft, the second end of y-axis support is fixed to the reflector assembly of antenna, and the rotation of y-axis support
Axis is perpendicular to the pivot center of x-axis support；Second end of the first gusset plate is fixed to fixed support；Second jiao
Second end of piece is fixed to y-axis support；X-axis rotating unit and y-axis rotating unit are able to outside
Rotate under the control of servo controller, drive x-axis support to rotate counterclockwise and drive y-axis support respectively
Rotate clockwise；And after priming system sickle receives the instruction cut-out check lock lever of outside, check lock lever energy
Enough bounce off locking releasing device in the presence of spring assembly, release x-axis support, the first end of the first gusset plate,
And second gusset plate first end.
Further, x-axis support includes first connecting portion, second connecting portion and contiguous block, wherein,
Second connecting portion connects to the side of first connecting portion, and the plane that second connecting portion is located is perpendicular to first
The plane that connecting portion is located, first connecting portion has the first installing hole, and x-axis support passes through this and first installs
Borehole jack is loaded on the output shaft of x-axis rotating unit；Second installing hole is provided with second connecting portion；Y-axis turns
Moving cell is fixed to the side of first connecting portion, and its output shaft passes through the second installing hole in second connecting portion
And stretch out, the first end of y-axis support is set in second installing hole of stretching out of the output shaft of y-axis rotating unit
Partly go up；Contiguous block is close to first connecting portion and arranges, and the plane at contiguous block place and first connecting portion
The plane being located is vertical, and contiguous block has the 3rd installing hole, and x-axis support passes through the 3rd installing hole suit
On check lock lever, and the plane of first end in contact with the first gusset plate of contiguous block is tapered ramp.
Further, y-axis support includes installing portions and connecting portion, installs the plane that portions are located and is connected
The plane that portion is located is vertical, and y-axis support is fixed to the reflector assembly of antenna by this installation portions；Connect
4th installing hole is had on portion, y-axis support is set in the output of y-axis rotating unit by the 4th installing hole
Axle.
Further, spring assembly includes spring, spring stop part, spring shield and nut, wherein,
Spring stop part, spring, spring shield and nut are sheathed on check lock lever from bottom to up successively, and
Spring stop part is located on the second gusset plate；Spring shield is in the inner chamber of spring shield, and the two ends of spring
It is connected to respectively between the inner roof wall of spring shield and spring stop part；Nut is arranged on the top of spring shield, will
Spring shield is fixed on check lock lever.
The present invention compared with prior art, has the advantage that
1st, adopt single-point to lock first, priming system only has 1, improve the reliability of antenna unblock, unblock
When reduce impact to antenna and celestial body, save resource for whole spark work product manager simultaneously；
2nd, the single-point fastening system according to the present invention, x-axis, y-axis slewing area are all locked in extreme position, fit
Close large rotation (± 110 °)；This fastening system makes that whole antenna structure is compacter, and envelope is little,
Achieve lightweight and the miniaturization of antenna development；
3rd, because the quantity of priming system is reduced to 1, the locking releasing device of respective antenna, low-frequency cable,
Connector etc. decreases, and greatlys save antenna development and production cost.
Brief description
Fig. 1 is the overall applicability schematic diagram of the single-point fastening system according to the present invention；
Fig. 2 is the structural representation of the single-point fastening system according to the present invention；
Fig. 3 is the x-axis rotating unit of the present invention and the schematic diagram of y-axis rotating unit；
Fig. 4 is the structural representation of the x-axis support of the present invention；
Fig. 5 is the structural representation of the y-axis support of the present invention；
Fig. 6 is the structural representation of first gusset plate of the present invention；
Fig. 7 is the structural representation of second gusset plate of the present invention；
Fig. 8 is the structural representation of the locking releasing device of the present invention；
Fig. 9 is the principle schematic of the single-point fastening system of the present invention.
Specific embodiment
Below in conjunction with the drawings and specific embodiments to the spaceborne movable antenna single-point fastening system according to the present invention
It is further described in detail.
As shown in Fig. 1-Fig. 9, the system of the present invention is that multiple for inner antenna rotational components are passed through gusset plate string
Locked by any after connection, mainly for reducing priming system quantity, improve reliability, realize miniaturization and light
A kind of system quantifying and designing.Antenna tracking some rotatable parts in-house, structure can be gone here and there
Connection compression, by the adjustment of its centroid position, single-point locking can be to meet intensity, and the demand of rigidity can
To be widely used on spaceborne movable antenna.
Fig. 1 is illustrated that the schematic diagram under the antenna locking state of single-point locking mode, the work of the present invention
Principle is: is in single-point locking state during antenna transmitting, after entering the orbit, the priming system in locking releasing device rises
Quick-fried, after outside servo controller drives development mechanism to launch to put in place, then drive x-axis rotating unit, y-axis
Rotating unit turns to antenna specified location.
As illustrated, according to the spaceborne movable antenna single-point fastening system of the present invention include locking releasing device 1,
First gusset plate 2, the second gusset plate 3, x-axis support 4, y-axis support 5, x-axis rotating unit 6, fixed support
7 and y-axis rotating unit 8.
As shown in figure 8, locking releasing device 1 includes priming system sickle 101, check lock lever 102, groups of springs
Part 105, locking bed 104, wherein, priming system sickle 101 is arranged on locking bed 104；Check lock lever
102 pass through the leading truck 1041 on locking bed 104 to extend vertically, and the first end of check lock lever is cut with priming system
Device 101 is associated, and the second end is provided with spring assembly 105.
The first end sequence from low to uper part of x-axis support 4, the first end of the first gusset plate 2 and the second gusset plate 3
Be sleeved on check lock lever 102, and be located between leading truck 1041 and spring assembly.
The first end of x-axis support 4 is set on the output shaft of x-axis rotating unit 6；X-axis rotating unit 6 is solid
It is scheduled on fixed support 7；Fixed support 7 is fixed on the expansion arm of antenna.
Y-axis rotating unit 8 is fixed to the second end of x-axis support 4；The first end of y-axis support 5 is set in y
The output shaft of axle rotating unit 8, the second end of y-axis support 5 is fixed to the reflector assembly of antenna, and y
The pivot center of bracing strut 5 is perpendicular to the pivot center of x-axis support 4.
Second end of the first gusset plate 2 is fixed to fixed support 7；Second end of the second gusset plate 3 is fixed to y-axis
Support 5.
X-axis rotating unit 6 and y-axis rotating unit 8 are able under the control of outside servo controller
Rotate, drive x-axis support 4 to rotate counterclockwise and drive y-axis support 5 to rotate clockwise respectively.
After priming system sickle 101 receives the instruction cut-out check lock lever 102 of outside, check lock lever 102 energy
Enough bounce off locking releasing device 1 in the presence of spring assembly, release x-axis support 4, the of the first gusset plate 2
One end and the first end of the second gusset plate 3.
Specifically, as shown in figure 4, x-axis support 4 include first connecting portion 401, second connecting portion 402,
And contiguous block 403.First connecting portion 401, second connecting portion 402 and contiguous block 403 are bulk
Structure.Wherein, second connecting portion 402 connects to the side of first connecting portion 401, and second connecting portion
The plane that is located perpendicular to first connecting portion 401 of planes at 402 places, first connecting portion 401 has the
One installing hole 4011, x-axis support 4 is set in the defeated of x-axis rotating unit 6 by this first installing hole 4011
On shaft；Second installing hole 4021 is provided with second connecting portion 402；Y-axis rotating unit 8 is fixed to
The side of one connecting portion 401, and its output shaft passes through the second installing hole 4021 in second connecting portion 402
And stretch out, what the first end of y-axis support 5 was set in the output shaft of y-axis rotating unit 8 stretches out the second installation
Partly the going up of hole 4021；Contiguous block 403 is close to first connecting portion 401 and arranges, and contiguous block 403
The plane being located is vertical with the plane that first connecting portion 401 is located, and contiguous block 403 has the 3rd installing hole
4031, x-axis support 4 is set on check lock lever 102 by the 3rd installing hole 4031, and contiguous block 403
The first end in contact with the first gusset plate plane be tapered ramp, setting tapered ramp purpose be to disappear
Except frictional force when it is separated with the first gusset plate.
As shown in figure 5, y-axis support 5 includes installing portions 501 and connecting portion 502, portions 501 institute is installed
Plane vertical with the plane that connecting portion 502 is located, it is fixing that y-axis support 5 passes through this installation portions 501
Reflector assembly to antenna；4th installing hole 503 is had on connecting portion 502, y-axis support 5 pass through this
Four installing holes 503 are set in the output shaft of y-axis rotating unit 8.
As shown in figure 8, spring assembly 105 include spring 1053, spring stop part 1051, spring shield 1052,
And nut, wherein, spring stop part 1051, spring 1053, spring shield 1052 and nut under
And Shangdi is sheathed on check lock lever 102 successively, and spring stop part 1051 is located on the second gusset plate；Bullet
Spring covers in the inner chamber of spring shield 1052, and the two ends of spring 1053 are connected to spring shield 1052 respectively
Inner roof wall and spring stop part 1051 between；Nut is arranged on the top of spring shield 1052, by spring shield
1052 are fixed on check lock lever.
Fig. 3 is the x-axis rotating unit of the present invention and the schematic diagram of y-axis rotating unit.In the present invention, x-axis
Rotating unit and y-axis rotating unit have identical structure, and as known to the skilled person, it is main
It is to be made up of motor, decelerator, angle measurement equipment, here is not done to its structure and excessively repeated.X-axis rotates
Unit and the action under the control of outside servo controller of y-axis rotating unit, respectively drive x-axis support and
The position that y-axis holder pivots need to antenna.
Fig. 6 and Fig. 7 respectively illustrates first gusset plate of system employing of the present invention and the structure of the second gusset plate.
In the present invention, by the series connection locking of the first gusset plate, the second gusset plate and x-axis support, improve whole single-point lock
The fundamental frequency of clamping system.In the present invention, the concrete structure of two gusset plates is not done with excessive restriction, as long as enabling it
Linkage function and possess certain rigidity.
The principle of the single-point fastening system according to the present invention is as shown in Figure 9.
After satellite launch is entered the orbit, when priming system sickle 101 receive outside instruction cut-out check lock lever 102 it
Afterwards, check lock lever 102 can bounce off locking releasing device 1 in the presence of spring assembly, release x-axis support 4,
The first end of the first gusset plate 2 and the first end of the second gusset plate 3.It is single that servo controller controls y-axis to rotate
Unit 8, drives y-axis support 5 around its rotating shaft rotationally clockwise；Then control x-axis rotating unit 6, drive
Dynamic x-axis support 4 is separated with the first gusset plate 2 until going to the position of antenna needs.
Realize step:
The first end of 1.x bracing strut 4 is set on the output shaft of x-axis rotating unit 6；X-axis rotating unit
6 are fixed on fixed support 7, and fixed support 7 is fixed on the expansion arm of antenna.
2.y axle rotating unit 8 is fixed to the second end of x-axis support 4；The first end suit of y-axis support 5
In the output shaft of y-axis rotating unit 8, the second end of y-axis support 5 is fixed to the reflector assembly of antenna.
3. the second end of the first gusset plate 2 is fixed to fixed support 7；Second end of the second gusset plate 3 is fixed to y
Bracing strut 5.
4. adjustment locked position is so as to be located at single-point fastening system structure center of mass.
The first end of 5.x bracing strut 4, the first end of the first gusset plate 2 and the second gusset plate 3 is from bottom to top
Sequentially it is sleeved on check lock lever 102, and be located between leading truck 1041 and spring assembly.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. a kind of spaceborne movable antenna single-point fastening system it is characterised in that include locking releasing device (1),
First gusset plate (2), the second gusset plate (3), x-axis support (4), y-axis support (5), x-axis rotating unit (6),
Fixed support (7) and y-axis rotating unit (8), wherein,
Locking releasing device (1) include priming system sickle (101), check lock lever (102), spring assembly (105),
Locking bed (104), wherein, priming system sickle (101) is arranged on locking bed (104)；Check lock lever
(102) pass through locking bed (104) on leading truck (1041) extend vertically, the first end of check lock lever with
Priming system sickle (101) is associated, and the second end is provided with spring assembly (105)；
The first end of x-axis support (4), the first end of the first gusset plate (2) and the second gusset plate (3) is certainly
Lower and on be sequentially sleeved on check lock lever (102), and be located at leading truck (1041) and spring assembly it
Between；
The first end of x-axis support (4) is set on the output shaft of x-axis rotating unit (6)；X-axis rotates single
First (6) are fixed on fixed support (7)；Fixed support (7) is fixed on the expansion arm of antenna；
Y-axis rotating unit (8) is fixed to the second end of x-axis support (4)；The first of y-axis support (5)
End is set in the output shaft of y-axis rotating unit (8), and the second end of y-axis support (5) is fixed to antenna
Reflector assembly, and the pivot center perpendicular to x-axis support (4) for the pivot center of y-axis support (5)；
Second end of the first gusset plate (2) is fixed to fixed support (7)；Second end of the second gusset plate (3) is solid
Determine to y-axis support (5)；
X-axis rotating unit (6) and y-axis rotating unit (8) are able in outside servo controller
Control lower rotation, drive x-axis support (4) to rotate counterclockwise and drive y-axis support (5) suitable respectively
Hour hands rotate；And
After priming system sickle (101) receives instruction cut-out check lock lever (102) of outside, check lock lever
(102) can bounce off locking releasing device (1) in the presence of spring assembly, release x-axis support (4),
The first end of the first gusset plate (2) and the first end of the second gusset plate (3).
2. spaceborne movable antenna single-point fastening system according to claim 1 is it is characterised in that x-axis
Support (4) includes first connecting portion (401), second connecting portion (402) and contiguous block (403), its
In,
Second connecting portion (402) connects to the side of first connecting portion (401), and second connecting portion (402)
The plane that the plane being located is located perpendicular to first connecting portion (401), first connecting portion has on (401)
First installing hole (4011), x-axis support (4) is set in x-axis by this first installing hole (4011) and turns
On the output shaft of moving cell (6)；Second installing hole (4021) is provided with second connecting portion (402)；y
Axle rotating unit (8) is fixed to the side of first connecting portion (401), and its output shaft passes through the second connection
The second installing hole (4021) in portion (402) and stretch out, the first end of y-axis support (5) is set in y
The output shaft of axle rotating unit (8) stretch out partly going up of the second installing hole (4021)；
Contiguous block (403) is close to first connecting portion (401) and arranges, and contiguous block (403) and first
Connecting portion (401) is vertical, and contiguous block (403) has the 3rd installing hole (4031), x-axis support (4)
Be set on check lock lever (102) by the 3rd installing hole (4031), and contiguous block (403) with
The plane of the first end in contact of the first gusset plate is tapered ramp.
3. spaceborne movable antenna single-point fastening system according to claim 1 it is characterised in that
Y-axis support (5) includes installing portions (501) and connecting portion (502), installs portions (501) institute
Plane vertical with the plane that connecting portion (502) is located, y-axis support (5) pass through this installation portions (501)
It is fixed to the reflector assembly of antenna；4th installing hole (503), y-axis support are had on connecting portion (502)
(5) it is set in the output shaft of y-axis rotating unit (8) by the 4th installing hole (503).
4. spaceborne movable antenna single-point fastening system according to claim 1 it is characterised in that
Spring assembly (105) include spring (1053), spring stop part (1051), spring shield (1052),
And nut, wherein, spring stop part (1051), spring (1053), spring shield (1052) and spiral shell
Mother is sheathed on check lock lever (102) from bottom to up successively, and spring stop part (1051) is located at second
On gusset plate；Spring shield is in the inner chamber of spring shield (1052), and the two ends of spring (1053) are divided
It is not connected between the inner roof wall of spring shield (1052) and spring stop part (1051)；Nut is arranged on bullet
The top of spring cover (1052), spring shield (1052) is fixed on check lock lever.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410513732.0A CN104319455B (en) | 2014-09-29 | 2014-09-29 | Satellite-borne movable antenna single-point locking system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410513732.0A CN104319455B (en) | 2014-09-29 | 2014-09-29 | Satellite-borne movable antenna single-point locking system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104319455A CN104319455A (en) | 2015-01-28 |
| CN104319455B true CN104319455B (en) | 2017-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410513732.0A Active CN104319455B (en) | 2014-09-29 | 2014-09-29 | Satellite-borne movable antenna single-point locking system |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108870034B (en) * | 2018-04-27 | 2023-09-15 | 中国科学院沈阳自动化研究所 | Robotic panoramic camera turntable adapting to lunar environment |
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|---|---|---|---|---|
| CN102683796A (en) * | 2012-05-29 | 2012-09-19 | 西安空间无线电技术研究所 | Satellite-borne folding mobile antenna and locking method thereof |
| CN202797273U (en) * | 2012-07-19 | 2013-03-13 | 北京空间飞行器总体设计部 | Thermal protection device for moving parts of movable spot beam antennas |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2989523B1 (en) * | 2012-04-13 | 2014-05-02 | Thales Sa | MULTI-REFLECTING ANTENNA FOR TELECOMMUNICATIONS SATELLITE |
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2014
- 2014-09-29 CN CN201410513732.0A patent/CN104319455B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102683796A (en) * | 2012-05-29 | 2012-09-19 | 西安空间无线电技术研究所 | Satellite-borne folding mobile antenna and locking method thereof |
| CN202797273U (en) * | 2012-07-19 | 2013-03-13 | 北京空间飞行器总体设计部 | Thermal protection device for moving parts of movable spot beam antennas |
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| Title |
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| "含柔性部件星载天线的展开锁定冲击";王朋朋 等;《空间电子技术》;20140325;第43-46页 * |
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