CN102730202A - Folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for solar wing - Google Patents
Folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for solar wing Download PDFInfo
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- CN102730202A CN102730202A CN2012102249043A CN201210224904A CN102730202A CN 102730202 A CN102730202 A CN 102730202A CN 2012102249043 A CN2012102249043 A CN 2012102249043A CN 201210224904 A CN201210224904 A CN 201210224904A CN 102730202 A CN102730202 A CN 102730202A
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- joint hinge
- substrate
- screw rod
- link span
- hinge
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Abstract
The invention discloses a folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for a solar wing. A motor and one end of a connecting frame joint hinge are fixedly connected with a satellite body; a small end of a connecting frame is connected with the other end of the connecting frame joint hinge; a big end of the connecting frame is connected with one end of a first baseplate joint hinge; the other end of the first baseplate joint hinge is fixedly connected with one end of a first baseplate; a main shaft of the motor is connected with a synchronous belt pulley through a coupling; the upper end of a screw rod of the connecting frame joint hinge is connected with the main shaft of the motor through a first synchronous belt drive mechanism; the lower end of the screw rod of the connecting frame joint hinge is connected with the lower end of a screw rod of the first baseplate joint hinge through a second synchronous belt drive mechanism; and the rotation directions of spatial cam grooves on the connecting frame joint hinge and the first baseplate joint hinge are reverse. A plurality of joint hinges and baseplates can be also added behind the first baseplate; the spatial cam grooves on the adjacent baseplate joint hinges are all 180 degrees; and the rotation directions are reverse in a mounting process. By using folding/unfolding-repeatable locking/unlocking mechanism, a repeated folding/unfolding motion is easy to realize, and the folding/unfolding-repeatable locking/unlocking mechanism can be applied to spatial and ground repeated folding/unfolding mechanisms such as the solar wing, and a missile folding wing.
Description
Technical field
The present invention relates to a kind of repeatable folding and unfolding locking mechanism, but especially relate to a kind of sun wing joint hinge repeatable folding and unfolding locking mechanism.
Background technology
Repeatable folding and unfolding locking mechanism is the important component part of sun wing folding exhibition mechanism.Present domestic most spacecrafts all adopt disposable space development lockout mechanism with the sun wing, and promptly the sun wing folds and draws in fairing at launching phase, the disposable mode of operation that is expanded in back of entering the orbit.When spacecraft became rail or orbit maneuver correction, the sun wing of its expansion was prone to cause the vibration of self flexible structure, and the spacecraft body is produced disturbance torque, influences the attitude stability of spacecraft.
Summary of the invention
In order to solve the repeatable folding and unfolding locking problem of the sun wing; But the object of the present invention is to provide a kind of sun wing joint hinge repeatable folding and unfolding locking mechanism; Realize the repeated folding exhibition of sun wing when spacecraft becomes rail operation or attitude regulating control; To improve the attitude stability of spacecraft, increase the service life, reduce the harmful effect that the sun wing trembles and produced when becoming rail.
The technical scheme that the present invention adopted is following:
The present invention includes motor, two synchronous belt drive mechanisms, link span joint hinge, link span, the first substrate joint hinge and first substrate; Motor and satellite body inside are affixed; One end and the satellite body outside of link span joint hinge are affixed; The small end of link span is connected with the other end of link span joint hinge; The big end of link span is connected with an end of first substrate joint hinge, and the other end of first substrate joint hinge and an end of first substrate are affixed; Electric machine main shaft is connected with synchronous pulley through coupler; The optical axis of the screw rod upper end of link span joint hinge is connected with electric machine main shaft through first synchronous belt drive mechanism, and the screw rod lower end optical axis of link span joint hinge is connected through the screw rod lower end optical axis of second synchronous belt drive mechanism with first substrate joint hinge; Space cam groove rotation direction on link span joint hinge and the first substrate joint hinge is opposite.
Described link span joint hinge comprises: first strut member, first pin-and-hole, first locating dowel pin, clutch shaft bearing, screw rod, nut, pin, space cam groove, space cylindrical cam, second strut member, second bearing, second pin-and-hole and second locating dowel pin; In the cylindrical cam of space nut is housed; The nut outside is connected with pin, and the nut upper surface is connected with first locating dowel pin, the nut lower surface is connected with second locating dowel pin, and nut cooperates with screw rod; Have 90 ° of dextrorotation space cam grooves on the cylindrical cam of space; Pin is spacing to be moved in the space cam groove, and the screw rod upper end is bearing in first strut member through clutch shaft bearing, and the screw rod lower end is bearing in second strut member through second bearing; In the complete deployed condition of link span, first locating dowel pin inserts in first pin-and-hole in first strut member, and at the link span folded state, second locating dowel pin inserts in second pin-and-hole in second strut member; First strut member and second strut member outside are affixed with the satellite body outside, and the cylindrical cam outside in space is affixed with link span;
The structure of described first substrate joint hinge is identical, and only the space cam groove on the hinge of the first substrate joint is 180 °, and the space cam groove rotation direction on space cam groove rotation direction on the hinge of the first substrate joint and the link span joint hinge is opposite.
One end of the other end of described first substrate and second substrate joint hinge is affixed; The other end of second substrate joint hinge and an end of second substrate are affixed; One end of the other end of second substrate and the 3rd substrate joint hinge is affixed; The other end of the 3rd substrate joint hinge and an end of the 3rd substrate are affixed, and an end of the other end of the 3rd substrate and tetrabasal joint hinge is affixed, and the other end of tetrabasal joint hinge and an end of tetrabasal are affixed; The screw rod upper end optical axis of first substrate joint hinge is connected with the screw rod upper end optical axis of second substrate joint hinge through the 3rd synchronous belt drive mechanism; The screw rod lower end optical axis of second substrate joint hinge is connected through the screw rod lower end optical axis of the 4th synchronous belt drive mechanism with the 3rd substrate joint hinge; The screw rod upper end optical axis of the 3rd substrate joint hinge is connected with the screw rod upper end optical axis of tetrabasal joint hinge through the 5th synchronous belt drive mechanism; Space cam groove on the hinge of adjacent two substrate joints is 180 °, and rotation direction is opposite during installation.
Comparing the beneficial effect that the present invention has with background technology is:
1, folding Zhan Hesuo separates mechanism and all is arranged on the joint hinge between substrate, has made full use of limited space between sun wing scale, compact conformation;
2, the input of repeatable folding and unfolding locking mechanism, output are coaxial, accurate positioning, and symmetry, load are good;
3, first order screw pair has auto-lock function, can realize that in theory sun wing scale separates the location at lock at any angle;
4, the locating dowel pin of nut two ends layout has guaranteed that sun substrate accurately turns to predetermined angular, and it is all less to the interference of spacecraft body and sun wing scale that this lock is separated mechanism, helps the maintenance of sun wing attitude stability in the spacecraft flight process.
5, applied range, the present invention is except can be applicable to the repetition fold-playing sun wing, also may be used on spaces such as deployable antenna, space extending arm, folding wings and repeats in development mechanisms and the relevant ground mechanism.
Description of drawings
Fig. 1 is an integral structure sketch of the present invention.
Fig. 2 is a link span joint hinge structure enlarged diagram.
Among the figure: 1. satellite body, 2. motor, 3. coupler, 4. synchronous pulley, 5. link span joint hinge, 6. synchronous belt drive mechanism; 7. first strut member, 8. first pin-and-hole, 9. first locating dowel pin, 10. clutch shaft bearing, 11. screw rods, 12. nuts; 13. pin, 14. space cam grooves, 15. space cylindrical cams, 16. second strut members, 17. second bearings, 18. second pin-and-holes; 19. second locating dowel pin, 20. link spans, 21. first substrate joints hinge, 22. first substrates, 23. second substrate joints hinge; 24. second substrate, 25. the 3rd substrate joints hinge, 26. the 3rd substrates, 27. tetrabasal joints hinge, 28. tetrabasals.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described further.
Like Fig. 1, shown in Figure 2, the present invention includes 2, two synchronous belt drive mechanisms of motor, link span joint hinge 5, link span 20, the first substrates 22 and first substrate joint hinge 21; Motor 2 is inner affixed with satellite body 1; One end of link span joint hinge and satellite body 1 are outside affixed; The small end of link span 20 is connected with the other end of link span joint hinge; The big end of link span 20 is connected with an end of first substrate joint hinge 21, and the other end of first substrate joint hinge 21 and an end of first substrate 22 are affixed; Motor 2 main shafts are connected with synchronous pulley 4 through coupler 3; The optical axis of screw rod 11 upper ends of link span joint hinge 5 is connected with motor 2 main shafts through first synchronous belt drive mechanism, and the screw rod 11 lower end optical axises of link span joint hinge 5 are connected through the screw rod lower end optical axis of second synchronous belt drive mechanism with first substrate joint hinge 21; Space cam groove rotation direction on the hinge 5 and first substrate joint, the link span joint hinge 21 is opposite.
Described link span joint hinge 5 comprises: first strut member, 7, the first pin-and-holes, 8, the first locating dowel pins 9, clutch shaft bearing 10; Screw rod 11, nut 12, pin 13, space cam groove 14; Space cylindrical cam 15, the second strut member 16, the second bearings, 17, the second pin-and-holes 18 and second locating dowel pins 19; Nut 12 is housed in the space cylindrical cam 15; Nut 12 outsides are connected with pin 13, and nut 12 upper surfaces are connected with first locating dowel pin 9, nut 12 lower surfaces are connected with second locating dowel pin 19, and nut 12 cooperates with screw rod 11; Have 90 ° of dextrorotation space cam grooves 14 on the space cylindrical cam 15; Pin 13 is spacing mobile in space cam groove 14, and screw rod 11 upper ends are bearing in first strut member 7 through clutch shaft bearing 10, and screw rod 11 lower ends are bearing in second strut member 16 through second bearing 17; In link span 20 complete deployed conditions, in first pin-and-hole 8 that first locating dowel pin 9 inserts in first strut member 7, at link span 20 folded states, in second pin-and-hole 18 that second locating dowel pin 19 inserts in second strut member 16; First strut member 7 and second strut member, 16 outsides and satellite body 1 outside are affixed, and space cylindrical cam 15 outsides and link span 20 are affixed;
The structure of described first substrate joint hinge 21 is identical, and only the space cam groove on the first substrate joint hinge 21 is 180 °, and the space cam groove rotation direction on space cam groove rotation direction on the first substrate joint hinge 21 and the link span joint hinge 5 is opposite.
One end of the other end of described first substrate 22 and second substrate joint hinge 23 is affixed; The other end of second substrate joint hinge 23 and an end of second substrate 24 are affixed; One end of the other end of second substrate 24 and the 3rd substrate joint hinge 25 is affixed; The other end of the 3rd substrate joint hinge 25 and an end of the 3rd substrate 26 are affixed, and an end of the other end of the 3rd substrate 26 and tetrabasal joint hinge 27 is affixed, and the other end of tetrabasal joint hinge 27 and an end of tetrabasal 28 are affixed; The screw rod upper end optical axis of first substrate joint hinge 21 is connected with the screw rod upper end optical axis of second substrate joint hinge 23 through the 3rd synchronous belt drive mechanism; The screw rod lower end optical axis of second substrate joint hinge 23 is connected through the screw rod lower end optical axis of the 4th synchronous belt drive mechanism with the 3rd substrate joint hinge 25; The screw rod upper end optical axis of the 3rd substrate joint hinge 25 is connected with the screw rod upper end optical axis of tetrabasal joint hinge 27 through the 5th synchronous belt drive mechanism; Space cam groove on the hinge of adjacent two substrate joints is 180 °, and rotation direction is opposite during installation.
Principle of work of the present invention is:
The screw pair and the combination of space cam kinematic pair that are arranged on the hinge of sun wing joint are used, realized sun wing repeatable folding and unfolding locking function.Motor 2 passes to the screw rod that cut with scissors in each joint through synchronous belt drive mechanism with output torque, and first order screw pair is converted into moving of right handed unt with the rotation of screw rod, thereby the pin that drives on it moves.Second stage kinematic pair is the space cam kinematic pair, and it is with the mobile rotation that be converted into space cylindrical cam of pin along cam path.And because of the sun wing is fixed on the cylindrical cam of space, historical facts or anecdotes has showed the folding of the sun wing and has launched.Utilize the locating dowel pin on the nut to realize sun wingfold, launch the locking of ultimate position, and the auto-lock function of first order screw pair has been guaranteed the redundant reliable location of folding and expanding ultimate position.Concrete working process is following:
Power is driven synchronous pulley 4 and is rotated counterclockwise by motor 2 output, is passed on the link span joint hinge 5 through first synchronous belt drive mechanism 6, drives screw rod 11 and rotates counterclockwise.In link span joint hinge 5, because screw rod 11 is a right-hand screw thread, so the right handed unt 12 that can drive cooperation with it that rotates counterclockwise of screw rod 11 moves down i.e. first order screw pair execution.Be connected with pin 13 on the right handed unt 12, pin 13 moves down in space cam groove 14, drives space cylindrical cam 15 and rotates counterclockwise 90o, i.e. second stage kinematic pair execution.Space cylindrical cam 15 connects firmly with link span 20, and the two rotates in the same way, and promptly link span 20 rotates counterclockwise 90o, accomplishes jackknife action.Motor stall this moment in second pin-and-hole 18 that second locating dowel pin 19 inserts on second strut member 16, make nut 12 stop motions, thereby space cylindrical cam 15 stops operating, and can realize the locking of this folding exhibition mechanism.Otherwise; If the motion of motor 2 cws drives screw rod 11 through first synchronous belt drive mechanism 6 and clockwise rotates, nut 12 moves up; Second locating dowel pin 19 of its lower surface withdraws from release from second pin-and-hole 18; The drive space cylindrical cam 15 that moves up of nut 12 clockwise rotates 90o simultaneously, thereby makes link span 20 clockwise rotate 90o, accomplishes and launches action.Motor 2 stalls this moment in first pin-and-hole 8 that first locating dowel pin 9 inserts in first strut member 7, are accomplished and are launched lock out action.The folding Zhan Yusuo of this mechanism separates function integration, and folding is opened up the rear motor stall that puts in place, by release-expansion-locking-unlocking-folding-this works of locking.
This mechanism adopts synchronously band as transmission device, not only transferring power but also play the interlock effect, and each belt wheel turns to identical.Because link span and inner panel corner are respectively 90 o and 180 o, so the transmitting ratio of synchronous belt drive mechanism is respectively: i
I-II=1/2, i
II-III=i
III-IV=i
IV-V=1; Space cam groove on the I axle is 90o, and the space cam groove on II, III, IV, the V axle is 180o, thereby guarantees each substrate synchronous expansion.
In like manner, the principle of work of first substrate joint hinge, 21, second substrate joint hinge the 23, the 3rd substrate joint hinge 25, tetrabasal joint hinge 27 and link span joint are cut with scissors 5 identical.Space cam groove rotation direction on the hinge of adjacent two substrates joint is opposite, to realize adjacent two substrates one a contrary fold exhibition.
Claims (3)
1. but a sun wing joint hinge repeatable folding and unfolding locking mechanism is characterized in that: comprise motor (2), two synchronous belt drive mechanisms, link span joint hinge (5), link span (20), first substrate (22) and first substrate joint hinge (21); Motor (2) is inner affixed with satellite body (1); One end of link span joint hinge (5) and satellite body (1) are outside affixed; The small end of link span (20) is connected with the other end of link span joint hinge (5); The big end of link span (20) is connected with the end that (21) are cut with scissors in the first substrate joint, and the other end of first substrate joint hinge (21) is connected with an end of first substrate (22); Motor (2) main shaft is connected with synchronous pulley (4) through coupler (3); The optical axis of the screw rod upper end of link span joint hinge (5) is connected with motor (2) main shaft through first synchronous belt drive mechanism, and the screw rod lower end optical axis of link span joint hinge (5) is connected with the screw rod lower end optical axis that (21) are cut with scissors in the first substrate joint through second synchronous belt drive mechanism; Space cam groove rotation direction on link span joint hinge (5) and the first substrate joint hinge (21) is opposite.
But 2. a kind of sun wing according to claim 1 joint hinge repeatable folding and unfolding locking mechanism, it is characterized in that: described link span joint hinge (5) comprising: first strut member (7), first pin-and-hole (8), first locating dowel pin (9); Clutch shaft bearing (10), screw rod (11), nut (12); Pin (13), space cam groove (14), space cylindrical cam (15); Second strut member (16), second bearing (17), second pin-and-hole (18) and second locating dowel pin (19); Nut (12) is housed in the space cylindrical cam (15); Nut (12) outside is connected with pin (13); Nut (12) upper surface is connected with first locating dowel pin (9), nut (12) lower surface is connected with second locating dowel pin (19); Nut (12) cooperates with screw rod (11), has 90 ° of dextrorotation space cam grooves (14) on the space cylindrical cam (15), and pin (13) is spacing to be moved in space cam groove (14); Screw rod (11) upper end is bearing in first strut member (7) through clutch shaft bearing (10), and screw rod (11) lower end is bearing in second strut member (16) through second bearing (17); In the complete deployed condition of link span (20); First locating dowel pin (9) inserts in first pin-and-hole (8) in first strut member (7); At link span (20) folded state, second locating dowel pin (19) inserts in second pin-and-hole (18) in second strut member (16); First strut member (7) and second strut member (16) outside are affixed with satellite body (1) outside, and space cylindrical cam (15) outside is affixed with link span (20);
The structure of described first substrate joint hinge (21) is identical; Only the space cam groove on the first substrate joint hinge (21) is 180 °, and the space cam groove rotation direction on space cam groove rotation direction on the first substrate joint hinge (21) and the link span joint hinge (5) is opposite.
3. but a kind of sun wing according to claim 1 joint hinge repeatable folding and unfolding locking mechanism; It is characterized in that: an end of the other end of described first substrate (22) and second substrate joint hinge (23) is affixed; The other end of second substrate joint hinge (23) and an end of second substrate (24) are affixed; One end of the other end of second substrate (24) and the 3rd substrate joint hinge (25) is affixed; The other end of the 3rd substrate joint hinge (25) and an end of the 3rd substrate (26) are affixed; One end of the other end of the 3rd substrate (26) and tetrabasal joint hinge (27) is affixed, and the other end of tetrabasal joint hinge (27) and an end of tetrabasal (28) are affixed; The screw rod upper end optical axis of first substrate joint hinge (21) cuts with scissors (23) through the 3rd synchronous belt drive mechanism and the second substrate joint screw rod upper end optical axis is connected; The screw rod lower end optical axis of second substrate joint hinge (23) is connected with the screw rod lower end optical axis that (25) are cut with scissors in the 3rd substrate joint through the 4th synchronous belt drive mechanism; The screw rod upper end optical axis of the 3rd substrate joint hinge (25) is connected with the screw rod upper end optical axis of tetrabasal joint hinge (27) through the 5th synchronous belt drive mechanism; Space cam groove on the hinge of adjacent two substrate joints is 180 °, and rotation direction is opposite during installation.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102249043A CN102730202A (en) | 2012-06-28 | 2012-06-28 | Folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for solar wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102249043A CN102730202A (en) | 2012-06-28 | 2012-06-28 | Folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for solar wing |
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| CN102730202A true CN102730202A (en) | 2012-10-17 |
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| CN2012102249043A Pending CN102730202A (en) | 2012-06-28 | 2012-06-28 | Folding/unfolding-repeatable locking/unlocking mechanism with joint hinges for solar wing |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103939554A (en) * | 2014-04-08 | 2014-07-23 | 哈尔滨工业大学 | Gear rotating type auxiliary reciprocating turnover mechanism for solar wings |
| CN104108476A (en) * | 2014-06-24 | 2014-10-22 | 上海宇航系统工程研究所 | Multifunctional solar wing for satellite |
| CN107914896A (en) * | 2017-11-07 | 2018-04-17 | 广西大学 | It is a kind of using five-bar mechanism as the space folding and unfolding mechanism that can open up unit |
| CN107914897A (en) * | 2017-11-07 | 2018-04-17 | 广西大学 | It is a kind of using double pneumatic cylinders as the space folding and unfolding mechanism that can open up unit |
| CN109768391A (en) * | 2018-12-29 | 2019-05-17 | 京信通信技术(广州)有限公司 | Antenna, the display system of antenna lower decline angle and its transmission mechanism |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102701A (en) * | 2009-12-18 | 2011-06-22 | 泰勒斯公司 | Device for the deployment and pointing of structure elements in a spatial environment |
| CN102134909A (en) * | 2010-01-26 | 2011-07-27 | 西法股份公司 | Device to control actively the vibrations of an articulated arm to pump concrete |
| CN202115709U (en) * | 2011-05-26 | 2012-01-18 | 浙江理工大学 | Space cam-spiral combined repeated folding unlocking mechanism |
| CN202657256U (en) * | 2012-06-28 | 2013-01-09 | 浙江理工大学 | Repeatable folding-unfolding locking-unlocking mechanism for joint hinge of solar wing |
-
2012
- 2012-06-28 CN CN2012102249043A patent/CN102730202A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102701A (en) * | 2009-12-18 | 2011-06-22 | 泰勒斯公司 | Device for the deployment and pointing of structure elements in a spatial environment |
| CN102134909A (en) * | 2010-01-26 | 2011-07-27 | 西法股份公司 | Device to control actively the vibrations of an articulated arm to pump concrete |
| CN202115709U (en) * | 2011-05-26 | 2012-01-18 | 浙江理工大学 | Space cam-spiral combined repeated folding unlocking mechanism |
| CN202657256U (en) * | 2012-06-28 | 2013-01-09 | 浙江理工大学 | Repeatable folding-unfolding locking-unlocking mechanism for joint hinge of solar wing |
Non-Patent Citations (1)
| Title |
|---|
| 胡明等: "重复折展锁解式太阳翼展开动力学建模与仿真", 《中国机械工程》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103939554A (en) * | 2014-04-08 | 2014-07-23 | 哈尔滨工业大学 | Gear rotating type auxiliary reciprocating turnover mechanism for solar wings |
| CN103939554B (en) * | 2014-04-08 | 2016-03-02 | 哈尔滨工业大学 | The reciprocal assisting overturn mechanism of pinion rotation formula solar wing |
| CN104108476A (en) * | 2014-06-24 | 2014-10-22 | 上海宇航系统工程研究所 | Multifunctional solar wing for satellite |
| CN104108476B (en) * | 2014-06-24 | 2016-07-06 | 上海宇航系统工程研究所 | A kind of satellite multifunctional solar wing |
| CN107914896A (en) * | 2017-11-07 | 2018-04-17 | 广西大学 | It is a kind of using five-bar mechanism as the space folding and unfolding mechanism that can open up unit |
| CN107914897A (en) * | 2017-11-07 | 2018-04-17 | 广西大学 | It is a kind of using double pneumatic cylinders as the space folding and unfolding mechanism that can open up unit |
| CN107914897B (en) * | 2017-11-07 | 2020-10-20 | 广西大学 | Space folding and unfolding mechanism with double air cylinders as unfolding units |
| CN107914896B (en) * | 2017-11-07 | 2020-10-20 | 广西大学 | Space folding and unfolding mechanism with five-link mechanism as unfolding unit |
| CN109768391A (en) * | 2018-12-29 | 2019-05-17 | 京信通信技术(广州)有限公司 | Antenna, the display system of antenna lower decline angle and its transmission mechanism |
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Application publication date: 20121017 |