CN201523070U - Satellite borne extensible reflector synchronous hinge device - Google Patents
Satellite borne extensible reflector synchronous hinge device Download PDFInfo
- Publication number
- CN201523070U CN201523070U CN2009202222186U CN200920222218U CN201523070U CN 201523070 U CN201523070 U CN 201523070U CN 2009202222186 U CN2009202222186 U CN 2009202222186U CN 200920222218 U CN200920222218 U CN 200920222218U CN 201523070 U CN201523070 U CN 201523070U
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- folding rod
- hinge device
- synchronous
- rod joint
- reflector
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Abstract
The utility model relates to a satellite borne extensible reflector synchronous hinge device, which is applied to extending folding rods of a reflector and guarantees the folding rods to extend in place synchronously. The satellite borne extensible reflector synchronous hinge device comprises a folding rod joint, a volute spiral spring, a synchronous hinge support, a rotating shaft and a synchronous gear, the folding rod joint is arranged on the synchronous hinge support through the rotating shaft, the volute spiral spring is arranged on the rotating shaft, the rotating shaft is fixed on the synchronous hinge support, and two ends of the folding rod joint are connected through meshing of synchronous gears arranged on the folding rod joint. The satellite borne extensible reflector synchronous hinge device obvious improves anti-fatigue property, is constant in torque during an extending process, large in holding torque when in place, small in starting torque, simple in structure and high in synchronous precision, can be popularized and applied to various satellite borne extensible reflectors, and has broad application prospect.
Description
Technical field
The utility model belongs to satellite antenna structure field, particularly relates to a kind of spaceborne deployable reflector synchronising hinge device.
Background technology
The synchronising hinge device is the core component of deployable reflector, and its articulated form is determining reflector to launch the precision that puts in place, the size of launching reliability and launching to impact.
Spaceborne deployable reflector generally all has the synchronising hinge device to guarantee the reflector synchronous expansion, it is to guarantee two rod member synchronous expansions that most common synchronization is launched the hinge arrangement form, traditional synchronising hinge is made up of five parts, that is: folding rod joint 1, rotation axis 2, synchronising hinge support 3, driven unit 4 and lead 5 are formed, version as shown in Figure 1, the driven unit of synchronising hinge is a torsion spring, drive folding rod by torsion spring and draw expansion in, folding rod joint and lead are realized synchronizing function by the tooth bar engagement.
The conventional synchronization hinge repeatedly launches the back and the torsion spring fatigue phenomenon occurs driving, launches the final states holding torque and descends, and folding rod can not launch fully.The reason of problem is the limitation that is subjected to installing space, and torsion spring antifatigue design margin is little, and anti-fatigue ability is poor.
Summary of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art, a kind of spaceborne deployable reflector synchronising hinge device is provided, this synchronising hinge device launches the synchronization accuracy height, expansion process moment is undamped, the final states holding torque is big, and simple in structure, the synchronization dependability height.
Above-mentioned purpose of the present utility model is achieved by following technical solution:
A kind of spaceborne deployable reflector synchronising hinge device, it is characterized in that: comprise folding rod joint, scroll spring, synchronising hinge support, rotation axis and synchromesh gear, described folding rod joint is installed on the synchronising hinge support by rotation axis, scroll spring is installed on the rotation axis, rotation axis is fixed on the synchronising hinge support, and folding rod joint two ends realize connecting by the engagement that the synchromesh gear on it is set.
In above-mentioned spaceborne deployable reflector synchronising hinge device, each end of folding rod joint is provided with two relative synchromesh gears, has circular hole in the middle of two relative synchromesh gears, and rotation axis passes circular hole, and the folding rod joint is installed on the synchronising hinge support.
In above-mentioned spaceborne deployable reflector synchronising hinge device, rotation axis passes through the copper sheathing bearing fixing on the synchronising hinge support.
In above-mentioned spaceborne deployable reflector synchronising hinge device, scroll spring is two, is installed in respectively on two rotation axiss.
The utility model compared with prior art has following advantage:
(1) driving element of the utility model synchronising hinge device is a scroll spring, drive folding rod by the vortex ring spring and draw expansion in, the driving element of conventional synchronization hinge means is a torsion spring, drive folding rod by torsion spring and draw expansion in, contrast two kinds of type of drive, the torsion spring anti-fatigue performance is poor, vortex ring spring anti-fatigue performance obviously is better than torsion spring, and it is little that scroll spring has the decay of expansion process moment, moment is constant, and the holding torque that puts in place is big, the characteristics that staring torque is little, the utility model driving element uses scroll spring to make the hinge means fatigue resistance obviously to promote, expansion process moment is constant, and the holding torque that puts in place is big, and staring torque is little;
(2) method of synchronization of the utility model synchronising hinge device is that gear is synchronous, the method of synchronization of conventional synchronization hinge means is that tooth bar is synchronous, employing lead guiding, contrast two kinds of methods of synchronization, the utility model synchronising hinge is taked the direct geared engagement synchronously, need not the lead guiding, version is simple, assembly manipulation is easy, and the synchronization accuracy height has improved the reliability of synchronising hinge;
(3) contrast conventional synchronization hinge expansion process, the synchronising hinge of the utility model synchronising hinge device launches final states and impacts little;
(4) adopt the copper sheathing bearing that rotation axis is fixed on the synchronising hinge support in the utility model, replace tradition to adopt the spring collar fixed bias circuit, more help the rotation of rotation axis, make synchronization accuracy improve.
Description of drawings
Fig. 1 is a conventional synchronization hinge means structural representation;
Fig. 2 is the utility model synchronising hinge apparatus structure schematic diagram;
Fig. 3 is the utility model synchronising hinge apparatus structure exploded view;
Fig. 4 is the scroll spring structure chart;
Fig. 5 a～Fig. 5 c is that the utility model synchronising hinge device launches principle schematic.
Specific embodiments
Below in conjunction with specific embodiment the utility model is described in further detail:
Be illustrated in figure 2 as the structural representation of the utility model synchronising hinge device, Figure 3 shows that synchronising hinge apparatus structure exploded view, hinge means comprises folding rod joint 6 as seen from the figure, scroll spring 7, synchronising hinge support 8, rotation axis 9, synchromesh gear 10 and copper sheathing bearing 11, folding rod joint 6 is installed on the synchronising hinge support 8 by rotation axis 9, wherein on each end of folding rod joint 6 two relative synchromesh gears 10 are set, have circular hole in the middle of two relative synchromesh gears 10, rotation axis 9 is two, after being installed respectively, scroll spring 7 passes circular hole, by copper sheathing bearing 11 folding rod joint 6 is installed on the synchronising hinge support 8, folding rod joint 6 two ends realize connecting by the engagement that the synchromesh gear 10 on it is set.
Be illustrated in figure 4 as the structure chart of synchronising hinge device scroll spring.
The course of work of the utility model synchronising hinge device is as follows:
Shown in Fig. 5 a, the synchronising hinge device is folded to rounding state by artificial external force;
Shown in Fig. 5 b, the folding rod structure of synchronising hinge device realizes synchronous expansion under the effect of driven unit scroll spring 7, and the folding rod start point is synchronous in the expansion process, i.e. start point θ
1=θ
2
Shown in Fig. 5 c, synchronising hinge folding device bar structure is launched to put in place, under the effect of driven unit scroll spring pretightning force, has certain holding torque that puts in place.
The above; it only is the embodiment of the utility model the best; but protection range of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the variation that can expect easily or replacement all should be encompassed within the protection range of the present utility model.
The content that is not described in detail in the utility model specification belongs to this area professional and technical personnel's known technology.
Claims (4)
1. spaceborne deployable reflector synchronising hinge device, it is characterized in that: comprise folding rod joint (6), scroll spring (7), synchronising hinge support (8), rotation axis (9) and synchromesh gear (10), described folding rod joint (6) is installed on the synchronising hinge support (8) by rotation axis (9), scroll spring (7) is installed on the rotation axis (9), rotation axis (9) is fixed on the synchronising hinge support (8), and folding rod joint (6) two ends realize connecting by the engagement that the synchromesh gear (10) on it is set.
2. a kind of spaceborne deployable reflector synchronising hinge device according to claim 1, it is characterized in that: each end of described folding rod joint (6) is provided with two relative synchromesh gears (10), have circular hole in the middle of two relative synchromesh gears (10), described rotation axis (9) passes circular hole, and folding rod joint (6) is installed on the synchronising hinge support (8).
3. a kind of spaceborne deployable reflector synchronising hinge device according to claim 1, it is characterized in that: described rotation axis (9) is fixed on the synchronising hinge support (10) by copper sheathing bearing (11).
4. a kind of spaceborne deployable reflector synchronising hinge device according to claim 1, it is characterized in that: described scroll spring (7) is two, is installed in respectively on two rotation axiss (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202222186U CN201523070U (en) | 2009-08-31 | 2009-08-31 | Satellite borne extensible reflector synchronous hinge device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202222186U CN201523070U (en) | 2009-08-31 | 2009-08-31 | Satellite borne extensible reflector synchronous hinge device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201523070U true CN201523070U (en) | 2010-07-07 |
Family
ID=42509246
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202222186U Expired - Lifetime CN201523070U (en) | 2009-08-31 | 2009-08-31 | Satellite borne extensible reflector synchronous hinge device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201523070U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
| CN102176531A (en) * | 2011-01-10 | 2011-09-07 | 圆刚科技股份有限公司 | Double-antenna module capable of automatically expanding outwards |
| CN103032451A (en) * | 2012-12-21 | 2013-04-10 | 中国科学院长春光学精密机械与物理研究所 | Clamping stagnation prevention precision synchronization hinge |
| CN103594796A (en) * | 2012-08-15 | 2014-02-19 | 宏达国际电子股份有限公司 | Portable electronic devices and methods for positioning antennas of such devices |
| CN105757208A (en) * | 2016-03-21 | 2016-07-13 | 清华大学 | Spatial net-shaped antenna passive unfolding drive based on non-circular gear |
| CN106129576A (en) * | 2016-08-11 | 2016-11-16 | 西安电子科技大学 | A kind of spaceborne Electrostatic deformation film reflector face deployable antenna sub-truss device |
| CN106229603A (en) * | 2016-08-31 | 2016-12-14 | 燕山大学 | Torsion spring drives scissor-type annular truss deployable antenna mechanism |
| CN107171053A (en) * | 2017-05-19 | 2017-09-15 | 浙江龙游公任电子有限公司 | A kind of convenient exterior aerial drawn in |
| CN107642577A (en) * | 2017-09-07 | 2018-01-30 | 星展测控科技股份有限公司 | A kind of antenna pitching is with horizontal member, trim support and the trimmer with horizontal member containing antenna pitching |
-
2009
- 2009-08-31 CN CN2009202222186U patent/CN201523070U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
| CN102011922B (en) * | 2010-12-03 | 2012-07-25 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
| CN102176531A (en) * | 2011-01-10 | 2011-09-07 | 圆刚科技股份有限公司 | Double-antenna module capable of automatically expanding outwards |
| CN103594796A (en) * | 2012-08-15 | 2014-02-19 | 宏达国际电子股份有限公司 | Portable electronic devices and methods for positioning antennas of such devices |
| CN103032451A (en) * | 2012-12-21 | 2013-04-10 | 中国科学院长春光学精密机械与物理研究所 | Clamping stagnation prevention precision synchronization hinge |
| CN105757208A (en) * | 2016-03-21 | 2016-07-13 | 清华大学 | Spatial net-shaped antenna passive unfolding drive based on non-circular gear |
| CN106129576A (en) * | 2016-08-11 | 2016-11-16 | 西安电子科技大学 | A kind of spaceborne Electrostatic deformation film reflector face deployable antenna sub-truss device |
| CN106129576B (en) * | 2016-08-11 | 2018-11-16 | 西安电子科技大学 | A kind of spaceborne Electrostatic deformation film reflector face deployable antenna sub-truss device |
| CN106229603A (en) * | 2016-08-31 | 2016-12-14 | 燕山大学 | Torsion spring drives scissor-type annular truss deployable antenna mechanism |
| CN107171053A (en) * | 2017-05-19 | 2017-09-15 | 浙江龙游公任电子有限公司 | A kind of convenient exterior aerial drawn in |
| CN107171053B (en) * | 2017-05-19 | 2019-04-26 | 浙江龙游公任电子有限公司 | A kind of exterior aerial facilitating gathering |
| CN107642577A (en) * | 2017-09-07 | 2018-01-30 | 星展测控科技股份有限公司 | A kind of antenna pitching is with horizontal member, trim support and the trimmer with horizontal member containing antenna pitching |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100707 |