CN103482084A - Novel band-spring-based solar sailboard unfolding and supporting mechanism - Google Patents
Novel band-spring-based solar sailboard unfolding and supporting mechanism Download PDFInfo
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- CN103482084A CN103482084A CN201310384757.0A CN201310384757A CN103482084A CN 103482084 A CN103482084 A CN 103482084A CN 201310384757 A CN201310384757 A CN 201310384757A CN 103482084 A CN103482084 A CN 103482084A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E10/50—Photovoltaic [PV] energy
Abstract
A novel band-spring-based solar sailboard unfolding and supporting mechanism belongs to the field of unfolding mechanisms applied to satellite solar battery arrays and aims to solve the problems of low unfolding rigidity and low base frequency in the prior art. The mechanism comprises a solar sailboard, coil-spring driving hinges, a satellite body, strut hinges, a lower strut, a band spring and an upper strut; the solar sailboard and the satellite body are connected by the coil-spring driving hinges, two ends of the band spring are respectively connected with the upper and lower struts by adapters, the upper strut is connected with the solar sailboard by one strut hinge, and the lower strut is connected with the satellite body by the other strut hinge; coil springs in the coil-spring driving hinges, the band spring and the strut hinges provide unfolding moment so as to realize the unfolding of the solar sailboard. According to the novel band-spring-based solar sailboard unfolding and supporting mechanism, the solar sailboard, the satellite body and the upper and lower struts form a whole to constitute a stable supporting structure shaped like a spacial tetrahedron, so that the base frequency and the rigidity of a system under an unfolding state are improved.
Description
Technical field
The invention belongs to the development mechanism field that is applied to satellite sun energy battery battle array, particularly relate to novel Stretching of solar wings and supporting mechanism based on banded spring on a kind of " quick small satellite ".
Background technology
The solar energy sailboard development mechanism is one of important subsystem of earth observation from space satellite, and the case that can't work because of the development mechanism mechanical breakdown in history reaches tens of examples.Therefore in the space satellite engineering, the solar energy sailboard development mechanism is the emphasis part of design, test.
Existing earth observation satellite is swept the class earth observation satellite for large-scale the pushing away of tradition, the solar energy sailboard development mechanism that is applicable to this type of observation satellite utilizes the linkage of the energy-storage travelling wave tubes such as wind spring, torsion spring, after planned orbit, realize Automatic-expanding, the function automatically locked at satellite launch.
Referring to the solar energy sailboard development mechanism shown in accompanying drawing 1, comprise that solar array 1, wind spring drive hinge 2 and satellite celestial body 3, in the outspreading sailboard process, the main drive square derives from the wind spring pre-fastening moment that wind spring drives hinge 2, and drives the catch gear of hinge 2 to realize the locking of windsurfing by wind spring.There is the problem that outspreading sailboard rigidity is lower in this solar energy sailboard development mechanism.
Various countries fell over each other to propose the new ideas of " quick earth observation small satellite " in the last few years, because the attitude of " quick small satellite " ceaselessly changes, the posture adjustment frequency is very high, this just has higher requirement to the expansion fundamental frequency of solar array, traditional solar energy sailboard development mechanism only drives hinge to lock solar array by two wind springs, form cantilever design, fundamental frequency is lower, rigidity is lower, can not meet the requirement of quick earth observation small satellite to rigidity and fundamental frequency, conventional satellite development mechanism part damping ratio is 0.1%～0.5%, damping ratio is lower, therefore need a kind of expansion fundamental frequency of development high, rigidity is high, novel outspreading sailboard and supporting mechanism that damping ratio is high.
Summary of the invention
The object of the invention is to solve the problem that expansion rigidity is low, fundamental frequency is low, damping ratio is low that prior art exists, propose a kind of novel Stretching of solar wings and supporting mechanism based on banded spring of high stability, meet the operating needs of quick earth observation small satellite.
For achieving the above object, a kind of novel Stretching of solar wings and supporting mechanism based on banded spring of the present invention comprises that solar array, wind spring drive hinge, satellite celestial body, pole hinge, lower fulcrum bar, banded spring and upper rack posts;
Described solar array and satellite celestial body drive chain connection by wind spring, banded both ends of the spring is connected with described lower fulcrum bar with described upper rack posts by adaptor respectively, described upper rack posts is connected with described solar array by the pole hinge, and described lower fulcrum bar is connected with described satellite celestial body by the pole hinge; Described wind spring drives wind spring, banded spring and the pole hinge in hinge to provide and launches the expansion that moment realizes solar array.
Described banded spring is two curved bend knee-pieces of relatively arranging, and realizes 180 ° of forward bending or reversed bendings and can recoil to original shape.
Described banded both ends of the spring is connected and is specially with described lower fulcrum bar with described upper rack posts by adaptor respectively: described lower fulcrum bar and described adaptor are sticked together, described banded spring and described adaptor compress and are screwed by two compact heaps, and the connection mode of described upper rack posts and banded spring is identical with the connection mode of lower fulcrum bar and banded spring.
Between described lower fulcrum bar and pole hinge, cushion block is arranged, can by the thickness of adjusting cushion block, come suitable adjusting lever long, upper rack posts be identical with the connection mode of pole hinge.
Described pole hinge comprises male hinge and female hinge, and described male hinge is connected with described female the hinge by axle, oscillating bearing, back-up ring, realizes that male hinge cuts with scissors rotation around mother, and described public affairs are cut with scissors both sides and are separately installed with torsion spring.
Good effect of the present invention: a kind of novel Stretching of solar wings and supporting mechanism based on banded spring of the present invention substituted with the simple banded spring of principle the complicated linkage easily gone wrong, banded spring has played linkage effect that can crooked 180 °, mechanism element is few, principle is simple, the linkage formed than the dozens of part, make supporting mechanism be become simple by complexity, reliability significantly promotes; With the pole hinge at two ends, be fixed by screws on solar array and satellite celestial body, make the integral body that solar array, satellite celestial body and upper rack posts and lower fulcrum bar form form a tetrahedral stable support structure in space, elevator system is fundamental frequency and rigidity under deployed condition; With traditional outspreading sailboard system, compare, replaced cantilever design with the space tetrahedral structure, under deployed condition, damping ratio reaches 3%, stability is high, meets the fundamental frequency demand of " quick small satellite " posture control system, and, when being disturbed the generation vibration, can recover faster plateau.
The accompanying drawing explanation
Fig. 1 is Stretching of solar wings mechanism structure schematic diagram in prior art;
Fig. 2 is expansion of the present invention and supporting mechanism structural representation;
Structural representation when Fig. 3 is expansion of the present invention and supporting mechanism structure rounding state;
Fig. 4 is banded spring occupation mode schematic diagram of the present invention;
Fig. 5 is banded spring of the present invention and upper rack posts and lower fulcrum bar connection mode structural representation;
Fig. 6 is pole hinge arrangement schematic diagram of the present invention;
Wherein: 1, solar array, 2, wind spring drives hinge, 3, the satellite celestial body, 4, the pole hinge, 5, lower fulcrum bar, 6, banded spring, 7, upper rack posts, 8, compact heap, 9, adaptor, 10, public hinge, 11, female hinge, 12, torsion spring, 13, cushion block.
The specific embodiment
Below in conjunction with accompanying drawing, embodiments of the present invention are described further.
Referring to accompanying drawing 2, a kind of novel solar array 1 based on banded spring 6 of the present invention launches to comprise that with supporting mechanism solar array 1, wind spring drive hinge 2, satellite celestial body 3, pole hinge 4, lower fulcrum bar 5, banded spring 6 and upper rack posts 7;
Described solar array 1 drives hinge 2 to be connected with satellite celestial body 3 by wind spring, banded spring 6 two ends are connected with described lower fulcrum bar 5 with described upper rack posts 7 by adaptor 9 respectively, described upper rack posts 7 is connected with described solar array 1 by pole hinge 4, and described lower fulcrum bar 5 is connected with described satellite celestial body 3 by pole hinge 4.
Referring to accompanying drawing 3, the described solar array 1 of rounding state of the present invention is parallel with described satellite celestial body 3, described upper rack posts 7 and described lower fulcrum bar 5 are in folded state, wind spring drives hinge 2 to rotate 90 °, make wind spring in the compressed energy-storage state, 45 ° of pole two ends hinge through, 180 ° of banded spring 6 bendings, in compressive state.In expansion process, wind spring drives hinge 2 that main expansion moment is provided, and pole hinge 4 and banded spring 6 also have certain additional function, and assisted Extraction is for launching moment.
Referring to accompanying drawing 4, described banded spring 6 is two curved bend knee-pieces of relatively arranging, its principle is similar to metallic tape, can the forward bending or 180 ° of reversed bendings can recoil to original shape, the crooked required torque of forward is much smaller than the reversed bending moment of torsion, after banded spring 6 launches, bending stiffness is higher, is difficult for bending.Two mechanisms that relatively rearrange, the both direction bending stiffness is all higher, as calculated, can meet the support stiffness requirement.
Referring to accompanying drawing 5, described banded spring 6 two ends are connected and are specially with described lower fulcrum bar 5 with described upper rack posts 7 by adaptor 9 respectively: described lower fulcrum bar 5 is sticked together with described adaptor 9, described banded spring 6 compresses and is screwed by two compact heaps 8 with described adaptor 9, and upper rack posts 7 parts also connect by same connection mode.
Referring to accompanying drawing 6, between described upper rack posts 7 and pole hinge, cushion block 13 is arranged, can by the thickness of adjusting cushion block 13, come suitable adjusting lever long, lower fulcrum bar 5 is identical with the connection mode of pole hinge 4.
Described pole hinge 4 comprises male hinge 10 and female hinge 11, described male hinge 10 is connected by axle, oscillating bearing, back-up ring and described female hinge 11, realize that male hinge 10 cuts with scissors 11 rotations around mother, described public hinge 10 both sides are separately installed with torsion spring 12, and its Main Function is eliminate the oscillating bearing diameter clearance and certain expansion moment is provided.
Be more than the specific embodiment of the present invention, but limitation of the present invention absolutely not.
Claims (5)
1. novel Stretching of solar wings and the supporting mechanism based on banded spring, comprise that solar array (1), wind spring drive hinge (2) and satellite celestial body (3), and described solar array (1) drives hinge (2) to be connected with satellite celestial body (3) by wind spring;
It is characterized in that, described expansion and supporting mechanism also comprise pole hinge (4), lower fulcrum bar (5), banded spring (6) and upper rack posts (7); Described banded spring (6) two ends are connected with described lower fulcrum bar (5) with described upper rack posts (7) by adaptor (9) respectively, described upper rack posts (7) is connected with described solar array (1) by pole hinge (4), and described lower fulcrum bar (5) is connected with described satellite celestial body (3) by pole hinge (4); Wind spring drives wind spring, described banded spring (6) and the described pole hinge (4) in hinge (2) to provide expansion moment to realize the expansion of solar array (1).
2. a kind of novel Stretching of solar wings and supporting mechanism based on banded spring according to claim 1, it is characterized in that, described banded spring (6) is two curved bend knee-pieces of relatively arranging, and realizes 180 ° of forward bending or reversed bendings and can recoil to original shape.
3. a kind of novel Stretching of solar wings and supporting mechanism based on banded spring according to claim 1, it is characterized in that, described banded spring (6) two ends are connected and are specially with described lower fulcrum bar (5) with described upper rack posts (7) by adaptor (9) respectively: described lower fulcrum bar (5) is sticked together with described adaptor (9), described banded spring (6) compresses and is screwed by two compact heaps (8) with described adaptor (9), the connection mode of described upper rack posts (7) and banded spring (6) is identical with the connection mode of banded spring (6) with lower fulcrum bar (5).
4. a kind of novel Stretching of solar wings and supporting mechanism based on banded spring according to claim 1, it is characterized in that, between described upper rack posts (7) and pole hinge (4), cushion block (13) is arranged, by the thickness of adjusting cushion block (13), come suitable adjusting lever long, the connection mode of lower fulcrum bar (5) and pole hinge (4) is identical with the connection mode of pole hinge (4) with identical upper rack posts (7).
5. a kind of novel Stretching of solar wings and supporting mechanism based on banded spring according to claim 1, it is characterized in that, described pole hinge (4) comprises male hinge (10) and female hinge (11), described male hinge (10) is connected by axle, oscillating bearing, back-up ring and described female hinge (11), realize that male hinge (10) is around mother's hinge (11) rotation, described public hinge (10) both sides are separately installed with torsion spring (12).
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| CN201310384757.0A CN103482084B (en) | 2013-08-29 | 2013-08-29 | A kind of novel Stretching of solar wings based on banded spring and supporting mechanism |
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| CN103482084B CN103482084B (en) | 2016-01-13 |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105370713A (en) * | 2015-11-20 | 2016-03-02 | 北京卫星制造厂 | Microsatellite unfolding mechanism |
| CN105539880A (en) * | 2016-01-13 | 2016-05-04 | 广西大学 | Large-area unfoldable solar energy turnover plate |
| CN105539885A (en) * | 2015-12-25 | 2016-05-04 | 南京理工大学 | Locking and releasing mechanism for expandable solar cell array of cubic satellite |
| CN105836163A (en) * | 2016-04-14 | 2016-08-10 | 北京卫星制造厂 | Boosting type spreading device applicable to flexible dynamic boundary connection |
| CN105909714A (en) * | 2016-04-19 | 2016-08-31 | 长光卫星技术有限公司 | Impact damping device suitable for unfolding of solar panel substrate |
| CN107757952A (en) * | 2017-10-09 | 2018-03-06 | 长光卫星技术有限公司 | Microsatellite solar wing spreading locking device |
| CN108327928A (en) * | 2018-03-29 | 2018-07-27 | 长光卫星技术有限公司 | Integral type solar wing supporting mechanism |
| CN108767416A (en) * | 2018-04-17 | 2018-11-06 | 南京航空航天大学 | It is a kind of that there is driving to consolidate surface antenna with the satellite of lock function and connect compound hinges |
| CN110979742A (en) * | 2019-11-29 | 2020-04-10 | 北京卫星制造厂有限公司 | High-expansion-ratio unfolding mechanism suitable for space environment |
| CN111354257A (en) * | 2020-04-02 | 2020-06-30 | 沈阳航空航天大学 | Space solar power station ground experiment platform |
| CN112623280A (en) * | 2021-01-04 | 2021-04-09 | 上海宇航系统工程研究所 | Two-degree-of-freedom solar cell array unfolding device |
| CN113548201A (en) * | 2021-07-21 | 2021-10-26 | 上海宇航系统工程研究所 | Fan-shaped solar wing repeated unfolding and folding locking mechanism |
| CN113568134A (en) * | 2021-08-09 | 2021-10-29 | 吉林大学 | Unfolding mechanism of spatial diffraction primary mirror with heat dissipation and low impact characteristics |
| CN114056602A (en) * | 2020-08-04 | 2022-02-18 | 南京理工大学 | Variable-configuration cube star for simulating space debris and working method thereof |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105370713A (en) * | 2015-11-20 | 2016-03-02 | 北京卫星制造厂 | Microsatellite unfolding mechanism |
| CN105539885A (en) * | 2015-12-25 | 2016-05-04 | 南京理工大学 | Locking and releasing mechanism for expandable solar cell array of cubic satellite |
| CN105539880A (en) * | 2016-01-13 | 2016-05-04 | 广西大学 | Large-area unfoldable solar energy turnover plate |
| CN105836163A (en) * | 2016-04-14 | 2016-08-10 | 北京卫星制造厂 | Boosting type spreading device applicable to flexible dynamic boundary connection |
| CN105909714A (en) * | 2016-04-19 | 2016-08-31 | 长光卫星技术有限公司 | Impact damping device suitable for unfolding of solar panel substrate |
| CN107757952B (en) * | 2017-10-09 | 2023-05-30 | 长光卫星技术股份有限公司 | Microsatellite solar wing span unlocking and fixing device |
| CN107757952A (en) * | 2017-10-09 | 2018-03-06 | 长光卫星技术有限公司 | Microsatellite solar wing spreading locking device |
| CN108327928A (en) * | 2018-03-29 | 2018-07-27 | 长光卫星技术有限公司 | Integral type solar wing supporting mechanism |
| CN108327928B (en) * | 2018-03-29 | 2023-09-15 | 长光卫星技术股份有限公司 | Integrated solar wing supporting mechanism |
| CN108767416B (en) * | 2018-04-17 | 2020-02-21 | 南京航空航天大学 | Satellite fixed surface antenna connection composite hinge with driving and locking functions |
| CN108767416A (en) * | 2018-04-17 | 2018-11-06 | 南京航空航天大学 | It is a kind of that there is driving to consolidate surface antenna with the satellite of lock function and connect compound hinges |
| CN110979742A (en) * | 2019-11-29 | 2020-04-10 | 北京卫星制造厂有限公司 | High-expansion-ratio unfolding mechanism suitable for space environment |
| CN111354257A (en) * | 2020-04-02 | 2020-06-30 | 沈阳航空航天大学 | Space solar power station ground experiment platform |
| CN114056602A (en) * | 2020-08-04 | 2022-02-18 | 南京理工大学 | Variable-configuration cube star for simulating space debris and working method thereof |
| CN114056602B (en) * | 2020-08-04 | 2023-02-28 | 南京理工大学 | Variable-configuration cube star for simulating space debris and working method thereof |
| CN112623280A (en) * | 2021-01-04 | 2021-04-09 | 上海宇航系统工程研究所 | Two-degree-of-freedom solar cell array unfolding device |
| CN113548201A (en) * | 2021-07-21 | 2021-10-26 | 上海宇航系统工程研究所 | Fan-shaped solar wing repeated unfolding and folding locking mechanism |
| CN113548201B (en) * | 2021-07-21 | 2022-08-05 | 上海宇航系统工程研究所 | Fan-shaped solar wing repeated unfolding and folding locking mechanism |
| CN113568134A (en) * | 2021-08-09 | 2021-10-29 | 吉林大学 | Unfolding mechanism of spatial diffraction primary mirror with heat dissipation and low impact characteristics |
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