CN103482084B - A kind of novel Stretching of solar wings based on banded spring and supporting mechanism - Google Patents
A kind of novel Stretching of solar wings based on banded spring and supporting mechanism Download PDFInfo
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- CN103482084B CN103482084B CN201310384757.0A CN201310384757A CN103482084B CN 103482084 B CN103482084 B CN 103482084B CN 201310384757 A CN201310384757 A CN 201310384757A CN 103482084 B CN103482084 B CN 103482084B
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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Abstract
Belong to based on the novel Stretching of solar wings of banded spring and supporting mechanism the development mechanism field being applied to satellite sun energy cell array, object is to solve the problem that expansion rigidity is low, fundamental frequency is low that prior art exists.The present invention includes solar array, wind spring drives hinge, satellite health, pole hinge, lower fulcrum bar, banded spring and upper rack posts; Solar array and satellite health drive chain connection by wind spring, banded both ends of the spring is connected with upper rack posts and lower fulcrum bar respectively by adaptor, upper rack posts is connected with described solar array by pole hinge, and lower fulcrum bar is connected with described satellite health by pole hinge; Wind spring drives wind spring, described banded spring and described pole hinge in hinge to provide and launches the expansion that moment realizes solar array.The entirety that solar array of the present invention, satellite health and upper rack posts and lower fulcrum bar form forms a tetrahedral stable support structure in space, and elevator system is fundamental frequency and rigidity in the deployed state.
Description
Technical field
The invention belongs to the development mechanism field being applied to satellite sun energy cell array, particularly relate to the novel Stretching of solar wings based on banded spring in one " quick small satellite " and supporting mechanism.
Background technology
Solar energy sailboard development mechanism is one of important subsystem of earth observation from space satellite, and the case that cannot normally work because of development mechanism mechanical breakdown in history reaches tens of example.Therefore, in space satellite engineering, solar energy sailboard development mechanism is the intermediate portions of design, test.
Existing earth observation satellite is that large-scale the pushing away of tradition sweeps class earth observation satellite, the solar energy sailboard development mechanism being applicable to this type of observation satellite utilizes the linkage of the energy-storage travelling wave tube such as wind spring, torsion spring, after satellite launch to planned orbit, the function realize Automatic-expanding, automatically locking.
See the solar energy sailboard development mechanism shown in accompanying drawing 1, comprise solar array 1, wind spring drives hinge 2 and satellite health 3, in outspreading sailboard process, 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 lower problem of outspreading sailboard rigidity in this solar energy sailboard development mechanism.
Various countries fell over each other the new ideas proposing " quick Small Earth observation satellite " in the last few years, because the attitude of " quick small satellite " ceaselessly changes, 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, the requirement of quick Small Earth observation satellite to rigidity and fundamental frequency can not be met, conventional satellite development mechanism part damping ratio is 0.1% ~ 0.5%, damping ratio is lower, therefore need to develop a kind of fundamental frequency that launches high, rigidity is high, the novel outspreading sailboard that damping ratio is high and supporting mechanism.
Summary of the invention
The object of the invention is to the problem that expansion rigidity is low, fundamental frequency is low, damping ratio is low solving prior art existence, propose a kind of novel Stretching of solar wings based on banded spring and supporting mechanism of high stability, meet the operating needs of quick Small Earth observation satellite.
For achieving the above object, a kind of novel Stretching of solar wings based on banded spring of the present invention and supporting mechanism comprises solar array, wind spring drives hinge, satellite health, pole hinge, lower fulcrum bar, banded spring and upper rack posts;
Described solar array and satellite health drive chain connection by wind spring, banded both ends of the spring is connected with described upper rack posts and described lower fulcrum bar respectively by adaptor, described upper rack posts is connected with described solar array by pole hinge, and described lower fulcrum bar is connected with described satellite health by pole hinge; Described wind spring drives wind spring, banded spring and pole hinge in hinge to provide and launches the expansion that moment realizes solar array.
Described banded spring is the curved bend knee-piece of two arranged opposite, realizes the bending or reversed bending 180 ° of forward and can recoil to original shape.
Described banded both ends of the spring to be connected with described upper rack posts and described lower fulcrum bar respectively by adaptor and to be specially: described lower fulcrum bar and described adaptor are sticked together, described banded spring and described adaptor are compressed by two compact heaps and are screwed, and described upper rack posts is identical with the connection mode of lower fulcrum bar and banded spring with the connection mode of banded spring.
Have cushion block between described lower fulcrum bar and pole hinge, can carry out suitable adjusting lever by the thickness adjusting cushion block long, upper rack posts is identical with the connection mode of pole hinge.
Described pole hinge comprises male hinge and female hinge, and described male hinge is cut with scissors by axle, oscillating bearing, back-up ring and described mother and is connected, and realizes male hinge and cuts with scissors rotation around mother, and described public affairs hinge both sides are separately installed with torsion spring.
Good effect of the present invention: a kind of novel Stretching of solar wings based on banded spring of the present invention and the simple banded spring of supporting mechanism principle instead of the complicated linkage easily gone wrong, banded spring serves the linkage effect that can bend 180 °, mechanism element is few, principle is simple, compared to the linkage of dozens of part composition, supporting mechanism is become simple by complexity, and reliability significantly promotes; Be fixed by screws on solar array and satellite health with the pole hinge at two ends, the entirety that solar array, satellite health and upper rack posts and lower fulcrum bar are formed forms a tetrahedral stable support structure in space, and elevator system is fundamental frequency and rigidity in the deployed state; Compared with traditional outspreading sailboard system, instead of cantilever design with 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 generation vibration, plateau can be recovered faster.
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;
Fig. 3 be expansion of the present invention and supporting mechanism structure rounding state time structural representation;
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, satellite health, 4, 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.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the present invention are described further.
See accompanying drawing 2, a kind of novel solar array 1 based on banded spring 6 of the present invention launches with supporting mechanism comprises solar array 1, wind spring drives hinge 2, satellite health 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 health 3 by wind spring, banded spring 6 two ends are connected with described upper rack posts 7 and described lower fulcrum bar 5 respectively by adaptor 9, 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 health 3 by pole hinge 4.
See accompanying drawing 3, solar array 1 described in rounding state of the present invention is parallel with described satellite health 3, described upper rack posts 7 is in folded state with described lower fulcrum bar 5, wind spring drives hinge 2 to rotate 90 °, wind spring is made to be in compressed energy-storage state, pole two ends hinge through 45 °, banded spring 6 bends 180 °, is in compressive state.In expansion process, wind spring drives hinge 2 to provide main expansion moment, and pole hinge 4 and banded spring 6 also have certain additional function, and assisted Extraction is for launching moment.
See accompanying drawing 4, described banded spring 6 is the curved bend knee-piece of two arranged opposite, its principle is similar to metallic tape, can the bending or reversed bending 180 ° of forward can original shape be recoiled to, forward bends required torque much smaller than reversed bending moment of torsion, it is higher that banded spring 6 launches rear bending stiffness, not easily bends.The mechanism of two panels arranged opposite composition, both direction bending stiffness is all higher, as calculated, can meet support stiffness requirement.
See accompanying drawing 5, described banded spring 6 two ends to be connected with described upper rack posts 7 and described lower fulcrum bar 5 respectively by adaptor 9 and to be specially: described lower fulcrum bar 5 is sticked together with described adaptor 9, described banded spring 6 is compressed with described adaptor 9 by two compact heaps 8 and is screwed, and upper rack posts 7 part also connects by same connection mode.
See accompanying drawing 6, have cushion block 13 between described upper rack posts 7 and pole hinge, can carry out suitable adjusting lever by the thickness adjusting cushion block 13 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 cut with scissors 11 by axle, oscillating bearing, back-up ring and described mother and is connected, realize male hinge 10 and cut with scissors 11 rotations around mother, described public affairs hinge 10 both sides are separately installed with torsion spring 12, and its Main Function eliminates oscillating bearing diameter clearance and provides certain expansion moment.
Be more than the specific embodiment of the present invention, but limitation of the present invention absolutely not.
Claims (5)
1., based on novel Stretching of solar wings and the supporting mechanism of banded spring, comprise solar array (1), wind spring drives hinge (2) and satellite health (3), described solar array (1) drives hinge (2) to be connected with satellite health (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 upper rack posts (7) and described lower fulcrum bar (5) respectively by adaptor (9), 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 health (3) by pole hinge (4); Wind spring drives wind spring, described banded spring (6) and described pole hinge (4) in hinge (2) to provide and launches the expansion that moment realizes solar array (1).
2. a kind of novel Stretching of solar wings based on banded spring according to claim 1 and supporting mechanism, it is characterized in that, described banded spring (6) is the curved bend knee-piece of two arranged opposite, realizes the bending or reversed bending 180 ° of forward and can recoil to original shape.
3. a kind of novel Stretching of solar wings based on banded spring according to claim 1 and supporting mechanism, it is characterized in that, described banded spring (6) two ends to be connected with described upper rack posts (7) and described lower fulcrum bar (5) respectively by adaptor (9) and to be specially: described lower fulcrum bar (5) and described adaptor (9) are sticked together, described banded spring (6) and described adaptor (9) are compressed by two compact heaps (8) and are screwed, described upper rack posts (7) is identical with the connection mode of banded spring (6) with lower fulcrum bar (5) with the connection mode of banded spring (6).
4. a kind of novel Stretching of solar wings based on banded spring according to claim 1 and supporting mechanism, it is characterized in that, cushion block (13) is had between described upper rack posts (7) and pole hinge (4), carry out suitable adjusting lever by the thickness of adjustment cushion block (13) long, lower fulcrum bar (5) is identical with the connection mode of pole hinge (4) with identical upper rack posts (7) with the connection mode of pole hinge (4).
5. a kind of novel Stretching of solar wings based on banded spring according to claim 1 and supporting mechanism, it is characterized in that, described pole hinge (4) comprises male hinge (10) and female hinge (11), described male hinge (10) is cut with scissors (11) by axle, oscillating bearing, back-up ring and described mother and is connected, realize male hinge (10) to rotate around mother's hinge (11), described public affairs 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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| 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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| CN103482084A CN103482084A (en) | 2014-01-01 |
| CN103482084B true CN103482084B (en) | 2016-01-13 |
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| 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 |
| CN105539880B (en) * | 2016-01-13 | 2017-10-13 | 广西大学 | A kind of large area can open up solar energy turnover panel |
| CN105836163B (en) * | 2016-04-14 | 2018-03-09 | 北京卫星制造厂 | A kind of boosting-type expanding unit suitable for the connection of flexible dynamic boundary |
| 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 |
| 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 |
| CN110979742B (en) * | 2019-11-29 | 2021-12-07 | 北京卫星制造厂有限公司 | High-expansion-ratio unfolding mechanism suitable for space environment |
| CN111354257B (en) * | 2020-04-02 | 2021-11-30 | 沈阳航空航天大学 | Space solar power station ground experiment platform |
| 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 |
| 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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| CN101850852A (en) * | 2010-05-26 | 2010-10-06 | 中国科学院空间科学与应用研究中心 | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite |
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