CN105197259B - Turnover type solar panel capable of unfolding towards light directionally - Google Patents
Turnover type solar panel capable of unfolding towards light directionally Download PDFInfo
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- CN105197259B CN105197259B CN201510692530.1A CN201510692530A CN105197259B CN 105197259 B CN105197259 B CN 105197259B CN 201510692530 A CN201510692530 A CN 201510692530A CN 105197259 B CN105197259 B CN 105197259B
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- solar panel
- transmission shaft
- satellite
- solar energy
- power transmission
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Abstract
The invention particularly relates to a turnover type solar panel capable of unfolding towards light directionally and solves the problems that the stability of the satellite is influenced, the working life is shortened and the solar panel is easy to damage because the conventional solar panel is unreasonable in structure. Grooves are formed in lateral edges of a satellite body; a solar panel body is arranged in each groove; a torsion spring is arranged between each solar panel body and the satellite body; each solar panel body comprises a strip-shaped frame; transmission shafts are arranged in each strip-shaped frame; memory alloy is arranged at the two ends of each transmission shaft; solar cell substrates are connected onto the memory alloy; a driving wheel is arranged on each transmission shaft; a driving belt is wound on the driving wheels; a driving motor is arranged in each strip-shaped frame; a worm and gear mechanism is arranged between the output shaft of each driving motor and the corresponding transmission shaft at any of the left end and the right end. According to the invention, the problem of failure of the whole solar panel because partial parts are damaged is avoided; meanwhile, the unfolding process is more stable.
Description
Technical field
The present invention relates to microsatellite is powered uses solar energy sailboard, specially a kind of orientation launches convertible solar energy to light
Windsurfing.
Background technology
The microsatellite developed both at home and abroad at present is placed directly against setting for microsatellite surface using solar panel mostly
Meter mode.Although this design reduces microsatellite volume and quality, but occupies microsatellite major part celestial body table
Area, limits the lift-launch amount of microsatellite payload, and the orientation of solar panel can not be realized to light action.Cause
This, for microsatellite, while ensureing that compact conformation, lightweight, solar energy sailboard provide sufficient electrical energy, carries more
Many payload simultaneously realize a more multi-functional importance for being to study microsatellite.
Conventional solar energy sailboard structure often has that span is big, rigidity is low, structural damping is weak, coupling stiffness is more low between plate
Feature, any one small disturbance all easily evoke structural vibration.However, satellite is in running, various interference factors
Unavoidably, the such as external disturbance such as space junk, solar wind, heat radiation, temperature shock, and satellite posture adjustment, become rail, control
The internal disturbance of the generations such as the limit cycles oscillations of system, the motion of spacecraft internal mechanism.There is no atmospheric damping in vacuum environment,
Said external is disturbed or internal disturbance is once excited, it will be difficult to carry out self decay, dangerous self-evident, gently then affects to defend
The attitude stability of star, shortens working life；Heavy then directly damage solar energy sailboard mechanism, mechanism once faces global failure,
Will be unable to continue as celestial body offer electric energy, satellite also will be unable to normal operation.
When traditional solar energy sailboard launches, more using torsionspring come produces driving force square, during expansion, the moment of resistance
Gradually increase with angle change, but driving moment is but reduced therewith, in order to ensure entirely to launch process, certain power need to be left
Square nargin, this remaining kinetic energy for allowing for launching to end have no alternative but be converted into mechanism's locking impact load, endanger more serious.
The content of the invention
The present invention affects satellite stability, shortens work to solve existing solar energy sailboard as unreasonable structure is present
Life-span and the problem of fragile solar energy sailboard, there is provided a kind of compact conformation, it is lightweight, can realize orient to light, save
Satellite table area and remain able to be continued the orientation of power supply by other solar battery sheets after part solar battery sheet is damaged
Convertible solar energy sailboard is launched to light.
The present invention adopts the following technical scheme that realization：Orientation launches convertible solar energy sailboard to light, including rectangular
Body shape satellite body, is provided with groove, is provided with and is hinged and leads to satellite body in each groove at the incline of satellite body
The solar energy sailboard body of blasting bolt connection is crossed, between solar energy sailboard body and satellite body, torsionspring is provided with；Too
Positive energy windsurfing body includes strip framework, the transmission for some being provided with strip framework through its front-rear side walls and being parallel to each other
Axle, the two ends of power transmission shaft are provided with the memorial alloy being hinged with which, and solar cell substrate is respectively connected with memorial alloy, pass
Drive is provided with moving axis, the driving belt being close to which on drive, is wound with, motor in strip framework, is provided with,
The worm-and-wheel gear being connected with both is provided between the power transmission shaft of the output shaft and left and right either end of motor.
When satellite reaches predetermined work track, control system lights blasting bolt, and four solar energy sailboard bodies are being reversed
Under Spring driving, eject from satellite body；After solar energy sailboard body is ejected completely, control system excites memorial alloy, makes
Solar cell substrate launches, and after solar cell substrate is deployed into specified location, the control system in satellite main body sends
Instruction, starts motor, and power transmission shaft drives drive and driving belt to rotate, and then drives each power transmission shaft and solar cell substrate
Rotate；Most intense light irradiation is sensed control of the angle feed-back to inside satellite by sensing by the optical sensor on solar cell substrate
System processed, then the motor rotations for reaching that this angle needs are calculated by control system, output signal controlled motor is rotated, by transmission
The each solar cell substrate of belt drive is rotated, and realizes that the orientation of solar cell substrate is adjusted to light, so that solar-electricity
Pond substrate receives maximum illuminating area, improves illumination utilization rate, overcomes existing solar energy sailboard as unreasonable structure is present
Affect satellite stability, shorten the problem of working life and fragile solar energy sailboard.
The end of power transmission shaft is installed with bearing pin, and memorial alloy is installed with bearing pin, and the bottom side of memorial alloy is tied for arc-shaped
Structure, and it is close to strip framework side wall.
It is excessive in order to prevent cell panel from launching, when solar cell substrate turns to memorial alloy base plane and strip frame
After frame side wall is close to, memorial alloy is realized spacing.
Present configuration reliability reasonable in design, small volume, light weight are placed in satellite body, save celestial body surface area, so as to
Seeds of First Post-flight more multi-load, make satellite realize more functions, and the structure of multi-disc solar cell substrate, it is to avoid the sun
Energy cell substrates are because of external interferences such as space junk, solar winds so that mechanism is only because a part of parts damages are but caused entirely too
The problem of positive energy windsurfing paralysis；Simultaneously to launch process more steady for solar energy sailboard, it is to avoid the problem of greater impact load.
Description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of solar energy sailboard body in Fig. 1；
Fig. 3 is the structural representation at memorial alloy in Fig. 1.
In figure：1- satellite bodies, 2- grooves, 3- solar energy sailboard bodies, 4- strip frameworks, 5- power transmission shafts, 6- memories are closed
Gold, 7- solar cell substrates, 8- drives, 9- driving belts, 10- motors, 11- worm-and-wheel gears, 12- bearing pins.
Specific embodiment
Orientation launches convertible solar energy sailboard, including rectangular-shape satellite body 1 to light, at the incline of satellite body 1
Groove 2 is provided with, and the solar energy sailboard for being hinged with satellite body 1 and being connected by blasting bolt is provided with each groove 2
Body 3, is provided with torsionspring between solar energy sailboard body 3 and satellite body 1；Solar energy sailboard body 3 includes strip frame
Frame 4, the power transmission shaft 5 for some being provided with strip framework 4 through its front-rear side walls and being parallel to each other, the two ends of power transmission shaft 5 are equal
The memorial alloy 6 being hinged with which is provided with, solar cell substrate 7 is respectively connected with memorial alloy 6, is respectively provided with power transmission shaft 5
There is drive 8, the driving belt 9 being close to which is wound with drive 8, motor 10 in strip framework 4, is provided with, electricity is driven
The worm-and-wheel gear 11 being connected with both is provided between the power transmission shaft 5 of the output shaft and left and right either end of machine 10.
The end of power transmission shaft 5 is installed with bearing pin 12, and memorial alloy 6 is installed with bearing pin 12, and the bottom side of memorial alloy 6 is circle
Arc structure, and it is close to strip framework side wall.
In specific implementation process, the size of satellite body 1 is 320mm × 320mm × 700mm；Memorial alloy 6 is super-elasticity
Ultimum Ti.
Claims (1)
1. a kind of orientation launches convertible solar energy sailboard to light, it is characterised in that：Including rectangular-shape satellite body（1）, defend
Star body（1）Incline at be provided with groove（2）, each groove（2）Inside it is provided with and satellite body（1）It is hinged and by quick-fried
Fry bolted solar energy sailboard body（3）, solar energy sailboard body（3）With satellite body（1）Between be provided with torsion bullet
Spring；Solar energy sailboard body（3）Including strip framework（4）, strip framework（4）Some are inside provided with through its front-rear side walls and
The power transmission shaft being parallel to each other（5）, power transmission shaft（5）Two ends be provided with the memorial alloy being hinged with which（6）, memorial alloy（6）
On be respectively connected with solar cell substrate（7）, power transmission shaft（5）On be provided with drive（8）, drive（8）On be wound with and which
The driving belt being close to（9）, strip framework（4）Motor is provided with inside（10）, motor（10）Output shaft with left and right
The power transmission shaft of either end（5）Between be provided with the worm-and-wheel gear being connected with both（11）, power transmission shaft（5）End be installed with pin
Axle（12）, bearing pin（12）On be installed with memorial alloy（6）, memorial alloy（6）Bottom side be convex structure, and be close to strip
Frame side wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510692530.1A CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510692530.1A CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105197259A CN105197259A (en) | 2015-12-30 |
| CN105197259B true CN105197259B (en) | 2017-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510692530.1A Expired - Fee Related CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742084B (en) * | 2016-11-23 | 2019-08-02 | 上海卫星工程研究所 | A kind of eight prism support devices uniformly installed suitable for 15 antennas |
| CN107954005B (en) * | 2017-12-21 | 2024-01-30 | 星际漫步（北京）航天科技有限公司 | Expansion mechanism and expansion method for telescopic solar cell sailboard |
| CN109484673B (en) * | 2018-12-24 | 2022-04-22 | 深圳航天东方红海特卫星有限公司 | Load platform separated remote sensing micro satellite configuration and assembly method thereof |
| CN110641741B (en) * | 2019-10-23 | 2020-12-18 | 北京国电高科科技有限公司 | Double-freedom-degree solar panel control method and control system thereof |
| CN117154372B (en) * | 2023-10-31 | 2024-01-02 | 银河航天科技(南通)有限公司 | Satellite turns over board expansion device with angle modulation |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19728844C2 (en) * | 1997-07-05 | 1999-04-15 | Daimler Benz Aerospace Ag | Gearbox for moving panels provided with solar cells on a spacecraft |
| CN2815880Y (en) * | 2005-06-01 | 2006-09-13 | 梁锡昌 | Solar-cell sailboard straightening and positioning mechanism |
| CN100585194C (en) * | 2008-09-19 | 2010-01-27 | 航天东方红卫星有限公司 | Automatic locking device for movable support rod memory alloy |
| CN102324438B (en) * | 2011-08-18 | 2013-01-23 | 哈尔滨工业大学 | Inflation expansion truss solar panel array capable of on-orbit assembling |
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| CN105197259A (en) | 2015-12-30 |
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Granted publication date: 20170412 Termination date: 20171023 |