CN103662101B - Solar wing device is drawn in a kind of repeatedly expansion of applicable lunar surface environment in - Google Patents
Solar wing device is drawn in a kind of repeatedly expansion of applicable lunar surface environment in Download PDFInfo
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- CN103662101B CN103662101B CN201310583734.2A CN201310583734A CN103662101B CN 103662101 B CN103662101 B CN 103662101B CN 201310583734 A CN201310583734 A CN 201310583734A CN 103662101 B CN103662101 B CN 103662101B
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Abstract
Solar wing device is drawn in the repeatedly expansion that the invention discloses a kind of applicable lunar surface environment in, comprising: rover structure; + Y the wing cell panel of the coated multilayer insulation assembly in the back side, it is connected in rover structure by+Y a wing driver train and+Y a wing compensation mechanism;-Y wing cell panel, it launches lockout mechanism by one and is connected to rover structure; Compressing releasing mechanism, for when drawing transmitting in, respectively+Y wing cell panel and-Y wing cell panel being pressed in rover structure; Integrated electronics mechanism, compresses releasing mechanism by detonating and unlocks to-Y wing cell panel, and can control+Y wing driver train and can realize Direct to the sun respectively to drive+Y wing cell panel to open to, block the angle that the sun and moonlit night be incubated.Solar wing device of the present invention can realize repeatedly launching, drawing operation in, can realize Direct to the sun, block the lunar surface environment multiple-task such as the sun and moonlit night insulation, applying flexible, powerful.
Description
Technical field
Solar wing device is drawn in the repeatedly expansion that the invention discloses a kind of applicable lunar surface environment in, can realize multitask demand.
Background technology
At present, known domestic spacecraft solar wing spreading is mostly the scheme adopting same expansion direction, disposable continuous spreading.If current version FY-3, DFH-3 etc. are all the power relying on operating spring in hinge, disposable for the cell panel assigned position that is deployed into, then rely on blocking device in hinge that cell panel is fixed on assigned position.The solar wing of this form is no matter from the degree of ripeness of designing technique, or the application of model is all good, but for needing repeatedly to launch, drawing in and the solar wing of particular job pattern such as multi-functional demand, its weak point is mainly manifested in:
A. solar wing function ratio is more single;
B. solar wing spreading is uncontrollable, can not carry out inverse operation under error conditions and repeatedly launch, draws operation in, the precision requirement that also out of reach is higher of control.
Do not find explanation or the report of technology similar to the present invention at present, not yet collect similar data both at home and abroad yet.
Summary of the invention
Cannot realize repeatedly moving to solve existing spacecraft solar wing, inverse operation can not be carried out under error conditions or repeatedly launch, draw the problems such as operation in, and the satisfied moon face multifunctional demand, realization can Direct to the sun, block the function such as the sun and moonlit night insulation, the invention provides a kind of repeatedly expansion being applicable to lunar surface environment and draw solar wing device in, this device is utilized repeatedly to launch and to draw solar wing in, and Direct to the sun can be realized, block the sun and moonlit night heat insulation function, meet the demand of multitask.
In order to reach foregoing invention object, the technical solution adopted in the present invention is:
A solar wing device is drawn in the repeatedly expansion being applicable to lunar surface environment in, comprising:
Rover structure;
+ Y wing cell panel, should be connected in described rover structure by+Y a wing driver train and+Y a wing compensation mechanism by+Y wing cell panel, cell piece be pasted in described+Y wing cell panel front, the coated multilayer insulation assembly in the back side;
-Y wing cell panel, it launches lockout mechanism by one and is connected to described rover structure, and cell piece is pasted in described-Y wing cell panel front;
Compressing releasing mechanism, for when drawing transmitting in, respectively+Y wing cell panel and-Y wing cell panel being pressed in described rover structure;
Integrated electronics mechanism, by detonating, described compression releasing mechanism unlocks to-Y wing cell panel, make its disposable expansion and lock, and can control+Y wing driver train can realize Direct to the sun respectively to drive+Y wing cell panel to open to, block the sun and the moonlit night insulation angle.-Y wing cell panel expanded angle can be 190 °.
In the preferred embodiment of the present invention, described compression releasing mechanism forms primarily of compressor arm, base and cutter, cut off described compressor arm by described cutter and realize described-Y wing cell panel unlocking function, by being extracted from the hold-down apertures of described+Y wing cell panel by compressor arm, described+Y wing cell panel can normally be opened.
In the preferred embodiment of the present invention, one end of described+Y wing driver train and described+Y wing compensation mechanism is separately fixed in described rover structure, and the other end is connected with described+Y wing cell panel respectively; Described expansion lockout mechanism one end is fixed in described rover structure, and the other end is connected with described-Y wing cell panel; Described+Y wing driver train is formed primarily of stepping motor, planetary reduction gear, harmonic speed reducer, magslip and seal ring; Described+Y wing compensation mechanism is formed primarily of centre drawer hinge bracket, centre drawer hinge, bearing and seal ring; Described expansion lockout mechanism is formed primarily of centre drawer hinge bracket, centre drawer hinge, bearing and plane scroll spring.
Above-mentioned repeatedly expansion drew solar wing device in before solar wing is opened, by compressing releasing mechanism ,+Y wing cell panel and the series connection of-Y wing cell panel are compressed, cut off compressor arm when solar wing is opened by cutter and discharge solar wing,-Y wing cell panel launches to put in place under the effect launching lockout mechanism, compressor arm is extracted from+Y wing cell panel hold-down apertures simultaneously, avoid the work affecting+Y wing cell panel; Thereafter the development rate that sends according to integrated electronics mechanism of+Y wing driver train and angle command, under the cooperation of+Y wing compensation mechanism, drive+Y wing cell panel to produce with the speed of regulation launch or draw action in, realize Direct to the sun, after+Y wing cell panel moves to the angle position of specifying, keep motionless.When needs block the sun or moonlit night insulation ,+Y wing cell panel moves to the position of specifying and carries out sunshade or insulation by the multilayer insulation assembly at its back side according to the angle command that integrated electronics mechanism sends.
Compared with prior art, the present invention has following beneficial effect:
Solar wing device is drawn in a kind of repeatedly expansion being applicable to lunar surface environment of the present invention in, owing to taking above-mentioned vibrational power flow technical scheme, make this solar wing device can be applicable to the multitask demand of lunar surface environment, as Direct to the sun, block the sun and moonlit night insulation etc., meet the requirement that lunar surface environment uses, and achieve the object that solar wing repeatedly launches and draw in, there is applying flexible, the advantage such as powerful.
Accompanying drawing explanation
Fig. 1 and Fig. 2 is that solar wing device rounding state side and front schematic view are drawn in a kind of repeatedly expansion being applicable to lunar surface environment of the embodiment of the present invention in;
Fig. 3 and Fig. 4 is that solar wing device deployed condition side and front schematic view are drawn in a kind of repeatedly expansion being applicable to lunar surface environment of the embodiment of the present invention in;
Fig. 5 is a kind of structural representation repeatedly launching to draw in solar wing device+Y wing driver train being applicable to lunar surface environment of the embodiment of the present invention;
Fig. 6 is a kind of structural representation repeatedly launching to draw in solar wing device+Y wing compensation mechanism being applicable to lunar surface environment of the embodiment of the present invention;
Fig. 7 is a kind of structural representation repeatedly launching the expansion lockout mechanism drawing solar wing device in being applicable to lunar surface environment of the embodiment of the present invention;
Fig. 8 is a kind of structural representation repeatedly launching the compression releasing mechanism drawing solar wing device in being applicable to lunar surface environment of the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described.
See Fig. 1, Fig. 2, Fig. 3 and Fig. 4, the repeatedly expansion being applicable to lunar surface environment of the present embodiment is drawn solar wing device in and is comprised:
Rover structure 3;
+ Y wing cell panel 4, cell piece is pasted in its front, the coated multilayer insulation assembly 5 in the back side; Should be connected in rover structure 3 by+Y a wing driver train 1 and+Y a wing compensation mechanism 2 by+Y wing cell panel 4; Specifically in the present embodiment, one end of+Y wing driver train 1 and+Y wing compensation mechanism 2 is separately fixed in rover structure 3, and the other end is connected with+Y wing cell panel 4 respectively; Wherein, + Y wing driver train 1 is formed primarily of stepping motor 11, planetary reduction gear 12, harmonic speed reducer 13, magslip 14 and seal ring 15, its structure is see Fig. 5, + Y wing driver train 1 is fixed in rover structure 3 by a T-shape structure 16, is connected with+Y wing cell panel 4 by a connection structure 17; + Y wing compensation mechanism 2 is formed primarily of centre drawer hinge bracket 21, centre drawer hinge 22, bearing 23 and seal ring 24, and its structure is see Fig. 6, and it is connected with+Y wing cell panel 4 by centre drawer hinge bracket 21, is fixed in rover structure 3 by centre drawer hinge 22;
-Y wing cell panel 7, it launches lockout mechanism 6 by one and is connected to rover structure 3, should paste cell piece in-Y wing cell panel 7 front; Specifically in the present embodiment, launching lockout mechanism 6 one end is fixed in rover structure 3, the other end is connected with-Y wing cell panel 7, particularly, launch lockout mechanism 6 to form primarily of centre drawer hinge bracket 61, centre drawer hinge 62, bearing 63 and plane scroll spring 64, its structure is see Fig. 7, and it is connected with-Y wing cell panel 7 by centre drawer hinge bracket 61, is fixed in rover structure 3 by centre drawer hinge 62;
Compressing releasing mechanism 8, for when drawing transmitting in, respectively+Y wing cell panel 4 and-Y wing cell panel 7 being pressed in rover structure 3; Particularly, compress releasing mechanism 8 to form primarily of compressor arm 10, base 101 and cutter 9, its structure is see Fig. 8, compressor arm 10 is successively through+Y wing cell panel 4 and-Y wing cell panel 7, compressor arm 10 is cut off to realize-Y wing cell panel 7 unlocking function by cutter 9, and by being extracted from the hold-down apertures of+Y wing cell panel 4 by compressor arm 10 ,+Y wing cell panel 4 can normally be opened; Compressing releasing mechanism 8 is fixed in rover structure 3 by base 101;
Integrated electronics mechanism, compress releasing mechanism 8 to unlock to-Y wing cell panel 7 by detonating, make that-Y wing cell panel 7 is disposable to be expanded to 190 ° and to lock, and the angle that+Y wing driver train 1 can realize Direct to the sun respectively to drive+Y wing cell panel 4 to open to, block the sun and moonlit night insulation can be controlled.
Below course of action of the present invention is described:
Above-mentioned repeatedly expansion drew solar wing device in before solar wing is opened, by compressing releasing mechanism 8 ,+Y wing cell panel 4 and-Y wing cell panel 7 are connected compression, when solar wing is opened, integrated electronics mechanism gives and compresses releasing mechanism 8 fuze, cutter 9 is made to cut off compressor arm 10, now-Y wing cell panel 7 launches to put in place under the effect launching lockout mechanism 6, is extracted by compressor arm 10 from+Y wing cell panel 4 hold-down apertures simultaneously, avoids the work affecting+Y wing cell panel 4; Thereafter the development rate that sends according to integrated electronics mechanism of+Y wing driver train 1 and angle command, under the cooperation of+Y wing compensation mechanism 2, drive+Y wing cell panel 4 to produce with the speed of regulation launch or draw action in, realize Direct to the sun, after moving to the angle position of specifying, keep motionless; When needs block the sun or moonlit night insulation, the angle command that+Y wing cell panel 4 sends according to integrated electronics mechanism moves to the position of specifying, and carries out sunshade or insulation by the multilayer insulation assembly 5 at its back side.
As mentioned above, of the present inventionly repeatedly launch to draw in solar wing device and achieve and repeatedly launch, draw motion in, meet lunar surface Direct to the sun, block the multi-functional requirement such as the sun and moonlit night insulation.
The disclosed preferred embodiment of the present invention just sets forth the present invention for helping above.Preferred embodiment does not have all details of detailed descriptionthe, does not limit the detailed description of the invention that this invention is only described yet.Obviously, according to the content of this specification sheets, can make many modifications and variations.This specification sheets is chosen and is specifically described these embodiments, is to explain principle of the present invention and practical application better, thus makes art technical personnel understand well and to utilize the present invention.The present invention is only subject to the restriction of claims and four corner and equivalent.
Claims (4)
1. a solar wing device is drawn in the repeatedly expansion being applicable to lunar surface environment in, it is characterized in that, comprising:
Rover structure;
+ Y wing cell panel, should be connected in described rover structure by+Y a wing driver train and+Y a wing compensation mechanism by+Y wing cell panel, cell piece be pasted in described+Y wing cell panel front, the coated multilayer insulation assembly in the back side;
-Y wing cell panel, it launches lockout mechanism by one and is connected to described rover structure, and cell piece is pasted in described-Y wing cell panel front; Described expansion lockout mechanism one end is fixed in described rover structure, and the other end is connected with described-Y wing cell panel; Described expansion lockout mechanism is formed primarily of centre drawer hinge bracket, centre drawer hinge, bearing and plane scroll spring;
Compressing releasing mechanism, for when drawing transmitting in, respectively+Y wing cell panel and-Y wing cell panel being pressed in described rover structure; Described compression releasing mechanism forms primarily of compressor arm, base and cutter, cut off described compressor arm by described cutter and realize described-Y wing cell panel unlocking function, by being extracted from the hold-down apertures of described+Y wing cell panel by compressor arm, described+Y wing cell panel can normally be opened;
Integrated electronics mechanism, by detonating, described compression releasing mechanism unlocks to-Y wing cell panel, and can control+Y wing driver train and can realize Direct to the sun respectively to drive+Y wing cell panel to open to, block the angle that the sun and moonlit night be incubated.
2. solar wing device is drawn in the repeatedly expansion being applicable to lunar surface environment as claimed in claim 1 in, it is characterized in that, one end of described+Y wing driver train and described+Y wing compensation mechanism is separately fixed in described rover structure, and the other end is connected with described+Y wing cell panel respectively.
3. solar wing device is drawn in the repeatedly expansion being applicable to lunar surface environment as claimed in claim 1 or 2 in, and it is characterized in that, described+Y wing driver train is formed primarily of stepping motor, planetary reduction gear, harmonic speed reducer, magslip and seal ring.
4. solar wing device is drawn in the repeatedly expansion being applicable to lunar surface environment as claimed in claim 1 or 2 in, and it is characterized in that, described+Y wing compensation mechanism is formed primarily of centre drawer hinge bracket, centre drawer hinge, bearing and seal ring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310583734.2A CN103662101B (en) | 2013-11-20 | 2013-11-20 | Solar wing device is drawn in a kind of repeatedly expansion of applicable lunar surface environment in |
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| CN201310583734.2A CN103662101B (en) | 2013-11-20 | 2013-11-20 | Solar wing device is drawn in a kind of repeatedly expansion of applicable lunar surface environment in |
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| CN103662101A CN103662101A (en) | 2014-03-26 |
| CN103662101B true CN103662101B (en) | 2015-11-18 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103939460B (en) * | 2014-04-24 | 2016-03-02 | 哈尔滨工业大学 | A kind of intermittent type spring launches Hinge retarding mechanism |
| CN104154110B (en) * | 2014-08-25 | 2016-09-07 | 哈尔滨工业大学 | A kind of expansion of based on spring and linkage Hinge retarding mechanism |
| CN106927067A (en) * | 2015-12-31 | 2017-07-07 | 中国科学院沈阳自动化研究所 | A kind of solar sail development mechanism |
| CN106628256A (en) * | 2017-01-20 | 2017-05-10 | 银河航天（北京）科技有限公司 | Solar wing device |
| CN106989684B (en) * | 2017-05-19 | 2019-05-28 | 上海宇航***工程研究所 | Splice the non-visual portion structure gap measuring apparatus of antenna and measurement method |
| CN108791963A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Suitable for rotating unit low-power consumption thermal compensation device and method outside star |
| CN109677641A (en) * | 2019-01-17 | 2019-04-26 | 上海卫星工程研究所 | A kind of satellite cooling device that type body dress sun shell is thermally isolated |
| CN109857138B (en) * | 2019-01-28 | 2021-10-01 | 北京卫星环境工程研究所 | Rapid installation and adjustment method based on spacecraft non-reference structure multi-coupling dimension chain mechanism |
| CN111824462B (en) * | 2020-06-04 | 2021-09-03 | 上海宇航***工程研究所 | Secondary unlocking device and method for step-by-step expansion of flexible solar cell array |
| CN112099543B (en) * | 2020-08-14 | 2021-09-21 | 华南理工大学 | Vibration control device and control method for moving two-dimensional multi-unfolding plate |
| CN113247312B (en) * | 2021-07-14 | 2021-10-15 | 北京智星空间技术研究院有限公司 | Unlocking and unfolding structure of cubic star solar sailboard |
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| CN102700728A (en) * | 2012-06-18 | 2012-10-03 | 上海卫星工程研究所 | Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method |
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