CN103466197A - Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm - Google Patents
Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm Download PDFInfo
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- CN103466197A CN103466197A CN2013104463046A CN201310446304A CN103466197A CN 103466197 A CN103466197 A CN 103466197A CN 2013104463046 A CN2013104463046 A CN 2013104463046A CN 201310446304 A CN201310446304 A CN 201310446304A CN 103466197 A CN103466197 A CN 103466197A
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Abstract
The invention discloses a supporting packaging structure oriented to a solar sail adopting an inflatable auxiliary self-rebounding supporting arm. The structure comprises a center body (1), the inflatable supporting arm (2), a supporting arm flange (3), a guide rod (5), a supporting arm guide structure (6), a sail surface (7), a sail surface rolling shaft (8), a supporting structure (9), a sail surface rolling shaft rotating bearing (10), a connecting mechanism (11), an external packaging box body side plate (12), an external packaging box body upper plate (13), an external packaging box body bottom plate (14), an external packaging upper plate unlocking mechanism (15) and an external packaging side plate unfolding mechanism (16). A solar sail spacecraft adopting the inflatable auxiliary self-rebounding supporting arm is specifically designed, and the inflatable auxiliary self-rebounding supporting arm and the flexible sail surface are folded and supported simultaneously. Due to the adoption of the supporting packaging structure, the solar sail spacecraft can be stably and sequentially unfolded by being stressed in only one direction.
Description
Technical field
The present invention relates to a kind of support and packaging structure of solar sail folding and expanding, be particularly useful for adopting taking in of the auxiliary hundred meter level solar sail structures from the back springing type hold-down arm of inflation.
Background technology
Solar sail spacecraft refers to that utilizing solar pressure to obtain propulsive force carries out cosmonautic course of new aircraft, its specific impulse infinity in theory, can continue to accelerate under the effect of sun optical pressure, may ultimately reach traditional spacecraft 5-10 speed doubly, extremely be conducive to carry out survey of deep space.The U.S., Europe, Japan and Russia have all carried out the in-depth study of solar sail Push Technology.
Because Solar sail spacecraft and traditional spacecraft have the difference of internal in configuration, main body only has sail face and two parts of supporting construction of large flexibility, and sail face size maximum reaches hundred meters magnitudes.So in the solar sail technology a very important technology be the structure that how to design sail sail body and supporting construction can compact wiring up while making emission, after entering the orbit in order failure-free launch.Generally should select the packaging scheme consistent with method of deploying, and require packaging volume minimum and inside there is no remaining gas; In the solar sail structure, the expansion of all elements should be controlled, stable and insensitive to defect and little disturbance reaction.Due to the difference of expansion mode, supporting way, sail face folding mode, there is larger difference between individuality between the solar sail individuality of various countries' development.Can divide circle, square, flaabellum shape by sail face shape; For the difference by expansion mode, can be divided into self-rotary expansion, hold-down arm expansion; And can be divided into from forms such as back springing type, extensible truss-likes according to the form of hold-down arm.Every kind of form all according to separately specifically the mode of taking in design and be supported in accordingly packaging structure.
For example Japanese IKAROS solar sail is that self-rotary launches, the sail face by after folding on centrosome, end is furnished with mass, driving the sail face by mass in spin launches to reach stable gradually, there do not is complicated container structure, only need centrosome and external packing structure to get final product, with the Solar sail spacecraft version that adopts the hold-down arm form, there is the difference of internal.And no matter the Solar sail spacecraft of hold-down arm form is from back springing type or expanded truss formula, after being hold-down arm compression being taken in, end points is protruding, drives the pattern that the sail face launches.Although adopt the auxiliary hundred meter level solar sail from the back springing type hold-down arm of inflation to belong to the hold-down arm expansion equation, but because size reaches hundred meter levels, so adopt the inflation supplementary structure on the basis from the back springing type hold-down arm, cause hold-down arm to take in the difference that form and other forms have internal.For example U.S. NANO-D Sail solar sail adopts from the resilience hold-down arm, and hold-down arm is rotated and takes in around central support shaft, and the sail face is accommodated on the accommodating mechanism coaxial with hold-down arm.Order about the hold-down arm end points by screen resilience and outwards stretch, the sail face launches in company with hold-down arm, the hold-down arm end points straight-line motion that substantially be non-leap year in consistent with sail face end points mode of motion, and accommodating mechanism is very compact simple.There is inflatable structure and inflation is auxiliary from the back springing type hold-down arm, need inflatable appliance, can only adopt root to fix, the mode that containing section outwards ejects, hold-down arm and sail face mode of motion are inharmonious.And size reaches hundred meters magnitude rear support arm sizes and folding sail face size differs larger, a series of difficult points of taking in expansion that can bring thus.
Due to the constraint of hold-down arm form, and the constraint that brings of huge size, be not directed to the auxiliary supporting package structure from the back springing type Solar sail spacecraft of inflation at present.Because interindividual variation is larger, it is auxiliary from the back springing type Solar sail spacecraft that the supporting package structure of Solar sail spacecraft can't be applicable to hundred meter level inflations in the past.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of towards adopting the auxiliary supporting package structure from back springing type hold-down arm solar sail of inflation.
Technical solution of the present invention is: towards adopting the auxiliary supporting package structure from back springing type hold-down arm solar sail of inflation to comprise centrosome, inflatable hold-down arm, hold-down arm flange, pilot bar, hold-down arm guide frame, sail face, sail face spool, supporting construction, sail face spool rolling bearing, bindiny mechanism, external packing box side plate, external packing box body upper plate, external packing box body base plate, external packing upper plate release mechanism, external packing side plate development mechanism.
The supporting construction that centrosome is total, external packing box body upper plate and external packing box body base plate are arranged on respectively two end faces up and down of centrosome, the side of centrosome is by circumferential symmetrical four the inflatable hold-down arms of installing of hold-down arm flange, each inflatable hold-down arm be take pilot bar as core to curls inward from outer point respectively, until the hold-down arm volume extremely contacts with centrosome, the inflatable hold-down arm is by being arranged on the gas filled device inflation of centrosome inside; Quadruplet hold-down arm guide frame is separately fixed at the side of centrosome, and provides guide path for pilot bar; The sail face is accommodated on sail face spool, and is fixed on centrosome by supporting construction, between sail face spool and supporting construction, rolling bearing is installed, and the outer end points of sail face adopts bindiny mechanism to be connected with the pilot bar end points; One side of external packing box side plate is connected on external packing box body base plate by external packing side plate development mechanism, and opposite side is connected with external packing box body upper plate by external packing upper plate release mechanism.
Described bindiny mechanism is the universal spherical hinge.
The present invention compared with prior art beneficial effect is:
(1) for adopting, inflation is auxiliary has carried out the specific aim design from back springing type hold-down arm Solar sail spacecraft in the present invention, when having realized adopting the auxiliary hold-down arm from back springing type of inflation and flexible sail face, takes in and supports.
(2) the supporting package structure in the present invention has guaranteed that Solar sail spacecraft only needs the stressed expansion that can complete steady ordered of single direction.
(3) the present invention is compressed to hundred meter level Solar sail spacecrafts in 5 cubic meters, has greatly reduced the volume of taking in of Solar sail spacecraft, has improved the degree of utilization of packaging structure, meets launch requirements.
(4) the invention solves the auxiliary inharmonious rotation with sail face synchronous expansion time the from the back springing type hold-down arm of inflation.
The accompanying drawing explanation
Fig. 1 is solar sail integrated support packaging structure schematic diagram of the present invention;
Fig. 2,3 takes in supporting construction birds-eye view and front view for topsail face of the present invention;
Fig. 4 is hold-down arm guide frame schematic diagram in the present invention;
Bindiny mechanism's schematic diagram that Fig. 5 is hold-down arm pilot bar and sail face outer end in the present invention;
Fig. 6 is schematic three dimensional views of the present invention;
Fig. 7 is release mechanism schematic diagram of the present invention;
Fig. 8 is external packing side plate development mechanism schematic diagram of the present invention.
The specific embodiment
Referring to accompanying drawing, developing simultaneously, the present invention is described in more detail for embodiment.
The present invention is fully for adopting the auxiliary Solar sail spacecraft from the back springing type hold-down arm of inflation, as shown in Fig. 1～6, comprise: centrosome 1, inflatable hold-down arm 2, hold-down arm flange 3, pilot bar 5, hold-down arm guide frame 6, sail face 7, sail face spool 8, sail face spool supporting construction 9, sail face spool rolling bearing 10, bindiny mechanism 11, external packing box side plate 12, external packing box body upper plate 13, external packing box body base plate 14, external packing upper plate release mechanism 15, external packing side plate development mechanism 16.
The main force support structure that centrosome 1 is whole supporting package structure, for whole packaging structure and all parts provide a supporting role.
External packing box body upper plate 13 and external packing box body base plate 14 are arranged on respectively two end faces up and down of centrosome 1, and the side of centrosome 1 is by circumferential symmetrical four the inflatable hold-down arms 2 of installing of hold-down arm flange 3.Gas filled device is taken in centrosome supporting construction 1 inside, is 2 inflations of inflatable hold-down arm.
The outermost end of inflatable hold-down arm 2 seals by outer end cap, pilot bar 5 is fixed on the outer end cap outside by mounting structure, each inflatable hold-down arm 2 be take respectively pilot bar 5 as core to curls inward, until hold-down arm 2 volumes extremely contact with centrosome 1, the root of inflatable hold-down arm 2 and centrosome 1 side are fixed; Quadruplet hold-down arm guide frame 6 is separately fixed at the side of centrosome 1, (supplement the description to guide frame 6 structures, describe concept and the guide groove that embodies both sides by structure, and the word of the end of learning to write by tracing over characters printed in red below inciting somebody to action is in passing revised and replenished herein);
One side of external packing box side plate 12 is connected on external packing box body base plate 14 by external packing side plate development mechanism 16, and opposite side is connected with external packing box body upper plate 13 by external packing upper plate release mechanism 15.External packing box side plate 12, external packing box body upper plate 13,14 pairs of totals of external packing box body base plate play the effect of packing protection.External packing upper plate release mechanism 15 adopts based on the SMA(marmem) the control that external packing is launched of small-sized quick release device.As shown in Figure 7, comprise SMA silk 162, spring 163, slide block 164, shell 165, snap close 167 and bolt 168; The SMA silk is connected shell 165 with slide block 164, wherein be separated with spring 163 and keep relative position.Slide block 164 and the mutual fastening of snap close 167.Snap close 167 is fixed on side plate 12 by bolt 168.When control system is sent unlock command, energising is shunk SMA silk 162, and band movable slider 164 moves, and the releasing that is connected of slide block 164 and side plate 12 realizes separating of side plate and upper plate, reaches the release purpose.16 employings of external packing side plate development mechanism can independently launch structure from springback hinge after release.As shown in Figure 8, adopt the restoring force of spring that side plate is launched voluntarily, also the mechanism such as available other reeds replaces herein.
At first describe and take in process: hold-down arm 2 is fixed on centrosome supporting construction 1 by hold-down arm flange 3.Each inflatable hold-down arm 2 take respectively pilot bar 5 as core to centrosome 1 direction roll, taking in direction is that pilot bar 5 is taken in to center with Packaging box body base plate 14 is parallel.After forming the hold-down arm roller and being involved in the Packaging box body scope, pilot bar 5 will enter hold-down arm guide frame 6, and volume is to after centrosome contact, and hold-down arm guide frame 6 plays the effect hold-down arm integral body that limits the position, left and right and enters fixed position.Sail face 7 is carried out after zigzag folds twisting on sail face spool 8, spool 8 is by the rotation with realizing spool being connected of rolling bearing 10, rolling bearing 10 is fixed on centrosome 1 by sail face spool supporting construction 9 again, realizes taking in, supporting and fixing sail face 7.After hold-down arm 2 and sail face 7 are fixing, utilize bindiny mechanism 11 to realize the cooperative motion of hold-down arm 2 and sail face 7 pilot bar 5 ends and sail face 7 ends.Then overcome restoring force by external packing side plate development mechanism after 16 reverse closing up, by the external packing upper plate based on the SMA(marmem) 15 fastenings of small-sized quick release device release mechanism, so far the process of taking in completes.
Expansion process: at first external packing upper plate release mechanism 15 actions, 8 side plates 12 break away from upper plate simultaneously.Now the side plate development mechanism 16, and the restoring force of take launches 8 side plates as driving.After side plate launches fully, the inflatable structure of centrosome 1 inside starts, with stable pressure and flow, hold-down arm 2 is started to inflation, makes it the expansion of steady ordered.Along with hold-down arm 2 starts to launch, pilot bar 5 moves along the guiding direction in hold-down arm guide frame 6, to avoid other sensors and load on hold-down arm and other spacecrafts to interfere to some extent, guide frame 6 launches guide support arm 2 until the hold-down arm roller breaks away from the packaging structure main body.Along with the outside expansion of hold-down arm 2, sail face 7 is driven simultaneously and launches.Sail face spool 8 is under the drive of sail face, and the rotation by rolling bearing 10 realizes pulling out, launching of sail face.But because pilot bar 5 has rotation alongst, and sail face end points is plane motion, two parts motion can't be mated, now the bindiny mechanism 11 of hold-down arm pilot bar and sail face outer end plays a role, universal bearing has been eliminated two-part relative motion, makes hold-down arm 2 can drive the expansion of sail face 7 steady ordereds
After launching fully, inflatable appliance maintains the stable gas pressure in hold-down arm 2, guarantees its rigidity of structure.The Packaging box body side plate 12 and the base plate 14 that launch are provided with solar panel, and after the Solar sail spacecraft external packing structure launches fully, solar panel starts working as supplementary powers such as sensor, load.
What by the supporting package structure in above-mentioned flow process the present invention, make Solar sail spacecraft takes in, supports, packs, launches to be able to good running.Guaranteed the reasonable Arrangement under carrying capacity requires, minimum is taken in ratio, and makes hold-down arm 2 and sail face 7 be able to stable expansion in order by supplementary structure and mechanism, at track, carries out normally work.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. towards adopting the auxiliary supporting package structure from back springing type hold-down arm solar sail of inflation, it is characterized in that: comprise centrosome (1), inflatable hold-down arm (2), hold-down arm flange (3), pilot bar (5), hold-down arm guide frame (6), sail face (7), sail face spool (8), supporting construction (9), sail face spool rolling bearing (10), bindiny mechanism (11), external packing box side plate (12), external packing box body upper plate (13), external packing box body base plate (14), external packing upper plate release mechanism (15), external packing side plate development mechanism (16),
The supporting construction that centrosome (1) is total, external packing box body upper plate (13) and external packing box body base plate (14) are arranged on respectively two end faces up and down of centrosome (1), the side of centrosome (1) is by circumferential symmetrical four the inflatable hold-down arms (2) of installing of hold-down arm flange (3), each inflatable hold-down arm (2) be take pilot bar (5) as core to curls inward from outer point respectively, until hold-down arm (2) volume extremely contacts with centrosome (1), inflatable hold-down arm (2) is by being arranged on the inner gas filled device inflation of centrosome (1); Quadruplet hold-down arm guide frame (6) is separately fixed at the side of centrosome (1), and provides guide path for pilot bar (5); Sail face (7) is accommodated on sail face spool (8), and be fixed on centrosome (1) by supporting construction (9), between sail face spool (8) and supporting construction (9), rolling bearing (10) is installed, the outer end points of sail face (7) adopts bindiny mechanism (11) to be connected with pilot bar (5) end points; It is upper that one side of external packing box side plate (12) is connected to external packing box body base plate (14) by external packing side plate development mechanism (16), and opposite side is connected with external packing box body upper plate (13) by external packing upper plate release mechanism (15).
2. according to claim 1 towards adopting the auxiliary supporting package structure from back springing type hold-down arm solar sail of inflation, it is characterized in that: described bindiny mechanism (11) is the universal spherical hinge.
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| CN201310446304.6A CN103466197B (en) | 2013-09-26 | 2013-09-26 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
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Cited By (8)
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| CN103863580A (en) * | 2014-03-10 | 2014-06-18 | 中国空间技术研究院 | Folding method applicable to sail surfaces of blocked square support rod type solar sails |
| CN104002994A (en) * | 2014-05-16 | 2014-08-27 | 中国科学院空间科学与应用研究中心 | Sliding block executing mechanism used for attitude control over solar sail spacecraft |
| CN104058105A (en) * | 2014-06-24 | 2014-09-24 | 中国空间技术研究院 | Deep space solar sail spacecraft driven by utilizing sunlight pressure |
| CN105711857A (en) * | 2016-04-28 | 2016-06-29 | 兰州空间技术物理研究所 | Membrane aerospace craft deploying and locking mechanism |
| CN105857643A (en) * | 2016-04-01 | 2016-08-17 | 上海微小卫星工程中心 | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing |
| CN106809407A (en) * | 2016-12-28 | 2017-06-09 | 中国电子科技集团公司第十八研究所 | On-orbit flexible solar cell array unfolding device for spacecraft |
| 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 |
| CN113401367A (en) * | 2021-06-28 | 2021-09-17 | 南京理工大学 | Expansion device of micro-nano satellite solar sail propulsion system |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863580A (en) * | 2014-03-10 | 2014-06-18 | 中国空间技术研究院 | Folding method applicable to sail surfaces of blocked square support rod type solar sails |
| CN103863580B (en) * | 2014-03-10 | 2016-06-29 | 中国空间技术研究院 | A kind of method for folding being suitable to piecemeal quadrate support rod-type solar sail sail face |
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| 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 |
| CN105857643A (en) * | 2016-04-01 | 2016-08-17 | 上海微小卫星工程中心 | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing |
| CN105857643B (en) * | 2016-04-01 | 2018-05-25 | 中国科学院上海微系统与信息技术研究所 | The flexible solar wing of power satellite and the two degrees of freedom storage device applied to the flexibility solar wing |
| CN105711857A (en) * | 2016-04-28 | 2016-06-29 | 兰州空间技术物理研究所 | Membrane aerospace craft deploying and locking mechanism |
| CN106809407A (en) * | 2016-12-28 | 2017-06-09 | 中国电子科技集团公司第十八研究所 | On-orbit flexible solar cell array unfolding device for spacecraft |
| CN106809407B (en) * | 2016-12-28 | 2019-05-07 | 中国电子科技集团公司第十八研究所 | On-orbit flexible solar cell array unfolding device for spacecraft |
| CN113401367A (en) * | 2021-06-28 | 2021-09-17 | 南京理工大学 | Expansion device of micro-nano satellite solar sail propulsion system |
| CN113401367B (en) * | 2021-06-28 | 2022-03-18 | 南京理工大学 | Expansion device of micro-nano satellite solar sail propulsion system |
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