CN106394933B - A kind of distributed satellites traction Solar sail spacecraft configuration - Google Patents
A kind of distributed satellites traction Solar sail spacecraft configuration Download PDFInfo
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- CN106394933B CN106394933B CN201610859580.9A CN201610859580A CN106394933B CN 106394933 B CN106394933 B CN 106394933B CN 201610859580 A CN201610859580 A CN 201610859580A CN 106394933 B CN106394933 B CN 106394933B
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- 239000010408 film Substances 0.000 claims abstract description 87
- 239000004973 liquid crystal related substance Substances 0.000 claims abstract description 14
- 239000010409 thin film Substances 0.000 claims abstract description 4
- 238000006243 chemical reaction Methods 0.000 claims abstract description 3
- 230000006641 stabilisation Effects 0.000 claims description 9
- 238000011105 stabilization Methods 0.000 claims description 9
- 238000000926 separation method Methods 0.000 claims description 7
- 108091092878 Microsatellite Proteins 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 230000003287 optical effect Effects 0.000 claims description 4
- 229920003223 poly(pyromellitimide-1,4-diphenyl ether) Polymers 0.000 claims description 4
- 238000002310 reflectometry Methods 0.000 claims description 4
- 238000005269 aluminizing Methods 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 2
- 238000001514 detection method Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000005119 centrifugation Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 102100037799 DNA-binding protein Ikaros Human genes 0.000 description 1
- 101150016712 IKZF1 gene Proteins 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012761 high-performance material Substances 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of distributed satellites to draw Solar sail spacecraft configuration, is made of center spacecraft, distributed satellites and rectangular solar sail sail film.Distributed satellites are connected and fixed with center spacecraft by connecting separator, and distributed satellites are detached by connecting separator with the ejection of center spacecraft, obtain relative velocity, while drawing tether control, realize the pull-out expansion of solar sail sail film.After expanding in place, the active role power of distributed satellites makes system play rotation, and generates the tensile force for keeping solar sail sail film smooth.It is used as distributed payload platform when providing tractive force, in-orbit in-flight offer centrifugal force during expansion, implementing detection mission by multiple distributed satellites.Thin-film solar cells, liquid crystal reflection device are pasted on solar sail sail film；The electric energy of solar cell conversion is stored in power-supply management system, for generating the electric energy needed for satellite borne equipment work and realizing the gesture stability of center spacecraft.
Description
Technical field
The present invention relates to a kind of spacecraft configuations, specifically, being related to a kind of using distributed satellites traction expansion and sharp
The Solar sail spacecraft configuration of sail film tensioning is kept with spin.
Background technology
The large-scale film expansion spacecraft that Solar sail spacecraft is made of the sail film and support construction of large area, its profit
The power for providing flight for spacecraft with reflection optical pressure of the sun on the smooth sail film of large area is one kind not against chemical propulsion
Realize the aircraft of follow-on mission.Compared to conventional aerospace device, Solar sail spacecraft has huge superiority, without consuming combustion
Material, therefore the service life in space is not restricted by limited fuel；Using high performance material, the matter of spacecraft structure itself
Amount is very light, reduces launch mass so that launching costs are lower；The continuous acceleration provided using solar light pressure, through it is long when
Between accelerate, Solar sail spacecraft can be flown with the speed of 93km/s, and speed relies on the most fast spacecraft of rocket propulsion more now
Fast 4~6 times.Currently, Solar sail spacecraft has become the research hotspot of survey of deep space.
In the design of Solar sail spacecraft, one of critical problem is to determine the configuration of suitable Solar sail spacecraft,
Namely in space how deploying solar sail sail film, in flight course keep sail film tensioning and how to carry out the sun
The gesture stability of sail.The sail film expansion mode of existing Solar sail spacecraft can be divided mainly into two types:One is by supporting rod
Traction expansion；One is utilize centrifugal force rotary expansion.
By supporting rod draw expansion sail film principle be using be fixed on the spaceborne cantilever strut in center be unfolded with
It is tensioned sail film, mainly has using inflatable structure, be folded mechanically structure or multistable configuration flexible deformation three kinds of forms of expansion.Support
In bar stretching process, the sail film for drawing Solar sail spacecraft is unfolded；After in place, the rigidity of supporting bar structure itself is utilized
Tight sail film.The typical case of this expansion mode, as the Nanosail-D series and Light-sail series solar sail in the U.S. are navigated
Its device.In general, sail film size is bigger, the bending load that supporting rod is born is bigger, and the additional mass of supporting rod is bigger,
Therefore the program to lightweight, high rigidity, multistable material it is more demanding.Due to that need not rotate, Solar sail spacecraft is general
Using three-axis stabilization scheme.
Principle using centrifugal force rotary expansion sail film is that the centrifugal force caused by spacecraft spin throws the thin of folding away
Film, and keep the position shape after expansion.During expansion, center spacecraft constantly adjusts rotary acceleration, in order to generate enough
Tractive force, generally fix several mass blocks in the outside of sail film.The IKAROS of the typical case of this expansion mode such as Japan
Solar sail spacecraft.Compared to the expansion mode for drawing expansion sail film by supporting bar structure, centrifugal force rotary expansion sail film is utilized
Mainly there are following characteristics:(1) spin centrifugal force can provide the in-plane stiffness of structure, effectively reduce the weight of support construction；(2) no
The limitation of rod structure size supported can theoretically realize the expansion of arbitrary large scale sail film.
The spin expansion spacecraft proposed at present be all using center spacecraft thruster start generate torque make be
System rotates to realize.Since sail film sole mass density is very low, the mass block for relying on sail film end is needed to be led to provide centrifugation
Gravitation and tensile force.When solar sail film, which accumulates, to be increased, system rotary inertia sharply increases, it is desirable that the very big ability of the angular speed of system
Sail film is unfolded, the input torque that center spacecraft provides is required very high.Therefore, the configuration of spin expansion at present it is also difficult to achieve
Application in overlarge area solar sail.
Invention content
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of distributed satellites draw Solar sail spacecraft structure
Type.
The technical solution adopted by the present invention to solve the technical problems is：Distributed satellites draw Solar sail spacecraft structure
Type, including center spacecraft, distributed satellites, connection separator, liquid crystal reflection device, solar cell, solar sail sail film,
Tether, it is characterised in that the center spacecraft is connect with distributed satellites, solar sail sail film by tether, distributed satellites according to
Center spacecraft is symmetrical, and in the same plane, solar sail sail film between center spacecraft and distributed satellites,
The solar sail sail film is rectangular, and is divided into polylith triangular structure according to center spacecraft, pastes film on solar sail sail film
The electric energy of solar cell, liquid crystal reflection device, solar cell conversion is stored in power-supply management system, for running spaceborne set
Electric energy needed for standby work, liquid crystal reflection device realize center space flight by the variation of the reflectivity and transmissivity to sunlight
The gesture stability of device；
When solar sail sail film folds gathering, distributed satellites are connected and fixed with center spacecraft by connecting separator,
Solar sail sail film folds in such a way that star folds；Distributed satellites are by connecting separator ejection and center spacecraft point
From, acquisition relative velocity, while tether control is drawn, realize the pull-out expansion of solar sail sail film；
The distributed satellites are microsatellite, each distributed satellites energy three-axis stabilization, the spacecraft positioning of opposite center
And carry different payload；
The tether, which is drawn by tether controller in distributed satellites, applies tether before solar sail sail film is fully deployed
Resistance reduces the relative separation speed of distributed satellites to zero and tether tensioning is made to reach predetermined tensile force.
The solar sail sail film is polyimide film material of aluminizing, and Kapton is used for reflected sunlight, realizes
Optical pressure promotes.
The distributed satellites are multiple and identical in quality.
Advantageous effect
A kind of distributed satellites proposed by the present invention draw Solar sail spacecraft configuration, utilize the tether control of distributed satellites
System realizes the expansion of solar sail sail film；After expanding in place, system is set to play rotation using the active role power of distributed satellites, and produce
The raw tensile force for keeping solar sail sail film smooth.By multiple distributed microsatellites provided during expansion tractive force,
Rail in-flight provides centrifugal force, implements to be used as distributed payload platform when detection mission, has multifunctionality.
Distributed satellites of the present invention draw Solar sail spacecraft configuration, and the active force that traction expansion mode applies is in solar sail
Sail film edge, deployable large-sized sail film.The initial ejection speed and tether of spacecraft are relied primarily on during traction expansion
Passive friction eceleration need not consume the energy, greatly reduce the weight demands that spacecraft carries fuel.It is long after expanding in place
In time flight course, the holding of sail layer tension is realized using system spinning, is had the characteristics that reliable, stable.Control system
For the effect point of force application of rotation far from system centre, spin control efficiency is higher.The pose adjustment of Solar sail spacecraft passes through control
Liquid crystal reflectors on solar sail sail film processed generate the control moment at opposite center to realize.
Description of the drawings
Below in conjunction with the accompanying drawings with embodiment to a kind of present invention distributed satellites traction Solar sail spacecraft configuration make into
One step is described in detail.
Fig. 1 a are that distributed satellites of the present invention draw schematic diagram before the expansion of Solar sail spacecraft structure.
Fig. 1 b are that distributed satellites of the present invention draw schematic diagram after the expansion of Solar sail spacecraft structure.
Fig. 2 is the solar sail sail film folding mode schematic diagram that distributed satellites of the present invention draw Solar sail spacecraft.
Process schematic is unfolded in Fig. 3 a, Fig. 3 b, the solar sail sail film that Fig. 3 c are the present invention.
Fig. 4 is the solar sail sail film expansion process flow diagram flow chart that distributed satellites of the present invention draw Solar sail spacecraft.
In figure
1. distributed satellites 2. connect 3. center spacecraft of separator, 4. liquid crystal reflection device, 5. solar cell
6. 7. tether of solar sail sail film
Specific implementation mode
The present embodiment is a kind of distributed satellites traction Solar sail spacecraft configuration.
Refering to fig. 1~Fig. 4, the present embodiment distributed satellites draw Solar sail spacecraft configuration, by distributed satellites 1, in
Heart spacecraft 3, solar sail sail film 6 and connection separator 2, liquid crystal reflection device 4, solar cell 5, tether 7 form.Center
Spacecraft 3 is connect with distributed satellites 1, solar sail sail film 6 by tether 7, and distributed satellites 1 symmetrically divide according to center spacecraft 3
Cloth, and in same plane.Distributed satellites 1 are four in the present embodiment, and four distributed satellites 1 are identical in quality；Each
1 energy three-axis stabilization of distributed satellites, opposite center spacecraft 3 position and carry different payload.Solar sail sail film 6 connects
Between center spacecraft 3 and distributed satellites 1；Solar sail sail film 6 is rectangular, and is divided into polylith three according to center spacecraft 3
Angular structure pastes thin-film solar cells 5, liquid crystal reflection device 4, the electric energy that solar cell 5 converts on solar sail sail film 6
It is stored in power-supply management system, for running the electric energy needed for satellite borne equipment work；Liquid crystal reflection device 4 is by sunlight
The gesture stability of center spacecraft 3 is realized in the variation of reflectivity and transmissivity.When solar sail sail film 6 folds gathering, distribution is defended
Star 1 is connected and fixed with center spacecraft 3 by connecting separator 2, and solar sail sail film 6 folds in such a way that star folds；Exhibition
Before opening, whole Space Vehicle System is in three-axis stabilization state without spin.Distributed satellites 1 by connect separator 2 ejection with
Center spacecraft 3 detaches, and obtains relative velocity, while drawing the control of tether 7, and the solar sail sail film 6 being fixed on tether is drawn
Go out expansion.Tether 7 draws to apply tether 7 before solar sail sail film 6 is fully deployed by tether controller in distributed satellites 1 to be hindered
Power reduces the relative separation speed of distributed satellites 1 to zero and tether 7 is made to be tensioned.Under 6 fully unfolded position of solar sail sail film,
Four distributed satellites are located at four vertex of rectangular solar sail sail film 6, are connect with center spacecraft 3 by tether 7.
Spacecraft is in spin states, and four distributed satellites 1 rotate provided centrifugal force around center spacecraft 3 makes entire solar sail
Sail film 6 is in tensioning state.
The course of work
Distributed satellites draw Solar sail spacecraft by carrying four distributed satellites, the center space flight of different payload
Device, rectangular solar sail sail film composition.Four distributed satellites are microsatellite identical in quality, and single quality is in 10kg.Distribution
Formula satellite is made of relative navigation system, attitude control system, payload, thruster, tether, relative navigation system be used for
The positioning of center spacecraft and determine appearance, attitude control system is used for the three-axis attitude stabilization of distributed satellites, and payload is used for
Complete different detection missions；Thruster is used to generate the active force needed for distributed satellites control, and tether is distributed for connecting
Formula satellite, solar sail sail film and center spacecraft.Center spacecraft is controlled by power-supply management system, connection piece-rate system, tether
Device, communication system, autonomous navigation system composition, power-supply system is for storing the electric energy that solar cell is converted, connection separation
Device is used for the fixation and ejection of distributed satellites, and tether controller is fully deployed for distributed satellites traction solar sail sail film
Preceding to apply resistance to tether, to reduce the relative separation speed of distributed satellites to zero and tether is made to be tensioned, communication system is used
In spacecraft and ground communication, autonomous flight of the autonomous navigation system for spacecraft is navigated.Solar sail sail film is more by being divided into
The Kapton composition of aluminizing of block triangle, paste on solar sail sail film thin-film solar cells, liquid crystal reflection device and
Connecting cable.Kapton is used for reflected sunlight, realizes that optical pressure promotes, solar cell is for generating satellite borne equipment work
Electric energy needed for making, liquid crystal reflection device realize the posture of spacecraft by the variation of the reflectivity and transmissivity to sunlight
Control, cable are used to transmit electric energy from solar cell to accumulator.
Four distributed satellites are connect by tether respectively with center spacecraft, and solar sail sail film is defended with tether, distribution
Star and center spacecraft have the connection of distributing point.Before expansion, whole Space Vehicle System is in three-axis stabilization state without spin.Four
Distributed satellites are detached by connecting separator with center spacecraft, are obtained relative velocity, while dragging tether, will be fixed on
Sail film on tether pulls out；Before expanding in place, carries friction drag reduction control design case using tether and is gradually reduced relative separation speed,
And certain tensile force is generated on tether；Tentatively in place after, distributed satellites carry out pose adjustment, establish opposite center space flight
The three-axis stabilization posture of device radially and tangentially applies active force, further tensioning system simultaneously along direction center spacecraft later
Rope, and system is made to play rotation simultaneously.After system is rotated, distributed satellites bring up again break-off for system sail film as staying
It is tensioned required centrifugal force.In flight course, the pose adjustment of solar sail is produced by adjusting the reflectance factor of solar sail sail film
The torque at opposite center is given birth to complete.The adjustment of angular velocity of rotation is completed by the synergistic effect of four distributed satellites.
System does not rotate during expansion, is controlled using the tether of distributed satellites, realizes the expansion of solar sail sail film；It expands in place
Afterwards, so that system is played rotation using the active role power of distributed satellites, and generate the tensile force for keeping solar sail sail film smooth.
Solar sail sail film folds under rounding state, and four distributed satellites are connected by connecting separator with center spacecraft
It connects, solar sail sail film folds in such a way that star folds.
Under solar sail sail film fully unfolded position, four distributed satellites are located at four tops of rectangular solar sail sail film
At angle, it is connect with center spacecraft by tether.Whole spacecraft is in spin states, and four distributed satellites are around center space flight
Centrifugal force makes entire sail film be in tensioning state caused by device rotation.
Solar sail sail film expansion process includes the following steps:
Step 1. connects separator unlock, under connection separator effect of four distributed satellites after unlock, with
Initial velocity four direction ejections perpendicular to each other into solar sail sail membrane plane；
Step 2. is before distributed satellites move to the permitted maximum position of ejection, the work of tether controller so that
The resistance of tether release increases, and detaching the relative velocity of satellite, to continuously decrease be zero；
The step 3. hereafter form regulation system work on distributed satellites, establishes the three-axis stabilization of opposite center spacecraft
Posture, it is ensured that four distributed satellites are generally aligned in the same plane interior with center spacecraft；
Step 4. distributed satellites thruster works, and applies the active force of direction center spacecraft radially, and tether is into one
Step, which is tensioned, reaches scheduled tensile force；
Step 5. distributed satellites thruster works, and generates the thrust along solar sail sail film circumferential direction, and entire solar sail is made to navigate
Its device plays rotation, and the rotational angular velocity back pressure device for reaching needs is stopped；
Step 6. solar sail sail film is fully deployed under the centrifugation force effect that spin generates, and is in tensioning state.
Claims (3)
1. a kind of distributed satellites draw Solar sail spacecraft configuration, including center spacecraft, distributed satellites, connection separation dress
It sets, liquid crystal reflection device, solar cell, solar sail sail film, tether, it is characterised in that:
The center spacecraft is connect with distributed satellites, solar sail sail film by tether, and distributed satellites are according to center spacecraft
It is symmetrical, and in same plane, solar sail sail film is between center spacecraft and distributed satellites, the solar sail
Sail film is rectangular, and is divided into polylith triangular structure according to center spacecraft, pasted on solar sail sail film thin-film solar cells,
The electric energy of liquid crystal reflection device, solar cell conversion is stored in power-supply management system, for running needed for satellite borne equipment work
Electric energy, liquid crystal reflection device realizes the posture control of center spacecraft by the variation of the reflectivity and transmissivity to sunlight
System；
When solar sail sail film folds gathering, distributed satellites are connected and fixed with center spacecraft by connecting separator, the sun
Sail sail film folds in such a way that star folds；Distributed satellites are detached by connecting separator ejection with center spacecraft, are obtained
Relative velocity is obtained, while drawing tether control, realizes the pull-out expansion of solar sail sail film；
The distributed satellites are microsatellite, and each distributed satellites energy three-axis stabilization, opposite center spacecraft are positioned and taken
Carry different payload；
The tether is drawn by tether controller in distributed satellites applies resistance before solar sail sail film is fully deployed to tether,
The relative separation speed of distributed satellites is reduced to zero and tether tensioning is made to reach predetermined tensile force.
2. distributed satellites according to claim 1 draw Solar sail spacecraft configuration, it is characterised in that:The solar sail
Sail film is polyimide film material of aluminizing, and Kapton is used for reflected sunlight, realizes that optical pressure promotes.
3. distributed satellites according to claim 1 draw Solar sail spacecraft configuration, it is characterised in that:The distribution
Satellite is multiple and identical in quality.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610859580.9A CN106394933B (en) | 2016-09-28 | 2016-09-28 | A kind of distributed satellites traction Solar sail spacecraft configuration |
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| CN201610859580.9A CN106394933B (en) | 2016-09-28 | 2016-09-28 | A kind of distributed satellites traction Solar sail spacecraft configuration |
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| CN106394933A CN106394933A (en) | 2017-02-15 |
| CN106394933B true CN106394933B (en) | 2018-07-13 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110901959B (en) * | 2019-12-04 | 2020-07-31 | 成都星时代宇航科技有限公司 | Passive satellite derailment device, remote sensing satellite and satellite |
| CN110979744B (en) * | 2019-12-30 | 2024-01-30 | 中国科学院沈阳自动化研究所 | Regular polygon solar sail membrane structure and folding method |
| CN112340066B (en) * | 2020-11-23 | 2022-04-19 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
| CN112272001B (en) * | 2020-11-27 | 2021-12-21 | 东南大学 | Foldable solar cell film and cell panel for spaceflight |
| CN112591142B (en) * | 2020-12-14 | 2022-11-08 | 兰州空间技术物理研究所 | Storage device suitable for flexible spacecraft |
| CN113682495B (en) * | 2021-08-27 | 2022-09-23 | 中国空间技术研究院 | Space film satellite integrating communication transmission and fragment removal |
| CN114802808B (en) * | 2022-04-20 | 2024-06-18 | 中国人民解放军国防科技大学 | Chemical molecular satellite with strong deformability |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3785590A (en) * | 1970-12-21 | 1974-01-15 | Communications Satellite Corp | Spacecraft body with roller mechanism for deployable-retractable thin film solar array |
| 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 |
| CN104627389A (en) * | 2015-02-14 | 2015-05-20 | 哈尔滨工业大学 | Controllably and orderly inflated self-supporting type solar sail structure |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| CN205554630U (en) * | 2016-04-04 | 2016-09-07 | 蓝灿玉 | Convenient safe spacecraft of intelligence |
-
2016
- 2016-09-28 CN CN201610859580.9A patent/CN106394933B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3785590A (en) * | 1970-12-21 | 1974-01-15 | Communications Satellite Corp | Spacecraft body with roller mechanism for deployable-retractable thin film solar array |
| 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 |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| CN104627389A (en) * | 2015-02-14 | 2015-05-20 | 哈尔滨工业大学 | Controllably and orderly inflated self-supporting type solar sail structure |
| CN205554630U (en) * | 2016-04-04 | 2016-09-07 | 蓝灿玉 | Convenient safe spacecraft of intelligence |
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