CN106394933A - Solar-sail spacecraft structure provided with distributed satellites for traction - Google Patents
Solar-sail spacecraft structure provided with distributed satellites for traction Download PDFInfo
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- CN106394933A CN106394933A CN201610859580.9A CN201610859580A CN106394933A CN 106394933 A CN106394933 A CN 106394933A CN 201610859580 A CN201610859580 A CN 201610859580A CN 106394933 A CN106394933 A CN 106394933A
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- Prior art keywords
- sail
- spacecraft
- film
- solar
- distributed satellites
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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
Abstract
The invention discloses a solar-sail spacecraft structure provided with distributed satellites for traction. The solar-sail spacecraft structure provided with the distributed satellites for traction is composed of a central spacecraft, the distributed satellites and a square solar sail film. The distributed satellites are fixedly connected with the central spacecraft through connection and separation devices, and the distributed satellites are ejected to be separated from the central spacecraft through the connection and separation devices, so that the relative speed is obtained; and tied ropes are pulled to be controlled at the same time, so that the solar sail film is pulled out and unfolded. After the solar sail film is unfolded in place, a system is made to spin up through active acting force of the distributed satellites, and tensile force for keeping the solar sail film flat is generated. The multiple distributed satellites are used for providing traction force in the unfolding process, providing centrifugal force in the on-orbit flight process and serving as a distributed effective loading platform when a detection task is carried out. A thin-film solar cell and a liquid crystal reflection device are pasted onto the solar sail film; and electric energy converted by the solar cell is stored in a power source management system, serves as electric energy required for operation of satellite-borne equipment and is used for achieving posture control of the central spacecraft.
Description
Technical field
The present invention relates to a kind of spacecraft configuation, specifically, it is related to a kind of using distributed satellites traction expansion and sharp
Keep the Solar sail spacecraft configuration of sail film tensioning with spin.
Background technology
The large-scale thin film expansion spacecraft that Solar sail spacecraft is made up of large-area sail film and supporting construction, its profit
The power of flight is provided for spacecraft with reflection optical pressure on large area smooth sail film for the sun, is a kind of not against chemical propulsion
Realize the aircraft of follow-on mission.Compared to conventional aerospace device, Solar sail spacecraft has huge superiority, need not consume combustion
Material, the service life therefore 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 being provided using solar light pressure, through long when
Between accelerate, Solar sail spacecraft can be flown with the speed of 93km/s, and its speed rely on rocket-propelled the fastest spacecraft more now
Fast 4～6 times.At present, Solar sail spacecraft has become the study 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 the sail film of deploying solar sail, keep the tensioning of sail film in flight course 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 kind is by support bar
Traction launches；One kind is using centrifugal force rotary expansion.
By support bar draw launch sail film principle be using be fixed on center spaceborne cantilever strut launch and
Tensioning sail film, mainly has using inflatable structure, is folded mechanically structure or multistable configuration elastic deformation three kinds of forms of expansion.Support
In bar stretching process, the sail film of traction Solar sail spacecraft is launched；After putting in place, the rigidity using supporting bar structure itself is opened
Tight sail film.The Nanosail-D series of typical case's application of this expansion mode, the such as U.S. and Light-sail series solar sail boat
Its device.In general, sail film size is bigger, the bending load that support bar is born is bigger, and the additional mass of support bar is bigger,
The therefore requirement to lightweight, high rigidity, multistable material for the program is higher.Due to not needing to rotate, Solar sail spacecraft is general
Using three-axis stabilization scheme.
Principle using centrifugal force rotary expansion sail film is that centrifugal force produced by spacecraft spins throws the thin of folding away
Film, and keep the position shape after launching.During launching, center spacecraft constantly adjusts rotary acceleration, in order to produce enough
Pull strength, typically the outside of sail film fix some masses.The typical case application such as the IKAROS of Japan of this expansion mode
Solar sail spacecraft.Draw the expansion mode launching sail film compared to by supporting bar structure, using centrifugal force rotary expansion sail film
Mainly there are following characteristics:(1) spin centrifugal force can provide the in-plane stiffness of structure, effectively reduces the weight of supporting construction；(2) no
The restriction of bar physical dimension supported, can achieve the expansion of any large scale sail film in theory.
The spin expansion spacecraft proposing at present be all made using the thruster start generation moment of torsion of center spacecraft be
System rotation is realizing.Because sail film sole mass density is very low, need the mass relying on sail film end providing centrifugation to lead
Gravitation and tensile force.When solar sail film amasss and increases, system rotary inertia sharply increases it is desirable to the very big ability of the angular velocity of system
Launch sail film, the input torque that center spacecraft provides is required very high.Therefore, the configuration that spin launches at present it is also difficult to achieve
Application in overlarge area solar sail.
Content of the invention
The deficiency existing in order to avoid prior art, the present invention proposes a kind of distributed satellites and draws Solar sail spacecraft structure
Type.
The technical solution adopted for the present invention to solve the technical problems is：Distributed satellites draw Solar sail spacecraft structure
Type, including center spacecraft, distributed satellites, connect segregation apparatuss, liquid crystal reflection device, solaode, solar sail sail film,
Tether it is characterised in that described center spacecraft is connected by tether with distributed satellites, solar sail sail film, distributed satellites according to
Center spacecraft is symmetrical, and is in same plane, and solar sail sail film is located between center spacecraft and distributed satellites,
Described solar sail sail film is square, and is divided into polylith triangular structure, sticking film on solar sail sail film according to center spacecraft
Solaode, liquid crystal reflection device, solaode conversion electrical power storage in power-supply management system, for running spaceborne setting
The required electric energy of standby work, liquid crystal reflection device is by the reflectance of sunlight and the change of absorbance, realizing center space flight
The gesture stability of device；
Solar sail sail film folds when drawing in, and distributed satellites are connected by being connected segregation apparatuss with center spacecraft,
Solar sail sail film is folded in the way of star folding；Distributed satellites are divided with center spacecraft by connecting segregation apparatuss ejection
From, acquisition relative velocity, traction tether control simultaneously, the pull-out realizing solar sail sail film launches；
Described distributed satellites are microsatellite, each distributed satellites energy three-axis stabilization, relatively center spacecraft positioning
And carry different payload；
Described tether pass through tether controller distributed satellites draw solar sail sail film fully deployed front to tether applying
Resistance, the relative separation speed reducing distributed satellites to zero and makes tether tensioning reach predetermined tensile force.
Described solar sail sail film is polyimide film material of aluminizing, and Kapton is used for reflected sunlight, realizes
Optical pressure advances.
Described distributed satellites are multiple and identical in quality.
Beneficial effect
A kind of distributed satellites proposed by the present invention draw Solar sail spacecraft configuration, using the tether control of distributed satellites
System, realizes the expansion of solar sail sail film；After launching to put in place, the active role power using distributed satellites makes system play rotation, and produces
The raw tensile force keeping solar sail sail film smooth.By multiple distributed microsatellites launch during provide pull strength,
Rail in-flight provides centrifugal force, implements during detection mission as distributed payload platform, 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.Traction relies primarily on initial ejection speed and the tether of spacecraft during launching
Passive friction eceleration, it is not necessary to consume the energy, greatly reduces the weight demands that spacecraft carries fuel.After launching to put in place, long
In time flight course, the holding of sail layer tension utilizes system spinning to realize, and has the characteristics that reliable, stable.Control system
, away from system centre, the control efficiency that spins is higher for the effect point of force application of rotation.The pose adjustment of Solar sail spacecraft passes through control
Liquid crystal reflectors on solar sail sail film processed produce to realize with respect to the control moment at center.
Brief description
Below in conjunction with the accompanying drawings with embodiment to the present invention a kind of distributed satellites traction Solar sail spacecraft configuration make into
One step describes in detail.
Fig. 1 a is schematic diagram before distributed satellites of the present invention traction Solar sail spacecraft structure expansion.
Fig. 1 b is schematic diagram after distributed satellites of the present invention traction Solar sail spacecraft structure expansion.
Fig. 2 draws the solar sail sail film folding mode schematic diagram of Solar sail spacecraft for distributed satellites of the present invention.
Fig. 3 a, Fig. 3 b, Fig. 3 c are that the solar sail sail film of the present invention launches process schematic.
The solar sail sail film that Fig. 4 draws Solar sail spacecraft for distributed satellites of the present invention launches process flow diagram flow chart.
In figure
1. distributed satellites 2. connect segregation apparatuss 3. center spacecraft, 4. liquid crystal reflection device 5. solaode
6. solar sail sail film 7. tether
Specific embodiment
The present embodiment is a kind of distributed satellites traction Solar sail spacecraft configuration.
Refering to Fig. 1 a, Fig. 1 b～Fig. 4, the present embodiment distributed satellites draw Solar sail spacecraft configuration, are defended by distributed
Star 1, center spacecraft 3, solar sail sail film 6 and connection segregation apparatuss 2, liquid crystal reflection device 4, solaode 5, solar sail sail
Film 6, tether 7 form.Center spacecraft 3 is connected by tether 7 with distributed satellites 1, solar sail sail film 6, distributed satellites 1 according to
Center spacecraft 3 is symmetrical, and is in same plane.In the present embodiment, distributed satellites 1 are four, and four distributed to defend
Star 1 is identical in quality；Each distributed satellites 1 energy three-axis stabilization, center spacecraft 3 relatively position and carry different effective loads
Lotus.Solar sail sail film 6 is connected between center spacecraft 3 and distributed satellites 1；Solar sail sail film 6 is square, and according to center boat
Its device 3 is divided into polylith triangular structure, sticking film solaode 5, liquid crystal reflection device 4, the sun on solar sail sail film 6
Can battery 5 conversion electrical power storage in power-supply management system, the electric energy required for running satellite borne equipment work；Liquid crystal reflectors
Part 4 is by the reflectance of sunlight and the change of absorbance, realizing the gesture stability of center spacecraft 3.Solar sail sail film 6 folding
When overlapping is held together, distributed satellites 1 are connected by being connected segregation apparatuss 2 with center spacecraft 3, and solar sail sail film 6 is with star
The mode folding folds；Before expansion, overall Space Vehicle System is in three-axis stabilization state without spin.Distributed satellites 1 pass through even
Connect segregation apparatuss 2 and launch and separate with center spacecraft 3, obtain relative velocity, traction tether 7 controls, and will be fixed on tether simultaneously
On solar sail sail film 6 pull-out launch.Tether 7 passes through tether controller and opens up completely in distributed satellites 1 traction solar sail sail film 6
Before opening, resistance is applied to tether 7, the relative separation speed reducing distributed satellites 1 to zero and makes tether 7 tensioning.Solar sail sail film
Under 6 its fully unfolded positions, four distributed satellites are located at four drift angles of square solar sail sail film 6 respectively, by tether 7 with
Center spacecraft 3 connects.Spacecraft is in spin states, four distributed satellites 1 around center spacecraft 3 rotation provided from
Mental and physical efforts make whole solar sail sail film 6 be in tensioning state.
Work process
Distributed satellites traction Solar sail spacecraft is by four distributed satellites, the center space flight carrying different payload
Device, square solar sail sail film composition.Four distributed satellites are microsatellite identical in quality, and single quality is in 10kg.Distribution
Formula satellite is made up 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 for producing the active force needed for distributed satellites control, and tether is used for connecting distribution
Formula satellite, solar sail Fan Mohe 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 used for storing the electric energy that solaode is converted, connects and separate
Device is used for fixation and the ejection of distributed satellites, and it is fully deployed that tether controller is used for distributed satellites traction solar sail sail film
Front resistance is applied to tether, thus reducing the relative separation speed of distributed satellites to zero and to make tether tensioning, communication system is used
In spacecraft and ground communication, autonomous navigation system is used for the autonomous flight navigation of spacecraft.Solar sail sail film is many by being divided into
The Kapton composition of aluminizing of block triangle, sticking film solaode on solar sail sail film, liquid crystal reflection device and
Connection cable.Kapton is used for reflected sunlight, realizes optical pressure propulsion, and solaode is used for producing satellite borne equipment work
Make required electric energy, liquid crystal reflection device is by the reflectance of sunlight and the change of absorbance, realizing the attitude of spacecraft
Control, cable is used for transmitting electric energy from solaode to accumulator.
Four distributed satellites are connected by tether respectively with center spacecraft, solar sail sail film and tether, distributed defend
Xing Ji center spacecraft has distributing point to connect.Before expansion, overall Space Vehicle System is in three-axis stabilization state without spin.Four
Distributed satellites are separated with center spacecraft by connecting segregation apparatuss, obtain relative velocity, drag tether simultaneously, will be fixed on
Sail film pull-out on tether；Before launching to put in place, carry friction drag reduction control design case using tether and be gradually reduced relative separation speed,
And certain tensile force is produced on tether；After tentatively putting in place, distributed satellites carry out pose adjustment, set up center space flight relatively
The three-axis stabilization attitude of device, tailing edge point to the radially and tangentially to apply active force simultaneously of center spacecraft, further tensioning system
Rope, and make system play rotation simultaneously.After system is rotated, distributed satellites, by break-off, are brought up again for system sail film as staying
Centrifugal force required for tensioning.In flight course, the reflection coefficient that the pose adjustment of solar sail passes through to adjust solar sail sail film produces
Give birth to complete with respect to the moment of torsion at center.The adjustment of angular velocity of rotation is completed by the synergism of four distributed satellites.?
During expansion, system does not rotate, and the tether using distributed satellites controls, and realizes the expansion of solar sail sail film；Expansion puts in place
Afterwards, make system play rotation using the active role power of distributed satellites, and produce the tensile force keeping solar sail sail film smooth.
Solar sail sail film folds under rounding state, and four distributed satellites pass through to connect segregation apparatuss with center spacecraft even
Connect, solar sail sail film is folded in the way of star folding.
Under solar sail sail film its fully unfolded position, four distributed satellites are located at four tops of square solar sail sail film respectively
At angle, it is connected with center spacecraft by tether.Overall spacecraft is in spin states, and four distributed satellites are around center space flight
Centrifugal force produced by device rotation makes whole sail film be in tensioning state.
Solar sail sail film launches process and comprises the following steps:
Step 1. connects segregation apparatuss unblock, four distributed satellites under the connection segregation apparatuss effect after unblock, with
Initial velocity four direction perpendicular to each other ejections into solar sail sail membrane plane；
Step 2. when distributed satellites move to ejection permission maximum position before, tether controller work so that
The resistance of tether release increases, and it is zero that the relative velocity of separation satellite is gradually lowered；
The step 3. hereafter form regulation system work on distributed satellites, sets up the three-axis stabilization of center spacecraft relatively
Attitude is it is ensured that in four distributed satellites and center spacecraft be generally aligned in the same plane；
Step 4. distributed satellites thruster works, and applies sensing center spacecraft active force radially, and tether enters one
Step is tensioned and reaches predetermined tensile force；
Step 5. distributed satellites thruster works, and produces the thrust along solar sail sail film circumference, makes whole solar sail boat
Its device plays rotation, and the rotational angular velocity back pressure device reaching needs quits work；
Step 6. solar sail sail film is fully deployed under the centrifugal action that spin produces, and is in tensioning state.
Claims (3)
1. a kind of distributed satellites draw Solar sail spacecraft configuration, including center spacecraft, distributed satellites, connect separation dress
Put, liquid crystal reflection device, solaode, solar sail sail film, tether it is characterised in that:
Described center spacecraft is connected by tether with distributed satellites, solar sail sail film, and distributed satellites are according to center spacecraft
Symmetrical, and be in same plane, solar sail sail film is located between center spacecraft and distributed satellites, described solar sail
Sail film is square, and is divided into polylith triangular structure according to center spacecraft, sticking film solaode on solar sail sail film,
Liquid crystal reflection device, the electrical power storage of solaode conversion is in power-supply management system, required for running satellite borne equipment work
Electric energy, liquid crystal reflection device is by the reflectance of sunlight and the change of absorbance, realizing the attitude control of center spacecraft
System；
Solar sail sail film folds when drawing in, and distributed satellites are connected by being connected segregation apparatuss with center spacecraft, the sun
Sail sail film is folded in the way of star folding；Distributed satellites are separated with center spacecraft by connecting segregation apparatuss ejection, obtain
Obtain relative velocity, traction tether controls simultaneously, the pull-out realizing solar sail sail film launches；
Described distributed satellites are microsatellite, and each distributed satellites energy three-axis stabilization, relatively center spacecraft position and take
Carry different payload；
Described tether pass through tether controller distributed satellites draw solar sail sail film fully deployed front to tether apply resistance,
The relative separation speed reducing distributed satellites to zero and makes tether tensioning reach predetermined tensile force.
2. distributed satellites according to claim 1 traction Solar sail spacecraft configuration it is characterised in that:Described solar sail
Sail film is polyimide film material of aluminizing, and Kapton is used for reflected sunlight, realizes optical pressure propulsion.
3. distributed satellites according to claim 1 traction Solar sail spacecraft configuration it is characterised in that:Described distributed
Satellite is multiple and identical in quality.
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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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901959A (en) * | 2019-12-04 | 2020-03-24 | 成都星时代宇航科技有限公司 | Passive satellite derailment device, remote sensing satellite and satellite |
| CN110979744A (en) * | 2019-12-30 | 2020-04-10 | 中国科学院沈阳自动化研究所 | Regular polygon solar sail membrane structure and folding method |
| CN112272001A (en) * | 2020-11-27 | 2021-01-26 | 东南大学 | Foldable solar cell film and cell panel for spaceflight |
| CN112340066A (en) * | 2020-11-23 | 2021-02-09 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
| CN112591142A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Storage device suitable for flexible spacecraft |
| CN113682495A (en) * | 2021-08-27 | 2021-11-23 | 中国空间技术研究院 | Space film satellite integrating communication transmission and fragment removal |
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| CN110901959A (en) * | 2019-12-04 | 2020-03-24 | 成都星时代宇航科技有限公司 | Passive satellite derailment device, remote sensing satellite and satellite |
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| CN112340066A (en) * | 2020-11-23 | 2021-02-09 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
| CN112272001A (en) * | 2020-11-27 | 2021-01-26 | 东南大学 | Foldable solar cell film and cell panel for spaceflight |
| CN112272001B (en) * | 2020-11-27 | 2021-12-21 | 东南大学 | Foldable solar cell film and cell panel for spaceflight |
| CN112591142A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Storage device suitable for flexible spacecraft |
| CN113682495A (en) * | 2021-08-27 | 2021-11-23 | 中国空间技术研究院 | Space film satellite integrating communication transmission and fragment removal |
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| CN106394933B (en) | 2018-07-13 |
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