CN108995828A - Spacecraft - Google Patents
Spacecraft Download PDFInfo
- Publication number
- CN108995828A CN108995828A CN201710418751.9A CN201710418751A CN108995828A CN 108995828 A CN108995828 A CN 108995828A CN 201710418751 A CN201710418751 A CN 201710418751A CN 108995828 A CN108995828 A CN 108995828A
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- China
- Prior art keywords
- component
- windsurfing
- spacecraft
- target
- reflecting
- Prior art date
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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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Astronomy & Astrophysics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Photovoltaic Devices (AREA)
Abstract
This disclosure relates to a kind of spacecraft.The spacecraft includes: spacecraft main body；Windsurfing component is located at spacecraft body side, is provided with solar panel on windsurfing component one side, is provided with reflecting part on another side；Control assembly controls the windsurfing component and reaches the target position, so that sunlight is reflected into the target reflecting area by the reflecting part for the positional relationship according to spacecraft orbit, solar orbit and target reflecting area.According to the embodiment of the present disclosure, windsurfing component can be controlled and reach target position, sunlight is allowed to be reflected into target reflecting area by the reflecting part being arranged on windsurfing component one side, the purpose of solar reflection optical can be observed the long period by realizing naked eyes in target reflecting area, and have the features such as low cost, low weight cost and strong operability.
Description
Technical field
This disclosure relates to space industry more particularly to a kind of spacecraft.
Background technique
The moving communication satellite system that iridium satellite is made of 66 satellites, iridium satellite flashing is many astrophiles or space flight
Fan is happy to a kind of chronometer phenomenon of experience.It is by the massive phased array antenna-reflected of spacecraft (for example, satellite) too
Sunlight, and spacecraft orbit and solar orbit based on acquisition, predicting earth surface specific position can see in particular moment
To the solar reflection optical reflected by phased array antenna.Obviously, spacecraft orbit and the real-time change of solar orbit make iridium satellite
Flashing has the shortcomings that the naked eyes Observable time is short, only particular moment specific position Observable, iridium satellite flashing brightness is non-adjustable.
For this purpose, installed usually on spacecraft active power source (such as LED array or laser lamp, with realize according to need into
Row shine) or adjustable direction reflecting plate (with reflected sunlight), to obtain the target reflecting area naked eyes long period
Observation effect.However, the spacecraft of both modes has the shortcomings that cost is big, weight cost is high and operability is lower.
Therefore, how under the premise of low cost, not increasing spacecraft weight cost and guaranteeing higher operability, realize that target is anti-
Penetrating naked eyes in area can observe that solar reflection optical is problem to be solved the long period.
Summary of the invention
In view of this, the present disclosure proposes a kind of spacecraft, in low cost, do not increase spacecraft weight cost and guarantor
Under the premise of demonstrate,proving higher operability, realize that naked eyes can observe that (- 8 wait stars or more to high brightness the long period in target reflecting area
Brightness) solar reflection optical.
According to the one side of the disclosure, a kind of spacecraft is provided, comprising:
Spacecraft main body；
Windsurfing component is located at the spacecraft body side, is provided with solar battery on the windsurfing component one side
Plate is provided with reflecting part on another side；
Control assembly, for the positional relationship according to spacecraft orbit, solar orbit and target reflecting area, described in control
Windsurfing component reaches the target position, so that sunlight is reflected into the target reflecting area by the reflecting part.
In one possible implementation, the spacecraft further include:
First driving assembly, for driving the spacecraft main body to carry out pose adjustment；
Second driving assembly, for driving the windsurfing component to rotate.
In one possible implementation, the control assembly controls the windsurfing component and reaches the target position,
Including at least one of following manner:
It controls first driving assembly and pose adjustment is carried out to the spacecraft main body, so that the windsurfing component reaches
The target position；
It controls second driving assembly and drives the windsurfing component rotation, so that the windsurfing component reaches the target
Position.
In one possible implementation, the control assembly is also used to: the change in location of the windsurfing component is controlled,
So that the reflecting part is reflected into the reflection optical flare of the target reflecting area.
In one possible implementation, the control assembly is also used to: controlling the change in location of the windsurfing component
Frequency, so that the reflected light is flashed with first frequency.
In one possible implementation, the solar panel and the reflecting part are on the windsurfing component
It is oppositely arranged.
In one possible implementation, the windsurfing component is multiple, wherein is arranged at least one windsurfing component
There is reflecting part.
In one possible implementation, the reflecting part includes optical solar reflector OSR.
According to the spacecraft of the disclosure, windsurfing component can be controlled and reach target position, sunlight is allowed to pass through sail
The reflecting part being arranged on board group part one side is reflected into target reflecting area, and realizing visually can the long period in target reflecting area
The purpose of solar reflection optical is observed, and has the features such as low cost, low weight cost and strong operability.
According to below with reference to the accompanying drawings to detailed description of illustrative embodiments, the other feature and aspect of the disclosure will become
It is clear.
Detailed description of the invention
Comprising in the description and constituting the attached drawing of part of specification and specification together illustrates the disclosure
Exemplary embodiment, feature and aspect, and for explaining the principles of this disclosure.
Fig. 1 is a kind of block diagram of spacecraft shown according to an exemplary embodiment.
Fig. 2 is a kind of structural schematic diagram of spacecraft shown according to an exemplary embodiment.
Fig. 3 is a kind of block diagram of spacecraft shown according to an exemplary embodiment.
Fig. 4 is a kind of spacecraft shown according to an exemplary embodiment using exemplary schematic diagram.
Reference signs list:
1: sunlight；2: target reflecting area；10: spacecraft；11: spacecraft main body；12: windsurfing component；121: solar energy
Solar panel；122: reflecting part；13: control assembly；14: the first driving assemblies；15: the second driving assemblies；30: the sun；50: ground
Ball.
Specific embodiment
Various exemplary embodiments, feature and the aspect of the disclosure are described in detail below with reference to attached drawing.It is identical in attached drawing
Appended drawing reference indicate component functionally identical or similar.Although the various aspects of embodiment are shown in the attached drawings, remove
It non-specifically points out, it is not necessary to attached drawing drawn to scale.
Dedicated word " exemplary " means " being used as example, embodiment or illustrative " herein.Here as " exemplary "
Illustrated any embodiment should not necessarily be construed as preferred or advantageous over other embodiments.
In addition, giving numerous details in specific embodiment below to better illustrate the disclosure.
It will be appreciated by those skilled in the art that without certain details, the disclosure equally be can be implemented.In some instances, for
Method, means, component and circuit well known to those skilled in the art are not described in detail, in order to highlight the purport of the disclosure.
Embodiment 1
Fig. 1 is a kind of block diagram of spacecraft shown according to an exemplary embodiment.As shown in Figure 1, the spacecraft 10 wraps
It includes:
Spacecraft main body 11；
Windsurfing component 12 is located at 11 side of spacecraft main body, is provided with the sun on 12 one side of windsurfing component
Can solar panel 121, be provided with reflecting part 122 on another side；
Control assembly 13, control assembly 13 are used for the position according to spacecraft orbit, solar orbit and target reflecting area
Relationship controls the windsurfing component 12 and reaches the target position, so that sunlight is reflected into institute by the reflecting part 122
State target reflecting area.
According to the spacecraft of the embodiment of the present disclosure, windsurfing component can be controlled and reach target position, so that sunlight can be with
It is reflected into target reflecting area by the reflecting part being arranged on windsurfing component one side, forms one on target reflecting area ground
The hot spot of diameter dozens of kilometres, and reach the brightness of the stars such as highest -8, thus when realizing that naked eyes can be longer in target reflecting area
Between observe the purpose of solar reflection optical, and have low cost, low weight cost and the features such as strong operability.
In one possible implementation, the windsurfing component 12 of the spacecraft 10 is multiple, wherein at least one windsurfing
Reflecting part 122 is provided on component 12.
Fig. 2 is a kind of structural schematic diagram of spacecraft shown according to an exemplary embodiment.For example, such as Fig. 2 institute
Show, which includes expansion windsurfing component 12, and wherein windsurfing component 12 is two, is set on one of windsurfing component 12
It is equipped with reflecting part 122.
In this way, sunlight can be realized in the case where guarantee section solar panel 121 works normally
1 is reflected into target reflecting area 2 by reflecting part 122.It will be understood by those skilled in the art that the quantity of windsurfing component 12 and setting
The quantity for being equipped with the windsurfing component 12 of reflecting part 122, which can according to need, to be configured, simply by the presence of can be anti-by sunlight 1
It is mapped to the reflecting part 122 of target area, the disclosure is without limitation.
In one possible implementation, solar panel 121 and reflecting part 122 are opposite on windsurfing component 12
Setting.
For example, solar panel 121 can be set on 12 one side of windsurfing component, for obtaining solar energy.
Reflecting part 122 is set on the another side opposite with the solar panel 121, is used to reflected sunlight.In this way, navigating
When its device 10 needs windsurfing component 12 to generate electricity, the rotation of windsurfing component 12 can control, so that being provided with solar panel 121
One side is towards the sun, to generate electricity；When spacecraft 10 needs windsurfing component 12 reflective, windsurfing component 12 can control
Rotation, so that being provided with the another side of reflecting part 122 towards the sun, to carry out reflective.Those skilled in the art should manage
Solution, the positional relationship of solar panel 121 and reflecting part 122, which can according to need, to be configured, if can be realized by
Sunlight 1 is reflected into target reflecting area 2, and the disclosure is without limitation.
In one possible implementation, reflecting part 122 may include optical solar reflector OSR.Wherein, optics is too
Positive reflecting mirror OSR includes the surface for having high reflectance to solar spectrum, can be used for reflected sunlight.In addition, OSR is as a kind of excellent
The passive thermal control coating of matter has the characteristics that lighter weight, at low cost, and is relatively easy to be arranged on windsurfing component 12.For example, can
To coat optical solar reflector OSR by technique on the one side of windsurfing component 12.
In this way, in the existing component of spacecraft 10 (in order to meet the windsurfing component of spacecraft power demand)
The optical solar reflector OSR coating of lighter weight is set, can guarantee low cost, do not increase spacecraft weight cost and
Under conditions of guaranteeing higher operability, realize that target reflecting area 2 can observe solar reflection optical the long period.Those skilled in the art
Member should be understood that the material of reflecting part 122 and form can according to need and be configured, as long as reflex can be played,
The disclosure is without limitation.
In one possible implementation, control assembly 13 can be that single-chip microcontroller, CPU, MPU, FPGA etc. are any can be into
The control unit of row data processing.Control assembly 13 can be realized by special hardware circuit, can also pass through general controls group
Part combines executable logical order to realize, to execute the control process of control assembly.
In one possible implementation, spacecraft 10 may also include memory module (not shown), to store control group
The data, such as spacecraft orbit data, solar orbit data etc. that part 13 obtains.
In one possible implementation, the available spacecraft orbit of control assembly 13, solar orbit and target
The positional relationship of echo area 2, wherein target reflecting area 2 refers to the region for wishing to be reflected into sunlight 1.It should be noted that
The track of spacecraft 10 can be designed according to the position of target reflecting area 2, for example, spacecraft 10 can be designed in working as
19 points of ground time is to flying over 2 overhead of target reflecting area during 5:00 AM.Control assembly 13 can be based on the positional relationship, really
The target position of the fixed windsurfing component 12.Wherein, target position refers to when windsurfing component 12 is located at herein, can make too
Sunlight 1 is reflected into target reflecting area 2 by reflecting part 122.After determining target position, control assembly 13 can control windsurfing
Component 12 reaches target position, to realize that sunlight 1 is reflected into target reflecting area 2 by reflecting part 122.Art technology
Personnel, which should be understood that, can realize control group by the multiple hardwares mode such as digital circuit, discrete hardware elements and integrated circuit
Part 13 simultaneously executes the corresponding function of control assembly 13, and the disclosure is without limitation.
In this way, sunlight may be implemented and target area is reflected by reflecting part.Those skilled in the art
It should be understood that control assembly 13 can be configured as needed, as long as can make sunlight can be by anti-by control assembly 13
Light component 122 reflexes to target area, and the disclosure is without limitation.
Fig. 3 is a kind of block diagram of spacecraft shown according to an exemplary embodiment.In one possible implementation,
As shown in figure 3, the spacecraft 10 may also include that
First driving assembly 14, for driving spacecraft main body 11 to carry out pose adjustment；
Second driving assembly 15, for driving windsurfing component 12 to rotate.
For example, the first driving assembly 14 can be Spacecraft Attitude Control mechanism, determine spacecraft attitude, and root
According to needing to drive spacecraft main body to carry out pose adjustment.Second driving assembly 15 can be solar panel driving device
(Solar Array Drive Assembly, SADA).It should be noted that spacecraft 10 may include multiple solar batteries
Plate driving device can according to need the one or more solar panel driving devices of selection, to drive windsurfing component 122 to revolve
Turn.
In one possible implementation, control assembly 13 controls the windsurfing component 12 and reaches the target position,
Including at least one of following manner:
It controls the first driving assembly 14 and pose adjustment is carried out to spacecraft main body 11, so that windsurfing component 12 reaches target position
It sets；
It controls the second driving assembly 15 driving windsurfing component 12 to rotate, so that windsurfing component 12 reaches target position.
For example, behind the target position that windsurfing component 12 has been determined, it can control the first driving assembly 14 to space flight
Device main body 11 carries out pose adjustment, or control the second driving assembly 15 driving windsurfing component 12 rotates；Also it can control first
Driving assembly 14 carries out pose adjustment to spacecraft main body 11, while controlling the second driving assembly 15 driving windsurfing component 12 and revolving
Turn, so that windsurfing component 12 reaches target position.
In this way, windsurfing component 12 can be controlled in several ways reaches target position.Those skilled in the art
Member it should be understood that driving assembly concrete form, control windsurfing component 12 reach target position concrete mode can as needed into
Row selection, as long as can control windsurfing component 12 reaches target position, the disclosure is without limitation.
In one possible implementation, control assembly 13 can also be used in: the change in location of control windsurfing component 12, with
Reflecting part 122 is set to be reflected into the reflection optical flare of target reflecting area.
It for example, can be by controlling 12 change in location of windsurfing component, for example, passing through the first driving assembly 14 control boat
Its 11 attitudes vibration of device main body, or windsurfing component 12 is controlled by the second driving assembly 15 and is rotated, so that the angle of reflection of sunlight
Degree changes, so that target reflecting area ground hot spot synchronous shift, completes naked-eye observation and dodge to solar reflection optical light and shade
Bright effect.
In this way, allow user to observe the solar reflection optical of light and shade flashing in target reflecting area, increase
Entertainment effect.It will be understood by those skilled in the art that can be more by digital circuit, discrete hardware elements and integrated circuit etc.
Kind hardware mode realizes control assembly 13 and executes corresponding function；Also, control 12 change in location of windsurfing component can adopt
It is realized with various ways, as long as reflecting part can be made to be reflected into the reflection optical flare of target reflecting area, the disclosure pair
This is with no restrictions.
In one possible implementation, control assembly 13 can also be used in: the change in location frequency of control windsurfing component 12
Rate, so that reflected light is flashed with first frequency.
For example, the change in location frequency of windsurfing component 12, the sun that target reflecting area can be made to observe are controlled
The flicker effect of certain rule (such as Morse code) is presented in reflected light.For example, the position that can control windsurfing component 12 becomes
Change frequency, so that reflected light is flashed with first frequency, first frequency flashing can for example meet Morse code rule, so that
The flicker effect of Morse code is showed in the light and shade flashing that target reflecting area observes, so as to transmit information.Ability
Field technique personnel should be understood that can be realized by the multiple hardwares mode such as digital circuit, discrete hardware elements and integrated circuit
Control assembly 13 simultaneously executes corresponding function, and the disclosure is without limitation.
In this way, information can be transmitted to target reflecting area by the spacecraft 10, realizes spacecraft 10 and ground
World interaction between the user of face, improves space flight interest.
Using example
Fig. 4 is a kind of spacecraft shown according to an exemplary embodiment using exemplary schematic diagram.Art technology
Personnel should be understood that this, merely for the sake of the purpose for being easy to understand the embodiment of the present disclosure, is not construed as to disclosure reality using example
Apply the limitation of example.
As shown in figure 4, for the track example of a spacecraft, the earth and the sun.This using in example it can be seen that,
Under the sunlight 1 of the sun 30 irradiates, the earth 50 include daytime and night while.Spacecraft 10 (such as satellite) is located at
On its track (sun synchronization morning and evening track).It can be according to spacecraft orbit, the positional relationship of solar orbit and target reflecting area 2
(considering earth rotation), determines the target position of windsurfing component；And control windsurfing component and reach target position, so that sunlight 1
Sunlight 1 is reflexed into target reflecting area 2 (positioned at the one of earth night by the reflecting part on the windsurfing component of spacecraft 10
On face).In this case, target reflecting area 2 can be with naked-eye observation to solar reflection optical.Wherein it is possible to be reflected according to target
The position in area 2 is designed the track of spacecraft 10, for example, spacecraft 10 can be designed in 19 points of local time to morning 5
Target reflecting area overhead is flown over during point.
According to the embodiment of the present disclosure, windsurfing component can be controlled and reach target position, sunlight is allowed to pass through windsurfing
The reflecting part being arranged on component one side is reflected into target reflecting area, and realizing naked eyes in target reflecting area can see the long period
The purpose of shoot the sun reflected light, and have the features such as low cost, low weight cost and strong operability.
The presently disclosed embodiments is described above, above description is exemplary, and non-exclusive, and
It is not limited to disclosed each embodiment.Without departing from the scope and spirit of illustrated each embodiment, for this skill
Many modifications and changes are obvious for the those of ordinary skill in art field.The selection of term used herein, purport
In the principle, practical application or technological improvement to the technology in market for best explaining each embodiment, or lead this technology
Other those of ordinary skill in domain can understand each embodiment disclosed herein.
Claims (8)
1. a kind of spacecraft characterized by comprising
Spacecraft main body；
Windsurfing component is located at the spacecraft body side, is provided with solar panel on the windsurfing component one side, separately
Reflecting part is provided on one side；
Control assembly controls the windsurfing for the positional relationship according to spacecraft orbit, solar orbit and target reflecting area
Component reaches the target position, so that sunlight is reflected into the target reflecting area by the reflecting part.
2. spacecraft according to claim 1, which is characterized in that further include:
First driving assembly, for driving the spacecraft main body to carry out pose adjustment；
Second driving assembly, for driving the windsurfing component to rotate.
3. spacecraft according to claim 2, which is characterized in that the control assembly controls the windsurfing component and reaches institute
State at least one of target position, including following manner:
It controls first driving assembly and pose adjustment is carried out to the spacecraft main body, so that described in windsurfing component arrival
Target position；
It controls second driving assembly and drives the windsurfing component rotation, so that the windsurfing component reaches the target position
It sets.
4. spacecraft according to claim 1, which is characterized in that the control assembly is also used to:
The change in location of the windsurfing component is controlled, so that the reflecting part is reflected into the reflection color break-up of the target reflecting area
It is bright.
5. spacecraft according to claim 1, which is characterized in that the control assembly is also used to:
The change in location frequency of the windsurfing component is controlled, so that the reflected light is flashed with first frequency.
6. spacecraft according to any one of claims 1-5, which is characterized in that the solar panel and described anti-
Light component is oppositely arranged on the windsurfing component.
7. spacecraft according to any one of claims 1-5, which is characterized in that the windsurfing component be it is multiple,
Wherein, reflecting part is provided at least one windsurfing component.
8. spacecraft according to any one of claims 1-5, which is characterized in that the reflecting part includes the optical sun
Reflecting mirror OSR.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710418751.9A CN108995828B (en) | 2017-06-06 | 2017-06-06 | Spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710418751.9A CN108995828B (en) | 2017-06-06 | 2017-06-06 | Spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN108995828A true CN108995828A (en) | 2018-12-14 |
| CN108995828B CN108995828B (en) | 2023-02-10 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710418751.9A Active CN108995828B (en) | 2017-06-06 | 2017-06-06 | Spacecraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114952757A (en) * | 2021-02-20 | 2022-08-30 | 北京九天微星科技发展有限公司 | Assembly support vehicle |
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| CN103274060A (en) * | 2013-04-27 | 2013-09-04 | 中国空间技术研究院 | Spacecraft energy-complementing system based on sunlight reflection |
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| US4305555A (en) * | 1977-10-20 | 1981-12-15 | Davis Charles E | Solar energy system with relay satellite |
| US5909299A (en) * | 1997-04-28 | 1999-06-01 | Sheldon, Jr.; L. Philip | Microsatellite system for high-volume orbital telemetry |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN114952757A (en) * | 2021-02-20 | 2022-08-30 | 北京九天微星科技发展有限公司 | Assembly support vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108995828B (en) | 2023-02-10 |
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