CN107757951A - A kind of microsatellite zero momentum realizes the device and method of solar energy capture - Google Patents
A kind of microsatellite zero momentum realizes the device and method of solar energy capture Download PDFInfo
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- CN107757951A CN107757951A CN201711156240.0A CN201711156240A CN107757951A CN 107757951 A CN107757951 A CN 107757951A CN 201711156240 A CN201711156240 A CN 201711156240A CN 107757951 A CN107757951 A CN 107757951A
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- sun
- satellite
- magnetometer
- control
- magnetic
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- 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
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
- B64G1/363—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using sun sensors
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- 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
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
- B64G1/366—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using magnetometers
Abstract
The invention provides the device and method that a kind of microsatellite zero momentum realizes sun acquisition, described device includes：Analog sun sensor, magnetometer and magnetic torquer；The analog sun sensor is used for the posture of determination satellite jointly with the magnetometer；The magnetic torquer is used to provide the control moment during rate damping, and for the normal axis of satellite sun windsurfing to be pointed to the direction vector of the sun, control satellite sun windsurfing normal and the angle in solar vector direction are less than predetermined threshold value, realize that the zero momentum magnetic control mode of satellite captures the sun.This invention simplifies Attitude and orbit control system mode of operation, the reliability of satellier injection preliminary work is improved.
Description
Technical field
The present invention relates to satellite technology field, and in particular to a kind of microsatellite zero momentum realizes the device of solar energy capture
And method.
Background technology
Microsatellite separates initial stage in the satellite and the rocket, in order to realize quick racemization, the general control mode for using thruster, realizes
Three axle rate dampings of satellite.After attitude angular velocity reaches threshold value, star sensor and momenttum wheel are introduced, makes the solar sail of satellite
Plate normal points to the sun, and so as to complete sun acquisition task, the energy for realizing satellite is independently supplied.
Although microsatellite can realize quick racemization by using thruster, installation 6 is at least needed on satellite
Thruster, this considerably increases the construction weight of satellite and complexity.Meanwhile star sensor is just introduced before sun acquisition is realized
With the big power consumption unit such as momenttum wheel, the energy of satellite in itself not only can be largely consumed, and there is a possibility that momenttum wheel is rapidly saturated,
Cause posture out of control.
The content of the invention
For in the prior art the defects of, the invention provides a kind of microsatellite zero momentum realize solar energy capture dress
Put and method, this invention simplifies Attitude and orbit control system mode of operation, improve the reliability of satellier injection preliminary work.
To achieve the above object, the invention provides following technical scheme：
In a first aspect, the invention provides the device that a kind of microsatellite zero momentum realizes sun acquisition, including：It is analog
Sun sensor, magnetometer and magnetic torquer；
The analog sun sensor is used for the posture of determination satellite jointly with the magnetometer；
The magnetic torquer is used to provide the control moment during rate damping, and is used for the method for satellite sun windsurfing
Bobbin points to the direction vector of the sun, and control satellite sun windsurfing normal and the angle in solar vector direction are less than predetermined threshold value,
Realize that the zero momentum magnetic control mode of satellite captures the sun.
Further, the magnetic strength is calculated as three axis magnetometer.
Further, the magnetometer is additionally operable to determine the angle of pitch of satellite when satellite enters ground shadow.
Further, the output of the magnetic torquer acts on the body of satellite after pre-set delay, for providing speed
Control moment in rate damping process.
Further, the magnetic torquer is used to reducing the angular speed of the axle of satellite three, control satellite sun windsurfing normal with
The angle in solar vector direction is less than predetermined threshold value.
Second aspect, present invention also offers a kind of method that microsatellite zero momentum realizes sun acquisition, this method is adopted
The device for realizing sun acquisition with microsatellite zero momentum as described above realizes that this method comprises the following steps：
During S1, rate damping, control moment is provided by magnetic torquer；
S2, sun acquisition and magnetic control process, appearance is determined jointly using analog sun sensor and magnetometer, and use magnetic force
Square device points to the normal axis of satellite sun windsurfing the direction vector of the sun；
S3, when performing S2, while reduce the angular speed of the axle of satellite three, control satellite sun windsurfing normal and solar vector
The angle in direction is less than predetermined threshold value, so as to realize the zero momentum magnetic control sun acquisition of satellite.
Further, determine appearance FORM algorithms by double vectors, determined jointly with magnetometer using analog sun sensor
The three-axis attitude matrix of satellite.
As shown from the above technical solution, microsatellite zero momentum provided by the invention realizes the device of sun acquisition, passes through
Use " analog sun sensor+magnetometer+magnetic torquer " at satellier injection initial stage as attitude measurement and control unit, by
In the present invention and the big power consumption control unit such as gyro, star sensor, thruster and momenttum wheel is not introduced into, thus not only simplify
The configuration of Attitude and orbit control system, while also improve the reliability of whole star.In addition, in the present invention, because each unit output quantity is equal
For analog quantity, therefore mass data processing links are avoided, can in the work in rate damping stage so as to improve attitude control subsystem
By property.Further, in the present invention, because simulated solar sensor, magnetometer and magnetic torquer belong to low-power consumption list
Member, therefore the present invention can substantially reduce energy consumption on star.In summary, this invention simplifies Attitude and orbit control system mode of operation, improve
The reliability of satellier injection preliminary work, realize after the satellite and the rocket separation resource needed for the attitude control process of rate damping process most
Smallization.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are the present invention
Some embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
These accompanying drawings obtain other accompanying drawings.
Fig. 1 is the structural representation for the device that the microsatellite zero momentum that one embodiment of the invention provides realizes sun acquisition
Figure；
Fig. 2 is that the microsatellite zero momentum that one embodiment of the invention provides realizes that the operation principle of the device of sun acquisition is shown
It is intended to；
Fig. 3 is the flow chart for the method that the microsatellite zero momentum that another embodiment of the present invention provides realizes sun acquisition.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, clear, complete description is carried out to the technical scheme in the embodiment of the present invention, it is clear that described embodiment is
Part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
The problem of existing for prior art, the present invention provide one kind and quickly realize the sun suitable for microsatellite zero momentum
The device and method of capture, to simplify Attitude and orbit control system mode of operation, improve the reliability of satellier injection preliminary work.Lead to below
Specific embodiment is crossed to describe to the present invention program in detail.
One embodiment of the invention provides the device that a kind of microsatellite zero momentum realizes sun acquisition, referring to Fig. 1, the dress
Put including：Analog sun sensor 11, magnetometer 12 and magnetic torquer 13；
The analog sun sensor 11 is used for the posture of determination satellite jointly with the magnetometer 12；
The magnetic torquer 13 is used to provide the control moment during rate damping, and is used for satellite sun windsurfing
Normal axis points to the direction vector of the sun, controls the angle in satellite sun windsurfing normal and solar vector direction to be less than default threshold
Value, realizes that the zero momentum magnetic control mode of satellite captures the sun.It is understood that the predetermined threshold value can be according to being actually needed
Set, the present invention is not limited this.
Wherein, the microsatellite zero momentum that the present embodiment provides realizes that the operation principle of the device of sun acquisition can be found in figure
Shown in 2.
It is understood that the output of the magnetic torquer acts on the body of satellite after pre-set delay, for carrying
For the control moment during rate damping.
It is understood that when the sun is appeared in the visual field of analog sun sensor, can be determined by double vectors
Appearance FORM algorithms, simulated solar sensor and magnetometer determine the three-axis attitude matrix of satellite jointly.When satellite enters ground shadow
When, the angle of pitch of satellite can be determined by magnetometer.
It is understood that the magnetic torquer is used for the angular speed for reducing the axle of satellite three, satellite sun windsurfing method is controlled
Line and the angle in solar vector direction are less than predetermined threshold value.
It is understood that the magnetometer is preferably three axis magnetometer.
It is understood that can measure geomagnetic fieldvector using three axis magnetometer, geomagnetic fieldvector is on satellite position
The function put, then by introducing international root-mean-square-deviation standard value, you can determine position and the speed of satellite.Due to earth magnetism
There is uncertain and change in long term in field model, so single use magnetometer can not accurately determine appearance, therefore the present embodiment uses
The mode that magnetometer is combined with sun sensor, the High-precision Vector information and geomagnetic field information phase that sun sensor is exported
With reference to for low rail microsatellite, realizing inexpensive autonomous orbit determination, and reach certain orbit determination accuracy.It is understood that
Belong to prior art to Satellite Attitude Determination process using analog sun sensor and magnetometer, therefore the present embodiment is no longer done in detail to this
It is thin to introduce.
It is understood that the present embodiment is not introduced into star sensor, only sun sensor, similarly, can expand to
Only with earth sensor.
As seen from the above description, the microsatellite zero momentum that the present embodiment provides realizes the device of sun acquisition, by making
By the use of " analog sun sensor+magnetometer+magnetic torquer " at satellier injection initial stage as attitude measurement and control unit, due to
The present embodiment is simultaneously not introduced into the big power consumption control unit such as gyro, star sensor, thruster and momenttum wheel, thus not only simplify
The configuration of Attitude and orbit control system, while also improve the reliability of whole star.In addition, in the present embodiment, due to each unit output quantity
It is analog quantity, therefore avoids mass data processing links, so as to improves work of the attitude control subsystem in the rate damping stage
Reliability.Further, in the present embodiment, because simulated solar sensor, magnetometer and magnetic torquer belong to low work(
Unit is consumed, therefore the present embodiment can substantially reduce energy consumption on star.In summary, this embodiment simplifies Attitude and orbit control system Working mould
Formula, the reliability of satellier injection preliminary work is improved, realized after the satellite and the rocket separate needed for the attitude control process of rate damping process
The minimum of resource.
Another embodiment of the present invention additionally provides a kind of method that microsatellite zero momentum realizes sun acquisition, and this method is adopted
The device for realizing sun acquisition with the microsatellite zero momentum as described in above example realizes that, referring to Fig. 3, this method is included such as
Lower step：
Step 101：During rate damping, control moment is provided by magnetic torquer.
Step 102：Sun acquisition and magnetic control process, appearance is determined jointly using analog sun sensor and magnetometer, and adopt
The normal axis of satellite sun windsurfing is pointed to the direction vector of the sun with magnetic torquer.
In this step, appearance FORM algorithms are determined by double vectors, it is jointly true with magnetometer using analog sun sensor
Determine the three-axis attitude matrix of satellite.
Step 103：When performing step 102, while reduce the angular speed of the axle of satellite three, control satellite sun windsurfing normal
It is less than predetermined threshold value with the angle in solar vector direction, so as to realize the zero momentum magnetic control sun acquisition of satellite.
Because the microsatellite zero momentum that the present embodiment provides realizes the method for sun acquisition using described in above-described embodiment
Microsatellite zero momentum realize that the device of sun acquisition realizes that therefore its principle is similar with beneficial effect, here is omitted.
Above example is merely to illustrate technical scheme, rather than its limitations；Although with reference to the foregoing embodiments
The present invention is described in detail, it will be understood by those within the art that：It still can be to foregoing each implementation
Technical scheme described in example is modified, or carries out equivalent substitution to which part technical characteristic；And these are changed or replaced
Change, the essence of appropriate technical solution is departed from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. a kind of microsatellite zero momentum realizes the device of sun acquisition, it is characterised in that including：Analog sun sensor,
Magnetometer and magnetic torquer；
The analog sun sensor is used for the posture of determination satellite jointly with the magnetometer；
The magnetic torquer is used to provide the control moment during rate damping, and is used for the normal axis of satellite sun windsurfing
The direction vector of the sun is pointed to, control satellite sun windsurfing normal and the angle in solar vector direction are less than predetermined threshold value, realized
The zero momentum magnetic control mode of satellite captures the sun.
2. device according to claim 1, it is characterised in that the magnetic strength is calculated as three axis magnetometer.
3. device according to claim 1, it is characterised in that the magnetometer is additionally operable to determine when satellite enters ground shadow
The angle of pitch of satellite.
4. device according to claim 1, it is characterised in that the output of the magnetic torquer acts on after pre-set delay
In the body of satellite, for providing the control moment during rate damping.
5. device according to claim 1, it is characterised in that the magnetic torquer is used for the angle speed for reducing the axle of satellite three
Degree, control satellite sun windsurfing normal and the angle in solar vector direction are less than predetermined threshold value.
6. a kind of method that microsatellite zero momentum realizes sun acquisition, it is characterised in that this method use as claim 1~
Microsatellite zero momentum described in 5 any one realizes that the device of sun acquisition realizes that this method comprises the following steps：
During S1, rate damping, control moment is provided by magnetic torquer；
S2, sun acquisition and magnetic control process, appearance is determined jointly using analog sun sensor and magnetometer, and use magnetic torquer
The normal axis of satellite sun windsurfing is pointed to the direction vector of the sun；
S3, when performing S2, while reduce the angular speed of the axle of satellite three, control satellite sun windsurfing normal and solar vector direction
Angle be less than predetermined threshold value, so as to realize the zero momentum magnetic control sun acquisition of satellite.
7. according to the method for claim 6, it is characterised in that determine appearance FORM algorithms by double vectors, using it is analog too
Positive sensor determines the three-axis attitude matrix of satellite with magnetometer jointly.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711156240.0A CN107757951A (en) | 2017-11-20 | 2017-11-20 | A kind of microsatellite zero momentum realizes the device and method of solar energy capture |
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| CN201711156240.0A CN107757951A (en) | 2017-11-20 | 2017-11-20 | A kind of microsatellite zero momentum realizes the device and method of solar energy capture |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110589028A (en) * | 2019-09-29 | 2019-12-20 | 上海航天控制技术研究所 | Autonomous mode switching method for abnormal satellite attitude maneuver |
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| CN101934863A (en) * | 2010-09-29 | 2011-01-05 | 哈尔滨工业大学 | Satellite posture all-round controlling method based on magnetic moment device and flywheel |
| CN104097791A (en) * | 2014-06-24 | 2014-10-15 | 上海微小卫星工程中心 | Magnetic sensor and star sensor-based full attitude capture method and device thereof |
| CN104097793A (en) * | 2014-06-24 | 2014-10-15 | 上海微小卫星工程中心 | Zero momentum magnetic control sun capture device and method of satellite |
| CN105899430A (en) * | 2013-11-25 | 2016-08-24 | 空中客车防务和空间公司 | Method and device for control of a sunlight acquisition phase of a spacecraft |
| CN207510746U (en) * | 2017-11-20 | 2018-06-19 | 北京千乘探索科技有限公司 | A kind of microsatellite zero momentum realizes the device of solar energy capture |
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2017
- 2017-11-20 CN CN201711156240.0A patent/CN107757951A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101934863A (en) * | 2010-09-29 | 2011-01-05 | 哈尔滨工业大学 | Satellite posture all-round controlling method based on magnetic moment device and flywheel |
| CN105899430A (en) * | 2013-11-25 | 2016-08-24 | 空中客车防务和空间公司 | Method and device for control of a sunlight acquisition phase of a spacecraft |
| CN104097791A (en) * | 2014-06-24 | 2014-10-15 | 上海微小卫星工程中心 | Magnetic sensor and star sensor-based full attitude capture method and device thereof |
| CN104097793A (en) * | 2014-06-24 | 2014-10-15 | 上海微小卫星工程中心 | Zero momentum magnetic control sun capture device and method of satellite |
| CN207510746U (en) * | 2017-11-20 | 2018-06-19 | 北京千乘探索科技有限公司 | A kind of microsatellite zero momentum realizes the device of solar energy capture |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110589028A (en) * | 2019-09-29 | 2019-12-20 | 上海航天控制技术研究所 | Autonomous mode switching method for abnormal satellite attitude maneuver |
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