CN106843250A - A kind of limited plane of illumination determination methods in 01 formula sun sensor visual field - Google Patents
A kind of limited plane of illumination determination methods in 01 formula sun sensor visual field Download PDFInfo
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- CN106843250A CN106843250A CN201710081265.2A CN201710081265A CN106843250A CN 106843250 A CN106843250 A CN 106843250A CN 201710081265 A CN201710081265 A CN 201710081265A CN 106843250 A CN106843250 A CN 106843250A
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- 238000000034 method Methods 0.000 title claims abstract description 18
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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
- B64G1/244—Spacecraft control systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C1/00—Measuring angles
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Abstract
The invention provides a kind of limited plane of illumination determination methods in 01 formula sun sensor visual field, wherein being projected in the position of satellite orbit face projection vector according to the sun ephemeris computation sun；Calculate the position interval of the ground shadow on track；Whether interval in illumination calculate current time satellite；Whether whether the 01 formula sun sensor that judgement is not blocked is shone, and judges there is illumination by other five quadrants blocked beyond satellite quadrant；Judgement is blocked whether satellite quadrant is shone.01 formula sensor and in-orbit recursion shade illumination ephemeris that i.e. the present invention can not blocked by judgement, joint judge solar azimuth, solve to block sun sensor because of load, the sensitive solar irradiation loss of learning problem for causing.
Description
Technical field
The present invention relates to satellite guidance, navigation and control technology, a kind of 01 formula sun sensor visual field is related in particular to
Limited plane of illumination determination methods.
Background technology
After attitude of satellite unstability, security control pattern can be entered, attitude control system need to be according to the information of 01 formula sensor
Judge the orientation of sunshine, the sun can be directed at by attitude maneuver solar battery array, to ensure that whole energy source of star is supplied.According to this
It is required that, the visual field of 01 formula sensor need to cover 6 quadrants of celestial body.At present, 01 formula sensor generally uses one neutralizing
Whether certainly scheme, a 01 formula sun sensor can measure three quadrants by Lighting information, and it is sensitive that Fig. 1 show the 01 formula sun
The configuration picture of device.
In recent years, the resolution ratio of load over the ground of earth observation satellite is improved constantly, and its physical dimension is continuously increased, can be to defending
The 01 formula sun sensor of+Zb direction of principal axis of star causes to block.Fig. 2 show the whole star of 01 formula sun sensor and installs polarity letter
Figure, it is known that satellite is furnished with two 01 formula sensors, ideally can just calculate sunny side according to two 01 formula sensors
Position, but due to the interference of load over the ground ,+Zb direction of principal axis can not sensitivity go out whether solar irradiation information, so can not be according to biography
System method is processed.
The content of the invention
In view of the shortcomings of the prior art, the present invention provides a kind of limited plane of illumination in 01 formula sun sensor visual field and judges
Method, solves to block sun sensor because of load, the sensitive solar irradiation loss of learning problem for causing.
In order to achieve the above object, one technical scheme of the present invention is to provide a kind of limited light in 01 formula sun sensor visual field
Show up determination methods, it includes procedure below：
Control software calculates the position that the sun is projected in satellite orbit face projection vector according to sun ephemeris on step one, star
Put；
Control software calculates the position interval of the ground shadow on track on step 2, star；
Whether control software calculates current time satellite in illumination interval on step 3, star；
Control software judges whether the 01 formula sun sensor not blocked is shone on step 4, star；
Control software judges to be blocked whether satellite quadrant is shone on step 5, star.
In the present invention, whether satellite is in-orbit is in area of illumination, can be carried out according to satellite orbit parameter, sun ephemeris information
The judgement in geometry domain, then the information according to other formula sensors of 5 quadrants 01 whether judge the quadrant that is blocked in light
According to so as to realize the determination to solar azimuth.
The method that the present invention is used, compared with prior art, its advantage and beneficial effect are：The present invention can be in 01 sensor
When being blocked by load, the orientation of the sun is judged, so as to smoothly realize to sun-orientation control, it is ensured that whole energy source of star safety.
Brief description of the drawings
Fig. 1 is the configuration picture of 01 formula sun sensor multiple directions.
Fig. 2 is that the whole star of 01 formula sun sensor installs polarity sketch.
Fig. 3 is the flow chart of the limited plane of illumination determination methods in 01 formula sun sensor visual field of the present invention.
Fig. 4 is the ground sketch that calculates of shadow in the present invention.
Specific embodiment
The present invention can judge what is blocked according to satellite orbit, sun ephemeris, 01 sensor not blocked combination
Whether satellite quadrant is shone.
As shown in figure 3, the present invention provides a kind of 01 formula sun sensor visual field limited plane of illumination determination methods, it include with
Lower step：
Control software is projected in the position of satellite orbit face projection vector according to the sun ephemeris computation sun on step one, star
Put；
Control software calculates the position interval of the ground shadow on track on step 2, star；
Whether control software calculates current time satellite in illumination interval on step 3, star；
Control software calculates whether 01 sensor not blocked is shone on step 4, star；
Control software judges to be blocked whether satellite quadrant is shone on step 5, star.
Below with reference to drawings and Examples, each step to the inventive method is described further.
1) in step one, calculated comprising the projected angle to the sun in satellite orbit face：
Sun Dec, declination are calculated
δs=arcsin (sin Λ sin ε)
Wherein, Λ, ε represent solar celestial longitude and yellow red angle respectively.
The corresponding latitude argument of projection of the solar vector in orbital plane
Wherein, i, Ω represent the orbit inclination angle and right ascension of ascending node of satellite respectively.
2) in step 2, calculated comprising the ground shadow on track：
Coordinate of the satellite orbit face normal direction under J2000 can be expressed as
Ssat=-[sin Ω sini-cos Ω sini cosi]T (3)
According to Sun Dec αsWith declination δs, there is shown coordinate of the solar vector under inertial system J2000
Ssun=[cos αscosδs sinαscosδs sinδs]T (4)
In can be to calculate the angle between satellite orbit face normal negative sense and solar vector
The earth regards a circle, its radius length R aseRepresent, then the earth is one on the vertical face of solar vector
Circle, the roundlet in corresponding diagram 4；The track of satellite is near-circular orbit, its on the vertical face of solar vector be projected as one it is ellipse
Circle, the oval semi-major axis is satellite orbit semi-major axis a, semi-minor axis is a | cos β |.
Can be obtained by the relation in Fig. 4, the half-shade angle α of ground shadow is
3) whether in step 3, interval in illumination current time satellite is calculated：
So in t, if the latitude argument of satellite meets following relation, in area of illumination.
ut-u0∈[0,π-α]∪[π+α,2π] (7)
Wherein, utIt is the latitude argument of satellite.
4) in step 4, whether 01 sensor that judgement is not blocked is shone
AD sample rate current results according to 01 sensor not blocked, On board computer can judge to be blocked satellite as
Whether other five quadrants beyond limit have the sun.
5) in step 5, judgement is blocked whether satellite quadrant is shone
According to the result of step 4, if in area of illumination, the 01 sensor no signal do not blocked, then presumption is blocked and defended
Astrology limit has sun signal.
In sum, after satellite unstability, attitude control system need to be according to where 01 formula sun sensor judges sunshine
The quadrant of satellite, the motor-driven guarantee windsurfing of the attitude of satellite is carried out to day state according to solar direction, it is ensured that whole energy source of star supply.Due to
Satellite health external applied load physical size is larger, a certain quadrant can be caused to block 01 formula sun sensor visual field, and the present invention can
With the 01 formula sensor and in-orbit recursion shade illumination ephemeris that are not blocked by judgement, joint judges solar azimuth.
Although present disclosure is discussed in detail by above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read the above, for of the invention
Various modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (5)
1. a kind of 01 formula sun sensor visual field is limited plane of illumination determination methods, it is characterised in that comprising procedure below：
Control software calculates the position that the sun is projected in satellite orbit face projection vector according to sun ephemeris on step one, star；
Control software calculates the position interval of the ground shadow on track on step 2, star；
Whether control software calculates current time satellite in illumination interval on step 3, star；
Control software judges whether the 01 formula sun sensor that is not blocked is shone on step 4, star, judge to be blocked satellite as
Whether other five quadrants beyond limit have illumination；
Control software judges to be blocked whether satellite quadrant is shone on step 5, star：If do not blocked during in area of illumination
01 formula sun sensor no signal, then judge that being blocked satellite quadrant has sun signal.
2. 01 formula sun sensor visual field described in claim 1 is limited plane of illumination determination methods, it is characterised in that in step one
In, ask for the corresponding latitude argument of projection of the solar vector on satellite orbit face
Wherein, i, Ω represent the orbit inclination angle and right ascension of ascending node of satellite respectively；
Sun Dec αs, declination δsFor
δs=arcsin (sin Λ sin ε)
Wherein, Λ, ε represent solar celestial longitude and yellow red angle respectively.
3. 01 formula sun sensor visual field described in claim 2 is limited plane of illumination determination methods, it is characterised in that in step 2
In, the half-shade angle α for asking for ground shadow is
Wherein, ReIt is earth radius length；Satellite orbit projects formation ellipse, the half of the ellipse on the vertical face of solar vector
Major axis is satellite orbit semi-major axis a, semi-minor axis is a | cos β |.
Angle between satellite orbit face normal negative sense and solar vector
β=arccos (Ssat·Ssun)
=arccos (- cos δssin i sinΔα-cos i sinδs)
Coordinate of the satellite orbit face normal direction under inertial system J2000
Ssat=-[sin Ω sin i-cos Ω sin i cos i]T
Coordinate of the solar vector under inertial system J2000
Ssun=[cos αscosδs sinαscosδs sinδs]T。
4. 01 formula sun sensor visual field described in claim 3 is limited plane of illumination determination methods, it is characterised in that
In step 3, the latitude argument of current time t satellite meets following relation, judges that current time satellite is in area of illumination
Between：
ut-u0∈[0,π-α]∪[π+α,2π]
Wherein, utIt is the latitude argument of satellite.
5. 01 formula sun sensor visual field described in claim 1 or 4 is limited plane of illumination determination methods, it is characterised in that
In step 4, On board computer judges to be hidden according to the AD sample rate current results of the 01 formula sun sensor not blocked
Whether other five quadrants beyond gear satellite quadrant have illumination.
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