CN106404002B - A kind of in-orbit bearing calibration of high-precision imaging moment - Google Patents
A kind of in-orbit bearing calibration of high-precision imaging moment Download PDFInfo
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- CN106404002B CN106404002B CN201610946528.7A CN201610946528A CN106404002B CN 106404002 B CN106404002 B CN 106404002B CN 201610946528 A CN201610946528 A CN 201610946528A CN 106404002 B CN106404002 B CN 106404002B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
Abstract
The present invention provides a kind of in-orbit bearing calibration of high-precision imaging moment, comprising: step 1, the imaging moment point by infusing on ground is obtained on star；Step 2, according to the imaging moment of acquisition point, the satellite information forecast using GPS receiver obtains the position and speed of the moment satellite；Step 3, according to the imageable target point position infused on position and speed combined ground, correction time deviation is calculated；Step 4, revised imaging moment is calculated；Step 5, judge whether correction time deviation meets required precision, using the time of step 4 as imaging moment point if being unsatisfactory for, repeat step 2 ~ step 5；Imaging moment correction calculates and terminates if meeting, and is switched on and is imaged with revised imaging moment.Operand very little of the invention is realized convenient for spaceborne computer, can be applied to satellite normal work period high-precision imaging moment and determines, provides high-precision time reference for imaging.
Description
Technical field
The invention belongs to satellite high-precision technical field of imaging, and in particular to a kind of in-orbit correction side of high-precision imaging moment
Method.
Background technique
The imaging precision requirement of present satellite is higher and higher, and corresponding every factor for influencing imaging precision requires to carry out
Optimize and to minimize the error.The factor of one of them influence imaging precision is exactly the accurate determination of imaging moment.
According to the floor planning of satellite task, will upload it is more everyday in imageable target points geographic latitude and longitude with it is corresponding
Imaging booting moment tk.Due to ground rail recursion error, the corresponding imaging optimal boot time of imageable target point there may be
Certain error needs to be corrected the booting moment on star, obtains optimal observation effect with expectation.Current shortage can
The method that high-precision imaging moment is calculated by optimizing correction measure in terms of software design on star, the precision of existing method
Not high or algorithm is complicated, is unfavorable for the realization of spaceborne computer.
Summary of the invention
In order to which in-orbit high precision computation obtains the optimal imaging moment, optimal observation effect, present invention benefit are obtained with expectation
With the data of satellite in-orbit kinetic characteristic and GPS, the algorithm based on setting provides a kind of in-orbit correction of high-precision imaging moment
Method.
In order to achieve the above object, technical program of the present invention lies in provide a kind of in-orbit correction side of high-precision imaging moment
Method includes the following steps:
Step 1, the imaging moment point by infusing on ground is obtained on star；
Step 2, according to the imaging moment of acquisition point, the satellite information forecast using GPS receiver obtains the moment satellite
Position and speed；
Step 3, according to the imageable target point position infused on position and speed combined ground, correction time deviation is calculated；
Step 4, revised imaging moment is calculated；
Step 5, judge whether correction time deviation meets required precision, if being unsatisfactory for using the time of step 4 as at
As moment point, step 2~step 5 is repeated；Imaging moment correction calculates and terminates if meeting, and is switched on revised imaging moment
Imaging.
The in-orbit bearing calibration of high-precision imaging moment of the present invention is carried out on star using GPS parameter due to taking
The calculation method of correction imaging time deviation, solving the planning of ground long-range mission, there are the corresponding imaging of imageable target point is best
The problem of available machine time, there may be certain errors solves on star if autonomous long-term calculate may need very macrooperation amount
Problem, this method calculate simply, are suitable for independently realizing on star, and modified precision can achieve ms grades, achieve and utilize amendment
The moment be switched on applied to high-precision satellite booting imaging direction benchmark beneficial effect.
Detailed description of the invention
Fig. 1 is the flow diagram of the in-orbit bearing calibration of high-precision imaging moment of the present invention.
Specific embodiment
The relative theory of the specific embodiment of the invention is first introduced below:
Doppler centroid fDIt is defined as
In formula: λSARFor load operation wavelength；For the velocity vector of satellite relative target point；R is satellite relative target point
Position vector；R is the distance of satellite relative target point.
Wherein,
R=Rs-Rt (2)
In formula: RsPosition vector for satellite with respect to the earth's core；RtPosition vector for imageable target point with respect to the earth's core.
After satellite in orbit carries out two-dimentional guiding, the Doppler frequency that theoretically center of antenna is directed toward opposite imaging point is zero,
I.e. optimal imaging point is relative position and the speed Relative vertical of satellite and target point.Therefore, the purpose of imaging moment correction
It is to correct the imaging moment point of floor planning, finally makes imaging momentIt is orthogonal with R, i.e.,
Inner orbit recursion error was little due to more days, and the booting moment after predetermined booting moment and correction is not much different, small
It is interior in this time frame in 1s, velocity vector can be considered as constant value.In the case where ground is admittedly, designing near the booting moment in Δ t
Satellite position can be expressed as
Rs=R0+V0Δt (4)
In formula, R0And V0The satellite position and velocity vector that moment GPS respectively corresponding with booting is uploaded is provided.RtBy upper
Position vector that the target point longitude and latitude of biography is converted to indicates.Ground is that lower target spot speed is 0 admittedly, thenTo upload booting pair
The satellite velocity vector for answering moment GPS to provide, i.e. V0。
These variables are substituted into formula (3), are obtained
V0·(R0+V0·Δt-Rt)=0 (5)
Then correction time is
Wherein, R0、V0The GPS data offer of imaging moment point is provided by corresponding to；RtBy being turned by target geographic longitude and latitude
Position vector under the ground of chemical conversion is admittedly indicates.
Imaging moment t after correction1=t0+Δt。
Due to using the approximation of speed in above-mentioned correcting mode, there is certain deviation in primary amendment certainly, to
Seek higher time complexity curve precision, it is necessary to carry out successive ignition amendment.
Find out from above-mentioned calculation method, the operand very little at high-precision imaging amendment moment is calculated using this method, it is spaceborne
Computer is easily achieved.
As shown in Figure 1, the in-orbit bearing calibration of high-precision imaging moment of the present invention, includes the following steps:
Step 1, the imaging moment point t by infusing on ground is obtained on stark, moment point tkWhen to need modified imaging
Punctum；
Step 2, according to the imaging moment of acquisition point tkWith the satellite information of GPS receiver forecast, the t is obtainedkMoment satellite
Position and speed Rk、Vk。
Step 3, according to tkPosition vector R of the moment satellite with respect to the earth's corekWith velocity vector Vk, infuse on combined ground at
Position vector R as target point with respect to the earth's coret, calculate correction time
Step 4, imaging moment point t after correcting is calculatedk=tk+Δtk；
Step 5, judge Δ tkWhether required precision is met.If time precision is unsatisfactory for requiring, step 4 is calculated
Time (tkValue) as modified imaging moment point is needed, return step 2 simultaneously re-execute the steps 2~step 5, carries out next
Secondary iterated revision calculates；Otherwise imaging moment correction calculates and terminates, the time (t that step 4 is calculated at the end ofkValue) conduct
Revised high-precision imaging moment point, booting imaging at this moment on star.
In conclusion method of the invention calculates simple and flexible, can be applied to satellite work normally period it is high-precision at
The picture moment determines, provides high-precision time reference for imaging.
It is discussed in detail although the contents of the present invention have passed through 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 above content, for of the invention
A variety of modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (1)
1. a kind of in-orbit bearing calibration of high-precision imaging moment, which comprises the steps of:
Step 1, the imaging moment point t by infusing on ground is obtained on stark, as the modified imaging moment point of needs；
Step 2, according to the imaging moment of acquisition point tkWith the satellite information of GPS receiver forecast, t is respectively obtainedkMoment satellite phase
To the position vector R in the earth's corekWith velocity vector Vk；
Step 3, position vector R of the imageable target point infused on combined ground with respect to the earth's coret, calculate correction time:
Step 4, t is calculatedk=tk+ΔtkAs revised imaging moment point；
Step 5, judge Δ tkWhether time precision requirement is met；If meeting the requirements, imaging moment correction, which calculates, to be terminated, with knot
The t that step 4 is calculated when beamkValue boots up imaging as revised imaging moment point；
If being unsatisfactory for requiring, enter next iteration corrected Calculation: the t that step 4 is calculatedkValue is modified as needing
Imaging moment point, substitutes into the step 2 of next iteration corrected Calculation, and re-execute the steps 2~step 5.
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Citations (3)
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|---|---|---|---|---|
| CN103323029A (en) * | 2013-06-18 | 2013-09-25 | 北京空间飞行器总体设计部 | Method for testing error of initial imaging moment of satellite remote sensing camera |
| CN105823485A (en) * | 2016-04-25 | 2016-08-03 | 航天东方红卫星有限公司 | Time planning method of satellite calibration for moon |
| CN105928525A (en) * | 2016-04-25 | 2016-09-07 | 航天东方红卫星有限公司 | Attitude determination method for satellite in calibration relative to moon |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103323029A (en) * | 2013-06-18 | 2013-09-25 | 北京空间飞行器总体设计部 | Method for testing error of initial imaging moment of satellite remote sensing camera |
| CN105823485A (en) * | 2016-04-25 | 2016-08-03 | 航天东方红卫星有限公司 | Time planning method of satellite calibration for moon |
| CN105928525A (en) * | 2016-04-25 | 2016-09-07 | 航天东方红卫星有限公司 | Attitude determination method for satellite in calibration relative to moon |
Non-Patent Citations (1)
| Title |
|---|
| "高分一号"卫星遥感成像特性;陆春玲，等，;《航天返回与遥感》;20140831;第35卷(第4期);第67-73页 |
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