CN108548528B - The in-orbit image quality adjustment method of quick satellite and fexible unit - Google Patents
The in-orbit image quality adjustment method of quick satellite and fexible unit Download PDFInfo
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Abstract
The present invention relates to a kind of in-orbit image quality adjustment method of agility satellite and fexible units, belong to agile satellite imagery technical field, this method and fexible unit are by repeatedly focusing to quick satellite load front end optical system with a fixed step size in focusing section, and Utilization assessment function determines optimal position of focal plane, realize the autonomous focusing to the in-orbit picture quality of quick satellite, after completing autonomous focusing, image after focusing is obtained again, and it takes a drift, the image planes of quick satellite load front end optical system are adjusted according to drift angle, realize the autonomous bias current adjusting to the in-orbit picture quality of quick satellite.The present invention, which passes through quick satellite platform and stablizes the multiple shooting at moment, can be achieved at the same time and independently focuses on star and bias current adjusting, optimal position of focal plane information and bias current angle information are more easily obtained using image calculation, complete the in-orbit picture quality adjustment of quick satellite, traditional complicated adjustment mode is avoided, provides guarantee for the acquisition of high-resolution remote sensing image.
Description
Technical field
The present invention relates to agile satellite imagery technical fields, adjust more particularly to a kind of quick in-orbit picture quality of satellite
Method and fexible unit.
Background technique
The quick in-orbit picture quality adjustment of satellite is to ensure the committed step of aerospace optical remote sensing system imaging quality, mainly
It is related to focusing and two processes of bias current adjusting.During satellite launch lift-off, the series of factors such as vibration, pressure, temperature are direct
Cause the defocus problem of load optical system；Satellite in orbit after, due to by satellite own orbit movement and earth rotation
Etc. factors influence, ground scenery imaging system focal plane picture exist simultaneously vertical rail Xiang Yuyan rail to as move, formed drift angle.
The presence of defocus and drift angle directly results in the degeneration of imaging system image quality, influences the acquisition of high-resolution remote sensing image.Cause
This, the research for the in-orbit autonomous picture quality adjustment technology of quick satellite is particularly significant.
At present in China, the work of the quick in-orbit picture quality adjustment of satellite is still complicated and cumbersome.For image matter
Autonomous focusing in amount adjustment, is usually preconditioned first with the estimated value of ground simulation, after satellier injection, passes through data
Under come into row artificial judgment, repeatedly adjusted by experience and be placed on optimum state, but this method process is cumbersome, relied on artificial dry
In advance, efficiency is lower.For the autonomous bias current adjusting in picture quality adjustment, current method predominantly passes through scenery coordinate to image planes
Multiple coordinate transform between coordinate calculates the shifting of transverse and longitudinal picture and drift angle under present satellites posture track condition, passes through drift angle
Real-time resolving and adjustment realize image shift compensation, but the process model is sufficiently complex, and efficiency is lower.
Summary of the invention
Based on this, it is necessary to autonomous focusing and autonomous bias current adjusting when being adjusted for the current quick in-orbit picture quality of satellite
The lower problem of efficiency provides a kind of in-orbit image quality adjustment method of quick satellite and fexible unit.
To solve the above problems, the invention adopts the following technical scheme:
A kind of in-orbit image quality adjustment method of agility satellite, method includes the following steps:
Focusing section is determined according to the focal depth position of ground calibration；
It is at least focused three times with the first step-length to quick satellite load front end optical system in the focusing section,
And the image with overlapping region is obtained after each focusing, obtain image sequence；
Utilization assessment function carries out image quality evaluation to described image sequence, determines optimal imaging focal plane position section；
Judge whether the optimal imaging focal plane position section is greater than default focusing accuracy threshold value, if so, described in adjustment
First step-length to the second step-length, and second step-length is less than first step-length, and with described the in the focusing section
Two step-lengths at least focus to the quick satellite load front end optical system three times, until the optimal imaging focal plane position
Section is less than or equal to the default focusing accuracy threshold value；
Determine that focal plane corresponding to the maximum value of the evaluation function is optimal in the optimal imaging focal plane position section
Position of focal plane, and the image planes of the quick satellite load front end optical system are adjusted to the optimal position of focal plane；
Obtain the focusing that at least two width that the quick satellite load front end optical system is continuously shot have overlapping region
Image afterwards, image sequence after being focused；
The first mismatch information of image sequence after the focusing, the first mismatch information packet are calculated using image registration method
It includes the first vertical rail and prolongs rail to amount of mismatch to amount of mismatch and first；
Calculate the second mismatch information caused by quick satellite orbit motion, second mismatch information include the second vertical rail to
Amount of mismatch and second prolongs rail to amount of mismatch；
The practical mismatch information of the quick satellite is calculated according to first mismatch information and second mismatch information,
And it is taken a drift according to the practical mismatch information；The practical mismatch information includes that practical vertical rail prolongs to amount of mismatch and actually
Rail is to amount of mismatch, and the reality rail that hangs down to amount of mismatch is equal to the described first vertical rail to amount of mismatch and the described second vertical rail to mismatch
Amount difference, it is described actually prolong rail to amount of mismatch be equal to described first prolong rail to amount of mismatch with described second prolong rail to amount of mismatch it
Difference, the tangent function value of the drift angle are equal to the reality and hang down rail to amount of mismatch and the rail that actually prolongs to the ratio between amount of mismatch；
Judge whether the drift angle is more than or equal to default drift angle adjustment threshold value, if so, according to the bias current
Angle adjusts the image planes of the quick satellite load front end optical system.
Correspondingly the present invention also proposes that the quick satellite based on the in-orbit image quality adjustment method of above-mentioned quick satellite is in-orbit
Picture quality adjusts fexible unit, which includes image capture module, imaging resolving module, focusing component and bias current adjusting group
Part, described image acquisition module connects with quick satellite load front end optical system, the imaging resolving module respectively with it is described
Image capture module, the focusing component are connected with the bias current adjusting component, the focusing component and the bias current adjusting component point
It is not connect with described image acquisition module；
Described image acquisition module is used to obtain image from the quick satellite load front end optical system, and will acquire
Described image sequence and the focusing after image sequence be sent to the imaging and resolve module；
The imaging resolves module for determining the optimal position of focal plane and calculating the drift angle；
The focal depth position that the focusing component is used to be demarcated according to ground determines focusing section, and in the focusing section
It focuses to the quick satellite load front end optical system, and by the picture of the quick satellite load front end optical system
Face is adjusted to the optimal position of focal plane；
The bias current adjusting component is used to adjust the picture of the quick satellite load front end optical system according to the drift angle
Face.
The in-orbit image quality adjustment method of above-mentioned agility satellite and fexible unit pass through quick satellite platform and stablize the moment
Repeatedly independently focusing and bias current adjusting can be achieved at the same time on star in shooting, more easily obtains optimal coke using image calculation
Face location information and bias current angle information complete the in-orbit picture quality adjustment of quick satellite, avoid traditional complicated adjustment side
Formula provides guarantee for the acquisition of high-resolution remote sensing image.
Detailed description of the invention
Fig. 1 is the flow diagram of the one of embodiment of the quick in-orbit image quality adjustment method of satellite of the present invention；
Fig. 2 is the process signal of the one of specific embodiment of the quick in-orbit image quality adjustment method of satellite of the present invention
Figure；
Fig. 3 is the structural representation that the quick in-orbit picture quality of satellite of the present invention adjusts the one of embodiment of fexible unit
Figure.
Specific embodiment
Technical solution of the present invention is described in detail below in conjunction with attached drawing and preferred embodiment.
In one of the embodiments, as shown in Figure 1, the quick in-orbit image quality adjustment method of satellite includes following step
It is rapid:
S1 determines focusing section according to the focal depth position that ground is demarcated；
S2 at least focuses to quick satellite load front end optical system with the first step-length in focusing section three times, and
The image with overlapping region is obtained after each focusing, obtains image sequence；
S3 Utilization assessment function carries out image quality evaluation to image sequence, determines optimal imaging focal plane position section；
S4 judges whether optimal imaging focal plane position section is greater than default focusing accuracy threshold value, if so, the adjustment first step
It is long that and the second step-length is less than the first step-length to the second step-length, and in focusing section with the second step-length to quick satellite load before
End optical system is at least focused three times, until optimal imaging focal plane position section is less than or equal to default focusing accuracy threshold
Value；
S5 determines that focal plane corresponding to the maximum value of optimal imaging focal plane position section inner evaluation function is optimal focal plane position
It sets, and the image planes of quick satellite load front end optical system is adjusted to optimal position of focal plane；
After at least two width that the quick satellite load front end optical system of S6 acquisition is continuously shot have the focusing of overlapping region
Image, image sequence after being focused；
S7 calculates the first mismatch information of image sequence after focusing using image registration method；
S8 calculates the second mismatch information caused by quick satellite orbit motion；
S9 calculates the practical mismatch information of quick satellite according to the first mismatch information and the second mismatch information, and according to reality
Mismatch information takes a drift；
S10 judges whether drift angle is more than or equal to default drift angle adjustment threshold value, if so, being adjusted according to drift angle
The image planes of quick satellite load front end optical system.
Specifically, in the present embodiment, step S1 determines quick satellite load front end according to the focal depth position that ground is demarcated
The focusing section of optical system.
Determine focusing section after, in the focusing section, with the first step-length to quick satellite load front end optical system into
Row n times focusing (N >=3) and in-orbit fast imaging obtain once the image with overlapping region after each focusing, obtain tool altogether
There are the N width image of overlapping region, I1,I2,…IN, obtain image sequence.
After carrying out a series of quantizations, correction process to obtained image sequence, image I is resolved1,I2,…INOverlay region
Domain, Utilization assessment function carry out image quality evaluation to image sequence, determine optimal imaging focal plane position d1And d2, so that it is determined that optimal
Imaging focal plane position interval Δ d=d1-d2.Carried out in the present embodiment when image quality evaluation used evaluation function can there are many
Selection, such as the sum of existing frequently-used gradient energy function, Laplace function, grey scale difference absolute value function etc. can also be with
Evaluation function is customized according to different application scenarios.The selection of evaluation function is not the emphasis of invention in the present invention, but no matter
Which kind of evaluation function to achieve the purpose that focusing all in protection scope of the present invention using method and step scheme of the invention using
It is interior.
After determining optimal imaging focal plane position section, in step s 4, whether the optimal imaging focal plane position section is judged
Greater than default focusing accuracy threshold value Δ d', if Δ d≤Δ d', thens follow the steps S5；If Δ d > Δ d', return step S2, and
First step-length is adjusted to the second step-length, and the second step-length is less than the first step-length, such as the half of a length of first step-length of second step,
N times focusing (N >=3) are carried out to quick satellite load front end optical system with the second step-length in focusing section, obtain focusing step
Long image sequence adjusted, Utilization assessment function carry out image quality evaluation to focusing step-length image sequence adjusted, again really
Fixed optimal imaging focal plane position section, until optimal imaging focal plane position section is less than or equal to default focusing accuracy threshold value,
That is Δ d≤Δ d', stops the adjustment of focusing step-length, and executes step S5.
It is burnt to meet the optimal imaging of Δ d≤Δ d' condition after optimal imaging focal plane position section meets Δ d≤Δ d'
Focal plane corresponding to the maximum value of face position section inner evaluation function is optimal position of focal plane, by quick satellite load front-end optical
The image planes of system adjust the autonomous focusing so far completed to optimal position of focal plane to the in-orbit picture quality of quick satellite.
After completing autonomous focusing, step S6 obtains at least two width that quick satellite load front end optical system is continuously shot
Image after focusing with overlapping region, image sequence after being focused.
After carrying out a series of quantizations, correction process to image sequence after obtained focusing, the overlapping region of image is resolved, is walked
Rapid S7 calculates the first mismatch information of image sequence after focusing using image registration method, wherein the first mismatch information is hung down including first
Rail prolongs rail to amount of mismatch to amount of mismatch and first.Image registration method in the present embodiment for calculating image mismatch information can have
Multiple choices, such as existing frequently-used cross-correlation method, shadow matching method, phase correlation method, SUSAN Operator Method, SIFT Operator Method
Etc. a series of classic algorithms and it is correspondingly improved and innovates algorithm.The selection of method for registering images is not emphasis in the present invention,
But no matter which kind of method for registering images is applied to achieve the purpose that bias current adjusting all in this hair using method and step scheme of the invention
In bright protection scope.
The second mismatch information after focusing caused by the quick satellite platform track movement of step S8 calculating between image, wherein
Second mismatch information prolongs rail to amount of mismatch to amount of mismatch and second including the second vertical rail.
In step s 9, the second mismatch being calculated according to step S7 the first mismatch information being calculated and step S8
Information calculates the practical mismatch information of quick satellite, and is taken a drift β according to practical mismatch information.
For example, scheming after obtaining two width that quick satellite load front end optical system is continuously shot there is the focusing of overlapping region
As F1And F2, exchange defocused image F1And F2After carrying out a series of quantizations, correction process, the overlapping region of image is resolved, figure is utilized
As image F after registration method calculating focusing1And F2The first mismatch information, wherein the first mismatch information include first laterally (hang down rail
To) amount of mismatch x1With first longitudinal direction (prolong rail to) amount of mismatch y1；After calculating two width focusing caused by quick satellite platform track movement
Image F1And F2Between the second mismatch information, wherein the second mismatch information includes second lateral (hang down to rail to) amount of mismatch x2With second
Longitudinal (prolong rail to) amount of mismatch y2；The practical mismatch letter of quick satellite is calculated according to the first mismatch information and the second mismatch information
Breath, wherein practical mismatch information prolongs rail to amount of mismatch Δ x and actually to amount of mismatch Δ y including practical vertical rail, and the rail that actually hangs down
It is equal to the first vertical rail to amount of mismatch and the second vertical rail to the difference of amount of mismatch to amount of mismatch, actually prolongs rail and prolong to amount of mismatch equal to first
Rail prolongs difference of the rail to amount of mismatch to amount of mismatch and second, i.e.,
Δ x=x1-x2, Δ y=y1-y2
After calculating the practical mismatch information for obtaining quick satellite, taken a drift β according to practical mismatch information, specifically,
The tangent function value of drift angle β is equal to practical vertical rail and prolongs rail to the ratio between amount of mismatch, i.e., to amount of mismatch and actually
β=arctan (Δ x/ Δ y)
Finally, step S10 judge drift angle β whether be more than or equal to default drift angle adjustment threshold value beta ', if β >=β ',
The image planes of quick satellite load front end optical system are adjusted, according to drift angle β then to realize to the in-orbit picture quality of quick satellite
Autonomous bias current adjusting；If β < β ', return step S6, reacquire what quick satellite load front end optical system was continuously shot
At least two width are with image after the focusing of overlapping region, image sequence after being focused, and circulation executes step S6 to S10.
The in-orbit image quality adjustment method of quick satellite that above-described embodiment is proposed is used for the in-orbit automatic tune of quick satellite
Burnt and automatic deflection adjusting stream, this method, which passes through quick satellite platform, which stablizes the multiple shooting at moment, can be achieved at the same time on star from homophony
Burnt and bias current adjusting more easily obtains optimal position of focal plane information and bias current angle information using image calculation, completes quick
The prompt in-orbit picture quality adjustment of satellite, avoids traditional complicated adjustment mode, mentions for the acquisition of high-resolution remote sensing image
It has supplied to ensure.
As a kind of specific embodiment, quick satellite load front-end optical system is adjusted according to drift angle in step S10
It is further comprising the steps of after the image planes of system:
S11 judges whether to receive stopping imaging instruction, if so, stopping obtaining quick satellite load front end optical system
Image after the focusing being continuously shot；If it is not, then reacquiring quick satellite load front end optical system is continuously shot at least two
Width is with image after the focusing of overlapping region, image sequence after being focused.
In the present embodiment, as shown in Fig. 2, adjusting quick satellite load front-end optical according to drift angle in step S10
After the image planes of system, judge whether the stopping imaging instruction for receiving ground control centre transmission, if receiving stopping imaging
Instruction then stops obtaining image after the focusing that quick satellite load front end optical system is continuously shot；If according to drift angle tune
It is not received by stopping imaging instruction after the image planes of whole agility satellite load front end optical system, then re-execute the steps S6 and obtains
At least two width for taking quick satellite load front end optical system to be continuously shot are focused with image after the focusing of overlapping region
Image sequence afterwards, entrance autonomous bias current adjusting process next time.
Meanwhile the present invention also proposes that a kind of quick satellite based on the in-orbit image quality adjustment method of above-mentioned quick satellite exists
Rail picture quality adjusts fexible unit, in one of the embodiments, as shown in figure 3, the fexible unit includes Image Acquisition mould
Block 100, imaging resolve module 200, focusing component 300 and bias current adjusting component 400, and image capture module 100 and quick satellite carry
Lotus front end optical system 500 connect, imaging resolve module 200 respectively with image capture module 100, focusing component 300 and tuningout
It flows component 400 to connect, focusing component 300 and bias current adjusting component 400 are connect with image capture module 100 respectively, and the present embodiment is logical
Cross image capture module 100, imaging resolves module 200, focusing component 300 and 400 4 part of bias current adjusting component and cooperated jointly
At the in-orbit picture quality adjustment of quick satellite.
In the present embodiment, image capture module 100 is used to obtain from quick satellite load front end optical system 500 and scheme
Picture, and image sequence is sent to imaging resolving module 200 after the image sequence that will acquire and focusing.Preferably, Image Acquisition
Module 100 includes focal plane unit, planar array detector and image forming process unit, more efficiently from quick satellite load front end light
System 500 obtains image.
Imaging resolves module 200 for determining optimal position of focal plane and taking a drift.Specifically, imaging resolves module
200, which pass through image capture module 100, obtains the image with overlapping region after focusing every time, obtains image sequence；Utilization assessment
Function carries out image quality evaluation to image sequence, determines optimal imaging focal plane position section；Judge optimal imaging focal plane position section
Whether default focusing accuracy threshold value is greater than, if so, focusing component 300 adjusts the first step-length to the second step-length, and the second step-length
At least three are carried out to quick satellite load front end optical system 500 with the second step-length less than the first step-length, and in focusing section
Secondary focusing, until imaging resolves module 200 and judges that optimal imaging focal plane position section is less than or equal to default focusing accuracy threshold
Value；Imaging resolves module 200 and determines that focal plane corresponding to the maximum value of optimal imaging focal plane position section inner evaluation function is most
Excellent position of focal plane.Meanwhile resolving module 200 is imaged and is also used to obtain quick satellite load front end by image capture module 100
At least two width that optical system 500 is continuously shot are with image after the focusing of overlapping region, image sequence after being focused；It utilizes
Image registration method calculates the first mismatch information of image sequence after focusing；Calculate the second mismatch caused by quick satellite orbit motion
Information；The practical mismatch information of quick satellite is calculated according to the first mismatch information and the second mismatch information, and according to practical mismatch
Information takes a drift.
The focal depth position that focusing component 300 is used to be demarcated according to ground determines focusing section, and to quick in focusing section
Prompt satellite load front end optical system 500 is focused, and the image planes of quick satellite load front end optical system 500 are adjusted
To optimal position of focal plane.Focusing component 300 resolves module 200 with imaging respectively and image capture module 100 is connect, focusing component
300 by formulating the mobile mesh for reaching realization adjustment optical camera depth of focus of image planes in step size controlling image capture module 100
, focusing component 300 may include focusing frame, worm reduction box, lead screw assembly, straight-line motion mechanism, stepper motor
With encoder etc..
Bias current adjusting component 400 is used to adjust the image planes of quick satellite load front end optical system 500 according to drift angle.Tuningout
By formulating, image planes in bias current angle control image acquisition module 100 are mobile to reach realization adjustment optics phase to stream component 400
The purpose of machine bias current, bias current adjusting component 400 include bias current adjusting pedestal, pinboard, driving assembly, slide block assembly, arc guide rail axis
Module, encoder component etc..
It is in-orbit certainly that the in-orbit picture quality adjustment fexible unit of the quick satellite that above-described embodiment is proposed is used for quick satellite
Dynamic focusing and automatic deflection adjusting stream, the device can be achieved at the same time on star certainly by the multiple shooting that quick satellite platform stablizes the moment
Homophony is burnt and bias current adjusting, introducing imaging resolve module, more easily obtains optimal position of focal plane using image calculation and believes
Breath and bias current angle information complete the in-orbit picture quality adjustment of quick satellite, avoid traditional complicated adjustment mode, be high score
The acquisition of resolution remote sensing images provides guarantee.
As a kind of specific embodiment, image capture module 100 is also used to judge whether to receive stopping imaging and refers to
It enables, if receiving stopping imaging instruction, image capture module 100 stops obtaining quick satellite load front end optical system 500
Image after the focusing being continuously shot；If the judgement of image capture module 100 is not received by stopping imaging instruction, Image Acquisition mould
Block 100 reacquires the focusing that at least two width that quick satellite load front end optical system 500 is continuously shot have overlapping region
Image afterwards, image sequence after being focused, entrance autonomous bias current adjusting process next time.
Each technical characteristic of embodiment described above can be combined arbitrarily, for simplicity of description, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, all should be considered as described in this specification.
The embodiments described above only express several embodiments of the present invention, and the description thereof is more specific and detailed, but simultaneously
It cannot therefore be construed as limiting the scope of the patent.It should be pointed out that coming for those of ordinary skill in the art
It says, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to protection of the invention
Range.Therefore, the scope of protection of the patent of the invention shall be subject to the appended claims.
Claims (8)
1. a kind of in-orbit image quality adjustment method of agility satellite, which comprises the following steps:
Focusing section is determined according to the focal depth position of ground calibration；
It is at least focused three times with the first step-length to quick satellite load front end optical system in the focusing section, and
The image with overlapping region is obtained after focusing every time, obtains image sequence；
Utilization assessment function carries out image quality evaluation to described image sequence, determines optimal imaging focal plane position section；
Judge whether the optimal imaging focal plane position section is greater than default focusing accuracy threshold value, if so, adjustment described first
Step-length is to the second step-length, and second step-length is less than first step-length, and with the second step in the focusing section
It is long at least to be focused three times to the quick satellite load front end optical system, until the optimal imaging focal plane position section
Less than or equal to the default focusing accuracy threshold value；
Determine that focal plane corresponding to the maximum value of the evaluation function is optimal focal plane in the optimal imaging focal plane position section
Position, and the image planes of the quick satellite load front end optical system are adjusted to the optimal position of focal plane；
Scheme after obtaining at least two width that the quick satellite load front end optical system is continuously shot there is the focusing of overlapping region
Picture, image sequence after being focused；
Calculate the first mismatch information of image sequence after the focusing using image registration method, first mismatch information includes the
One vertical rail prolongs rail to amount of mismatch to amount of mismatch and first；
Calculate the second mismatch information caused by quick satellite orbit motion, second mismatch information includes the second vertical rail to mismatch
Amount and second prolongs rail to amount of mismatch；
The practical mismatch information of the quick satellite, and root are calculated according to first mismatch information and second mismatch information
It takes a drift according to the practical mismatch information；The practical mismatch information include practical vertical rail prolong to amount of mismatch and actually rail to
Amount of mismatch, and the reality hang down rail to amount of mismatch be equal to the described first vertical rail to amount of mismatch and the described second vertical rail to amount of mismatch it
Difference, it is described actually prolong rail and be equal to described first to amount of mismatch prolong rail and prolong difference of the rail to amount of mismatch, institute to amount of mismatch and described second
The tangent function value for stating drift angle is equal to the reality and hangs down rail to amount of mismatch and the rail that actually prolongs to the ratio between amount of mismatch；
Judge whether the drift angle is more than or equal to default drift angle adjustment threshold value, if so, according to the drift angle tune
The image planes of the whole quick satellite load front end optical system.
2. the in-orbit image quality adjustment method of agility satellite according to claim 1, which is characterized in that described according to institute
It is further comprising the steps of after stating the image planes step that drift angle adjusts the quick satellite load front end optical system:
Judge whether to receive stopping imaging instruction, if so, stopping obtaining the quick satellite load front end optical system company
Image after the focusing of continuous shooting；It is continuously shot at least if it is not, then reacquiring the quick satellite load front end optical system
Two width are with image after the focusing of overlapping region, image sequence after being focused.
3. the in-orbit image quality adjustment method of agility satellite according to claim 1 or 2, which is characterized in that
The half of a length of first step-length of second step.
4. the in-orbit image quality adjustment method of agility satellite according to claim 1 or 2, which is characterized in that
The evaluation function is any one in the sum of gradient energy function, Laplace function, grey scale difference absolute value function
Kind.
5. the in-orbit image quality adjustment method of agility satellite according to claim 1 or 2, which is characterized in that
It is in cross-correlation method, shadow matching method, phase correlation method, SUSAN Operator Method and SIFT Operator Method that described image, which is registrated method,
Any one.
6. a kind of agility based on the in-orbit image quality adjustment method of quick satellite as described in claim 1 to 5 any one
The in-orbit picture quality of satellite adjusts fexible unit, which is characterized in that resolves module, focusing group including image capture module, imaging
Part and bias current adjusting component, described image acquisition module are connect with quick satellite load front end optical system, and the imaging resolves mould
Block is connect with described image acquisition module, the focusing component and the bias current adjusting component respectively, the focusing component and described
Bias current adjusting component is connect with described image acquisition module respectively；
Described image acquisition module is used to obtain image, and the institute that will acquire from the quick satellite load front end optical system
Image sequence is sent to the imaging resolving module after stating image sequence and the focusing；
The imaging resolves module for determining the optimal position of focal plane and calculating the drift angle；
The focal depth position that the focusing component is used to be demarcated according to ground determines focusing section, and to institute in the focusing section
It states quick satellite load front end optical system to focus, and by the image planes tune of the quick satellite load front end optical system
The optimal position of focal plane；
The bias current adjusting component is used to adjust the image planes of the quick satellite load front end optical system according to the drift angle.
7. the in-orbit picture quality of agility satellite according to claim 6 adjusts fexible unit, which is characterized in that
Described image acquisition module is also used to judge whether to receive stopping imaging instruction, if so, described image acquisition module
Stopping obtains image after the focusing that the quick satellite load front end optical system is continuously shot；If it is not, then described image acquires
Module reacquires the focusing that at least two width that the quick satellite load front end optical system is continuously shot have overlapping region
Image afterwards, image sequence after being focused.
8. the in-orbit picture quality of agility satellite according to claim 6 or 7 adjusts fexible unit, which is characterized in that
Described image acquisition module includes focal plane unit, planar array detector and image forming process unit.
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| CN113945218A (en) * | 2021-08-26 | 2022-01-18 | 中国空间技术研究院 | Agile remote sensing satellite in-orbit autonomous focusing method based on moon imaging |
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|---|---|---|---|---|
| CN101839977A (en) * | 2010-04-27 | 2010-09-22 | 中国科学院长春光学精密机械与物理研究所 | Simulation testing system and method for real-time adjusting drift closed loop by space optical remote sensor |
| CN103248838A (en) * | 2013-05-17 | 2013-08-14 | 中国科学院长春光学精密机械与物理研究所 | CMOS camera image bias adjusting method based on digital field TDI (time delayed and integration) algorithm |
| CN106767705A (en) * | 2016-11-22 | 2017-05-31 | 航天恒星科技有限公司 | Imaging posture modeling method during a kind of Optical remote satellite point target observation mission is dynamic |
| CN107525492A (en) * | 2017-07-20 | 2017-12-29 | 航天东方红卫星有限公司 | A kind of drift angle simulating analysis suitable for quick earth observation satellite |
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2018
- 2018-04-10 CN CN201810317000.2A patent/CN108548528B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101839977A (en) * | 2010-04-27 | 2010-09-22 | 中国科学院长春光学精密机械与物理研究所 | Simulation testing system and method for real-time adjusting drift closed loop by space optical remote sensor |
| CN103248838A (en) * | 2013-05-17 | 2013-08-14 | 中国科学院长春光学精密机械与物理研究所 | CMOS camera image bias adjusting method based on digital field TDI (time delayed and integration) algorithm |
| CN106767705A (en) * | 2016-11-22 | 2017-05-31 | 航天恒星科技有限公司 | Imaging posture modeling method during a kind of Optical remote satellite point target observation mission is dynamic |
| CN107525492A (en) * | 2017-07-20 | 2017-12-29 | 航天东方红卫星有限公司 | A kind of drift angle simulating analysis suitable for quick earth observation satellite |
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