CN107659776A - High-resolution satellite dynamic mobility prolonging exposure time method - Google Patents
High-resolution satellite dynamic mobility prolonging exposure time method Download PDFInfo
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- CN107659776A CN107659776A CN201710886486.7A CN201710886486A CN107659776A CN 107659776 A CN107659776 A CN 107659776A CN 201710886486 A CN201710886486 A CN 201710886486A CN 107659776 A CN107659776 A CN 107659776A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/70—Circuitry for compensating brightness variation in the scene
- H04N23/73—Circuitry for compensating brightness variation in the scene by influencing the exposure time
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/70—Circuitry for compensating brightness variation in the scene
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Abstract
High-resolution satellite dynamic mobility prolonging exposure time method, it is related to high-resolution satellite technical field of imaging, during solution agile satellite imagery, it is expected that imaging resolution is high and the time for exposure short integrations of the TDI CCD caused by series is more, the problem of IMC difficulty is high, the present invention carries out imaging task planning according to satellite orbit parameter and target longitude and latitude, then the flying speed of satellite and corresponding Imagewise exposure time are determined according to orbit parameter, and then required satellite accuracy of image motion compensation is determined by the time for exposure, finally judge whether satellite disclosure satisfy that the required precision, if meet, then imaging is performed according to above-mentioned program results；If not satisfied, pendulous compensator parameter after then adding one, calculates time for exposure and accuracy of image motion compensation again, until meeting to require.The inventive method is simple, reliable, easy, improves stability and the flexibility of high-resolution satellite imaging, realizes the purpose of optimal imaging.
Description
Technical field
The present invention relates to high-resolution satellite technical field of imaging, and in particular to a kind of high-resolution satellite dynamic mobility prolongs
Long time for exposure method.
Background technology
At present, for the resolution ratio of high-resolution earth observation satellite mostly in the range of meter level, imaging effect is not ideal enough.Defend
Star is in order to improve the imaging effect of camera, main using increase focal length or to reduce track both sides according to Optical System Design
Method.Because increase focal length can bring many difficulties to the development of camera, including design, process, cast and overall weight is excessive etc.
Problem, so usually taking the method for reducing satellite orbital altitude.But while satellite orbital altitude is reduced, Satellite Camera number
According to time for exposure can significantly reduce, it is to hinder orbit altitude to reduce so as to improving ground pixel resolution that the time for exposure, which reduces,
Bottleneck, it is mainly manifested in following two aspect：1st, the time for exposure, which reduces, makes the generation of TDI CCD driver' s timing waveforms increase difficulty；
2nd, the time for exposure reduces drive waveforms when influenceing carry load work, so as to influence the blur-free imaging of camera.Therefore, it is herein solution
This predicament, according to time for exposure and the relation of relative ground velocity, it is proposed that rear on the basis of original imaging posture to swing state machine
The method of dynamic compensation, while ensureing not reduce imaging resolution, the pressure of spaceborne each system, realization pair are significantly reduced again
The optimal selection of ground Imagewise exposure time.
The content of the invention
During the present invention is solves agile satellite imagery, it is expected that imaging resolution is high and the time for exposure is short caused by
The problem of TDI CCD integration series is more, IMC difficulty is high, there is provided during a kind of high-resolution satellite dynamic mobility prolonged exposure
Between method.
High-resolution satellite dynamic mobility prolonging exposure time method, this method are realized by following steps：
Step 1: satellite flight speed is determined according to orbit altitude；
Step 2: the satellite flight speed obtained according to step 1 calculates TDI CCD time for exposure；
Step 3: the time for exposure obtained according to step 2, calculates the accuracy of image motion compensation of satellite imagery；
Step 4: whether the accuracy of image motion compensation that judgment step three obtains is less than a TDI CCD pixel, if it is, meter
Calculation process terminates；If not, filling into rear pendulous compensator angle parameter, return to step one, until meeting satellite index request, realization is prolonged
The long time for exposure.
Beneficial effects of the present invention：The present invention mainly carries out imaging task rule according to satellite orbit parameter and target longitude and latitude
Draw, then determine the flying speed of satellite and corresponding Imagewise exposure time according to orbit parameter, so it is true by the time for exposure
Required satellite accuracy of image motion compensation is made, finally judges whether satellite disclosure satisfy that the required precision, if satisfied, then foundation
Above-mentioned program results performs imaging；If not satisfied, pendulous compensator parameter after then adding one, calculates the time for exposure and is mended as moving again
Precision is repaid, until meeting to require.
High-resolution imaging of the present invention is in order to obtain the high quality graphic of different target point, it is necessary to which TDICCD is in-orbit
Strict matching exposure is carried out, and high requirement is had also been proposed to the precision of satellite IMC system in exposure process, and then
Influence imaging definition.The present invention considers high-resolution and the high request to IMC system, it is proposed that puts afterwards motor-driven
Compensation policy, make it possible that space flight TDI CCD carry out high quality imaging to target point.Led in camera space low-light staring imaging
Domain and military project optical technical field provide a kind of motor-driven time for exposure computational methods of Intelligent Dynamic, and method is simple and easy, significantly
Improve the feasibility and image definition of high-resolution imaging.
Method of the present invention considers high-resolution and to IMC system from satellite image quality over the ground
The high request of system, had both remained high-resolution advantage, alleviated the pressure of satellite IMC system again.The inventive method carries
The stability of high high-resolution satellite imaging and flexibility, realize the purpose of optimal imaging.
Brief description of the drawings
Fig. 1 is the flow chart of high-resolution satellite dynamic mobility prolonging exposure time method of the present invention.
Embodiment
Embodiment one, illustrate present embodiment, high-resolution satellite dynamic mobility prolonging exposure time with reference to Fig. 1
Method, method are as follows：
Step 1：Satellite carries out imaging task planning according to orbit parameter and target longitude and latitude；
Step 2：Satellite flight speed is determined according to orbit altitude；
Step 3：The corresponding time for exposure is calculated according to satellite flight speed；
Step 4：By calculating the accuracy of image motion compensation needed for time for exposure analysis satellite imagery；
Step 5：If satellite disclosure satisfy that the accuracy of image motion compensation in step 3, calculating process terminates；If can not, need
Pendulous compensator angle parameter after adding oneThe satellite time for exposure is calculated again, is circulated successively, until meeting that satellite index will
Ask, calculating terminates.
Embodiment two, present embodiment are that the high-resolution satellite dynamic mobility described in embodiment one prolongs
The embodiment of long time for exposure method：
1st, (track half-court axle 6878.14km, orbital eccentricity 0, the rail of the sun-synchronous orbit six roots of sensation number according to where satellite
97.4 ° of road inclination, 90 ° of argument of perigee, 256.732 ° of right ascension of ascending node, 33 ° of true anomaly) and target point Changchun longitude and latitude
(125.32 °, 43.88 °), using STK softwares, imaging model of the satellite to target point is established, posture control system control satellite exists
To earth target point stablize sensing under J2000 inertial coodinate systems, and draw and change over time accordingly according to 2Hz cycle
Three-axis attitude information report.
2nd, when satellite trajectory meets target visual range, the projection of satellite flight on the ground is calculated according to orbit parameter
Speed vGround：
Wherein, M is earth quality, and G is gravitational constant, is definite value, and R is earth radius corresponding to satellite position, and H is
Satellite orbital altitude.Substitute into numerical computations and obtain the projection speed v of satellite flight on the groundGround=7.06km/s, is mapped to image planes
On speed be vPicture=0.0847m/s.
3rd, by analyzing satellite and camera parameter, camera optical system matching relationship is established, is calculated tight with TDI CCD cameras
The time for exposure of lattice registration：
Wherein, T is the time for exposure, and a is TDI CCD camera pixel dimensions, size 8.75um.Substitute into numerical computations and obtain T
=8.26 × 10-5s。
4th, during satellite imagery relative ground high-speed motion, it is necessary to carry out accurate IMC to camera.Utilize phase
Machine focal plane vector establishes image planes picture with attitude of satellite variation relation and moves computation model, passes through the derivation to position vector and optical system
The product of system focal length obtains image motion velocity vector, by satellite in the time for exposure surely as caused by attitudes vibration as shifting amount is no more than
One pixel, calculate accuracy of image motion compensation：
Wherein, ψc, it is satellite yaw angle,For satellite yaw rate, θcFor the satellite angle of pitch,For satellite angle of pitch speed
Degree,For satellite roll angle,For satellite roll angular speed, (g1,g2,g3) be camera focal plane initial position vector, it is such as burnt
Planar central point vector is (0,0,1).(c1,c2,c3) be attitudes vibration after position of focal plane diverse vector, position of focal plane is become
Change vector equation both sides to being multiplied by focal length f after t derivations and making t=0, then can obtain image planes image motion velocity vector：
5th, compared with the accuracy of image motion compensation of camera itself, if can meet, calculating terminates；If can not meet, defend
Pendulous compensator rate of pitch after star itself attitude control system control satellite increases by oneThe time for exposure of camera imaging is：
6th, repeat step 4-5, constantly increaseThe size of angle, form frame frequency departure and carry out feedback adjustment, Zhi Daoman
Toe mark demand, now, time for exposure are chosen optimal：
T'=0.216 × 10-3s
Obviously, above-described embodiment is only intended to clearly illustrate example, and is not the restriction to embodiment.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of change or
Change.There is no necessity and possibility to exhaust all the enbodiments.And the obvious change thus extended out or
Among changing still in the protection domain of the invention.
Claims (3)
1. high-resolution satellite dynamic mobility prolonging exposure time method, it is characterized in that, this method is realized by following steps：
Step 1: satellite flight speed is determined according to orbit altitude；
Step 2: the satellite flight speed obtained according to step 1 calculates TDI CCD time for exposure；
Step 3: the time for exposure obtained according to step 2, calculates the accuracy of image motion compensation of satellite imagery；
Step 4: whether the accuracy of image motion compensation that judgment step three obtains is less than a TDI CCD pixel, if it is, calculating
Journey terminates；If not, filling into rear pendulous compensator angle parameter, return to step one, until meeting satellite index request, realize and extend exposure
Between light time.
2. high-resolution satellite dynamic mobility prolonging exposure time method according to claim 1, it is characterised in that according to
Orbit parameter calculates the projection speed v of satellite flight on the groundGround：
In formula, M is earth quality, and G is gravitational constant, and R is earth radius corresponding to satellite position, and H is that satellite orbit is high
Degree.
3. high-resolution satellite dynamic mobility prolonging exposure time method according to claim 1, it is characterised in that satellite
Being imaged dynamic mobility prolonging exposure time computational methods is：Established using TDI CCD focal planes vectors and attitude of satellite variation relation
Image planes picture moves computation model, and image motion velocity is obtained by the derivation of focusing plane change in location vector and the product of optical system focal length
Vector, calculated by the way that satellite in the time for exposure is steady as caused by attitudes vibration as shifting amount is no more than a pixel.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108961319A (en) * | 2018-07-10 | 2018-12-07 | 中国科学院长春光学精密机械与物理研究所 | Analysis method of the twin-line array TDI space camera to dynamic airplane kinetic characteristic |
| CN111402340A (en) * | 2020-03-08 | 2020-07-10 | 中国科学院微小卫星创新研究院 | Imaging control system and method for earth observation satellite |
| CN115426455A (en) * | 2022-11-03 | 2022-12-02 | 季华实验室 | Image motion compensation mechanism of space camera and control method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108961319A (en) * | 2018-07-10 | 2018-12-07 | 中国科学院长春光学精密机械与物理研究所 | Analysis method of the twin-line array TDI space camera to dynamic airplane kinetic characteristic |
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| CN111402340A (en) * | 2020-03-08 | 2020-07-10 | 中国科学院微小卫星创新研究院 | Imaging control system and method for earth observation satellite |
| CN111402340B (en) * | 2020-03-08 | 2020-11-03 | 中国科学院微小卫星创新研究院 | Imaging control system and method for earth observation satellite |
| CN115426455A (en) * | 2022-11-03 | 2022-12-02 | 季华实验室 | Image motion compensation mechanism of space camera and control method thereof |
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Application publication date: 20180202 |