CN106291546A - A kind of video satellite expand areas imaging push away staring imaging method - Google Patents
A kind of video satellite expand areas imaging push away staring imaging method Download PDFInfo
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- CN106291546A CN106291546A CN201610675482.XA CN201610675482A CN106291546A CN 106291546 A CN106291546 A CN 106291546A CN 201610675482 A CN201610675482 A CN 201610675482A CN 106291546 A CN106291546 A CN 106291546A
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- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
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Abstract
The invention discloses a kind of video satellite expansion areas imaging pushes away solidifying formation method, the method is from the inferior position of traditional staring imaging limited coverage area, devise during staring imaging, satellite is stared and is introduced K value when following the tracks of imaging in the change of the attitude angle of body relative orbit coordinate system, optical axis is made to elapse the most forward, thus along rail direction, non-along rail direction imaging fabric width increase, it is achieved on a large scale cover imaging push away staring imaging.The inventive method is simple and reliable, easy, expands staring imaging scope, extends the application of video satellite.The present invention is that domestic first pushing away for expansion staring imaging scope proposition stares the fast and reliable method that pattern combines.
Description
Technical field
The present invention relates to Satellite Attitude Dynamics and kinesiology technical field, be specifically related to a kind of video satellite and be expanded into picture
Scope push away staring imaging method.
Background technology
The imaging pattern of remote sensing satellite includes optical mechaical scanning mode, push-scanning image and staring imaging." staring " of satellite becomes
As pattern refers to that satellite is during orbital precession, although the relative position relation of target area and satellite is continually changing, but
By adjusting attitude angle and the attitude angular velocity of satellite, the optical axis of the optics payload in satellite can be made the most dynamically to point to
Tellurian appointment scene regions, thus realize optics payload to the target continuous imaging in scene regions, this mode
Obtain more more multidate information than conventional satellite, be of value to raising signal to noise ratio, the phenomenon that can occur in Continuous Observation full filed, time
Between resolution the highest, be particularly suitable for observe dynamic object, analyze its temporal properties.This low cost video satellite is just special with it
One of the advantage developing direction being increasingly becoming space remote sensing field.But area array CCD field range is less, general only several public affairs
In, " stare " in-orbit although satellite realizes high temporal resolution by same target carries out " staring " imaging, but cover model
It is with limit.Staring imaging area coverage is only dependent upon optics load full filed angle, leverages satellite in orbit imaging and covers
Scope.So video satellite to there is observation swath limited, the inferior position of spreadability difference.
Summary of the invention
In order to solve fabric width and the problem of limited coverage area of tradition area array cameras staring imaging, the present invention proposes one
That plants video satellite expansion areas imaging pushes away staring imaging method.
The technical solution of the present invention is:
A kind of video satellite expand areas imaging push away staring imaging method, comprise the following steps:
During staring imaging, by optical axis passage forward at the uniform velocity, make along rail direction, non-along rail direction imaging fabric width
Increase.
In technique scheme, what upper video satellite expanded areas imaging pushes away concretely comprising the following steps of staring imaging method:
During staring imaging, control luffing angle θ ' by Satellite Attitude Control System and meet:
θ '=θ × K,
Wherein, θ is for staring luffing angle, and K is proportionality coefficient, meets | K | < 1；Then have:
L1=h × tg θ
L2=h × tg θ '
L3=L1-L2
Wherein, when L1 is satellite pitching θ angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, and L2 is satellite
During pitching θ ' angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, when L3 is satellite pitching θ ' angle optical axis center with
Distance between optical axis center during satellite pitching θ angle.
The present invention compared with prior art provides the benefit that:
What the video satellite of the present invention expanded areas imaging pushes away staring imaging method, has considered the maneuverability of satellite
And imaging capability, and satellite stares the attitude angle of body relative orbit coordinate system and the change of angular velocity when following the tracks of imaging；Foundation
Stare the attitude angle of satellite dynamic tracking imaging and the change of attitude angular velocity and the impact on imaging of the dynamic tracking precision, design
The setting of K value coefficient, makes traditional staring imaging be promoted to push away solidifying imaging mode, and method is simple, expands staring imaging
Scope.
The present invention is on the basis of video satellite staring imaging pattern, it is proposed that pushes away the mode of extension stared, does not change machine
Tool hardware mechanism, the method being stared satellite luffing angle by fine setting increases its coverage, can disposably monitor big model
Enclose target area, can realize along rail and non-push away, along rail, the picture that congeals into, being greatly expanded the video satellite application to regional imaging.
The present invention is that domestic first pushing away for expansion staring imaging scope proposition stares the fast and reliable method that pattern combines.
Accompanying drawing explanation
With detailed description of the invention, the present invention is described in further detail below in conjunction with the accompanying drawings.
Fig. 1 is for pushing away staring imaging pattern diagram.
Fig. 2 is for pushing away congeal into picture and staring imaging coverage schematic diagram.
Fig. 3 is the method schematic diagram that known K value pushes away solidifying image coverage area.
Fig. 4 is the method schematic diagram of the expectation coverage reckoning K value determining that satellite pushes away the picture that congeals into.
Detailed description of the invention
The invention thought of the present invention is: the video satellite of the present invention expands the staring imaging method that pushes away of areas imaging mainly
During staring imaging, optical axis elapses the most forward, makes along rail direction, non-increases along rail direction imaging fabric width, thus real
Cover the purpose of imaging the most on a large scale.The most as shown in Figure 1.
What the video satellite of the present invention expanded areas imaging pushes away staring imaging method, for realizing satellite precession and earth rotation
In the case of satellite moving target is stared dynamic tracking, satellite gravity anomaly need ensure optical detector light axial vector begin
Pointing to target eventually, during staring imaging, satellite attitude control system needs satellite body coordinate system relative to the three of orbital coordinate system
Axle attitude angle (rollPitching θ, go off course ψ), control in real time.
Push away congeal into as during, satellite body coordinate system relative to orbital coordinate system yaw angle and roll angle with stare into
During Xiang, satellite body coordinate system is constant (i.e. relative to the yaw angle of orbital coordinate system and the holding of roll angle angle value
ψ '=ψ), on the basis of the original luffing angle of staring imaging, only add a Proportional coefficient K, and K value is in each mission planning
Time can choose according to areas imaging.
| K | < when 1, push away the luffing angle θ '=stare luffing angle θ × K that solidifying imaging pattern Satellite posture control system controls,
Multiplying factor K congeals into as with staring imaging coverage as shown in Figure 2 with pusher.During such as K=1, then push away stare pattern be equal to pass
System stares pattern.
The method of the present invention is described in further detail by the embodiment be given below in conjunction with accompanying drawing.
(1) on the premise of not considering earth curvature, it is known that K value, solidifying image coverage area is pushed away.
Assume satellite orbital altitude h=500km, satellite angle of pitch ability θ≤± 30 °, camera imaging scope 3km × 3km
=9km2, K=0.98, θ=30 °, θ '=30 ° × 0.98=29.4 °.Schematic diagram is as shown in Figure 3.
Known conditions is substituted into below equation:
L1=h × tg θ
L2=h × tg θ '
L3=L1-L2
When L1 is satellite pitching θ angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, and L2 is satellite pitching
During θ ' angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, optical axis center and satellite when L3 is satellite pitching θ ' angle
Distance between optical axis center during pitching θ angle.
L1=288.675km, L2=281.735km, L3=6.94km, S1=9km can be calculated2, S2=
20.82km2, wherein, when S1 is θ=30 °, camera is at the areas imaging on ground, S2 for from θ become θ ' time ground imaging region pair
The area increase answered；Because the luffing angle of satellite is ± 30 °, so the final solidifying image coverage that pushes away is 2 × S2+S1=
50.64km2.From result, K value is set to 0.98 coverage that just can realize bigger than traditional staring imaging 5.6 times.
(2) on the premise of not considering earth curvature, determine that satellite pushes away the expectation coverage of the picture that congeals into, calculate K value.
Assume satellite orbital altitude h=500km, satellite angle of pitch ability θ≤± 30 °, camera imaging scope 3km × 3km
=9km2, θ=30 °, L3=1km then pushes away and congeals into as expanding 6km2Coverage.Schematic diagram is as shown in Figure 4.
By above it is known that understand L1-L2=1km, then
Known conditions is substituted into formula, calculates θ=29.8989 °, then K=θ/θ '=0.99663.
Obviously, above-described embodiment is only for clearly demonstrating example, and not restriction to embodiment.Right
For those of ordinary skill in the field, can also make on the basis of the above description other multi-form change or
Variation.Here without also cannot all of embodiment be given exhaustive.And the obvious change thus extended out or
Change among still in the protection domain of the invention.
Claims (2)
1. what a video satellite expanded areas imaging pushes away staring imaging method, it is characterised in that comprise the following steps:
During staring imaging, by optical axis passage forward at the uniform velocity, make along rail direction, non-increase along rail direction imaging fabric width
Greatly.
What video satellite the most according to claim 1 expanded areas imaging pushes away staring imaging method, it is characterised in that concrete
Step is:
During staring imaging, control luffing angle θ ' by Satellite Attitude Control System and meet:
θ '=θ × K,
Wherein, θ is for staring luffing angle, and K is proportionality coefficient, meets | K | < 1；Then have:
L1=h × tg θ
L2=h × tg θ '
L3=L1-L2
Wherein, when L1 is satellite pitching θ angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, and L2 is satellite pitching
During θ ' angle, optical axis center is to the distance of optical axis center during 0 ° of angle of satellite pitching, optical axis center and satellite when L3 is satellite pitching θ ' angle
Distance between optical axis center during pitching θ angle.
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| CN107380485A (en) * | 2017-08-02 | 2017-11-24 | 上海航天控制技术研究所 | A kind of microsatellite large area array wide area multimode staring imaging control method |
| CN108382608A (en) * | 2018-01-31 | 2018-08-10 | 上海航天控制技术研究所 | It is a kind of freely to reconstruct and the earth observation Nano satellite group system of synergistic observation |
| CN109029367A (en) * | 2018-08-30 | 2018-12-18 | 中国科学院长春光学精密机械与物理研究所 | A kind of staring imaging method based on expansion target point |
| CN109828362A (en) * | 2019-01-30 | 2019-05-31 | 武汉大学 | Ultra-large-width imaging method based on whole-satellite fast swing |
| CN113460336A (en) * | 2021-08-14 | 2021-10-01 | 苏州吉天星舟空间技术有限公司 | Attitude trajectory planning method for satellite non-tracking curve imaging |
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| CN108382608A (en) * | 2018-01-31 | 2018-08-10 | 上海航天控制技术研究所 | It is a kind of freely to reconstruct and the earth observation Nano satellite group system of synergistic observation |
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| CN109828362A (en) * | 2019-01-30 | 2019-05-31 | 武汉大学 | Ultra-large-width imaging method based on whole-satellite fast swing |
| CN109828362B (en) * | 2019-01-30 | 2020-07-07 | 武汉大学 | Ultra-large-width imaging method based on whole-satellite fast swing |
| CN113460336A (en) * | 2021-08-14 | 2021-10-01 | 苏州吉天星舟空间技术有限公司 | Attitude trajectory planning method for satellite non-tracking curve imaging |
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