CN107329191A - GMS image-guidance and registering imaging test system and test method - Google Patents
GMS image-guidance and registering imaging test system and test method Download PDFInfo
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- CN107329191A CN107329191A CN201710349297.6A CN201710349297A CN107329191A CN 107329191 A CN107329191 A CN 107329191A CN 201710349297 A CN201710349297 A CN 201710349297A CN 107329191 A CN107329191 A CN 107329191A
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Abstract
The invention discloses a kind of GMS image-guidance and registering imaging test system and test method, GMS image-guidance includes satellite support, satellite body, load instrument, load instrument light shield, load instrument characteristic point measurement target ball, parallel light tube, laser tracker measurement optical axis etc. with registering imaging test system, satellite body is located above satellite support, and satellite body, load instrument light shield are all connected with load instrument.The present invention can carry out quantitative verification in the satellite development stage to the scheme of image-guidance registration.
Description
Technical field
The present invention relates to a kind of GMS, more particularly to a kind of GMS image-guidance with it is registering
Imaging test system and test method.
Background technology
, it is necessary to which localization region property complexity weather, tracks bad weather development trend and generate cloud atlas in numerical weather forecast
Animation, this needs the corresponding absolute geographical position accurate positioning of image, and the relative position relation registration of adjacent image is accurate.Image
It is quantitative distant that navigation registration accuracy is related to weather diagnosis, nephanalysis, the target identification of disaster monitoring application, and wind vector etc.
Feel the processing accuracy of product.Because the detector array of meteorological fixed statellite remote sensing instrument is small-sized, it is impossible to complete by single frames
Into regional imaging, it is necessary to be scanned motion by the scanning mirror inside remote sensing instrument, remote sensing instrument is scanned imaging, when distant
Feel instrument to complete after sector scanning, by the splicing of multiframe remote sensing images, form complete remote sensing images.The scanning of remote sensing instrument
Mirror servo error has certain correlation with the angle residing for scanning mirror, but because adjacent direction of line scan is different, error performance shape
Formula also has difference, causes successive objective in single-frame images to generate dislocation, causes frame in registration bias, and influence remote sensing images are matched somebody with somebody
Quasi- precision.Accordingly, it would be desirable to which it is as shown in Figure 3 to analyze influence of the scanning mirror servo error to satellite image frame in registration accuracy.
By literature search, " INR systems are used for quiet for periodical " spacecraft engineering ", the 93-100 pages of 01 phase in 2013, name
The only analysis of track lofty stance accuracy satel-lite ", author " Sun Xiaofeng, Pei Shengwei, Li Xingang " document describe image-guidance with
The concept and main processes of registration, are briefly described to the disturbing source of image-guidance and registration arrangement.This article is not
Introduce appraisal procedure registering in picture frame.
Periodical " Chinese Ph.D. Dissertation's full-text database ", name " the geostationary orbit payload optical axis in 2015
Compensation technique research ", author " Pan Wengui " document give determining for frame in registering (Within-Frame Registration)
Justice, it is indicated that " frame in registration " is to determine in same two field picture between the actual relative position of any two pixel and desired relative positions
Deviation meet set quota requirement.
Foreign language literature " GOES Users ' Conference " describe U.S. GOES, and (defend by geostationary orbit environment business
Star) the registering appraisal procedure of the in-orbit frame in of satellite and technical merit, but it is not directed to ground experiment method registering in picture frame.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of GMS image-guidance and tried with registering imaging
Check system and test method, it can carry out quantitative verification in the satellite development stage to scheme registering in picture frame.
The present invention is to solve above-mentioned technical problem by following technical proposals：A kind of GMS image-guidance
With registering imaging test system, it includes satellite support, satellite body, load instrument, load instrument light shield, load instrument
Characteristic point measurement target ball, parallel light tube, laser tracker measurement the optical axis, parallel light tube characteristic point measurement target ball, laser tracker,
Four-dimensional governor motion, imaging target, integrating sphere, satellite body are located above satellite support, satellite body, load instrument light shield
All it is connected with load instrument, load instrument light shield measures target ball provided with multiple load instrument characteristic points, satellite support is located at
On the left of four-dimensional governor motion, parallel light tube, imaging target, integrating sphere are all connected with four-dimensional governor motion top, are imaged target position
Between parallel light tube and integrating sphere, parallel light tube measures target ball provided with multiple parallel light tube characteristic points, and laser tracker is located at
On the right side of four-dimensional governor motion, laser tracker measures the optical axis by laser tracker and measures target with load instrument characteristic point respectively
Ball, parallel light tube characteristic point measurement target ball are connected.
The present invention also provides a kind of GMS image-guidance and comprised the following steps with registering imaging test method：
Step one is, it is necessary to carry out imaging system optical axis alignment, and carry out imaging test registering in picture frame；
Step 2, the imaging test of attitude motion compensation；
Step 3, the sensitive imaging test of fixed star.
Preferably, the step one comprises the following steps：
Step 11: whole star imaging test state is set up, for making remote sensing instrument sight to water by the adjustment of satellite support
Flat, remote sensing instrument possesses optical imagery condition；
Step 12: terrestrial optical imaging test system is built, with parallel light tube, imaging target and integrating sphere analog satellite
Imageable target over the ground, wherein parallel light tube are used to simulate directional light, and integrating sphere is that light source is used to adjust target light intensity, is imaged target
It is used for qualitative assessment frame in registration accuracy as known imageable target, by adjusting parallel light tube angles and positions by remote sensing instrument
The optical axis is aligned with parallel light tube optical axis；
Step 13: remote sensing instrument carries out zonule Imaging Evaluation image registration accuracy, north and south mirror is nearby carried out under the line
Motion, East and West direction scanning mirror moves back and forth imaging in the range of -4.35 °~4.35 °, to be connected two scannings in the ranks in image
The pixel number of striped dislocation makees registration accuracy in core picture frame；
Step 14: the frame in registration of multiple visual fields is assessed, for analyzing the remote sensing figure that scanning mirror is under different angles
Picture, the pixel number that adjacent rows striped staggers using in image is led as evaluation index, examination scanning mirror image in different angles
Boat and registering frame in registration accuracy.
Preferably, optical axis alignment is the optical imaging system optical axis alignment side based on laser tracker in the step 12
Method, its specific implementation step comprises the following steps：
Step 20: setting up whole star imaging test state, and by satellite riding, make the sight of the load instrument on star
Level, in order to be aligned with the optical axis of parallel light tube, carries out optical imagery；
Step 2 11, using parallel light tube, integrating sphere and imaging target build terrestrial optical imaging test system, wherein
Parallel light tube is used to simulate the star aberration from infinite point, and integrating sphere analog light source is used for the brightness for adjusting target, is imaged target
Mark is easy to qualitative assessment frame in registration accuracy；
Step 2 12, remote sensing instrument East and West direction scanning mirror are moved in the range of -4 °~4 °, are often carried out once, are adjusted
The optical axis of whole parallel light tube is pointed to, and confirms imaging target in remote sensing instrument visual field, scanning mirror is carried out by starting point of current location
Sector scanning is moved, and remote sensing instrument is scanned imaging to imaging target；
Step 2 13, analysis scanning mirror are in the remote sensing images under different angles, wrong with adjacent rows striped in image
The pixel number opened examines scanning mirror image-guidance and registering frame in registration accuracy in different angles as evaluation index.
Preferably, the step 2 comprises the following steps：Step 3 11, obtains the benchmark image under satellite zero attitude；
Step 3 12：Obtain image when satellite has attitude motion；Step 3 13：Obtain when satellite has an attitude motion to appearance
State moves the image after compensating；Step 3 14：Comparative evaluation attitude motion compensation effect.
Preferably, the step 3 11 comprises the following steps：Adjust in parallel light tube optical axis alignment satellite instrument visual field
The heart, satellite is imaged in the case where being not turned on pose compensation to target, and the image of acquisition is used as benchmark image.
Preferably, the step 3 12 comprises the following steps：Target translates one along satellite body system x-axis or y-axis direction
Segment distance, mobile effect of the target that the in-orbit attitude offsets of analog satellite are caused in visual field；Satellite is being not turned on pose compensation
In the case of to target be imaged, obtain attitude motion when image.
Preferably, the step 3 13 comprises the following steps：In inside satellite Attitude and orbit control computer software set with
The corresponding Attitude Offset parameter of target offset, satellite is imaged in the case where opening attitude motion compensation to target, is obtained
Image after compensation.
Preferably, the step 3 14 comprises the following steps：By the gray matrix of benchmark image respectively with attitude motion
When image, the gray matrix of image subtracts each other after compensation, so that the coincidence degree of observed image, two images misaligned pixel
Number.
Preferably, the step 3 comprises the following steps：Step 4 11：Set up and be superimposed by two slit plate right-angled intersections
The static asterism target imaging system of composition, adjustment target slit width generates larger asterism, adjustment two dimension linear motion platform position
Put, asterism is located near parallel light tube center；Satellite is likely to occur region to static asterism target and carries out large range of area
Bright spot position in domain scanning imagery, observation remote sensing images, static asterism orientation is calculated by center of gravity extraction method；Step 4 ten
Two：The two-dimensional scan mirror angle that satellite remote sensing instrument points to the position is calculated with static asterism orientation, remote sensing instrument scanning mirror is driven
The angle is pointed to, static asterism target should be appeared in remote sensing instrument instantaneous field of view；Step 4 13：Adjust target slit chi
It is very little, make asterism target size close to actual fixed star asterism subtended angle；Calculate quiet using parallel light tube focal length and rotational-angular velocity of the earth
Displacement of the lines speed of the state asterism target on two-dimentional linear motion platform, and with characteristics of motion driving linear motion platform, make star
Point at the uniform velocity streaks detector pixel along east-west direction；In east-west direction per back and forth streaking once, North and South direction utilizes two-dimentional straight line
The distance of the pixel of motion platform stepping 1/3；Step 4 14：Fixed star sensitive imaging experiments outcome evaluation.
The positive effect of the present invention is：The present invention can directly examine scanning mirror servo error to image-guidance
With the influence of registering frame in registration accuracy；And imaging test is carried out based on whole star, trystate and load instrument mode of operation are equal
With satellite is in-orbit is consistent, result of the test is genuine and believable.
Brief description of the drawings
Fig. 1 is system schematic of the invention.
Fig. 2 is the in-orbit imaging schematic diagram of GMS of the invention.
Fig. 3 is remote sensing instrument thing mirror servo error schematic diagram.
Fig. 4 is stripe pattern dislocation schematic diagram of the invention.
Embodiment
Present pre-ferred embodiments are provided below in conjunction with the accompanying drawings, to describe technical scheme in detail.
As shown in figure 1, GMS image-guidance of the present invention includes satellite support with registering imaging test system
1st, satellite body 2, load instrument 3, load instrument light shield 4, load instrument characteristic point measurement target ball 5, parallel light tube 6, laser
The tracker measurement optical axis 7, parallel light tube characteristic point measurement target ball 8, laser tracker 9, four-dimensional governor motion 10, imaging target
11st, integrating sphere 12, satellite body 2 is located at the top of satellite support 1, satellite body 2, load instrument light shield 4 all with load instrument 3
It is connected, load instrument light shield 4 measures target ball 5 provided with multiple load instrument characteristic points, satellite support 1 is located at four-dimensional regulation machine
The left side of structure 10, parallel light tube 6, imaging target 11, integrating sphere 12 are all connected with the four-dimensional top of governor motion 10, are imaged target 11
Between parallel light tube 6 and integrating sphere 12, parallel light tube 6 measures target ball 8, laser tracker provided with multiple parallel light tube characteristic points
9 are located at the four-dimensional right side of governor motion 10, laser tracker 9 by laser tracker measure the optical axis 7 respectively with load instrument feature
Point measurement target ball 5, parallel light tube characteristic point measurement target ball 8 are connected.
GMS image-guidance of the present invention comprises the following steps with registering imaging test method：
Step one is, it is necessary to carry out imaging system optical axis alignment, and carry out imaging test registering in picture frame；
Step 2, the imaging test of attitude motion compensation；
Step 3, the sensitive imaging test of fixed star.
The step one comprises the following steps：
Step 11: whole star imaging test state is set up, for making remote sensing instrument sight to water by the adjustment of satellite support
Flat, remote sensing instrument possesses optical imagery condition；
Step 12: terrestrial optical imaging test system is built, with parallel light tube, imaging target and integrating sphere analog satellite
Imageable target over the ground, wherein parallel light tube are used to simulate directional light, and integrating sphere is that light source is used to adjust target light intensity, is imaged target
It is used for qualitative assessment frame in registration accuracy as known imageable target, by adjusting parallel light tube angles and positions by remote sensing instrument
The optical axis is aligned with parallel light tube optical axis；
Step 13: remote sensing instrument carries out zonule Imaging Evaluation image registration accuracy, north and south mirror is nearby carried out under the line
Motion, East and West direction scanning mirror moves back and forth imaging in the range of -4.35 °~4.35 °, as shown in figure 4, with connected two in image
The pixel number of individual scanning striped dislocation in the ranks makees registration accuracy in core picture frame；
Step 14: the frame in registration of multiple visual fields is assessed, for analyzing the remote sensing figure that scanning mirror is under different angles
Picture, the pixel number that adjacent rows striped staggers using in image is led as evaluation index, examination scanning mirror image in different angles
Boat and registering frame in registration accuracy.
Optical axis alignment is the optical imaging system optical axis alignment methods based on laser tracker in the step 12, and it has
Body implementation steps comprise the following steps：
Step 20: setting up whole star imaging test state, and by satellite riding, make the sight of the load instrument on star
Level, in order to be aligned with the optical axis of parallel light tube, carries out optical imagery；
Step 2 11, using parallel light tube, integrating sphere and imaging target build terrestrial optical imaging test system, wherein
Parallel light tube is used to simulate the star aberration from infinite point, and integrating sphere analog light source is used for the brightness for adjusting target, is imaged target
Mark is easy to qualitative assessment frame in registration accuracy；
Step 2 12, remote sensing instrument East and West direction scanning mirror are moved in the range of -4 °~4 °, are often carried out once, are adjusted
The optical axis of whole parallel light tube is pointed to, and confirms imaging target in remote sensing instrument visual field, scanning mirror is carried out by starting point of current location
Sector scanning is moved, and remote sensing instrument is scanned imaging to imaging target；
Step 2 13, analysis scanning mirror are in the remote sensing images under different angles, wrong with adjacent rows striped in image
The pixel number opened examines scanning mirror image-guidance and registering frame in registration accuracy in different angles as evaluation index.
The step 2 comprises the following steps：Step 3 11, obtains the benchmark image under satellite zero attitude；Step 3 ten
Two：Obtain image when satellite has attitude motion；Step 3 13：Obtain when satellite has attitude motion to enter attitude motion
Image after row compensation；Step 3 14：Comparative evaluation attitude motion compensation effect.
The step 3 11 comprises the following steps：Adjust parallel light tube optical axis alignment satellite instrument field of view center, satellite
Target is imaged in the case where being not turned on pose compensation, the image of acquisition is used as benchmark image.
The step 3 12 comprises the following steps：Target translates a segment distance along satellite body system x-axis or y-axis direction,
Mobile effect of the target that the in-orbit attitude offsets of analog satellite are caused in visual field；Satellite is in the case where being not turned on pose compensation
Target is imaged, image during attitude motion is obtained.
The step 3 13 comprises the following steps：Set and offset with target in inside satellite Attitude and orbit control computer software
The corresponding Attitude Offset parameter of amount, satellite is imaged in the case where opening attitude motion compensation to target, is schemed after being compensated
Picture.
The step 3 14 comprises the following steps：By the gray matrix of benchmark image respectively with attitude motion when figure
The gray matrix of image subtracts each other after picture, compensation, so that the coincidence degree of observed image, the misaligned pixel number of two images.
The step 3 comprises the following steps：Step 4 11：Set up what is be made up of two slit plate right-angled intersection superpositions
Static asterism target imaging system, adjustment target slit width generates larger asterism, and adjustment two dimension linear motion platform position makes star
Point is located near parallel light tube center；Satellite static asterism target is likely to occur region carry out large range of sector scanning into
Bright spot position in picture, observation remote sensing images, static asterism orientation is calculated by center of gravity extraction method；Step 4 12：With static state
Asterism orientation calculates the two-dimensional scan mirror angle that satellite remote sensing instrument points to the position, and driving remote sensing instrument scanning mirror points to the angle
Degree, static asterism target should be appeared in remote sensing instrument instantaneous field of view；Step 4 13：Target slit sizes are adjusted, make star
The close actual fixed star asterism subtended angle of point target size；Static asterism target is calculated using parallel light tube focal length and rotational-angular velocity of the earth
The displacement of the lines speed on two-dimentional linear motion platform is marked on, and with characteristics of motion driving linear motion platform, makes asterism along thing
At the uniform velocity streak detector pixel in direction；In east-west direction per back and forth streaking once, North and South direction utilizes two-dimentional linear motion platform
The distance of the pixel of stepping 1/3；Step 4 14：Fixed star sensitive imaging experiments outcome evaluation.
As shown in Fig. 2 the present invention GMS it is in-orbit imaging using earth disk 20, scanning imagery region 21,
Instrument sight 22, GMS 23, geostationary orbit 24, scanning imagery region 21, instrument sight 22, static meteorology are defended
Star 23 is all connected with earth disk 20, and scanning imagery region 21 carries out thing scanning, scanning imagery region 21 in earth disk 20
On earth disk 20, GMS 23 carries out thing scanning to scanning imagery region 21 by instrument sight 22, quiet
Only meteorological satellite 23 is located at the bottom of earth disk 20, and geostationary orbit 24 prolongs geostationary orbit 24 and moved.
Particular embodiments described above, technical problem, technical scheme and beneficial effect to the solution of the present invention are carried out
It is further described, should be understood that the specific embodiment that the foregoing is only of the invention, be not limited to
The present invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. should be included in this
Within the protection domain of invention.
Claims (10)
1. a kind of GMS image-guidance and registering imaging test system, it is characterised in that it include satellite support,
Satellite body, load instrument, load instrument light shield, load instrument characteristic point measurement target ball, parallel light tube, laser tracker are surveyed
Measure the optical axis, parallel light tube characteristic point measurement target ball, laser tracker, four-dimensional governor motion, imaging target, integrating sphere, satellite sheet
Body is located above satellite support, and satellite body, load instrument light shield are all connected with load instrument, set on load instrument light shield
Have multiple load instrument characteristic points measurement target balls, satellite support is located on the left of four-dimensional governor motion, parallel light tube, imaging target,
Integrating sphere is all connected with four-dimensional governor motion top, and imaging target is located between parallel light tube and integrating sphere, and parallel light tube is provided with
Multiple parallel light tube characteristic points measure target ball, and laser tracker is located on the right side of four-dimensional governor motion, and laser tracker passes through laser
The tracker measurement optical axis is connected with load instrument characteristic point measurement target ball, parallel light tube characteristic point measurement target ball respectively.
2. a kind of GMS image-guidance and registering imaging test method, it is characterised in that it comprises the following steps：
Step one is, it is necessary to carry out imaging system optical axis alignment, and carry out imaging test registering in picture frame；
Step 2, the imaging test of attitude motion compensation；
Step 3, the sensitive imaging test of fixed star.
3. GMS image-guidance as claimed in claim 2 and registering imaging test method, it is characterised in that institute
Step one is stated to comprise the following steps：
Step 11: whole star imaging test state is set up, it is distant for making remote sensing instrument sight to level by the adjustment of satellite support
Sense instrument possesses optical imagery condition；
Step 12: building terrestrial optical imaging test system, with parallel light tube, imaging target and integrating sphere analog satellite over the ground
Imageable target, wherein parallel light tube are used to simulate directional light, and integrating sphere is that light source is used to adjust target light intensity, is imaged target conduct
Known imageable target is used for qualitative assessment frame in registration accuracy, by adjusting parallel light tube angles and positions by the remote sensing instrument optical axis
It is aligned with parallel light tube optical axis；
Step 13: remote sensing instrument carries out zonule Imaging Evaluation image registration accuracy, north and south mirror is nearby moved under the line,
East and West direction scanning mirror moves back and forth imaging in the range of -4.35 °~4.35 °, with two scannings striped in the ranks that is connected in image
The pixel number of dislocation makees registration accuracy in core picture frame；
Step 14: the frame in registration of multiple visual fields is assessed, for analyzing the remote sensing images that scanning mirror is under different angles, with
The pixel number that adjacent rows striped staggers in image as evaluation index, examination scanning mirror in different angles image-guidance with matching somebody with somebody
Accurate frame in registration accuracy.
4. GMS image-guidance as claimed in claim 3 and registering imaging test method, it is characterised in that institute
It is the optical imaging system optical axis alignment methods based on laser tracker, its specific implementation step to state optical axis alignment in step 12
Comprise the following steps：
Step 20: setting up whole star imaging test state, and by satellite riding, make the sight water of the load instrument on star
It is flat, in order to be aligned with the optical axis of parallel light tube, carry out optical imagery；
Step 2 11, using parallel light tube, integrating sphere and imaging target build terrestrial optical imaging test system, wherein parallel
Light pipe is used to simulate the star aberration from infinite point, and integrating sphere analog light source is used for the brightness for adjusting target, and imaging target is just
In qualitative assessment frame in registration accuracy；
Step 2 12, remote sensing instrument East and West direction scanning mirror are moved in the range of -4 °~4 °, are often carried out once, and adjustment is flat
The optical axis of row light pipe is pointed to, and confirms imaging target in remote sensing instrument visual field, scanning mirror carries out region by starting point of current location
Scanning motion, remote sensing instrument is scanned imaging to imaging target；
Step 2 13, analysis scanning mirror are in the remote sensing images under different angles, are staggered with adjacent rows striped in image
Pixel number examines scanning mirror image-guidance and registering frame in registration accuracy in different angles as evaluation index.
5. GMS image-guidance as claimed in claim 2 and registering imaging test method, it is characterised in that institute
Step 2 is stated to comprise the following steps：Step 3 11, obtains the benchmark image under satellite zero attitude；Step 3 12：Defended
There is image during attitude motion in star；Step 3 13：Obtain after being compensated when satellite has attitude motion to attitude motion
Image；Step 3 14：Comparative evaluation attitude motion compensation effect.
6. GMS image-guidance as claimed in claim 5 and registering imaging test method, it is characterised in that institute
Step 3 11 is stated to comprise the following steps：Parallel light tube optical axis alignment satellite instrument field of view center is adjusted, satellite is being not turned on appearance
State is imaged in the case of compensating to target, and the image of acquisition is used as benchmark image.
7. GMS image-guidance as claimed in claim 5 and registering imaging test method, it is characterised in that institute
Step 3 12 is stated to comprise the following steps：Target translates a segment distance along satellite body system x-axis or y-axis direction, and analog satellite exists
Mobile effect of the target that rail attitude offsets are caused in visual field；Satellite in the case where being not turned on pose compensation to target into
Picture, obtains image during attitude motion.
8. GMS image-guidance as claimed in claim 5 and registering imaging test method, it is characterised in that institute
Step 3 13 is stated to comprise the following steps：Set in inside satellite Attitude and orbit control computer software corresponding with target offset
Attitude Offset parameter, satellite is imaged in the case where opening attitude motion compensation to target, image after being compensated.
9. GMS image-guidance as claimed in claim 5 and registering imaging test method, it is characterised in that institute
Step 3 14 is stated to comprise the following steps：By the gray matrix of benchmark image respectively with attitude motion when image, compensation after scheme
The gray matrix of picture subtracts each other, so that the coincidence degree of observed image, the misaligned pixel number of two images.
10. GMS image-guidance as claimed in claim 2 and registering imaging test method, it is characterised in that
The step 3 comprises the following steps：Step 4 11：Set up the static asterism being made up of two slit plate right-angled intersection superpositions
Target imaging system, adjustment target slit width generates larger asterism, and adjustment two dimension linear motion platform position is located at asterism flat
Near row light pipe center；Satellite is likely to occur region to static asterism target and carries out large range of sector scanning imaging, observation
Bright spot position in remote sensing images, static asterism orientation is calculated by center of gravity extraction method；Step 4 12：With static asterism orientation
The two-dimensional scan mirror angle that satellite remote sensing instrument points to the position is calculated, driving remote sensing instrument scanning mirror points to the angle, static star
Point target should be appeared in remote sensing instrument instantaneous field of view；Step 4 13：Target slit sizes are adjusted, make asterism target size
Close to actual fixed star asterism subtended angle；Static asterism target is calculated two-dimentional straight using parallel light tube focal length and rotational-angular velocity of the earth
Displacement of the lines speed on line motion platform, and with characteristics of motion driving linear motion platform, make asterism along east-west direction light paddling
Cross detector pixel；In east-west direction per back and forth streaking once, North and South direction utilizes the two-dimentional pixel of linear motion platform stepping 1/3
Distance；Step 4 14：Fixed star sensitive imaging experiments outcome evaluation.
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| CN111781113A (en) * | 2020-07-08 | 2020-10-16 | 湖南九九智能环保股份有限公司 | Dust grid positioning method and dust grid monitoring method |
| CN114153221A (en) * | 2022-02-09 | 2022-03-08 | 伸瑞科技（北京）有限公司 | Satellite high-precision tracking pointing control ground simulation system and method |
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