CN106872141B - Space solar telescope guiding is surely as method for testing precision and device - Google Patents
Space solar telescope guiding is surely as method for testing precision and device Download PDFInfo
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- CN106872141B CN106872141B CN201611231515.8A CN201611231515A CN106872141B CN 106872141 B CN106872141 B CN 106872141B CN 201611231515 A CN201611231515 A CN 201611231515A CN 106872141 B CN106872141 B CN 106872141B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The present invention relates to a kind of space solar telescope guidings surely as accuracy test mode and device,Belong to technical field of photoelectricity test,By implementing space solar telescope guiding proposed by the invention surely as method for testing precision and device,It can simulate for test space astronomical telescope guiding surely as the input target of precision,In the case where keeping space solar telescope and motionless guiding,Change input target,After steady camera structure completes normal steady picture work,The position pixel variable quantity of asterism dynamic object is calculated further according to the asterism dynamic object image of space optics telescope output,To determine the precision of the steady picture of space solar telescope guiding according to position pixel variable quantity,And after the multiple steady picture for passing through steady camera structure,The position pixel variable quantity for comparing multiple asterism dynamic object can be further improved guiding surely as the accuracy of accuracy test result.The present invention provides a kind of referential method and apparatus for the detection of big view field space astronomical telescope system.
Description
Technical field
The present invention relates to technical field of photoelectricity test, more particularly to a kind of space solar telescope guiding surely as precision is surveyed
Method for testing and device.
Background technique
Space solar telescope is a kind of is mounted on satellite platform, for setting to the science that Celestial Objects are observed
It is standby, due to its micro-vibration by the generations such as satellite platform attitudes vibration and itself motivation structure such as attitude control engine, solar array
Influence, the optical axis that will lead to observed object and space solar telescope deviates, cause space solar telescope at image quality
Amount decline.Therefore, astronomical telescope generally requires the multiple fine guidings of peripheral field installation in optical system, passes through guiding reality
When to star be imaged, the position of star is resolved to carry out the feedback of positional shift information, so that steady camera structure be driven to make astronomical telescope
Fast pendulum mirror quickly moves, and realizes the steady picture of smart grade to imaging.
Under normal conditions, the bore of the conventional surely parallel light tube as used in method for testing precision is all smaller, and space day
The bore of literary telescope is often all larger, therefore conventional surely as method for testing precision can not be accomplished to the complete of space solar telescope
Bore covering, to cannot achieve the steady accurate test as precision to space solar telescope；Meanwhile space solar telescope
Volume and quality it is all often larger, routine in the prior art is surely as method for testing precision cannot achieve to this volume and matter
Measure the steady test as precision of all biggish tested product.
Summary of the invention
Based on this, it is necessary in the prior art surely as method for testing precision cannot achieve to space solar telescope
The steady accurate test as precision the problem of, provide a kind of space solar telescope guiding surely as method for testing precision and device.
To solve the above problems, the invention adopts the following technical scheme：
A kind of space solar telescope guiding is steady as method for testing precision, the described method comprises the following steps：
Obtain the first asterism dynamic target generator through object plane be infinity space solar telescope primary mirror refraction after
The current first asterism dynamic object image and the second asterism dynamic target generator formed on first guiding is through the space
The current second asterism dynamic object image formed on the second guiding after primary mirror of astronomical telescope refraction, first asterism are dynamic
State target generator and the second asterism dynamic target generator are synchronous in timing, and first guiding and described second is led
Star is respectively positioned on the image space focal plane of the space solar telescope primary mirror；
It is generated according to the current first asterism dynamic object image and the current second asterism dynamic image for driving
The control instruction of the steady camera structure of dynamic space solar telescope；
After the steady camera structure completes surely picture according to the control instruction, the space solar telescope output is obtained
Asterism dynamic object image, the asterism dynamic object image of the space solar telescope output are third asterism dynamic object hair
The figure that image space focal plane of the raw device after space solar telescope primary mirror refraction in the space solar telescope primary mirror is formed
Picture, and the third asterism dynamic target generator and the first asterism dynamic target generator, second asterism dynamic
Target generator is synchronous in timing；
According to the asterism dynamic object image culminant star point dynamic object of space solar telescope output in the steady picture
Mechanism is surely as the position pixel variable quantity of front and back determines the precision of the steady picture of space solar telescope guiding.
Correspondingly, the present invention also proposes that a kind of space solar telescope guiding is steady as accuracy test device, described device packet
It includes：
Guiding image acquisition unit, for obtaining space day of the first asterism dynamic target generator through object plane for infinity
The current first asterism dynamic object image and the second asterism dynamic shaped on the first guiding after literary telescope primary mirror refraction
The current second asterism dynamic mesh that target generator is formed on the second guiding after space solar telescope primary mirror refraction
Logo image, the first asterism dynamic target generator and the second asterism dynamic target generator are synchronous in timing, institute
It states the first guiding and second guiding is respectively positioned on the image space focal plane of the space solar telescope primary mirror；
Instruction generation unit, for dynamic according to the current first asterism dynamic object image and current second asterism
State image generates the control instruction for driving the steady camera structure of space solar telescope；
Space solar telescope image acquisition unit, for completing steady picture according to the control instruction in the steady camera structure
Afterwards, the asterism dynamic object image of the space solar telescope output, the asterism of the space solar telescope output are obtained
Dynamic object image is for third asterism dynamic target generator in the space after space solar telescope primary mirror refraction
The image that the image space focal plane of primary mirror of astronomical telescope is formed, and the third asterism dynamic target generator and first asterism
Dynamic target generator, the second asterism dynamic target generator are synchronous in timing；
Steady picture precision determination unit, the asterism dynamic object image culminant star for being exported according to the space solar telescope
Point dynamic object is in the steady camera structure surely as the position pixel variable quantity of front and back determines that the space solar telescope guiding is steady
The precision of picture.
Above-mentioned space solar telescope guiding is surely as method for testing precision and device can be realized to space solar telescope
Guiding surely as the test of precision, overcome in the prior art since not bigbore enough parallel light tube can be with space day
The bore phase of literary telescope and lead to not accurately measure space solar telescope guiding surely to pass through implementation as the defect of precision
Space solar telescope guiding proposed by the invention as method for testing precision and device, can surely be simulated for the test space
Astronomical telescope guiding, in the case where keeping space solar telescope and motionless guiding, changes surely as the input target of precision
Target is inputted, after steady camera structure completes normal steady picture work, further according to the asterism dynamic object figure of space optics telescope output
Position pixel variable quantity as calculating asterism dynamic object, to determine that space solar telescope is led according to position pixel variable quantity
The precision of the steady picture of star, and after the multiple steady picture for passing through steady camera structure, the position pixel of more multiple asterism dynamic object changes
Amount can be further improved guiding surely as the accuracy of accuracy test result.The present invention is big view field space astronomical telescope system
Detection provide a kind of referential method and apparatus.
Detailed description of the invention
Fig. 1 is space solar telescope guiding in one embodiment of the invention surely as the process of method for testing precision is shown
It is intended to；
Fig. 2 is the positional diagram of guiding and space solar telescope；
Fig. 3 is space solar telescope guiding in one embodiment of the invention surely as the signal of accuracy test device
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, a kind of space solar telescope guiding is surely as method for testing precision,
Include the following steps：
S100 obtains the first asterism dynamic target generator and reflects through the space solar telescope primary mirror that object plane is infinity
Described in the current first asterism dynamic object image formed on the first guiding afterwards and the second asterism dynamic target generator warp
The current second asterism dynamic object image formed on the second guiding after the refraction of space solar telescope primary mirror, first star
Point dynamic target generator is synchronous in timing with the second asterism dynamic target generator, first guiding and described the
Two guidings are respectively positioned on the image space focal plane of the space solar telescope primary mirror；
S200 is generated and is used according to the current first asterism dynamic object image and the current second asterism dynamic image
In the control instruction of the steady camera structure of driving space solar telescope；
It is defeated to obtain the space solar telescope after the steady camera structure completes surely picture according to the control instruction by S300
The asterism dynamic object image of asterism dynamic object image out, the space solar telescope output is third asterism dynamic mesh
Mark generator is formed after space solar telescope primary mirror refraction in the image space focal plane of the space solar telescope primary mirror
Image, and the third asterism dynamic target generator and the first asterism dynamic target generator, second asterism
Dynamic target generator is synchronous in timing；
The asterism dynamic object image culminant star point dynamic object that S400 is exported according to the space solar telescope is described
Steady camera structure is surely as the position pixel variable quantity of front and back determines the precision of the steady picture of space solar telescope guiding.
Specifically, in the present embodiment, the object plane of space solar telescope primary mirror is infinity, the first asterism dynamic object
Generator forms the first asterism dynamic object image after the refraction of space solar telescope primary mirror on the first guiding, similarly,
Second asterism dynamic target generator forms the second asterism dynamic after the refraction of space solar telescope primary mirror on the second guiding
Target image, wherein the first asterism dynamic target generator and the second asterism dynamic target generator are synchronous in timing, meanwhile,
As shown in Fig. 2, the first guiding and the second guiding in the present embodiment are respectively positioned on the image space focal plane of space solar telescope primary mirror.
Here since the object plane of space solar telescope primary mirror is infinity, the first asterism dynamic target generator and the second asterism
Targeted transformation can be infinity by means of optical alignment system or parallel light tube by dynamic target generator, and space astronomy is hoped
Remote mirror primary mirror could will be on target sink to its image space focal plane.
In step s 200, the current first asterism dynamic object image and current second asterism obtained according to step S100
Dynamic object image generates control instruction, which is used to drive the steady camera structure of space solar telescope.The steady picture of guiding
Method be it is a kind of existing surely as developing the digital image stabilization method of comparative maturity in technology, be compared to other digital image stabilization methods, guiding
The steady picture effect of steady picture is also relatively ideal.According to the current first asterism dynamic object image of acquisition and currently in this step
Second asterism dynamic object image generates control instruction to drive steady camera structure, realizes the imaging effect to space solar telescope
Improvement, guiding and its control system are the prior arts here, and guiding is according to asterism image (i.e. current first star received
Point dynamic target image and current second asterism dynamic object image) control is surely as organisation operations, for those skilled in the art
For, it can use existing guiding completely surely as technology realizes that details are not described herein again.
In step S300, is completed surely as after in steady camera structure according to control instruction, obtain space solar telescope output
Asterism dynamic object image, wherein space solar telescope output asterism dynamic object image be third asterism dynamic object
The image that image space focal plane of the generator after the refraction of space solar telescope primary mirror in space solar telescope primary mirror is formed, and
Third asterism dynamic target generator and the first asterism dynamic target generator, the second asterism dynamic target generator are in timing
Upper synchronization.
Finally, in step S400, according to the asterism dynamic object image culminant star point dynamic of space solar telescope output
Target is in steady camera structure surely as the position pixel variable quantity of front and back determines the precision of the steady picture of space solar telescope guiding.Specifically
Ground, before steady picture organisation operations, space solar telescope can export an asterism dynamic object image, to the asterism dynamic object
Image carries out image procossing, obtains the location information of asterism dynamic object, and to the asterism dynamic object image and asterism dynamic
The location information of target is stored；It is completed surely as after in steady camera structure, space solar telescope will export a star again
Point dynamic target image similarly carries out image procossing to the asterism dynamic object image exported after steady picture, obtains asterism dynamic
The location information of target；By comparing surely as before organisation operations space solar telescope export asterism dynamic object image and
Surely as the asterism dynamic object image that space solar telescope exports after organisation operations, specifically movement images are broadcast TV programs by satellite a dynamic
The change in location of target how many pixel, and the position pixel variable quantity of asterism dynamic object is obtained, finally according to asterism dynamic
The position pixel variable quantity of target, which determines, surely shows sky if the position pixel variable quantity of asterism dynamic object is small as precision
Between the steady picture of astronomical telescope guiding precision it is high, on the contrary then the steady picture of space solar telescope guiding precision is low.
Space solar telescope guiding in the present embodiment surely looks in the distance to space astronomy as method for testing precision can be realized
The guiding of mirror overcomes in the prior art surely as the test of precision since not bigbore enough parallel light tube can be with space
The bore phase of astronomical telescope and lead to not accurately measure space solar telescope guiding surely to pass through reality as the defect of precision
It is steady as method for testing precision to apply the space solar telescope guiding that the present embodiment is proposed, can simulate for test space day
Literary telescope guiding, in the case where keeping space solar telescope and motionless guiding, changes defeated surely as the input target of precision
Enter target, after steady camera structure completes normal steady picture work, further according to the asterism dynamic object image of space optics telescope output
The position pixel variable quantity for calculating asterism dynamic object, to determine space solar telescope guiding according to position pixel variable quantity
The precision of steady picture, and after the multiple steady picture for passing through steady camera structure, the position pixel variable quantity of more multiple asterism dynamic object
It can be further improved guiding surely as the accuracy of accuracy test result.The present invention is big view field space astronomical telescope system
Detection provides a kind of referential method.
The first asterism dynamic target generator, the second asterism dynamic as a kind of specific embodiment, in the present invention
Target generator and third asterism dynamic target generator are liquid crystal on silicon (the Liquid Crystal on driver
Silicon, LCOS) panel, and by lock-out pulse card control timing synchronization between each LCOS panel；The photograph that first light source issues
Mingguang City's beam exposes to corresponding silica-based liquid crystal panel, silica-based liquid crystal panel reflects illuminating bundle after the reflection of the first beam splitter
It is irradiated into the first guiding parallel light tube to the first beam splitter, and after the refraction of the first beam splitter, the first guiding parallel light tube goes out
The directional light penetrated obtains current first asterism dynamic object image after the imaging of space solar telescope primary mirror；Second light source issues
Illuminating bundle after the reflection of the second beam splitter, expose to corresponding silica-based liquid crystal panel, silica-based liquid crystal panel is by illuminating bundle
The second beam splitter is reflexed to, and is irradiated into the second guiding parallel light tube, the second guiding directional light after the refraction of the second beam splitter
The directional light of pipe outgoing obtains current second asterism dynamic object image after the imaging of space solar telescope primary mirror；Third light source
The illuminating bundle of sending exposes to corresponding silica-based liquid crystal panel after the reflection of third beam splitter, and silica-based liquid crystal panel will illuminate
Light beam reflexes to third beam splitter, and main parallel light tube is irradiated into after the refraction of third beam splitter, main parallel light tube outgoing
Directional light obtains the asterism dynamic object image of space solar telescope output after the imaging of space solar telescope primary mirror.At this
In embodiment, since the bore of main parallel light tube is limited, the central vision of space solar telescope primary mirror can only be covered, because
This present embodiment is also provided with the position of the relatively small parallel light tube alignment guiding of 2 bores, i.e., according to the position of guiding
Provided with 2 guiding parallel light tubes, to guarantee that there is target in the image planes position of guiding and space solar telescope；This embodiment party
Formula also uses LCOS panel as asterism dynamic target generator, since LCOS panel can give birth under the control of main control computer
At arbitrary shape, therefore have the characteristics that easily modulation and low cost, while each LCOS panel will guarantee the synchronism of time, it must
There need be lock-out pulse to synchronize operation to these LCOS panels, so that the image for guaranteeing that LCOS panel generates is having the same
Move sequential relationship.
Meanwhile in another embodiment, the present invention also proposes that a kind of space solar telescope guiding is steady as accuracy test
Device, the device include：
Guiding image acquisition unit, for obtaining space day of the first asterism dynamic target generator through object plane for infinity
The current first asterism dynamic object image and the second asterism dynamic shaped on the first guiding after literary telescope primary mirror refraction
The current second asterism dynamic mesh that target generator is formed on the second guiding after space solar telescope primary mirror refraction
Logo image, the first asterism dynamic target generator and the second asterism dynamic target generator are synchronous in timing, institute
It states the first guiding and second guiding is respectively positioned on the image space focal plane of the space solar telescope primary mirror；
Instruction generation unit, for dynamic according to the current first asterism dynamic object image and current second asterism
State image generates the control instruction for driving the steady camera structure of space solar telescope；
Space solar telescope image acquisition unit, for completing steady picture according to the control instruction in the steady camera structure
Afterwards, the asterism dynamic object image of the space solar telescope output, the asterism of the space solar telescope output are obtained
Dynamic object image is for third asterism dynamic target generator in the space after space solar telescope primary mirror refraction
The image that the image space focal plane of primary mirror of astronomical telescope is formed, and the third asterism dynamic target generator and first asterism
Dynamic target generator, the second asterism dynamic target generator are synchronous in timing；
Steady picture precision determination unit, the asterism dynamic object image culminant star for being exported according to the space solar telescope
Point dynamic object is in the steady camera structure surely as the position pixel variable quantity of front and back determines that the space solar telescope guiding is steady
The precision of picture.
Since space solar telescope guiding is surely as the concrete methods of realizing of the function of each unit in accuracy test device,
Surely the implementation method as described in method for testing precision embodiment is identical with space solar telescope guiding above-mentioned, therefore herein not
It repeats again.Space solar telescope guiding in the present embodiment is surely as accuracy test device can be realized to space solar telescope
Guiding surely as the test of precision, overcome in the prior art since not bigbore enough parallel light tube can be with space day
The bore phase of literary telescope and lead to not accurately measure space solar telescope guiding surely to pass through implementation as the defect of precision
The space solar telescope guiding that the present embodiment is proposed can simulate surely as accuracy test device for test space astronomy
Telescope guiding, in the case where keeping space solar telescope and motionless guiding, changes input surely as the input target of precision
Target, after steady camera structure completes normal steady picture work, further according to the asterism dynamic object image meter of space optics telescope output
The position pixel variable quantity for calculating asterism dynamic object, to determine that space solar telescope guiding is steady according to position pixel variable quantity
The precision of picture, and after the multiple steady picture for passing through steady camera structure, the position pixel variable quantity of more multiple asterism dynamic object can
To further increase guiding surely as the accuracy of accuracy test result.
As a kind of specific embodiment, as shown in figure 3, the steady picture accuracy test device of space solar telescope guiding is also
Including first light source 11, second light source 21, third light source 31, the first beam splitter 12, the second beam splitter 22, third beam splitter 32,
First guiding parallel light tube 13, the second guiding parallel light tube 23, main parallel light tube 33 and lock-out pulse card；
First asterism dynamic target generator 14, the second asterism dynamic target generator 24 and third asterism dynamic object hair
Raw device 34 is the silica-based liquid crystal panel with driver, and by lock-out pulse card control timing between each silica-based liquid crystal panel
It is synchronous；
The illuminating bundle that first light source 11 issues exposes to corresponding silica-based liquid crystal panel after the reflection of the first beam splitter 12
14, illuminating bundle is reflexed to the first beam splitter 12 by silica-based liquid crystal panel 14, and is irradiated into after the refraction of the first beam splitter 12
The directional light of first guiding parallel light tube 13, the outgoing of the first guiding parallel light tube 13 obtains after the imaging of space solar telescope primary mirror
To current first asterism dynamic object image；
The illuminating bundle that second light source 21 issues exposes to corresponding silica-based liquid crystal panel after the reflection of the second beam splitter 22
24, illuminating bundle is reflexed to the second beam splitter 22 by silica-based liquid crystal panel 24, and is irradiated into after the refraction of the second beam splitter 22
The directional light of second guiding parallel light tube 23, the outgoing of the second guiding parallel light tube 23 obtains after the imaging of space solar telescope primary mirror
To current second asterism dynamic object image；
The illuminating bundle that third light source 131 issues exposes to corresponding liquid crystal on silicon face after the reflection of third beam splitter 32
Illuminating bundle is reflexed to third beam splitter 32 by plate 34, silica-based liquid crystal panel 34, and irradiate after the refraction of third beam splitter 32 into
Parallel light tube 33 is become owner of, the directional light that main parallel light tube 33 is emitted obtains space astronomy after the imaging of space solar telescope primary mirror
The asterism dynamic object image of telescope output.
In the present embodiment, the illumination path of light source and beam splitter composition can generate uniform parallel light, by LCOS
Target is generated after panel reflection, is launched by parallel light tube, infinity target is formed.Program is controlled by main control computer, it can
The liquid crystal dot matrix controlled one by one on LCOS panel at the appointed time successively works, i.e. modulation LCOS panel, realizes dynamic object
Simulation, moves back and forth it.
Due to having 3 parallel light tubes and 3 LCOS panels, so to guarantee the synchronism of time, it is necessary to there is synchronous arteries and veins
Punching synchronizes operation to 3 LCOS panels, has identical movement sequential relationship with the image for guaranteeing that 3 LCOS panels generate.
Main control computer downloads to preset image in the RAM of the driver of LCOS panel, and utilizes lock-out pulse card
Operation is synchronized to the driver of 3 LCOS panels, to guarantee that the work of LCOS panel is synchronous.LCOS panel is started to work
Asterism dynamic object is incident upon space astronomy respectively and is hoped by the asterism dynamic object for generating reciprocating motion afterwards by parallel light tube
In the imaging image planes of remote mirror and two guidings, guiding is to the first asterism dynamic object image received or the second asterism dynamic
Target image is handled, and real-time calculating position is carried out, and generates control instruction to drive steady camera structure to carry out surely as work, surely
Camera structure is completed surely as after, checks the asterism dynamic object image that astronomical telescope generates, and calculates asterism dynamic object thereon
Position.By repeatedly measuring the variable quantity of asterism dynamic target position, i.e., asterism dynamic object is repeatedly measured in steady picture each time
Mechanism is surely as the position pixel variable quantity of front and back, to determine the precision of the steady picture of guiding, realizes to guiding surely as quantitative point of precision
Analysis and evaluation.It is by the asterism dynamic object that the asterism dynamic object image viewing of space solar telescope output moves back and forth
It is no gradually stable, to verify guiding surely as precision.
In the present embodiment, since the bore of main parallel light tube is limited, space solar telescope primary mirror can only be covered
Central vision, therefore present embodiment is also provided with the relatively small parallel light tube alignment of 2 bores according to the position of guiding
The position of guiding is provided with 2 guiding parallel light tubes, to guarantee that the image planes position of guiding and space solar telescope has
Target；Present embodiment also uses LCOS panel as asterism dynamic target generator, since LCOS panel can be in master control meter
Arbitrary shape is generated under the control of calculation machine, therefore has the characteristics that easily modulation and low cost, while each LCOS panel will guarantee
The synchronism of time, it is necessary to there is lock-out pulse to synchronize operation to these LCOS panels, to guarantee that LCOS panel generates
Image movement sequential relationship having the same.
Space solar telescope guiding proposed by the invention is surely as in accuracy test device, examination is can be selected in main parallel light tube
The big parallel light tube of room bore is tested, to guarantee image quality, small-bore parallel light tube is can be used in guiding parallel light tube；Liquid crystal on silicon
(LCOS) the SXGA type liquid crystal display panel of 1280 × 1024 resolution ratio of ForthDD company can be used in panel, and the LCOS device is included
Display figure can be downloaded in RAM, realize that quick calling is shown by driver；Light source is using a gram Le lighting method, to guarantee to regard
Field intraoral illumination is uniform；The transmission that Xilinx Spartan6 type FPGA realizes lock-out pulse can be selected in lock-out pulse card, and the card is available
Pci bus interface chip PCI9054 realizes control of the computer to lock-out pulse card；Main control computer, which can be used, grinds magnificent IPC-
610 industrial personal computers are realized.
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 (6)
1. a kind of space solar telescope guiding is surely as method for testing precision, which is characterized in that include the following steps：
The first asterism dynamic target generator is obtained after the space solar telescope primary mirror refraction that object plane is infinity first
The current first asterism dynamic object image and the second asterism dynamic target generator formed on guiding is through the space astronomy
The current second asterism dynamic object image formed on the second guiding after the refraction of telescope primary mirror, the first asterism dynamic mesh
It marks generator and the second asterism dynamic target generator is synchronous in timing, first guiding and second guiding are equal
Positioned at the image space focal plane of the space solar telescope primary mirror；
It is generated according to the current first asterism dynamic object image and the current second asterism dynamic image for driving sky
Between astronomical telescope steady camera structure control instruction；
After the steady camera structure completes surely picture according to the control instruction, the asterism of the space solar telescope output is obtained
The asterism dynamic object image of dynamic object image, the space solar telescope output is third asterism dynamic target generator
The image that image space focal plane after space solar telescope primary mirror refraction in the space solar telescope primary mirror is formed, and
The third asterism dynamic target generator and the first asterism dynamic target generator, the second asterism dynamic object are sent out
Raw device is synchronous in timing；
According to the asterism dynamic object image culminant star point dynamic object of space solar telescope output in the steady camera structure
Surely as the position pixel variable quantity of front and back determines the precision of the steady picture of space solar telescope guiding.
2. space solar telescope guiding according to claim 1 is surely as method for testing precision, which is characterized in that
The first asterism dynamic target generator, the second asterism dynamic target generator and the third asterism dynamic mesh
Marking generator is the silica-based liquid crystal panel with driver, and by lock-out pulse control between each silica-based liquid crystal panel
Timing synchronization processed；
The illuminating bundle that first light source issues exposes to the corresponding silica-based liquid crystal panel, institute after the reflection of the first beam splitter
It states silica-based liquid crystal panel and the illuminating bundle is reflexed into first beam splitter, and irradiated after first beam splitter refraction
Into the first guiding parallel light tube, the directional light of the first guiding parallel light tube outgoing is through the space solar telescope primary mirror
The current first asterism dynamic object image is obtained after imaging；
The illuminating bundle that second light source issues exposes to the corresponding silica-based liquid crystal panel, institute after the reflection of the second beam splitter
It states silica-based liquid crystal panel and the illuminating bundle is reflexed into second beam splitter, and irradiated after second beam splitter refraction
Into the second guiding parallel light tube, the directional light of the second guiding parallel light tube outgoing is through the space solar telescope primary mirror
The current second asterism dynamic object image is obtained after imaging；
The illuminating bundle that third light source issues exposes to the corresponding silica-based liquid crystal panel, institute after the reflection of third beam splitter
It states silica-based liquid crystal panel and the illuminating bundle is reflexed into the third beam splitter, and irradiated after third beam splitter refraction
Into main parallel light tube, the directional light of the main parallel light tube outgoing obtains institute after space solar telescope primary mirror imaging
State the asterism dynamic object image of space solar telescope output.
3. a kind of space solar telescope guiding is surely as accuracy test device, which is characterized in that including：
Guiding image acquisition unit is hoped for obtaining the first asterism dynamic target generator through the space astronomy that object plane is infinity
The current first asterism dynamic object image and the second asterism dynamic object shaped on the first guiding after remote mirror primary mirror refraction
The current second asterism dynamic object figure that generator is formed on the second guiding after space solar telescope primary mirror refraction
Picture, the first asterism dynamic target generator and the second asterism dynamic target generator are synchronous in timing, and described
One guiding and second guiding are respectively positioned on the image space focal plane of the space solar telescope primary mirror；
Instruction generation unit, for according to the current first asterism dynamic object image and the current second asterism Dynamic Graph
As generating the control instruction for driving the steady camera structure of space solar telescope；
Space solar telescope image acquisition unit, for being completed surely as after in the steady camera structure according to the control instruction,
Obtain the asterism dynamic object image of the space solar telescope output, the asterism dynamic of the space solar telescope output
Target image is for third asterism dynamic target generator in the space astronomy after space solar telescope primary mirror refraction
The image that the image space focal plane of telescope primary mirror is formed, and the third asterism dynamic target generator and first asterism dynamic
Target generator, the second asterism dynamic target generator are synchronous in timing；
Steady picture precision determination unit, the asterism dynamic object image culminant star crawl for being exported according to the space solar telescope
State target the steady camera structure surely as the position pixel variable quantity of front and back determine the space solar telescope guiding it is steady as
Precision.
4. space solar telescope guiding according to claim 3 is surely as accuracy test device, which is characterized in that further include
First light source, second light source, third light source, the first beam splitter, the second beam splitter, third beam splitter, the first guiding parallel light tube,
Second guiding parallel light tube, main parallel light tube and lock-out pulse card,
The first asterism dynamic target generator, the second asterism dynamic target generator and the third asterism dynamic mesh
Marking generator is the silica-based liquid crystal panel with driver, and by the lock-out pulse between each silica-based liquid crystal panel
Card control timing synchronization；
The illuminating bundle that the first light source issues exposes to the corresponding liquid crystal on silicon after first beam splitter reflection
Panel, the illuminating bundle is reflexed to first beam splitter by the silica-based liquid crystal panel, and is rolled over through first beam splitter
The first guiding parallel light tube is irradiated into after penetrating, the directional light of the first guiding parallel light tube outgoing is through the space day
The current first asterism dynamic object image is obtained after literary telescope primary mirror imaging；
The illuminating bundle that the second light source issues exposes to the corresponding liquid crystal on silicon after second beam splitter reflection
Panel, the illuminating bundle is reflexed to second beam splitter by the silica-based liquid crystal panel, and is rolled over through second beam splitter
The second guiding parallel light tube is irradiated into after penetrating, the directional light of the second guiding parallel light tube outgoing is through the space day
The current second asterism dynamic object image is obtained after literary telescope primary mirror imaging；
The illuminating bundle that the third light source issues exposes to the corresponding liquid crystal on silicon after third beam splitter reflection
Panel, the illuminating bundle is reflexed to the third beam splitter by the silica-based liquid crystal panel, and is rolled over through the third beam splitter
The main parallel light tube is irradiated into after penetrating, the directional light of the main parallel light tube outgoing is through the space solar telescope primary mirror
The asterism dynamic object image of the space solar telescope output is obtained after imaging.
5. space solar telescope guiding according to claim 4 is surely as accuracy test device, which is characterized in that
The silica-based liquid crystal panel is the SXGA type liquid crystal display panel that resolution ratio is 1280 × 1024.
6. space solar telescope guiding according to claim 4 or 5 is surely as accuracy test device, which is characterized in that
The lock-out pulse card is the pulse cards that pulse is sent using Xilinx Spartan6 type FPGA.
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| CN109813526B (en) * | 2018-12-29 | 2021-05-11 | 中国科学院紫金山天文台 | Astronomical positioning-based optical telescope external field tracking precision detection method |
| CN110657960B (en) * | 2019-10-31 | 2020-09-25 | 中国科学院长春光学精密机械与物理研究所 | Image stabilization precision detection optical path system of large-view-field space astronomical telescope |
| CN110849318A (en) * | 2019-11-29 | 2020-02-28 | 中国科学院长春光学精密机械与物理研究所 | Method and device for acquiring sun altitude angle of spacecraft subsatellite point and imaging method |
| CN115437030B (en) * | 2022-08-23 | 2024-01-30 | 中国科学院云南天文台 | Star-guiding closed-loop tracking method and system for high-dispersion optical fiber spectrometer |
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