CN103278179A - Space camera field curvature detection device and method - Google Patents
Space camera field curvature detection device and method Download PDFInfo
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Abstract
The invention provides a space camera field curvature detection device and method, relating to the field of space optical remote sensing. The space camera field curvature detection device comprises a heavy-calibre normal lens, a space camera used for receiving parallel light of the heavy-calibre normal lens and positioned at the lower end of the heavy-calibre normal lens, an optical engine, a Z-direction micrometric displacement platform, a data processing display and synchronous control system, thirty optical probes and an X-Y-direction micrometric displacement regulating frame, a flat plate and two Z-direction regulating supports, wherein the lower surface of the optical engine is positioned at the focal plane of the heavy-calibre normal lens, the Z-direction micrometric displacement platform is connected with the optical engine, the data processing display and synchronous control system is connected with the Z-direction micrometric displacement platform, the thirty optical probes and the XY-direction micrometric displacement regulating frame are connected with the data processing display and synchronous control system, the thirty optical probes are distributed on the X-Y-direction micrometric displacement regulating frame in a manner in which three lines and ten rows are arranged, the upper surface of the flat plate is positioned on the focal plane of the space camera, the thirty optical probes are positioned at the lower end of the flat plate, and the two Z-direction regulating supports are respectively fixed at two ends of the flat plate. The space camera field curvature detection device is small in measurement and calculation errors; and according to the space camera field curvature detection device, the detection problem of field curvature of the space camera is effectively solved.
Description
Technical field
The present invention relates to the space optical remote technical field, be specifically related to a kind of space camera curvature of field pick-up unit and detection method.
Background technology
In the development of space camera, the error in mounting position of optical element will cause the curvature of field, and the curvature of field is destroyed the consistance of image planes sharpness, and therefore, the curvature of field is the aberration that needs strict control in the space camera development process.
At present the space camera area of computer aided debug with the wave aberration checkout procedure in, the autocollimation method of inspection that is based on interferometer of normal employing, because the focus of space camera optical system and the focus of interferometer standard mirror are difficult to accurately overlap, therefore, out of focus generally will be removed (each visual field is all like this) as systematic error in the wave aberration fit procedure, doing the problem of bringing like this is: even each visual field wave aberration is fine, the picture point that also can't prove these visual fields is coplanar, that is to say, the curvature of field of optical system can't effectively detect, in the imaging process of space camera, in case the residual curvature of field in the optical system, the unintelligible phenomenon of part image will appear, influence the usability of space camera greatly, and under existence conditions, want to eliminate the curvature of field in the optical system, must be after the installation of focal plane, static state biography letter to each position is tested, if find to have the curvature of field, must earlier the focal plane dismounting be installed again, and readjust the position of catoptron, efficient is very low.
(publication number is 102540751A to Chinese patent, be 2012.07.04 in open day) disclose " a kind of detect projection objective distorts and the method for the curvature of field ", utilize one 9 * 9 pinhole mask plates, a Wavefront sensor and an interferometer measurement assembly, the curvature of field and distortion to object lens are measured, this method utilizes wave front detector to survey focal length for the radius of curvature R of the outgoing wave of tested object lens behind a collimated light path of f, utilizes approximate formula △ z=-f
2/ R calculates curvature of field △ z, and the problem that this method mainly exists is: because the radius of curvature R that wave front detector is measured is fitting data, can not peel off the measuring error that out of focus causes, that calculating curvature of field △ z then utilizes is approximate formula △ z=-f
2/ R causes the error of calculation of the curvature of field, can not simulate the curvature of field curve of space camera effectively, and this curvature of field measurement for space camera is definitely unallowed, so the curvature of field that this method can not solve space camera effectively detects problem.
Summary of the invention
In order to solve existing a kind of problem that can not detect the space camera curvature of field effectively that detects the method existence of projection objective distortion and the curvature of field, the invention provides that a kind of measuring error is little, computational accuracy high spatial camera curvature of field pick-up unit and detection method thereof.
The technical scheme that the present invention adopts for the technical solution problem is as follows:
Space camera curvature of field pick-up unit comprises:
The heavy caliber standard lens;
Reception is from the directional light of described heavy caliber standard lens and be positioned at the space camera of its lower end;
Its lower surface is positioned at the light engine of described heavy caliber standard lens position of focal plane;
The Z direction micro-displacement platform that links to each other with described light engine;
The data processes and displays and the synchronous control system that link to each other with described Z direction micro-displacement platform;
30 optic probes that link to each other with described data processes and displays and synchronous control system and XY direction micrometric displacement adjusting bracket, described 30 optic probes are installed on the described XY direction micrometric displacement adjusting bracket and with triplex row ten row and arrange;
Its upper surface is positioned at the flat board of described space camera position of focal plane, and described 30 optic probes are positioned at the lower end of described flat board;
Two Z directions that are separately fixed at described dull and stereotyped two ends are regulated bearing.
Described data processes and displays and synchronous control system mainly are made up of data collecting card, central processing computer, display and controller, described data collecting card links to each other with central processing computer with described 30 optic probes respectively, described central processing computer links to each other with controller with described XY direction micrometric displacement adjusting bracket, display respectively, and described controller links to each other with described Z direction micro-displacement platform.
Described Z direction micro-displacement platform mainly is made of displacement accuracy＜0.001mm, velocity of displacement marble platform and PI actuator〉0.5mm/s.
Described light engine is selected liquid crystal on silicon, high-high brightness〉3000lm, the light engine frequency〉120Hz, spectral coverage is 500nm～600nm, pixel is 1920 * 1028.
The described dull and stereotyped K9 optical glass that adopts is made, and is of a size of 60mm * 300mm * 15mm, and surperficial plane parallel degree is better than 30 ", upper surface is the diffuse transmission surface, transmitance〉50%; Lower surface is polished surface, transmitance〉99%.
Described optic probe mainly is made up of microlens, CCD camera and micro-regulating mechanism, and field range is 20mm * 20mm.
The field range of each optic probe and adjacent optical probe overlapping 5mm on the directions X and on Y-direction also overlapping 5mm.
The detection method of space camera curvature of field pick-up unit, the concrete steps of this method are as follows:
The instruction control Z direction micro-displacement platform that step 1, controller receive central processing computer moves, and makes the lower surface of light engine be positioned at the position of focal plane of heavy caliber standard lens, and central processing computer is noted the position Z00 of Z direction micro-displacement platform this moment;
Step 2, mobile Z direction are regulated bearing makes dull and stereotyped upper surface be positioned at the position of focal plane of space camera, choose 30 visual field points of space camera, calculate 30 pixel Xij on the corresponding light engine, controller receives the instruction control light engine of central processing computer and lights this 30 pixel Xij;
The light that step 3, each pixel Xij send forms directional light and incides on the space camera behind the heavy caliber standard lens, converge to dull and stereotyped upper surface again and form disc of confusion;
Step 4, central processing computer control XY direction micrometric displacement adjusting bracket moves, and makes 30 optic probes be positioned at corresponding disc of confusion below, and each optic probe all sees through flat board to its corresponding disc of confusion imaging, forms 30 disc of confusion images;
Step 5, data collecting card is gathered these 30 disc of confusion images and is passed to central processing computer, display shows these 30 disc of confusion images and its size is monitored in real time, simultaneously, controller control Z direction micro-displacement platform continues stepping and moves, when display shows that the received disc of confusion image of certain optic probe hour, note this minimum disc of confusion image correspondence light engine pixel Xij and this moment Z direction micro-displacement platform position Zij, after corresponding 30 the minimum disc of confusion images of these 30 pixel Xij all find, stop mobile Z direction micro-displacement platform;
Step 6, according to the amount of movement Zij-Z00 of these 30 the corresponding Z direction of pixel Xij micro-displacement platforms, utilize software in the central processing computer to calculate the curvature of field △ Z'ij of these 30 corresponding 30 visual field points of pixel Xij, these 30 curvature of field △ Z'ij are carried out two-dimentional surface fitting, obtain the curvature of field curve of space camera, the computing formula of employing is as follows:
Wherein, f is the effective focal length of space camera; f
pEffective focal length for the heavy caliber standard lens; In step 2, step 3, step 5 and the step 6, the value of described i and j is respectively: i=1,2,3; J=1,2 ... 10.
Described 30 optic probes are installed on the described XY direction micrometric displacement adjusting bracket and arrange with triplex row ten row, the field range that each optic probe and adjacent optical are popped one's head in overlapping 5mm on the directions X and on Y-direction also overlapping 5mm.
Describedly these 30 curvature of field △ Z'ij are carried out two-dimentional surface fitting concrete what adopt is that least square method realizes.
Principle of work explanation: for the space camera of infinite distance imaging, can utilize the position of focal plane of the method calibrating space camera of directional light irradiation space camera.The light source that is placed on heavy caliber standard lens position of focal plane sends divergent beams, process heavy caliber standard lens converges and is parallel beam, it is a disperse hot spot that parallel beam incides that space camera converges, the position of disperse hot spot minimum is the position of focal plane of space camera, is δ if light source departs from the position of focal plane of heavy caliber standard lens
1, according to the Gaussian optics principle, then to depart from the position of focal plane of space camera be δ to disperse hot spot minimum position
2, δ
1With δ
2Relation as follows:
In the formula, f is the effective focal length of space camera, f
pEffective focal length for the heavy caliber standard lens.Utilize the method, measure the defocusing amount of each visual field of space camera, can simulate the curvature of field curve of space camera.
The invention has the beneficial effects as follows:
One, the present invention is provided with 30 measurement points according to the size of space camera focal plane, respectively corresponding 30 optic probes, the process of measurement and display analysis disc of confusion image is in real time synchronous, the data of measuring also are very accurate, the measuring error that has caused owing to out of focus when having avoided adopting Wavefront sensor to measure;
What two, the present invention adopted when calculating the curvature of field is accurate calculating formula, it is not the formula that is similar to, and the measurement of each data and analysis are in real time synchronous in the calculating formula, and be comparatively accurate, therefore add accurate measurement data by accurate calculating formula, the curvature of field that obtains must be quite accurate data, the error of calculation of the curvature of field is eliminated, just can simulate the curvature of field curve of space camera effectively, this curvature of field measurement for space camera is very necessary, so this method has solved the curvature of field detection problem of space camera effectively;
Three, in the curvature of field testing process of space camera, can realize that the curvature of field of optical system is carried out the scene to be detected in real time, having remedied interference detection in the active computer assistant resetting can only provide the deficiency of wave aberration data, has instructed the process of debuging effectively, has reduced measuring error.
Description of drawings
Fig. 1 is the structural representation of space camera curvature of field pick-up unit of the present invention;
Fig. 2 is 3 * 10 optic probe apparent field distribution schematic diagrams;
Fig. 3 is Cij optic probe field range and the overlapping synoptic diagram of adjacent optical probe field range.
Among the figure: 1, Z direction micro-displacement platform, 2, light engine, 3, the heavy caliber standard lens, 4, space camera, 5, the Z direction is regulated bearing, 6, flat board, 7, optic probe, 8, XY direction micrometric displacement adjusting bracket, 9, data processes and displays and synchronous control system, 10, data collecting card, 11, central processing computer, 12, display, 13, controller, 14, the field range of optic probe C11,15, the field range of optic probe C21,16, the field range of optic probe C31,17, the field range of optic probe C110,18, the field range of optic probe Cij, 19, with adjacent optical probe visual field overlapping region, 20, non-overlapping region.
Specific embodiments
Below in conjunction with accompanying drawing the present invention is described in further detail.
As shown in Figure 1, space camera curvature of field pick-up unit of the present invention, simulate the curvature of field curve of space camera 4 by the defocusing amount of measurement space camera 4 specific visual fields, mainly by Z direction micro-displacement platform 1, light engine 2, heavy caliber standard lens 3, the Z direction is regulated bearing 5, dull and stereotyped 6, optic probe 7, XY direction micrometric displacement adjusting bracket 8 and data processes and displays and synchronous control system 9 are formed, as shown in Figure 1, the x direction is vertical mutually with the z direction, y direction among Fig. 1 refers to direction vertical with paper and outside paper, as shown in Figures 2 and 3, the x direction is vertical mutually with the y direction, and Fig. 2 refers to direction vertical with paper and outside paper with z direction among Fig. 3.
Z direction micro-displacement platform 1 in the present embodiment mainly is made of displacement accuracy＜0.001mm, velocity of displacement marble platform and PI actuator〉0.5mm/s.
Light engine 2 in the present embodiment is selected the liquid crystal on silicon of big face battle array for use, is installed on the Z direction micro-displacement platform 1, can move in the Z direction with Z direction micro-displacement platform 1, high-high brightness〉3000lm, the light engine frequency〉120Hz, spectral coverage is 500nm～600nm, pixel is 1920 * 1028.
The bore of the heavy caliber standard lens 3 in the present embodiment is 300mm, and focal length is 2000mm, and field angle is 2 ° * 2 °, and the lower surface of light engine 2 is positioned at the position of focal plane of heavy caliber standard lens 3.
Space camera 4 in the present embodiment is space camera to be measured, position between heavy caliber standard lens 3 and dull and stereotyped 6.
It is two that Z direction in the present embodiment is regulated bearing 5, symmetrical dull and stereotyped 6 the two ends that are installed in are its upper end and are fixed together with dull and stereotyped 6 two ends respectively, are used for flat board 6 is adjusted to the position of focal plane of space camera 4, its Z direction range of adjustment is ± 5mm that degree of regulation is better than 0.05mm.
Flat board 6 in the present embodiment adopts K9 optical glass to make, and is of a size of 60mm * 300mm * 15mm, and surperficial plane parallel degree is better than 30 "; Dull and stereotyped 6 upper surface is made by nanometer technology becomes the diffuse transmission surface with lambert's characteristic, during the light vertical incidence, and transmitance〉50%; Dull and stereotyped 6 lower surface is the good polished surface of transmitance, the lower surface transmitance〉99%; Dull and stereotyped 6 are positioned at the position of focal plane of space camera 4.
Optic probe 7 in the present embodiment mainly is made up of microlens, CCD camera and micro-regulating mechanism, its field range is 20mm * 20mm, microlens is used for optical imagery, select olympus cx31 type industry microscope for use, the CCD camera is used for document image, select AVTGE1910 type CCD camera for use, micro-regulating mechanism can be realized the inching of optic probe 7 horizontal directions; As shown in Figure 2, the present invention adopts 30 optic probes 7 to arrange according to triplex row ten row, each optic probe 7 be numbered Cij(i=1,2,3; J=1,2 ... 10), on the x direction from left to right, the first behavior optic probe C11 is to optic probe C110, the second behavior optic probe C21 is to optic probe C210, the third line be optic probe C31 to optic probe C310, each optic probe 7 corresponding field range; As shown in Figure 3, in order to guarantee space camera 4 whole image planes by the seamless covering in the visual field of these 30 optic probes 7, the field range of each optic probe 7 and adjacent optical probe 7 is at the overlapping 5mm of directions X and in Y-direction also overlapping 5mm; These 30 optic probes 7 are installed on the XY direction micrometric displacement adjusting bracket 8,30 optic probes are all near dull and stereotyped 6 lower surface, can move at directions X and Y-direction with XY direction micrometric displacement adjusting bracket 8, can realize optic probe 7 inching in the horizontal direction by micro-regulating mechanism simultaneously.
Data processes and displays and synchronous control system 9 are made up of data collecting card 10, central processing computer 11, display 12 and controller 13, data collecting card 10 1 ends link to each other with 30 optic probes 7 on the XY direction micrometric displacement adjusting bracket 8, the other end links to each other with central processing computer 11, central processing computer 11 links to each other with controller 13 with XY direction micrometric displacement adjusting bracket 8, display 12 respectively, and controller 13 links to each other with Z direction micro-displacement platform 1; 30 disc of confusion image informations that data collecting card 10 these 30 optic probes 7 of collection detect also pass to central processing computer 11, display 12 demonstrates these 30 real-time disc of confusion images and the image size is monitored in real time, central processing computer 11 control XY direction micrometric displacement adjusting brackets 8 move at directions X and Y-direction respectively, controller 13 receives concrete instruction control Z direction micro-displacement platform that central processing computers 11 provide 1 and moves in the stepping of Z direction, positional information with Z direction micro-displacement platform 1 feeds back to central processing computer 11 simultaneously, and central processing computer 11 is lighted each pixel by sending instruction control light engine 2 for controller 13.
The concrete steps of the detection method of space camera curvature of field pick-up unit of the present invention are as follows:
Step 1, controller 13 receives instruction control Z direction micro-displacement platform that central processing computers 11 provide 1 and moves in the Z direction, drive the position of focal plane that lower surface that light engine 2 makes light engine 2 is positioned at heavy caliber standard lens 3 simultaneously, controller 13 feeds back to central processing computer 11 with the positional information of Z direction micro-displacement platform 1, and central processing computer 11 is noted the position Z00 of Z direction micro-displacement platform 1 at this moment; The instruction of the central processing computer 11 that controller 13 receives specifically refers to the order that Z direction micro-displacement platform 1 is moved in the Z direction, and controller 13 is carried out this order;
Step 2, mobile Z direction are regulated bearing 5, and drive simultaneously dull and stereotyped 6 makes the upper surface of flat board 6 be positioned at the position of focal plane of space camera 4; The position of focal plane of space camera 4 is determined by utilizing directional light irradiation space camera 4;
Step 3, choose 30 visual field points of space camera 4, manually calculate 30 pixel Xij(i=1 on the corresponding light engine 2,2,3; J=1,2 ... 10), controller 13 receives the instruction control light engine 2 that central processing computers 11 provide and lights this 30 pixel Xij(i=1,2,3; J=1,2 ... 10);
Step 4, each pixel Xij(i=1,2,3; J=1,2 ... 10) light that sends all can form a branch of directional light after through heavy caliber standard lens 3 and incide on the space camera 4, and this bundle directional light is through converging on dull and stereotyped 6 the upper surface and forming disc of confusion behind space camera 4; 30 pixel Xij(i=1,2,3; J=1,2 ... 10) respectively corresponding 30 discs of confusion;
Step 5, central processing computer 11 control XY direction micrometric displacement adjusting brackets 8 move at directions X and Y-direction, drive 30 optic probes 7 simultaneously and it is adjusted to corresponding disc of confusion below, optic probe 7 corresponding discs of confusion, each optic probe 7 all carries out imaging through dull and stereotyped 6 to its corresponding disc of confusion, finally forms 30 disc of confusion images;
Step 6, data collecting card 10 are gathered these 30 disc of confusion image informations and are passed to central processing computer 11, demonstrate these 30 disc of confusion images and its size is monitored in real time at display 12, simultaneously, controller 13 control Z direction micro-displacement platforms 1 continue stepping in the Z direction and move, in moving process, if show on the display 12 that the received disc of confusion image of certain optic probe 7 hour, find out the minimum disc of confusion of corresponding with it flat board 6 upper surfaces, note the pixel Xij(i=1 of the light engine 2 of this minimum disc of confusion correspondence, 2,3; J=1,2 ... 10) and this moment Z direction micro-displacement platform 1 position Zij(i=1,2,3; J=1,2 ... 10), make disc of confusion diffuse images degree minimum, 30 pixel Xij(i=1,2,3; J=1,2 ... 10) after corresponding 30 minimum discs of confusion all find, stop mobile Z direction micro-displacement platform 1;
When the lower surface of step 7, light engine 2 was positioned at the position of focal plane of heavy caliber standard lens 3, the position of Z direction micro-displacement platform 1 was Z00, and the position of the corresponding Z direction of each minimum disc of confusion micro-displacement platform 1 is Zij(i=1,2,3; J=1,2 ... 10), so 30 pixel Xij(i=1,2,3; J=1,2 ... 10) amount of movement of corresponding Z direction micro-displacement platform 1 is (Zij-Z00), according to 30 pixel Xij(i=1,2,3; J=1,2 ... 10) amount of movement (Zij-Z00) of corresponding Z direction micro-displacement platform 1 utilizes the software in the central processing computer 11 to calculate this 30 pixel Xij(i=1,2,3; J=1,2 ... 10) curvature of field △ Z'ij(i=1 of 30 of corresponding space camera 4 visual field points, 2,3; J=1,2 ... 10), the formula of employing is as follows:
Wherein, f is the effective focal length of space camera 4; f
pEffective focal length for heavy caliber standard lens 3; A pixel Xij(i=1,2,3; J=1,2 ... 10) correspondence calculates a curvature of field △ Z'ij(i=1,2,3; J=1,2 ... 10), in 30 curvature of field △ Z'ij(i=1,2,3; J=1,2 ... 10) all calculate finish after, adopt least square method to these 30 curvature of field △ Z'ij(i=1,2,3; J=1,2 ... 10) carry out two-dimentional surface fitting, simulate the curvature of field curve of space camera 4, and then obtain the curvature of field information of space camera 4.
Claims (10)
1. space camera curvature of field pick-up unit is characterized in that, comprising:
The heavy caliber standard lens;
Reception is from the directional light of described heavy caliber standard lens and be positioned at the space camera of its lower end;
Its lower surface is positioned at the light engine of described heavy caliber standard lens position of focal plane;
The Z direction micro-displacement platform that links to each other with described light engine;
The data processes and displays and the synchronous control system that link to each other with described Z direction micro-displacement platform;
30 optic probes that link to each other with described data processes and displays and synchronous control system and XY direction micrometric displacement adjusting bracket, described 30 optic probes are installed on the described XY direction micrometric displacement adjusting bracket and with triplex row ten row and arrange;
Its upper surface is positioned at the flat board of described space camera position of focal plane, and described 30 optic probes are positioned at the lower end of described flat board;
Two Z directions that are separately fixed at described dull and stereotyped two ends are regulated bearing.
2. space camera curvature of field pick-up unit according to claim 1, it is characterized in that, described data processes and displays and synchronous control system mainly are made up of data collecting card, central processing computer, display and controller, described data collecting card links to each other with central processing computer with described 30 optic probes respectively, described central processing computer links to each other with controller with described XY direction micrometric displacement adjusting bracket, display respectively, and described controller links to each other with described Z direction micro-displacement platform.
3. space camera curvature of field pick-up unit according to claim 1 is characterized in that, described Z direction micro-displacement platform mainly is made of displacement accuracy＜0.001mm, velocity of displacement marble platform and PI actuator〉0.5mm/s.
4. space camera curvature of field pick-up unit according to claim 1 is characterized in that, described light engine is selected liquid crystal on silicon, high-high brightness〉3000lm, the light engine frequency〉120Hz, spectral coverage is 500nm～600nm, pixel is 1920 * 1028.
5. space camera curvature of field pick-up unit according to claim 1 is characterized in that, the described dull and stereotyped K9 optical glass that adopts is made, and is of a size of 60mm * 300mm * 15mm, and surperficial plane parallel degree is better than 30 ", upper surface is the diffuse transmission surface, transmitance〉50%; Lower surface is polished surface, transmitance〉99%.
6. space camera curvature of field pick-up unit according to claim 1 is characterized in that, described optic probe mainly is made up of microlens, CCD camera and micro-regulating mechanism, and field range is 20mm * 20mm.
7. space camera curvature of field pick-up unit according to claim 1 is characterized in that, the field range of each optic probe and adjacent optical probe overlapping 5mm on the directions X and on Y-direction also overlapping 5mm.
8. the detection method of space camera curvature of field pick-up unit as claimed in claim 1 is characterized in that, the concrete steps of this method are as follows:
The instruction control Z direction micro-displacement platform that step 1, controller receive central processing computer moves, and makes the lower surface of light engine be positioned at the position of focal plane of heavy caliber standard lens, and central processing computer is noted the position Z00 of Z direction micro-displacement platform this moment;
Step 2, mobile Z direction are regulated bearing makes dull and stereotyped upper surface be positioned at the position of focal plane of space camera, choose 30 visual field points of space camera, calculate 30 pixel Xij on the corresponding light engine, controller receives the instruction control light engine of central processing computer and lights this 30 pixel Xij;
The light that step 3, each pixel Xij send forms directional light and incides on the space camera behind the heavy caliber standard lens, converge to dull and stereotyped upper surface again and form disc of confusion;
Step 4, central processing computer control XY direction micrometric displacement adjusting bracket moves, and makes 30 optic probes be positioned at corresponding disc of confusion below, and each optic probe all sees through flat board to its corresponding disc of confusion imaging, forms 30 disc of confusion images;
Step 5, data collecting card is gathered these 30 disc of confusion images and is passed to central processing computer, display shows these 30 disc of confusion images and its size is monitored in real time, simultaneously, controller control Z direction micro-displacement platform continues stepping and moves, when display shows that the received disc of confusion image of certain optic probe hour, note this minimum disc of confusion image correspondence light engine pixel Xij and this moment Z direction micro-displacement platform position Zij, after corresponding 30 the minimum disc of confusion images of these 30 pixel Xij all find, stop mobile Z direction micro-displacement platform;
Step 6, according to the amount of movement Zij-Z00 of these 30 the corresponding Z direction of pixel Xij micro-displacement platforms, utilize software in the central processing computer to calculate the curvature of field △ Z'ij of these 30 corresponding 30 visual field points of pixel Xij, these 30 curvature of field △ Z'ij are carried out two-dimentional surface fitting, obtain the curvature of field curve of space camera, the computing formula of employing is as follows:
Wherein, f is the effective focal length of space camera; f
pEffective focal length for the heavy caliber standard lens; In step 2, step 3, step 5 and the step 6, the value of described i and j is respectively: i=1,2,3; J=1,2 ... 10.
9. the detection method of space camera curvature of field pick-up unit according to claim 8, it is characterized in that, described 30 optic probes are installed on the described XY direction micrometric displacement adjusting bracket and arrange with triplex row ten row, the field range that each optic probe and adjacent optical are popped one's head in overlapping 5mm on the directions X and on Y-direction also overlapping 5mm.
10. the detection method of space camera curvature of field pick-up unit according to claim 8 is characterized in that, describedly these 30 curvature of field △ Z'ij is carried out two-dimentional surface fitting concrete what adopt is that least square method realizes.
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| CN104034352B (en) * | 2014-06-06 | 2017-02-15 | 中国科学院长春光学精密机械与物理研究所 | Method for measuring field curvature of space camera by adopting laser tracker and interference check |
| CN111220070A (en) * | 2018-11-26 | 2020-06-02 | 中国科学院长春光学精密机械与物理研究所 | Method for acquiring scattered spots of star point image |
| CN111263136A (en) * | 2018-11-30 | 2020-06-09 | 欧菲影像技术（广州）有限公司 | Method for detecting imaging field curvature, method for detecting imaging inclination and imaging detector |
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