CN219980897U - Space camera photoelectric system comprehensive test platform - Google Patents
Space camera photoelectric system comprehensive test platform Download PDFInfo
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- CN219980897U CN219980897U CN202320678385.1U CN202320678385U CN219980897U CN 219980897 U CN219980897 U CN 219980897U CN 202320678385 U CN202320678385 U CN 202320678385U CN 219980897 U CN219980897 U CN 219980897U
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- 238000012360 testing method Methods 0.000 title claims abstract description 77
- 238000013519 translation Methods 0.000 claims abstract description 33
- 238000006073 displacement reaction Methods 0.000 claims abstract description 8
- 230000000007 visual effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 229910052736 halogen Inorganic materials 0.000 claims description 2
- 150000002367 halogens Chemical class 0.000 claims description 2
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 claims description 2
- 229910052753 mercury Inorganic materials 0.000 claims description 2
- 238000005070 sampling Methods 0.000 claims description 2
- 230000005622 photoelectricity Effects 0.000 abstract 1
- 230000003287 optical effect Effects 0.000 description 16
- 238000012546 transfer Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 238000003384 imaging method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000005693 optoelectronics Effects 0.000 description 1
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- 230000005855 radiation Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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Abstract
The patent discloses a space camera photoelectricity system integrated test platform, including collimator, light source and target subassembly, horizontal and vertical two-dimensional translation platform, position and every single move two-dimensional revolving stage. The space camera to be measured is installed on the azimuth pitching two-dimensional turntable, the collimator is installed on the horizontal vertical two-dimensional translation stage, and each motion axis of the translation stage and the turntable is provided with a displacement measuring device. And (3) adjusting the combination of the azimuth pitching angle of the turntable and the vertical horizontal position of the translation table to align the clear aperture of the current field of view of the tested space camera with the clear aperture of the collimator. The light source and the target component are arranged on the focal plane of the collimator, and the test wavefront is generated through the beam expansion and collimation of the collimator and is input into the photoelectric system of the tested space camera. The quantitative decoupling adjustment between the corner of the tested space camera and the position of the collimator reduces the complexity of the test tool and the equipment, and the adjustment test of various parameters of the photoelectric system of the space camera can be realized on the platform.
Description
Technical Field
The patent belongs to the field of optical testing and relates to a test platform layout and implementation of a photoelectric remote sensing instrument or an imaging instrument for a space camera and the like and a photoelectric system thereof.
Background
In order to ensure that the space camera can achieve the preset various functions and performances, detailed adjustment and testing of the space camera photoelectric system or optical system are required, wherein the parameters comprise focal length, angle of view, angular resolution, stray light, distortion and the like.
With the progress of the related technology, various technical indexes of the space camera are obviously improved, the optical caliber of the space camera can reach 1m order of magnitude or more, the focal length of the space camera is 1-2 m and more, and the corresponding adjustment test precision and test item requirements are also improved.
The collimator is used as a reference for the space camera adjustment test, the light transmission aperture of the collimator is required to be larger than the light transmission aperture of the tested camera, the full aperture coverage of single or multiple instantaneous fields of view of the tested camera is met, but the angle of view of the collimator is limited, and is usually far larger than that of the collimator, so that the collimator can only test the extremely small fields of view of the tested camera.
If the full field of view of the space camera to be tested or the entire detector focal plane is tested, special tooling equipment is also required for processing. The existing equipment and method for adjusting and testing the photoelectric system of the space camera all need to use complex tooling equipment to adjust the position and angle of the tested camera relative to the collimator in multiple dimensions.
The space camera to be tested or the collimator is subjected to complex and fine overall position and angle adjustment in the test process, and the volume and the weight of the space camera to be tested and the collimator are large, so that the technical difficulty of corresponding test tools and equipment is large, the complexity of the space camera adjustment test work is increased, the stability of a corresponding adjusting mechanism is also difficult to ensure, and the precision of the space camera adjustment test work is influenced.
The existing commercialized equipment is to test around the tested camera with the collimator of small-bore, record the angle of the collimator, get the test result of the corresponding visual field. The test mode is only suitable for testing smaller-caliber lenses on a desktop, and the caliber, focal length, working wave band and adjustment range of the existing commercial products are limited, so that the test capability of the high-precision photoelectric system is limited.
For the ground imaging test of the space camera, CN114088359 and CN114088358 propose a test system, a scene simulation device is used as a target source, the target source irradiates a rotary scanning optical system to simulate earth rotation, then the rotary scanning optical system is used for introducing the focal plane of a collimator, the collimator is used for collimating and expanding beams to generate test wave fronts, and finally the space camera is used for simulating imaging.
For the ground transfer function test of a space camera, CN111586402 proposes a static transfer function test system, multiple grid targets with spatial frequencies are installed on the target surface of a collimator, a tested camera receives images with different frequencies, a low spatial frequency target calculates an object space modulation degree, a target with cut-off frequency calculates an image space modulation degree, and the static transfer function of the tested camera is calculated by using the relation between the object space modulation degree and the image space modulation degree.
The space camera test methods represented by the two examples can be used for carrying out full-caliber test on a current field of view of the space camera. However, if the full-view field test is to be performed on the tested space camera, fine position and angle adjustment of the tested camera relative to the collimator is also required, but the problem that the full-view field full-caliber test is performed on the large-view field space camera is not well solved in the prior art.
The two-dimensional rotation of the tested space camera and the two-axis translation of the collimator tube serving as a test reference are quantitatively decoupled and adjusted, so that a universal and multifunctional comprehensive test platform for the photoelectric system of the space camera is realized, and the full-caliber, full-view and various technical indexes of the large-view space camera or the optical system thereof are assembled and tested at one station.
Disclosure of Invention
The purpose of this patent is to solve the complicated problem of space camera photoelectric system test fixture equipment, accomplishes space camera photoelectric system's multiple optical test in a station.
The contents of this patent are as follows:
the space camera photoelectric system comprehensive test platform comprises a collimator 1, a light source and target assembly 2, a translation table vertical shaft 3, a translation table horizontal shaft 4, a pitching shaft 5 of a turntable, an azimuth shaft 6 and a detector assembly (8);
the tested space camera 7 or the photoelectric system and the detector component 8 are arranged on the pitching shaft 5 and the pitching shaft 6 of the pitching and azimuth two-dimensional turntable, and the collimator 1 and the light source and target component 2 are arranged on the vertical shaft 3 and the horizontal shaft 4 of the vertical and horizontal two-dimensional translation table;
the position of the vertical axis 3 of the translation table is adjusted to be matched with the angle of the pitching axis 5 of the turntable, and the angle is used for testing the vertical or pitching visual field of the tested space camera or the photoelectric system thereof;
the position of the horizontal axis 4 of the translation stage is adjusted to be matched with the angle of the azimuth axis 6 of the turntable, so as to be used for testing the visual field of the horizontal or azimuth direction of the tested space camera or the photoelectric system thereof;
the vertical shaft 3, the horizontal shaft 4 of the translation table, the pitching shaft 5 and the azimuth shaft 6 of the turntable are provided with quantitative linear displacement and angular displacement measuring and recording devices;
the light source 2-1 is selected according to the working wave band of the tested space camera, the ultraviolet band is a mercury lamp, the visible light band is a halogen lamp, and the short wave near infrared and middle-long wave infrared bands are black bodies as light sources.
Testing the photoelectric system of the tested space camera 7 independently, and sampling the focal plane or the position near the focal plane of the tested space camera or the detector component 8 of the tested space camera;
the collimator 1 is in the form of an on-axis or off-axis light path.
The target light source component is arranged on the focal plane of the collimator;
the target pattern is obtained by proportional calculation according to parameters of the collimator and the tested space camera, and the target pattern is collimated and expanded by the collimator to generate a test wave front which is used as input of the tested space camera or a photoelectric system thereof;
the clear aperture of the collimator is larger than the clear aperture of one or more instantaneous fields of view of the space camera to be tested, and the focal length of the collimator is multiple times that of the space camera to be tested;
adjusting the rotation angle of the turntable and the position combination of the translation table to align the clear aperture of the current measured field of the space camera with the collimator;
according to different target types, various indexes and parameters such as an optimal focal plane, a point spread function, a line spread function, an optical transfer function, an angular resolution, a field angle, a focal length, distortion, stray light, crosstalk and the like of the space camera can be adjusted and tested;
the angle and position combination of the turntable and the translation table can be recorded, quick and accurate reproduction can be performed, the repeatability is realized, and the repeated test is convenient.
Based on the technical characteristics and the implementation method, the technical effects which can be realized by the patent are as follows:
(a) The complexity of the tool equipment for the space camera adjustment test is simplified, the guide rail for bearing the collimator is only responsible for adjusting the translation dimension, and the turntable for bearing the tested camera is only responsible for adjusting the angle dimension;
(b) Through the combination of the two-dimensional translation guide rail and the two-dimensional azimuth pitching turntable, the full-view field adjustment and test of various technical indexes of the space camera photoelectric system can be realized at one station;
(c) The rotary table corner of the tested camera and the translation position of the collimator are quantitatively recorded, and the repeatability is realized, so that the traditional test can be rapidly and accurately repeated, the iterative and reciprocating adjustment and test of the space camera are facilitated, and meanwhile, the consistency of the test is ensured;
(d) The optical system of the space camera can be independently tested by the detector arranged near the focal plane, and the technical index of the optical system of the space camera can be directly tested.
Drawings
FIG. 1 is a schematic structural diagram of a comprehensive test platform for a space camera optoelectronic system;
FIG. 2 is a schematic diagram of a target light source assembly
FIG. 3 is an embodiment of performing a horizontal one-dimensional field of view test alone;
FIG. 4 is a top view of the integrated test platform of FIG. 3 tested for the center field of view of the spatial camera under test;
FIG. 5 is a top view of the integrated test platform of FIG. 3 tested against the edge field of view of the spatial camera under test;
reference numerals: 1 a collimator; 2 targets and light source components, 2-1 is a light source, 2-2 is a target; 3 a vertical translation axis; 4 horizontal translation axis; 5 pitching the rotating shaft; 6 azimuth rotating shafts; 7, a tested space camera or a photoelectric system thereof; and 8, a detector assembly of the tested space camera.
Detailed Description
The embodiment of the integrated test platform for optical parameters of the space camera shown in fig. 1 comprises a collimator 1, a target and light source assembly 2, a vertical translation shaft 3, a horizontal translation shaft 4, a pitching rotation shaft 5, an azimuth rotation shaft 6, a space camera 7 to be tested and a detector assembly 8 thereof.
The collimator 1 and the target and light source assembly 2 are arranged on a translation stage consisting of a vertical shaft 3 and a horizontal shaft 4 to perform vertical and horizontal displacement adjustment.
The tested space camera 7 and the detector assembly 8 thereof are arranged on an angle turntable consisting of a pitching axis 5 and an azimuth axis 6 to adjust the azimuth and pitching angles.
Each of the vertical axis 3, the horizontal axis 4 and the pitching axis 5 and the azimuth axis 6 of the translation stage is provided with an angular displacement sensor and a linear displacement sensor, and quantitative position and angle measurement and recording are carried out.
The light source and target assembly 2 as shown in fig. 2, the target and light source assembly 2-2 is provided with the focal plane of the collimator 1, a proper light source or radiation source 2-1 is selected, the target 2-2 is illuminated, and the collimated and expanded beam of the collimator 1 is used for generating a test wavefront.
And the rotation angles of the pitching axis 5 and the azimuth axis 6 and the position combinations of the vertical axis 3 and the horizontal axis 4 are adjusted, so that the clear aperture of the measured view field of the space camera 7 is aligned with the clear aperture of the collimator 1.
The space camera 7 to be tested receives the test wavefront from the collimator and outputs a signal through the detector 8.
The detector 8 of the space camera under test is installed at a position at or near the focal plane of the optical system of the space camera under test 7 according to the progress and requirements of the test work.
The clear aperture of the collimator 1 is larger than the clear aperture of one or more instantaneous fields of view of the spatial camera 7 under test, and the focal length of the collimator 1 is several times the focal length of the camera 7 under test.
The photoelectric parameters of the two-dimensional view field of the tested space camera 7 are tested one by one through the matching of the vertical axis 3 of the translation table and the angle of the pitching axis 5 of the turntable and the matching of the horizontal axis 4 of the translation table and the angle of the azimuth axis 6 of the turntable;
the rotation angles of the pitching axis 5 and the azimuth axis 6 of the turntable are quantitatively recorded, and the combination of the positions of the vertical axis 3 and the horizontal axis 4 of the translation table can be quickly and accurately reproduced, so that the repeatability and the consistency are realized, and the evaluation, the assembly and the test are convenient to carry out.
In combination with the corresponding light source and target component 2, the comprehensive test platform of the space camera photoelectric system shown in fig. 1 can complete the adjustment and test of various technical indexes of the tested space camera 7, including but not limited to the following:
(a) Optimal focal plane position, depth of focus, focal length, angle of view, angular resolution, etc.;
(b) Optical transfer function, line diffusion function, point diffusion function, etc.;
(c) Stray light, optical or electrical crosstalk, etc.;
(d) Internal orientation elements, distortion, curvature of field, etc.;
(f) Relative transmittance, relative illuminance, focusing, and the like;
fig. 3-5 illustrate an embodiment of the present patent for performing an optical test with respect to a line scanning camera, and further illustrate the present patent in connection with this example.
Fig. 3 shows the instrument layout of the test platform, fig. 4 is a top plan view of the platform for the center field test of the space camera 7 under test, and fig. 5 is a top plan view of the platform for the edge field test of the space camera 7 under test.
In fig. 3 to 5, the space camera 7 to be measured has a large field of view with a line spread in the horizontal direction and a small field of view in the vertical direction, so that the cooperation of the space camera 7 to be measured with the azimuth axis 6 of the turntable and the horizontal translation axis 4 of the collimator 1 is simplified.
The specific parameters of the examples described in fig. 3 to 5 are as follows:
the horizontal axis 4 of the translation stage adopts a linear grating to measure and record the position, the motor is driven, the travel is 4000mm (+ -2000 mmm), and the resolution is 0.5mm;
the azimuth shaft 6 of the turntable adopts an encoder to measure and record angles, a motor is driven, the azimuth angle ranges from-90 degrees to +90 degrees, and the angular resolution is better than 3.0';
the collimator 1 adopts an off-axis double-reflection light path, the effective light transmission aperture is 1000mmm, the focal length is 20m, and the angle of view is 0.005 degrees.
The target 2-2 is a multi-slit target, the line width of the slit is 400 mu m, the interval of the slit is 400 mu m, and the light source 2-1 is a surface source black body;
the distance between the space camera 7 to be measured and the collimator 1 is about 1-2 m.
The effective light-transmitting aperture of the tested space camera 7 is 800mm, the focal length is 2000mm, the field angle is larger than 10 degrees multiplied by 0.1 degrees, and the angular resolution is better than 20 mu rad.
The test of the practical adjustment test is proved by the examples shown in fig. 3-5, the adjustment of the tested space camera and the test of various functions and performance parameters of the photoelectric system are completed on the platform, and the accuracy and feasibility of the comprehensive test platform of the space camera photoelectric system provided by the patent are proved.
The collimator 1 and the target light source assembly 2 described in fig. 1 or fig. 3 to 5, the vertical axis 3 and the horizontal axis 4 of the translation stage, the pitch axis 5 and the azimuth axis 6 of the turntable, and various parameters of the space camera 7 to be tested or the detector assembly 8 thereof are modified or scaled, and can be used for testing and adjusting other parameters or types of space cameras or optical systems thereof.
Claims (1)
1. A comprehensive test platform for a space camera photoelectric system comprises a collimator (1), a light source and target assembly (2), a vertical axis (3) and a horizontal axis (4) of a translation table, a pitching axis (5) of a turntable, an azimuth axis (6) and a detector assembly (8); the method is characterized in that:
the tested space camera (7) or a photoelectric system and a detector assembly (8) thereof are arranged on a pitching axis (5) and a pitching axis (6) of the pitching and azimuth two-dimensional turntable, and the collimator (1) and the light source and target assembly (2) are arranged on a vertical axis (3) and a horizontal axis (4) of the vertical and horizontal two-dimensional translation table;
the position of a vertical axis (3) of the translation table is adjusted to be matched with the angle of a pitching axis (5) of the turntable, and the angle is used for testing the vertical or pitching visual field of a tested space camera or a photoelectric system thereof;
the position of a horizontal axis (4) of the translation stage is adjusted to be matched with the angle of an azimuth axis (6) of the turntable, and the horizontal axis is used for testing the visual field of the horizontal or azimuth direction of the tested space camera or a photoelectric system thereof;
the vertical shaft (3), the horizontal shaft (4) of the translation table, the pitching shaft (5) and the azimuth shaft (6) of the turntable are provided with quantitative linear displacement and angular displacement measuring and recording devices;
the light source (2-1) selects according to the working wave band of the tested space camera, the ultraviolet band selects a mercury lamp, the visible light band uses a halogen lamp, and the short wave near infrared and middle wave infrared bands use a blackbody as the light source;
the photoelectric system of the tested space camera (7) is tested independently, and the focal plane or the position near the focal plane of the tested space camera or the detector component (8) of the photoelectric system is installed for sampling;
the collimator (1) is in the form of an on-axis or off-axis light path.
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| CN202320678385.1U CN219980897U (en) | 2023-03-31 | 2023-03-31 | Space camera photoelectric system comprehensive test platform |
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| CN202320678385.1U CN219980897U (en) | 2023-03-31 | 2023-03-31 | Space camera photoelectric system comprehensive test platform |
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