CN209927417U - Device for rapidly measuring change of space laser load optical axis - Google Patents
Device for rapidly measuring change of space laser load optical axis Download PDFInfo
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- CN209927417U CN209927417U CN201920711985.7U CN201920711985U CN209927417U CN 209927417 U CN209927417 U CN 209927417U CN 201920711985 U CN201920711985 U CN 201920711985U CN 209927417 U CN209927417 U CN 209927417U
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Abstract
The patent discloses a device for rapidly measuring change of a space laser load optical axis, which is based on an auto-collimation function of a pyramid prism and divides incident collimated light into two beams of collimated light, wherein the collimated light of a transmission path is transmitted and then reaches the pyramid prism to rotate for 180 degrees and then is reflected and emitted out by the pyramid prism, and the transmission path is transmitted to an off-axis collimator tube through the pyramid prism and then is converged on a CCD camera and is an initial origin; the collimated light of the reflecting path enters a second light splitting prism after being reflected by the light splitting prism, then enters a testing system through the reflecting path of the second light splitting prism, passes through a transmission path of the second light splitting prism, returns through the pyramid prism, and then is reflected by the second light splitting prism again to enter another system (two light beams respectively irradiate towards two sides at 180 degrees). The system can quickly measure the deformation condition of the satellite bin plate. The device has simple structure and simple operation method.
Description
Technical Field
The patent relates to a device that rapid survey space laser load optical axis changes is applicable to test satellite storehouse board and warp, and high accuracy optical axis monitoring also is applicable to fields such as the plane benchmark relation system that the alignment requirement is high.
Background
In a new era of rapid development of the aerospace industry, satellites become indispensable bearing tools, more than 200 satellites are launched in 2018, and the quantity of the launched satellites is continuously increased. New aerospace ideas are continuously proposed in China, and civil aerospace also becomes a new mastery force for continuously adding bricks and tiles to aerospace industry. Along with the flight of the aerospace industry, the requirement on the satellite is higher and higher, and higher requirements are required on the precision and the speed of a measuring method. For the satellite, the deformation of the warehouse board is a very important index, and the traditional method for testing the deformation of the warehouse board of the satellite adopts a Leica theodolite alignment method and then carries out the orientation test of the measuring cubic prism. The patent provides a high-precision method for rapidly measuring deformation of a satellite warehouse board, and two absolutely parallel light spots forming 180 degrees are provided for calibrating two cubic prisms. The device adopts a visible light source, can quickly perform rough reading, and then adopts a high-precision CCD camera detector to perform testing.
The method has the advantages that the requirement of resolution is improved in the aerospace process, the adoption of the large caliber is an accepted trend, the optical axis registration degree is one of key technical indexes of a system in the process of installing and calibrating the large-caliber system, the detection level of the system is directly influenced by the change of the optical axis, the system is large in size and heavy in weight along with the increase of the caliber, the change of the optical axis registration is possibly brought during testing, the problem that the high coaxial precision is particularly obvious particularly when a polarization information load, an imaging load and a ranging load are carried out is solved, visible collimated light can be provided for carrying out the optical axis registration, the optical axis condition can be monitored in real time, and a practical feasible scheme is provided for the optical axis registration.
Disclosure of Invention
The purpose of this patent is to provide a device that rapid survey space laser load optical axis changes, and the supplementary dress of high accuracy axiality is proofreaded and correct and real-time supervision can be satisfied in the use of this patent device, also can carry out the dress of satellite plane reference mirror simultaneously and proofreaded and measure etc.. The patent is mainly characterized in that: 1) the structure is simple, and the cost is low; 2) the adjusting method is simple, and two beams of light which form 180 degrees with each other are established by utilizing the interaction of the beam splitter prism and the pyramid prism; 3) the optical axis of the visible light system can be assisted to be established and adjusted to provide a function of measuring when the rapid measurement is practical.
The patent device is shown as attached figure 1, and the working process of the device is as follows:
the single-mode fiber laser 1 emits free laser at the focus of the collimating mirror 2, and enters the first beam splitter prism (3) after being collimated by the collimating mirror 2 to be divided into 50 parts: 50, one laser beam is transmitted through the first beam splitter prism (3) and absorbed by the light absorber 4. Another beam of light enters a second beam splitting prism 5 through the first beam splitting prism 3 and is split into 50:50, and the reflected light enters the system after passing through the attenuation sheet 7. The transmitted light enters the pyramid prism 6 to rotate 180 degrees for emergence, and then is reflected by the second beam splitter prism 5 to enter another system. After rotating 180 degrees through the pyramid prism 6, the light enters the off-axis parallel light pipe 8 convergence CCD camera 9 through the second beam splitter prism 5 and the first beam splitter prism 3 to form a self-detection light spot. To initially scale the spot. And placing the adjusted system into a tested system 10, wherein the tested system 10 consists of a mounting plate 10-1, a reference mirror 10-2 and a reference mirror 10-3. During measurement, firstly, the reflected light of the reference mirror 10-3 is modulated to a self-detection light spot position, then the light spot center of mass returned by the reference mirror 10-2 is read, and the ratio of the value of the coordinate difference delta of the center of mass of the two light spots to the focal length f of the selected off-axis collimator 8 is the on-axis precision delta of the optical axis. The formula is expressed as:
δ＝Δ/2f
unit is urad
The schematic diagram of the high-precision device for rapidly measuring the deformation of the satellite bin plate is shown in figure 1, and the device is characterized by comprising the following steps:
1) adjusting the relation between the single-mode fiber laser 1 and the collimating mirror 2: utilize single mode fiber laser 1's one end to introduce laser and pass through collimating mirror 2 collimation, collimated light gets into collimator and forms images on focal plane beam analyzer after the reflection of beam splitter 3 No. one, through the relative position of the light emergent terminal surface of adjusting single mode fiber laser 1 and collimating mirror 2, make collimated light minimum at the last imaging point of beam analyzer, single mode fiber laser 1 and collimating mirror 2 are fixed as a whole and are the collimation optical group, accomplish the regulation of collimating mirror 2 and single mode fiber laser 1.
2) The off-axis collimator 8 and the CCD camera 9 are adjusted: firstly fixing the required wavelength at the focus of the collimator, emitting a parallel light beam in front of the collimator, preliminarily fixing the off-axis collimator 8 and the CCD camera 9 in a reference tool, adjusting the relative position of the CCD camera 9 to the off-axis collimator 8 to enable the spot imaging point to be the minimum position, and then fixing the off-axis collimator 8 and the CCD camera 9 into a whole to finish the adjustment of the off-axis collimator 8 and the CCD camera 9.
3) And (3) adjusting the collimated light group and the CCD camera group: firstly, two collimated light groups are mutually collimated and then fixed, then a beam splitter prism 3 is placed between the two collimated light groups, then the two collimated light groups are placed in front of a collimator, a first collimated light group is reflected by the beam splitter prism 3 and enters the collimator, a pyramid prism 6 is placed in the emergent direction of the opposite second collimated light group after reflection, the entered light enters the collimator after passing through the pyramid prism 6, then the rotating direction of the first beam splitter prism 3 is adjusted, the points of two collimated light beams which are injected into the collimator are superposed at the focus, the first beam splitter prism 3 is fixed, then the pyramid prism 6 is replaced by a CCD camera group, the CCD camera group is adjusted, the light spot is fixed at the center position of a detector of the CCD camera group, and then the collimated light group which is reflected and enters the CCD camera group is taken down and changed into a light absorber 4. And adjusting the collimated light group and the CCD camera group.
4) A second beam splitter prism 5 is added in front of a first beam splitter prism 3 of a fixed collimating light set and a CCD camera set, a pyramid prism 6 is respectively arranged opposite to a transmission path and a reflection path, the pyramid prism 6 of the transmission path is fixed, the second beam splitter prism 5 is adjusted to enable light spots to enter the pyramid prism 6 through transmission, then the light spots are reflected by the second beam splitter prism 5 and return to the CCD camera set through the original path of the other pyramid prism 6 to the center of a CCD camera set detector, and the second beam splitter prism 5 is fixed. At this time, the system equipment is modulated.
5) Attenuation factor confirmation: firstly, a first path of laser is reflected by a first beam splitter prism 3, the energy of the first path of laser is 0.5 times of the basic energy, then the first path of laser enters a second beam splitter prism 5 for reflection, and the first path of laser enters a system after being reflected and is emitted out with the energy of the second path of laser being 0.25 times of the basic energy; the other path of laser is reflected by the first beam splitter prism 3, the energy of the other path of laser is 0.5 times of the basic energy, then the other path of laser is transmitted by the second beam splitter prism 5, the transmitted energy is 0.25 times of the basic energy and is emitted to the pyramid prism 6, the transmitted energy is reflected to the second beam splitter prism 5 again through the pyramid prism 6, and the transmitted energy is reflected by the second beam splitter prism 5 and enters the system and is emitted by 0.125 times of the basic energy. In order to balance the energy, 0.5 times of attenuation sheet 7 is added in the first path, namely the energy is also 0.125 times of the basic energy to be emitted.
The patent characteristics of this patent device mainly reflect:
1) the structure is simple, and the cost is low;
2) this patent utilizes the interact of beam splitting prism and pyramid prism to establish one and becomes two bundles of light of absolute 180 degrees each other, accomplishes two-way emission effect.
3) The test device can assist in testing the deformation of the bin plate of the satellite platform, and can also provide functions of rapid measurement and real-time monitoring for the establishment and adjustment of the optical axis of the visible light system.
Drawings
FIG. 1 is a schematic diagram of an optical path of a high-precision device for rapidly measuring deformation of a satellite bin plate.
FIG. 2 is a diagram illustrating the alignment of the collimating optical assembly and the optical axis adjustment
FIG. 3 is a schematic diagram of the alignment light set and CCD camera set adjustment
Detailed Description
An embodiment of the method of the present patent will be described in detail below with reference to the accompanying drawings.
The main components employed in this patent are described below:
1) single mode fiber laser 1: the 671nm single-mode fiber laser of Changchun new industry photoelectric technology company Limited is adopted, and the main performance parameters are as follows: the working wave band is 671 +/-10 nm; continuous light output, light output energy of 50mw and energy stability of less than 5%.
2) The collimating mirror 2: the collimating mirror with model AL2520-B of Thorlabs company is adopted, and the main performance parameters are as follows: the working band is 650-1050 nm; the focal length is 20mm, and the clear aperture is 25 mm; the transmissive material is ECO 550;
3) first beam splitter prism 3 and second beam splitter prism 5: the non-polarizing beam splitter prism of Thorlabs model BS007 is adopted, and the main performance parameters are as follows: the working band is 700-1100 nm; the splitting ratio is 1: 1, the aperture of the light transmission is 25 mm;
4) the light absorber 4: customization, adopting perovskite material, the depth is 20mm, the bore is 25.4mm
5) Corner cube 6: the cube-corner prism of the Thorlabs company with the model number PS971 is adopted, and the main performance parameters are as follows: the surface profile of the light-transmitting surface is better than lambda/10 @632.8 nm; the rotation precision is less than 3', and the light transmission caliber is 25.4 mm;
6) the attenuation sheet 7: a fixed density optical filter of Zhuoli Han light is adopted, and the model is NDF 12505-A. The main performance parameters are as follows: the aperture is phi 25.4mm, the attenuation ratio is 0.5 times, and the surface type is better than lambda/20 @632.8 nm;
7) the off-axis collimator 8: customization, its main performance parameters: the aperture is 100mm and the transmissive material is K9.
7) CCD camera 9: the main performance parameters of the beam analyzer adopting the American Spiricon company model SP620 are as follows: the working band is 190nm-1100nm, the pixel size is 4.4um by 4.4um, and the number of pixels is 1600 by 1200;
this patent device schematic diagram of high accuracy that rapid survey satellite storehouse board warp is shown in fig. 1, and this patent device can be applicable to test satellite storehouse board warp (the test of plane cubic prism benchmark relation), and supplementary high accuracy optical axis is established and is tested and the optical axis monitoring, also is applicable to fields such as the plane benchmark relation system that the alignment requirement is high. The patent method comprises the following specific implementation steps:
1. adjusting the relation between the single-mode fiber laser 1 and the collimating mirror 2: the utility model discloses a focus face beam analyzer, including collimator 2, collimating mirror 3, the optical fiber outgoing end face of single mode fiber laser 1 and collimating mirror 2, the one end of utilizing single mode fiber laser 1 introduces laser and passes through collimating mirror 2 collimation, collimated light gets into collimator and forms images on focus face beam analyzer after the reflection of beam splitter 3 No. one, through the relative position of adjusting single mode fiber laser 1's optic fibre outgoing end face and collimating mirror 2, make collimated light minimum at the last imaging point of beam analyzer, single mode fiber laser 1 and collimating mirror 2 are fixed as a whole and are the collimation optical group, accomplish collimating mirror 2 and single mode fiber laser 1.
2. The off-axis collimator 8 and the CCD camera 9 are adjusted: firstly fixing the required wavelength at the focus of the collimator, emitting a parallel light beam in front of the collimator, preliminarily fixing the off-axis collimator 8 and the CCD camera 9 in a reference tool, adjusting the relative position of the CCD camera 9 to the off-axis collimator 8 to enable the spot imaging point to be the minimum position, and then fixing the off-axis collimator 8 and the CCD camera 9 into a whole to finish the adjustment of the off-axis collimator 8 and the CCD camera 9.
3. And (3) adjusting the collimated light group and the CCD camera group: firstly, after mutually collimating two collimated light groups, fixing the two collimated light groups, then placing a first beam splitter prism 3 between the two collimated light groups, then placing the two collimated light groups together in front of a collimator, enabling the first collimated light group to enter the collimator through the first beam splitter prism (3) in a reflection mode, placing a pyramid prism 6 in the outgoing direction of the opposite second collimated light group after reflection, enabling the entered light to enter the collimator through the pyramid prism 6, then adjusting the rotating direction of the first beam splitter prism 3, enabling the points of two beams of collimated light entering the collimator to coincide at the focus, fixing the first beam splitter prism 3, replacing the pyramid prism 6 with a CCD camera group, adjusting the CCD camera group, enabling the light spot to be fixed at the center position of a detector of the CCD camera group, then taking down the collimated light group reflected to enter the CCD camera group and changing the collimated light group into a light absorber 4. And adjusting the collimated light group and the CCD camera group.
4. A second beam splitter prism 5 is added in front of a first beam splitter prism 3 of a fixed collimating light set and a CCD camera set, a pyramid prism 6 is respectively arranged opposite to a transmission path and a reflection path, the pyramid prism 6 of the transmission path is fixed, the second beam splitter prism 5 is adjusted to enable light spots to enter the pyramid prism 6 through transmission, then the light spots are reflected by the second beam splitter prism 5 and return to the CCD camera set through the original path of the other pyramid prism 6 to the center of a CCD camera set detector, and the second beam splitter prism 5 is fixed. At this time, the system equipment is modulated.
5. Attenuation factor confirmation: firstly, a first path of laser is reflected by a first beam splitter prism 3, the energy of the first path of laser is 0.5 times of the basic energy, then the first path of laser enters a second beam splitter prism 5 for reflection, and the first path of laser enters a system after being reflected and is emitted out with the energy of the second path of laser being 0.25 times of the basic energy; the other path of laser is reflected by the first beam splitter prism 3, the energy of the other path of laser is 0.5 times of the basic energy, then the other path of laser is transmitted by the second beam splitter prism 5, the transmitted energy is 0.25 times of the basic energy and is emitted to the pyramid prism 6, the transmitted energy is reflected to the second beam splitter prism 5 again through the pyramid prism 6, and the transmitted energy is reflected by the second beam splitter prism 5 and enters the system and is emitted by 0.125 times of the basic energy. In order to balance the energy, 0.5 times of attenuation sheet 7 is added in the first path, namely the energy is also 0.125 times of the basic energy to be emitted.
Claims (8)
1. The utility model provides a device that rapid survey space laser load optical axis changes, includes single mode fiber laser (1), collimating mirror (2), beam splitter prism (3), light absorber (4), No. two beam splitter prisms (5), pyramid prism (6), decay piece (7), off-axis collimator (8), CCD camera (9) and surveyed system (10), its characterized in that:
the single-mode fiber laser (1) emits free laser at the focus of the collimating mirror (2), the free laser enters the first beam splitter prism (3) after being collimated by the collimating mirror (2) and is divided into two beams of uniform light with the ratio of 50:50, and one beam of laser is absorbed by the light absorber (4) through the first beam splitter prism (3); another beam of light is reflected by the first beam splitter prism (3) to enter the second beam splitter prism (5) and is divided into 50 parts: 50, the second beam splitter prism (5) is reflected to enter the system after passing through an attenuation sheet (7); the second beam splitter prism (5) enters the pyramid prism (6) through transmission and rotates for 180 degrees to be emitted, and then enters the other system through reflection of the second beam splitter prism (5); after rotating 180 degrees through the pyramid prism (6), the light enters the off-axis collimator (8) through the second light splitting prism (5) and the first light splitting prism (3) and is converged into the CCD camera (9) to form a self-detection light spot which is an initial calibration light spot; putting the adjusted system into a tested system (10), wherein the tested system (10) consists of a mounting plate (10-1), a reference mirror (10-2) and a reference mirror (10-3); during measurement, firstly, the reflected light of the reference mirror (10-3) is modulated to a self-inspection light spot position, then the center of mass of a light spot returned by the reference mirror (10-2) is read, and the coaxial precision delta of an optical axis is determined by reading half of the coordinate difference delta of the center of mass of the two light spots and dividing by the ratio of the focal length f of the selected off-axis collimator (8):
δ＝Δ/2f
the unit is urad.
2. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the surface shape deviation RMS value of the collimating mirror (2) is less than lambda/10 @632.8nm, and the refractive index error is less than 2%.
3. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the first beam splitter prism (3) and the second beam splitter prism (5) have a splitting ratio of 50: and 50, the splitting angle is 45 degrees +/-5 ', the parallelism precision of the two groups of horizontal light-passing surfaces is less than 5', and the surface shape deviation RMS value of each light-passing surface is less than lambda/10 @632.8 nm.
4. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the light absorber (4) adopts perovskite.
5. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the revolution precision of the pyramid prism (6) is less than 3'.
6. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the surface shape deviation RMS value of the attenuation sheet (7) is less than lambda/10, and the attenuation multiplying power is 0.5 times.
7. The device for rapidly measuring the change of the optical axis of the space laser load according to claim 1, is characterized in that: the system wave difference of the off-axis collimator (8) is better than lambda/15 @632.8 nm.
8. The device and the method for rapidly measuring the change of the optical axis of the space laser load according to claim 1 are characterized in that: the pixel size of the CCD camera (9) adopts 4.4um X4.4 um.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110146257A (en) * | 2019-05-17 | 2019-08-20 | 中国科学院上海技术物理研究所 | A kind of device and method of rapid survey space laser load optical axis variation |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110146257A (en) * | 2019-05-17 | 2019-08-20 | 中国科学院上海技术物理研究所 | A kind of device and method of rapid survey space laser load optical axis variation |
| CN110146257B (en) * | 2019-05-17 | 2024-02-20 | 中国科学院上海技术物理研究所 | Device and method for rapidly measuring change of optical axis of space laser load |
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