CN112987282A - Light beam pointing method based on lens transverse movement for co-orbit satellite laser communication - Google Patents
Light beam pointing method based on lens transverse movement for co-orbit satellite laser communication Download PDFInfo
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- CN112987282A CN112987282A CN202110262098.8A CN202110262098A CN112987282A CN 112987282 A CN112987282 A CN 112987282A CN 202110262098 A CN202110262098 A CN 202110262098A CN 112987282 A CN112987282 A CN 112987282A
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B26/00—Optical devices or arrangements for the control of light using movable or deformable optical elements
- G02B26/08—Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
- G02B26/0875—Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light by means of one or more refracting elements
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
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Abstract
The invention provides a light beam pointing method based on lens transverse movement for co-orbit satellite laser communication. The method comprises the following steps: the method is characterized in that a refraction type optical telescope is adopted, lenses of the refraction type optical telescope are divided into three groups, wherein the main optical axes of the two groups of lenses in the front along the incident light direction are on the same straight line, the last group of lenses are connected to a two-dimensional translational motion platform to enable the two-dimensional translational motion platform to transversely move along with the motion platform, and the different transverse positions of the lenses in the group correspond to different angles of output light beams of a laser communication terminal. The invention adopts a mode of transversely moving the optical lens in the light path to realize the adjustment of the beam angle. Compared with the existing implementation mode, the system can realize the 2-degree pointing angle range required by the co-orbit satellite communication under the condition of greatly reducing the volume and the weight of the system, and has good angle adjustment resolution.
Description
The technical field is as follows:
the invention relates to a light beam pointing method based on lens transverse movement for co-orbit satellite laser communication, and belongs to the technical field of optical equipment.
Background art:
in free space laser communication, bidirectional beam alignment needs to be realized by a beam pointing module. The pointing angle range and the pointing angle resolution of the beam pointing module both need to meet system requirements, and are usually realized by combining coarse pointing and fine pointing, and are assisted by a proper closed-loop/open-loop control strategy, so that laser communication terminals on two sides of communication can realize rapid mutual capture, and stable tracking is realized in the working process.
In the laser communication of the co-orbit satellite, the requirement of the pointing angle range of the light beam pointing module is small, and the pointing angle range is only about 2 degrees generally. In the prior art, the technical means for adjusting the beam pointing angle within the angle range includes: (1) fixing an optical system on a two-dimensional turntable, wherein the optical system and an output light beam integrally move along with the two-dimensional turntable; (2) adding one or two plane reflectors outside the light path, and realizing the angle change of the light beam by rotating the plane reflectors; (3) two prisms are added outside the light path, and the change of the angle of the output light beam is realized by rotating the prisms; the above modes can realize beam pointing in a wide range, wherein the modes (1) and (2) can be used for not only in-orbit satellite communication but also in off-orbit satellite communication, and the pointing angle range of the modes is excessive for in-orbit communication. However, the above methods all increase more optical-mechanical parts, increase system volume and weight, and are not beneficial to satellite application; on the other hand, the pointing angle resolution is low, and generally, the pointing angle resolution can only be used as a coarse pointing module, and an additional fine pointing is required to be matched with the system.
The invention content is as follows:
in view of the above problems, the present invention provides a beam pointing method based on lens lateral movement for co-orbit satellite laser communication, which uses a mode of moving an optical lens in a light path laterally to realize beam angle adjustment. Compared with the existing implementation mode, the system can realize the 2-degree pointing angle range required by the co-orbit satellite communication under the condition of greatly reducing the volume and the weight of the system, and has good angle adjustment resolution.
The above purpose is realized by the following technical scheme:
a light beam pointing method based on lens transverse movement for co-orbit satellite laser communication is disclosed, which comprises the following steps: the method is characterized in that a refraction type optical telescope is adopted, lenses of the refraction type optical telescope are divided into three groups, wherein the main optical axes of the two groups of lenses in the front along the incident light direction are on the same straight line, the last group of lenses are connected to a two-dimensional translational motion platform to enable the two-dimensional translational motion platform to transversely move along with the motion platform, and the different transverse positions of the lenses in the group correspond to different angles of output light beams of a laser communication terminal.
The light beam pointing method based on lens transverse movement is used for the co-orbit satellite laser communication, the two-dimensional motion platform is driven by a linear motor, the position precision is 2 microns, and the motion resolution is 0.5 micron.
The light beam pointing method based on lens transverse movement is used for the co-orbit satellite laser communication, and each group of optical lenses are single lenses or a combination of a plurality of lenses.
Has the advantages that:
the invention adopts a mode of transversely moving the optical lens in the light path to realize the adjustment of the beam angle. Compared with the existing implementation mode, the system can realize the 2-degree pointing angle range required by the co-orbit satellite communication under the condition of greatly reducing the volume and the weight of the system, and has good angle adjustment resolution.
Description of the drawings:
fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a trial case diagram of the present invention.
Fig. 1, a first set of optical lenses; 2. a second set of optical lenses; 3. a final set of optical lenses; 4. a two-dimensional translational motion platform.
The specific implementation mode is as follows:
as shown in fig. 1, a beam pointing method based on lens lateral movement for laser communication of an in-orbit satellite according to the present embodiment includes: the lenses of the refractive optical telescope are divided into three groups, namely a first group of optical lenses 1, a second group of optical lenses 2 and a last group of optical lenses 3 in the figure 1. The main optical axes of the two groups of front lenses 1 and 2 along the incident light direction are on the same straight line, the last group of lenses 3 is connected on the two-dimensional translational motion platform 4 so that the two-dimensional translational motion platform can move transversely, and the different transverse positions of the lenses of the group correspond to different angles of the output light beam of the laser communication terminal. Through proper optical design, the wave aberration of the system is small in the range of pointing angles.
The light beam pointing method based on lens transverse movement is used for the co-orbit satellite laser communication, the two-dimensional motion platform is driven by a linear motor, the position precision is 2 microns, and the motion resolution is 0.5 micron.
The light beam pointing method based on lens transverse movement is used for the co-orbit satellite laser communication, and each group of optical lenses are single lenses or a combination of a plurality of lenses.
Application example:
as shown in fig. 2, a 50mm aperture refractive system with a 5x expansion factor consists of three sets of lenses, in this case only one lens per set. The third set of lenses is laterally movable. When the group of lenses is positioned at the central position, the corresponding output light beam angle is 0 degree, and the design residual error of an optical system is 0.018 lambda rms @1550 nm; when the transverse movement is 7mm, the corresponding output light beam angle is about 0.7 degrees, and the design residual error of an optical system is 0.013 lambda rms @1550 nm; when the transverse movement is 10mm, the corresponding output beam angle is about 1 degree, and the optical system design residual error is 0.027 lambda rms @1550 nm. It can be seen that the optical design achieves good performance over its range of pointing angles, with wave aberrations all better than 0.07 λ rms @1550 nm. The two-dimensional motion platform for realizing the transverse motion of the lens can be directly driven by adopting a linear motor mode, the position precision is 2 microns, and the motion resolution is 0.5 micron. For the parameters in the case, the corresponding angle precision is 3.5urad, the angular motion resolution is 0.9urad, the precise tracking requirements of the laser communication terminal in most cases can be met, so that the parameters can be combined roughly and precisely, a precise pointing module in the laser communication terminal is omitted, the system is simplified, and the size, the volume and the power consumption are reduced.
The above embodiments are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical solution according to the technical idea of the present invention falls within the protection scope of the present invention. The technology not related to the invention can be realized by the prior art.
Claims (3)
1. A light beam pointing method based on lens transverse movement for co-orbit satellite laser communication is characterized in that: the method comprises the following steps: the method is characterized in that a refraction type optical telescope is adopted, lenses of the refraction type optical telescope are divided into three groups, wherein the main optical axes of the two groups of lenses in the front along the incident light direction are on the same straight line, the last group of lenses are connected to a two-dimensional translational motion platform to enable the two-dimensional translational motion platform to transversely move along with the motion platform, and the different transverse positions of the lenses in the group correspond to different angles of output light beams of a laser communication terminal.
2. The method of claim 1, wherein the method comprises: the two-dimensional motion platform is driven by a linear motor, the position precision is 2 microns, and the motion resolution is 0.5 micron.
3. The method of claim 1, wherein the method comprises: each group of the optical lenses is a single lens or a combination of a plurality of lenses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110262098.8A CN112987282A (en) | 2021-03-10 | 2021-03-10 | Light beam pointing method based on lens transverse movement for co-orbit satellite laser communication |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110262098.8A CN112987282A (en) | 2021-03-10 | 2021-03-10 | Light beam pointing method based on lens transverse movement for co-orbit satellite laser communication |
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| CN112987282A true CN112987282A (en) | 2021-06-18 |
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| CN202110262098.8A Pending CN112987282A (en) | 2021-03-10 | 2021-03-10 | Light beam pointing method based on lens transverse movement for co-orbit satellite laser communication |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0903608A2 (en) * | 1997-09-20 | 1999-03-24 | Matra Marconi Space Uk Limited | Beam steerer |
| US20090046338A1 (en) * | 2007-08-17 | 2009-02-19 | Asml Holding N.V. | Beam Positioning and Pointing |
| CN108663817A (en) * | 2017-03-28 | 2018-10-16 | 西莱斯激光工业公司 | The Optical devices of the direction of propagation of light beam and the system including the device can be changed |
| CN111290117A (en) * | 2019-12-24 | 2020-06-16 | 哈尔滨新光光电科技股份有限公司 | Light beam pointing control method and system |
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2021
- 2021-03-10 CN CN202110262098.8A patent/CN112987282A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0903608A2 (en) * | 1997-09-20 | 1999-03-24 | Matra Marconi Space Uk Limited | Beam steerer |
| US20090046338A1 (en) * | 2007-08-17 | 2009-02-19 | Asml Holding N.V. | Beam Positioning and Pointing |
| CN108663817A (en) * | 2017-03-28 | 2018-10-16 | 西莱斯激光工业公司 | The Optical devices of the direction of propagation of light beam and the system including the device can be changed |
| CN111290117A (en) * | 2019-12-24 | 2020-06-16 | 哈尔滨新光光电科技股份有限公司 | Light beam pointing control method and system |
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Application publication date: 20210618 |