CN112198646B - Satellite-borne transceiving integrated Cassegrain optical antenna system and application thereof - Google Patents
Satellite-borne transceiving integrated Cassegrain optical antenna system and application thereof Download PDFInfo
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- 230000003287 optical effect Effects 0.000 title claims abstract description 71
- 238000004891 communication Methods 0.000 claims abstract description 24
- 210000001747 pupil Anatomy 0.000 claims description 6
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- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 2
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- 239000004917 carbon fiber Substances 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims description 2
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- 239000010703 silicon Substances 0.000 claims description 2
- 229910052710 silicon Inorganic materials 0.000 claims description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 2
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 2
- 230000004075 alteration Effects 0.000 abstract description 28
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- 238000003384 imaging method Methods 0.000 description 9
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- 238000012546 transfer Methods 0.000 description 6
- 238000004458 analytical method Methods 0.000 description 5
- 206010010071 Coma Diseases 0.000 description 3
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- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0033—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use
- G02B19/009—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use for use with infrared radiation
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/08—Catadioptric systems
- G02B17/0804—Catadioptric systems using two curved mirrors
- G02B17/0808—Catadioptric systems using two curved mirrors on-axis systems with at least one of the mirrors having a central aperture
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/08—Catadioptric systems
- G02B17/0864—Catadioptric systems having non-imaging properties
- G02B17/0876—Catadioptric systems having non-imaging properties for light collecting, e.g. for use with a detector
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0004—Condensers, e.g. light collectors or similar non-imaging optics characterised by the optical means employed
- G02B19/0028—Condensers, e.g. light collectors or similar non-imaging optics characterised by the optical means employed refractive and reflective surfaces, e.g. non-imaging catadioptric systems
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0033—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use
- G02B19/0085—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use for use with both a detector and a source
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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Abstract
The invention discloses a satellite-borne integrated Cassegrain optical antenna system for receiving and transmitting and application thereof, and solves the problems that when the existing Cassegrain optical antenna is used as a satellite-borne laser communication terminal receiving and transmitting antenna, wave aberration is large, error rate of a laser communication system is high, and loss of mixing efficiency is large. The invention comprises an objective lens group and an eyepiece lens group, wherein the objective lens group comprises a main lens and a secondary lens, the main lens and the secondary lens are coaxial Cassegrain type optical antennas, and the eyepiece lens group consists of a plurality of lenses. The invention has the advantages of small wave aberration, higher error rate, small loss of mixing efficiency and the like.
Description
Technical Field
The invention relates to the technical field of satellite laser communication, in particular to a satellite-borne transceiver integrated Cassegrain optical antenna system and application thereof.
Background
Compared with the traditional microwave communication, the satellite laser communication has the characteristics of high transmission rate, strong anti-interference capability, small size, light weight and the like, becomes a popular direction of the development of the next-generation wireless communication technology, and particularly has a large application prospect in the communication between satellites without shielding objects and between satellites and the ground. The receiving and transmitting optical antenna is used as a key device in satellite laser communication, and the performance of the receiving and transmitting optical antenna is directly related to the success or failure of satellite laser communication, so that the design of the receiving and transmitting optical antenna with excellent performance becomes a serious problem in satellite laser communication.
The satellite-borne equipment has high requirements on integration and light weight, and the receiving and transmitting integrated optical antenna can effectively reduce the complexity of the satellite laser communication terminal and effectively reduce the quality of the terminal, so that the satellite-borne equipment is widely studied at home and abroad.
The Cassegrain form is the most commonly used form of an optical antenna system, a main lens of a Cassegrain objective lens is generally parabolic, a secondary lens is hyperboloid, the whole system has no spherical aberration, the optical system has simple structure and excellent image quality, and the Cassegrain lens is widely applied to satellite laser communication terminals.
However, when the conventional cassegrain optical antenna is used as a satellite-borne laser communication terminal transmitting and receiving antenna, the problems of large wave aberration, high error rate of a laser communication system, large loss of mixing efficiency and the like exist.
Therefore, it is necessary to design a cassegrain optical antenna applied to a receiving and transmitting antenna of a satellite-borne laser communication terminal so as to solve the above-mentioned problems.
Disclosure of Invention
The invention aims to solve the technical problems that: when the existing Cassegrain optical antenna is used as a satellite-borne laser communication terminal receiving and transmitting antenna, the problems of larger wave aberration, higher error rate of a laser communication system and larger loss of mixing efficiency exist.
The invention can be realized by the following technical scheme:
the satellite-borne receiving and transmitting integrated Cassegrain optical antenna system comprises an objective lens group and an eyepiece lens group, wherein the objective lens group comprises a main lens and a secondary lens, the main lens and the secondary lens are coaxial Cassegrain optical antennas, and the eyepiece lens group consists of a plurality of lenses.
The invention discloses a satellite-borne integrated Cassegrain optical antenna system, wherein the surface of a main mirror is a paraboloid of revolution, the caliber of the main mirror is 110mm, the effective caliber of the main mirror is 100mm, and the curvature radius of the vertex of the main mirror is 320mm.
The invention discloses a satellite-borne transceiver integrated Cassegrain optical antenna system, wherein a first through hole is formed in the center of a main mirror, and the diameter of the first through hole is 10mm.
The invention discloses a satellite-borne integrated Cassegrain optical antenna system, wherein the surface of a secondary mirror is a rotating hyperboloid, the caliber of the secondary mirror is 25mm, the effective caliber of the secondary mirror is 21.4mm, and the curvature radius of the vertex of the secondary mirror is 87.8mm.
The invention preferably discloses a satellite-borne transceiver integrated Cassegrain optical antenna system, wherein the distance between a primary mirror and a secondary mirror is 128mm.
The invention discloses a satellite-borne transceiver integrated Cassegrain optical antenna system, wherein an objective lens group consists of 4 lenses, the objective lens group is a focusing system, the focal extension amount is-10 mm, and the focal plane of the objective lens group is overlapped with the Cassegrain optical antenna.
The invention preferably discloses a satellite-borne transceiver integrated Cassegrain optical antenna system, wherein the reflecting surfaces of a primary mirror and a secondary mirror are plated with high-reflection films for increasing the laser reflection efficiency.
The invention preferably provides a satellite-borne integrated Cassegrain optical antenna system, wherein the input pupil diameter of the Cassegrain optical antenna is 100mm, the output pupil diameter is 10mm, and the magnification is 10 times.
The invention preferably provides a satellite-borne transceiver integrated Cassegrain optical antenna system, wherein the main mirror is made of one of microcrystalline glass, fused quartz, silicon carbide, a carbon fiber composite material, a silicon wafer and a metal material with a small thermal deformation coefficient.
According to the invention, through the design of the antenna structure and the size, the Cassegrain optical antenna system with excellent wave aberration, low error rate and low loss of mixing efficiency is obtained.
The application of the satellite-borne transceiver integrated Cassegrain optical antenna system is that the optical antenna system is suitable for satellite-borne laser communication terminals with the laser wavelength of 1550 nm.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the system angle of view of the invention is + -5mrad, the wave aberration RMS value in the whole field of view is better than 1/30 wavelength, the wave aberration in the central field of view is better than 1/50 wavelength, the error rate of the laser communication system can be effectively reduced, and the loss of the frequency mixing efficiency is reduced, so the invention is very suitable for being used as a receiving and transmitting antenna of a satellite-borne laser communication terminal.
2. The optical antenna of the invention emits light beams as parallel light, an ideal lens is added on the cross section of the parallel light beams to converge the parallel light beams, the parallel light beams are evaluated through the imaging quality of the ideal lens, and from the point diagram of the imaging surface of the ideal lens, the diameter of a light spot RMS of a 0 field is only 0.588 mu m, the diameter of a light spot RMS of a + -5mrad field is only 0.718 mu m, which indicates that the optical antenna system designed by the invention reaches the diffraction limit level.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention. In the drawings:
FIG. 1 is a schematic overall view of an optical antenna and eyepiece lens assembly;
FIG. 2 is a geometric diagram of the design of the objective lens of the optical antenna;
FIG. 3 is a plot analysis of the design results of the objective lens of the optical antenna;
FIG. 4 is a view field wave aberration analysis of the optical antenna objective lens design 0;
fig. 5 is an optical antenna transfer function MTF;
FIG. 6 is an optical antenna design result 0 field wave aberration analysis;
FIG. 7 is an optical antenna design result 5mrad field wave aberration analysis;
FIG. 8 is an optical antenna design result-5 mrad field wave aberration analysis;
fig. 9 is a dot column diagram of the optical antenna design result.
In the drawings, the reference numerals and corresponding part names:
1-primary mirror, 2-secondary mirror, 3-objective lens group, 4-focal plane.
Detailed Description
For the purpose of making apparent the objects, technical solutions and advantages of the present invention, the present invention will be further described in detail with reference to the following examples and the accompanying drawings, wherein the exemplary embodiments of the present invention and the descriptions thereof are for illustrating the present invention only and are not to be construed as limiting the present invention.
Example 1
As shown in fig. 1 and fig. 2, the satellite-borne integrated cassegrain optical antenna system comprises an objective lens group 3 and an eyepiece lens group, wherein the objective lens group 3 comprises a main lens 1 and a secondary lens 2, the main lens 1 and the secondary lens 2 are coaxial cassegrain optical antennas, and the eyepiece lens group consists of 4 lenses.
The plane type of the main mirror 1 is a paraboloid of revolution, the caliber of the main mirror 1 is 110mm, the effective caliber of the main mirror 1 is 100mm, the curvature radius of the vertex of the main mirror 1 is 320mm, a first through hole is formed in the center of the main mirror 1, and the diameter of the first through hole is 10mm.
The surface shape of the secondary mirror 2 is a hyperboloid of revolution, the caliber of the secondary mirror 2 is 25mm, the effective caliber of the secondary mirror 2 is 21.4mm, and the radius of curvature of the vertex of the secondary mirror 2 is 87.8mm.
The distance between the primary mirror 1 and the secondary mirror 2 is 128mm.
The Cassegrain type optical antenna objective lens consists of a parabolic primary lens 1 and a hyperboloid secondary lens 2, and focuses of two quadric surfaces are overlapped.
The optical antenna has an entrance pupil diameter of 100mm, an exit pupil diameter of 10mm and a magnification of 10 times.
The objective lens group 3 is a focusing system, the projecting amount of a focus is-10 mm, and the focal plane 4 of the objective lens group 3 is overlapped with the focal plane 4 of the Cassegrain type optical antenna.
The laser optics transmitted from the far end can be regarded as parallel light treatment on the surface of the main mirror 1, the parallel light beam is converged to the primary image surface after being incident, and no spherical aberration exists in the imaging process. The cassegrain system is an aplanatic system, and when an incident parallel light beam deflects, larger coma aberration occurs on a primary image plane.
The antenna parameters were calculated as follows:
1. determining the relative caliber of the antenna main mirror
The relative caliber of the main mirror of the Cassegrain antenna is limited by multiple factors, the larger the relative caliber of the main mirror is, the more compact the whole antenna is, and the higher the corresponding processing difficulty is. The aperture D of the antenna is 100mm, and the relative aperture is comprehensively considered to be 1:1.6. According to the sign rule, the focal length of the primary mirror image is negative, and then the focal length of the primary mirror is f 1 ’＝-1.6D＝-160mm。
2. Determining a Cassegrain antenna secondary mirror obscuration ratio alpha
The secondary mirror obscuration ratio of the cassegrain antenna is related to the secondary mirror size, approximating the ratio of the primary and secondary mirror apertures. The design selects a classical value of the blocking ratio of the cassegrain antenna, alpha=0.2.
3. Determining focal point protrusion delta of Cassegrain antenna objective lens
The Cassegrain antenna objective lens is a focal system, and the on-board terminal has the requirements of light weight and miniaturization, so that the system is compact in design, the axial length is reduced, and the focal length of the objective lens is positioned at the left side of the main lens, namely the focal point protrusion delta of the objective lens takes a negative value. However, the focal length of the objective lens should not be too far into the left side of the main lens, otherwise, the eyepiece lens set would enter into the opening of the antenna main lens, resulting in a great increase in the difficulty of installation and adjustment. The design is taken as delta= -10mm in comprehensive consideration.
4. Determining the value of the secondary mirror magnification beta of a Cassegrain antenna
The secondary mirror magnification β is determined by the antenna structure, and its value is calculated by the following formula:
bringing the corresponding values, and calculating to obtain beta= -3.6875.
5. Calculating the radius of curvature r of the primary mirror 1 Radius of curvature r of secondary mirror 2 Spacing between two mirrors
Bringing the corresponding numerical value into the calculation to obtain r 1 ＝-320mm，r 2 ＝-87.8mm，d＝-128mm。
6. Calculating quadric surface coefficients
The main mirror of the Cassegrain antenna is a paraboloid, and the quadric surface coefficient thereofThe secondary mirror is a paraboloid, and the calculation formula of the secondary surface coefficient under the spherical aberration elimination condition is as follows:
carry-in data is calculated to be available
The antenna eyepiece group adopts a 4-piece structure, so that residual coma aberration and chromatic aberration of the objective lens group can be well balanced, and field curvature of the objective lens group can be partially balanced.
Referring to fig. 3, there is shown a point column diagram of the objective lens of the optical antenna of cassegrain in the present invention on the primary image plane. From fig. 3, it can be seen that the cassegrain optical antenna objective lens in the present invention images as ideal imaging under the 0 field of view, which illustrates that the design of the present invention achieves the limit effect; in the invention, the field of view of the whole optical antenna is +/-5 mrad, the point diagram shown in fig. 3 also shows the condition of primary image plane imaging under the fields of 5mrad and-5 mrad, and the fact that the imaging under the two fields introduces great coma aberration can be seen, and the aberration is corrected by a subsequent eyepiece lens group to emit parallel light.
Referring to fig. 4, the wave aberration diagram of the optical antenna objective lens of the present invention is shown in 0 field, and it can be seen from the diagram that the wave aberration of the optical antenna objective lens of the present invention in 0 field is 0, which is an aberration-free point, and this characteristic has a great effect in processing and assembling, and can be used as a reference for installation during adjustment.
Referring to fig. 5, the transfer function of the optical antenna of the present invention is shown in fig. 5, where F1 represents the transfer function value of the optical antenna in the 0 field of view, F2 represents the transfer function value of the optical antenna in the +5mrad field of view, F3 represents the transfer function value of the optical antenna in the-5 mrad field of view, and T and R represent the meridian plane and the sagittal plane, where it is shown that the transfer function curves of the optical antenna designed by the present invention in the three fields of view have good coincidence, which indicates that the imaging quality reaches the diffraction limit level.
Referring to fig. 6, 7 and 8, wave aberration diagrams of the outgoing beam of the optical antenna of the present invention under different fields of view on the receiving surface are shown. Wherein, FIG. 6 shows 0 field wave aberration, FIG. 7 shows 5mrad field wave aberration, and FIG. 8 shows-5 mrad field wave aberration. Numerical calculations show that the 0 field wave aberration RMS value is 0.019 wavelengths, and that both the + -5mrad field wave aberration RMS values are 0.031 wavelengths. The wave aberration of the optical antenna designed by the invention is better than 1/30 (0.033) wavelength in the full field of view, and better than 1/50 (0.02) wavelength in the central field of view, so that the error rate of a laser communication system can be effectively reduced, the loss of the frequency mixing efficiency is reduced, and the technical requirements of the satellite-borne laser communication terminal receiving and transmitting antenna are completely met.
The optical antenna emits light beams into parallel light, an ideal lens is added on the cross section of the parallel light beams in the design to converge the parallel light beams, and the parallel light beams are evaluated through the imaging quality of the ideal lens.
Referring to fig. 9, which is a plot of the ideal lens imaging surface points, it can be seen that the 0 field spot RMS diameter is only 0.588 μm, and the ±5mrad field spot RMS diameter is only 0.718 μm, indicating that the design result reaches the diffraction limit level.
Example 2
The difference between this embodiment and embodiment 1 is that the reflective surfaces of the primary mirror 1 and the secondary mirror 2 are coated with a high-reflection film for increasing the reflection efficiency of laser, and the primary mirror 1 is made of microcrystalline glass.
Example 3
The optical antenna system in embodiment 1 or 2 is applied to a satellite-borne laser communication terminal with a laser wavelength of 1550nm, and the field angle of the optical antenna system is + -5 mrad.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (6)
1. The satellite-borne integrated Cassegrain optical antenna system is characterized by comprising an objective lens group and an eyepiece lens group (3), wherein the objective lens group comprises a main lens (1) and a secondary lens (2), the main lens (1) and the secondary lens (2) are coaxial Cassegrain type optical antennas, and the eyepiece lens group (3) consists of a plurality of lenses;
the plane shape of the main mirror (1) is a paraboloid of revolution, the caliber of the main mirror (1) is 110mm, the effective caliber of the main mirror (1) is 100mm, and the curvature radius of the vertex of the main mirror (1) is 320mm;
the surface shape of the secondary mirror (2) is a rotating hyperboloid, the caliber of the secondary mirror (2) is 25mm, the effective caliber of the secondary mirror (2) is 21.4mm, and the curvature radius of the vertex of the secondary mirror (2) is 87.8 mm;
the focuses of the primary mirror (1) and the secondary mirror (2) coincide;
the eyepiece lens group (3) consists of 4 lenses, the eyepiece lens group (3) is a focusing system, the focal point extending out is minus 10mm, and the focal plane (4) of the eyepiece lens group (3) is overlapped with the focal plane (4) of the Cassegrain type optical antenna;
the optical antenna has an entrance pupil diameter of 100mm, an exit pupil diameter of 10mm and a magnification of 10 times.
2. The satellite-borne integrated transmission and reception cassegrain optical antenna system according to claim 1, wherein a first through hole is formed in the center of the main mirror (1), and the diameter of the first through hole is 10mm.
3. An integrated satellite transceiver cassegrain optical antenna system according to claim 1, characterized in that the spacing between the primary mirror (1) and the secondary mirror (2) is 128mm.
4. The satellite-borne transceiving integrated cassegrain optical antenna system according to claim 1, wherein the reflective surfaces of the primary mirror (1) and the secondary mirror (2) are coated with a high reflective film which increases the laser reflection efficiency.
5. The satellite-borne transceiving integrated Cassegrain optical antenna system according to claim 1, wherein the main mirror (1) is made of one of microcrystalline glass, fused quartz, silicon carbide, carbon fiber composite material and silicon wafer.
6. An application of a satellite-borne transceiver integrated cassegrain optical antenna system, which is characterized in that the optical antenna system is suitable for a satellite-borne laser communication terminal with a laser wavelength of 1550 nm.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101598849A (en) * | 2008-06-06 | 2009-12-09 | 上海微小卫星工程中心 | Optical imaging system and manufacture method thereof |
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
| CN213122425U (en) * | 2020-11-02 | 2021-05-04 | 重庆两江卫星移动通信有限公司 | Satellite-borne transmitting-receiving integrated Cassegrain optical antenna system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101598849A (en) * | 2008-06-06 | 2009-12-09 | 上海微小卫星工程中心 | Optical imaging system and manufacture method thereof |
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
| CN213122425U (en) * | 2020-11-02 | 2021-05-04 | 重庆两江卫星移动通信有限公司 | Satellite-borne transmitting-receiving integrated Cassegrain optical antenna system |
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